Experimental study on thermal environment of scramjet combustor

:

2015 4

Experimental study on thermal environment of scramjet combustor

By

Di Cheng

A Dissertation Submitted to

University of Chinese Academy of Sciences

In partial fulfillment of the requirement

For the degree of

Doctor of Fluid Mechanics

Institute of Mechanics

April, 2015

I

CFD

CFD

1.5

12.452.84W/cm2/mV 35.312.5K/mV 8.231.20s

2 / 15 /

14

RP-3 ( 77320 K Mach 2.0 2.5

1305K 1701K 2.0kg/s 3.0kg/s 0.52 0.88

0.8

Mach

DES CFD

II

8 DES

DES 1/3

DES DES

CFD

CFD

III

Experimental study on thermal environment of scramjet combustor

Abstract

Di Cheng

Directed by Professor Xuejun Fan

Supersonic combustion ramjet is the key technology to implement hypersonic cruise. As the

essential part of supersonic combustion ramjet, supersonic combustor is working with the harshest

thermal environment. So the thermal environment measurement and analysis of supersonic

combustor is of great significance to the development of scramjet.

In this thesis, four subjects about thermal environment of scramjet were studied: existing

manufacturing and calibration method of heat flux sensor were improved to make it more stable

reliable and applicable to large scale test; Heat flux distribution of supercritical kerosene fueled,

supersonic combustor was experimentally and parametrically studied, and a group of data is

obtained and analyzed; Heat flux were compared with the results obtained from quasi-one-

dimensional performance analysis and Detached Eddy Simulation, the difference were analyzed

and discussed. An one-dimensionalizing method were proposed to reduce CFD result and verify

quasi-one-dimensional analysis code.

Firstly, in order to realize trouble-free operation of the heat flux measurement system in large

scale test. Original heat flux sensor design were analyzed to increase its stability and reliability.

A brazing and soldering process were proposed to replace the adhesion process to connect heat

conducting parts. The rate of finished products was increased by a factor of 1.5 times with new

process. And the finished products shown lesser degree of dispersion of their sensitivity and better

stability. The heat flux sensitivity is 12.452.84W/cm2/mV, and temperature difference sensitivity

is 35.312.5K/mV. And the response time is 8.231.20s. Anew rapid calibration device utilizing

electric heating were designed and manufactured as a supplement of original calibration methods

to facilitate and accelerate calibration of heat flux sensors. The time cost reduced from 2 hours per

sensor to 15 minutes per sensor.

Secondly, in order to investigate the key parameters influencing heat flux distribution in the

complex flow field supersonic combustor, five groups of 14 test runs were conducted to study the

heat flux distribution of a supercritical kerosene fueled, single-side expanded supersonic

IV

combustor with two dislocated opposing cavities on long duration direct-connect supersonic

combustion test facility in Institute of Mechanics. The isolator inlet Mach number is 2.0 and 2.5,

the total temperature is 1305 K to 1701 K and the mass flow rate is 2.0 kg/s to 3.0 kg/s. Pilot

hydrogen and liquid or supercritical (77320 K) China No.3 kerosene were injected in front of the

cavities with the equivalence ratio ranges from 0.52 to 0.88. Results show that heat flux increases

with the increasing of inlet temperature and mass flow rate, however, the influence of equivalence

ratio is nonmonotonic in the range of interest. The two inlet Mach numbers also trigger different

combustion modes, which further complicates the heat flux distribution. A three-parameter

correlation were proposed and fitted for average isolator heat flux of unburnt cases, but the

normalized heat flux distribution of burnt cases also shows certain degree of similarity.

Thirdly, the experimental result were compared with result of quasi-one-dimensiona l

performance analysis code (Q1dPAC) and Detached Eddy Simulation (DES) result. The trend and

order of magnitude could be matched, but there are still some differences locally. Q1dPAC result

tends to over predict heat flux in region with separation, such as isolator with strong shock-train,

because of decrease of core flow area. For weaker flow separation, Q1dPAC result is more accurate.

Comparing with DES result corresponding with the 8th test case, the general trend can be matched.

But the DES result is about 1/3 times higher in combustion region near the upper wall. And on the

lower wall where boundary layer is disturbed by the waves, DES heat flux is increased and become

higher than experimental results. The DES result indicates flow stratification and transverse effects

could influence spatial distribution of heat flux around a cross-section.

Finally, a one-dimensionalizing method was proposed for CFD results to verify the accuracy

and deviation of the Q1dPAC. The results shown that the averaged velocity calculated from

Q1dPAC is very accurate regardless of flow non-uniformity. But other cross-section average

quantities obtained can be influenced by flow non-uniformity. The source of error is identified as

the flow rate equation and specific sensible enthalpy equation. However, the relative error of cross-

section averaged quantities is limited in the supersonic combustor except around the cavity, and it

could meet the need of engineering. But the wall loss terms predicted by Q1dPAC differs

considerably from CFD result, especially in the combustion region.

KEY WORDS Supersonic combustion, heat flux distribution measurement,

V

supercritical kerosene, quasi-one-dimensional steady flow.

VII

............................................................. I

Abstract ......................................................... III

........................................................... VII

............................................................ XI

.......................................................... XVII

........................................................... XIX

...................................................... 1

1.1 ............................................................ 1

1.1.1 .................................................. 1

1.1.2 ................................................ 3

1.2 .......................................................... 5

1.2.1 ...................................................... 5

1.2.2 .................................................... 6

1.2.3 ...................................................... 6

1.3 .......................................... 7

1.3.1 .......................................................... 7

1.3.2 ......................................................... 21

1.3.3 ..................................................... 27

1.3.4 ......................................................... 29

1.4 ....................................................... 29

................................. 31

2.1 ............................................... 31

2.2 ..................................... 33

2.3 ....................................................... 34

2.3.1 ............................................... 36

2.4 ............................................. 37

2.4.1 ............................................... 37

2.4.2 ..................................................... 41

VIII

2.5 ............................................................... 44

.................... 45

3.1 ..................................................... 45

3.1.1 ............................................. 45

3.1.2 ....................................................... 45

3.1.3 ............................................. 46

3.1.4 ..................................................... 47

3.1.5 ..................................................... 50

3.1.6 ..................................................... 51

3.1.7 ..................................................... 52

3.1.8 ............................................... 54

3.2 ........................................................... 54

3.2.1 ............................................... 55

3.2.2 ................................................... 58

3.2.3 ............................................. 60

3.2.4 ........................................... 64

3.2.5 ............................................... 66

3.2.6 Mach ............................................ 68

3.3 ........................................................... 71

3.3.1 ................................. 72

3.4 ............................................................... 77

................................... 78

4.1 ........................................... 78

4.2 ....................................... 78

4.2.1 ....................................... 79

4.2.2 ................................................. 81

4.2.3 ................................................. 81

4.3 CFD ......................................... 84

4.4 ............................................................... 89

IX

.......................... 90

5.1 ....................................................... 90

5.1.1 ........................................... 91

5.1.2 ................................... 94

5.1.3 ................................... 95

5.2 CFD ............................. 97

5.2.1 CFD ..................................................... 97

5.2.2 ............................................... 98

5.2.3 ..................................................... 99

5.2.4 .................................................... 100

5.2.5 .................................................... 103

5.2.6 .................................................. 104

5.2.7 ................................................ 105

5.2.8 .................................................. 107

5.2.9 .............................................. 108

5.3 .............................................................. 109

.............................................. 111

6.1 .......................................................... 111

6.2 ............................................................ 112

6.3 .......................................................... 112

......................................................... 115

A: ...................................... 119

B: ........................................... 125

C: ............................................... 131

D: ....................................... 137

........................................................... 139

XI

1-1 ..................................................................................... 1

1-2 (a. b. c.

)............................................................................................................ 2

1-3 [1] ................................................................ 3

1-4 ........................................................................................ 3

1-5 [9] ..................................... 4

1-6 SJX61-1 [12] ........................................... 5

1-7 ........................................... 8

1-8 R.G. Morgan [22] ...................................................................... 9

1-9 .......................................................................................... 10

1-10 [23]1 Btu/s/ft2/R = 20428 W/m2K ..... 10

1-11 Dy:YAG 2D CFD [24] ................. 11

1-12 HyShot mm[25]............................................. 11

1-13 HyShot HEG 32.5km ........ 12

1-14 HyShot II ........................................................................................................ 12

1-15 HyShot II HEG CFD [26] ....................................... 13

1-16 HEG [26] ..................................................................... 13

1-17 ................................................................ 14

1-18 DCC 1=25.4mm[30]........................................................................ 15

1-19 JPL DCC [30]1Btu/inch2s = 163.4W/cm2 .................................. 16

1-20 DCAF 1 = 25.4mm[30] ................................................................... 16

1-21 DCAF [30]1Btu/inch2s = 163.4W/cm2 .................................................... 17

1-22 [31] ............................................................... 17

1-23 CFD [31]MVSV

........................................................................................................................... 18

1-24 [29] ........................................................... 18

1-25 [29] ............................................................................... 19

XII

1-26 mm[33] ......................... 20

1-27

[33] .................................................................................................................................. 20

1-28 HYPULSE [35] ..................................................................................... 22

1-29 HyShot II [36, 37] ............................................................................................... 22

1-30 HyShot II CFD [37] ............................................. 23

1-31 CFD [38] ..................................... 23

1-32 ................................................................................................ 24

1-33 RANS [39] ............................................ 24

1-34 ab[41] ............... 25

1-35 / .............................................. 26

1-36 [50] ..................................... 27

1-37 [53] ................................................ 28

1-38

[53] [61] ............................................................................................................................. 28

2-1 [33] ..................................................................................... 31

2-2 Gardon ....................................................................................... 32

2-3 Gardon [33] ....................................................................... 32

2-4 ...................................................................................... 33

2-5 M450 ...................................................................... 35

2-6 .......................................................................................... 36

2-7 .................................................................. 37

2-8 .......................................................................... 38

2-9 ...................................................................... 39

2-10 ..................................................................... 39

2-11 .............................................................................. 40

2-12 ............................................................................ 40

2-13 LabVIEW ................................................. 41

2-14 ............................................................ 42

XIII

2-15 ............................................................ 43

2-16 EHM HTBBRM

........................................................................................................................... 44

3-1 ............................................................................ 45

3-2 .................................................................................................. 46

3-3 ...................................................................................... 47

3-4 ............................................................................................ 48

3-5 ............................................................................................... 48

3-6 .......................................................................................................... 49

3-7 .......................................................................................................... 50

3-8 .............................................................................................. 51

3-9 7 ..................................................... 52

3-10 ............................................................. 53

3-11 ................................................. 53

3-12 1, Mach ...................................................... 56

3-13 1, ....................................................................................... 56

3-14 1, ....................................................................................... 57

3-15 1, ..................................................................................... 57

3-16 Origin 5%-95%. ........................................ 58

3-17 No.12 Mach........................................................ 59

3-18 No.12 ............................................................................... 59

3-19 No.12 ............................................................................... 60

3-20 No.12 ............................................................................... 60

3-21 3: kerosene0.5, 0.7, 0.9, T01300K, qm2.5 kg/s, H2 0.1.

Mach................................................................................................ 61


................................................................................................................... 61


................................................................................................................... 62


XIV

....................................................................................................................... 62

3-25 ......................................................................................... 63

3-26 2: qm 2.0 kg/s 3.0 kg/s T01300K, kerosene0.7, H2

0.1 Mach ..................................................................................... 64

3-27 2: qm 2.0 kg/s 3.0 kg/s T01300K, kerosene0.7, H2

0.1 ........................................................................................................ 65

3-28 2: qm 2.0 kg/s 3.0 kg/s T01300K, kerosene0.7, H20.1

............................................................................................................... 65


............................................................................................................... 66

3-30 4: T0 1289K 1687K qm 2.5 kg/s, kerosene0.7, H2

0.1 Mach................................................................................. 67


0.1 .................................................................................................... 67


0.1 .................................................................................................... 68


0.1 .................................................................................................... 68

3-34 1 Mach 2.5 2.0, T0 1650K, qm 2.5kg/s, kerosene

0.7, H20.1 Mach ................................................................. 69


0.7, H20.1 .................................................................................... 70


0.7, H20.1 .................................................................................... 70


0.7, H20.1 ................................................................................... 71

3-38 ................................................................................................................. 74

3-39 Mach 2.0 ............................................................................. 75

3-40 Mach 2.5 ............................................................................. 75

XV

3-41 Mach 2.0 ................................................................................. 76

3-42 Mach 2.5 ................................................................................ 76

4-1 .................................................................................. 79

4-2 2 ...................................................................... 81

4-3 6 ........................................................................................... 82

4-4 7 ........................................................................................... 82

4-5 8 .......................................................................................... 83

4-6 8 ...................... 84

4-7 DES .................................................................................. 85

4-8 DES .................................................................................. 86

4-9 DES .................................................................................. 86

4-10 DES ........................................................ 87

4-11 DES ......................................................................................... 88

4-12 .................................................................... 88

4-13 DES ................................................................ 89

5-1 (Control Volume) ......................................................................................... 92

5-2 CFD ...................................................... 97

5-3 mm 80mm ...................................................... 97

5-4 ..................................................... 98

5-5 ...................................................................................................... 99

5-6 (u_1d)(u_avg) ................................................. 100

5-7 ........................................................ 101

5-8 (Ac) ................................................................................................. 102

5-9 (T_1d)(T_avg)................................................ 103

5-10 MW_avg(MW_1d)

................................................................................................................................. 104

5-11 (hs_1d)(hs_avg) .................................... 105

5-12 (hs_1d) (hs_avg) .......................... 106

5-13 ................................................................................... 107

5-14 (F_avg)(F_1d) .......................................... 108

XVI

5-15 (Integrate Qw_avg)(Integrate Qw _1d)

............................................................................................................................. 109

XVII

2-1 .............................................................................................................. 35

3-1 .............................................................................................................. 54

3-2 .............................................................................................................. 54

3-3 .......................................................................................................... 73

3-4 R2......................................................................................... 74

A-1 ................................................................................ 123

A-2 ............................................................................................... 124

B-1 ............................................................................................... 129

XIX

x

q

A

K1

K2

h /

qm

u,v,w

p

T

Ma Mach

St Stanton

Re Reynolds

Pe Peclet

Pr Prandtl

Da Damkhler

Q

cf Darcy

F

f

LHV

cp

Ru

MW

XX

o 293.15K, 101.325 kPa

s

0

t

*

b

w

inlet

fuel

inj

c

1d

avg CFD

1

1.1

1.1.1

20km100km

/

/X37B X-43/X-51A 1-1

1-1

X-43 X-51A

(c)X-43 Ma10 H33.5 km (d)X-51A Ma=56 H21km

(b)X-37B Ma25 (a) Ma25

2

1-2 (a. b. c.)

Mach 5-12 1-3scramjet

3

1-3 [1]

1.1.2

1-4

Mach

1-4

Mach Damkhler Reyno lds

[2]

[3][4]

[5]/[6][7 ,

8]

4

100W/cm2

1000 1-5

Mach

1300KMach 5.0 1300K

2500K

1-5[9]

[10]

[11]

Mach 5-7

[12] 1-6 X-51A

5

1-6 SJX61-1 [12]

[10]

[13]

1.2

1.2.1

[14]

convective rad Dqq qq (1-1)

1. qconvective 2000 m/s

T0 2000K ~ 3000K

( )convective aw wq h T T (1-2)

2. qrad

(1-3)

6

gas Tgas w Tw

w gasT T

10%[15, 16]

4 4 4

rad gas gas w w gas gasT T Tq (1-3)

3. qD(1-4)

(1-4)Dimhi Yi i

D im i i

i

D Yq h (1-4)

1.2.2

1.

2.

3.

18mm 250mm 8.231.20

1.2.3

1. q

7

2. q Tw(1-2)

q Tw

3. Taw h

Taw h

q Tw

1.3

1.3.1

[17]

1.3.1.1

[18]

1.3.1.1.1

[19][20, 21]

1-7

-

8

0

0

( , 0)

( )

p

x

T Tc k

t x x

T x t T

Tk q t

x

( )q t( 0, )T x t

(a) (b)

0

-

( 0)

p

dTc qA

dt

T t T

V

( )T t

( )q t

1-7

1. R.G. Morgan 1986 [22]

1-8

Injector StrutThrust nozzle

9

1-8 R.G. Morgan [22]

2. Scott D. Stouffer 1997 Jet-A

Mach 5.6 82

MedTherm 1-9[23] 1-10

1.7 2.7

Jet-A

3

10

1-9

1-10 [23]1 Btu/s/ft2/R = 20428 W/m2K

3. K. Kontis 2002 Dy:YAG LIF

Mach 2.5 5bar

[24] 1-11 CFD LIF

800K

11

1-11 Dy:YAG 2D CFD [24]

4. A. Gardner 2004 HyShot 1:1

HEG Mach 7.8 27.1km

32.5km MedTherm E 1-12

1-12 HyShot mm[25]

32.5km 1-13

12

1-13 HyShot HEG32.5km

5. Jan Martinez 2008 HyShot II 1-14

HEG [26] Mach 7.6 28km

33km MedTherm TCS-061-E-XX-24-10866

1-14

1-14 HyShot II

1-15 CFD 1-16

13

CFD

(a) (b)

1-15 HyShot II HEG CFD [26]

1-16 HEG [26]

[17]

14

1.3.1.1.2

1-17 Gardon [27]

S. V. Bobashev (Grad ient

Heat Flux Sensor, GHFS) [28] K. Paul Direct-Write

Techonology[29]

q

(a)Gardon

(b)GHFS (c)

q q

1-17

1. 1980 NASP

Mach 6 0.52 Mach 8 0.37 DCC

8 1-18

1-19[30]

400 W/cm2

15

1-18 DCC1=25.4mm [30]

(a) Mach 8

(b) Mach 6

16

1-19 JPL DCC [30]1Btu/inch2s = 163.4W/cm2

2. DCAF

Mach10 Mach12 1.15 2.25

1-20[30]

1-21

DCC DCAF

VITMAC

1-20 DCAF1 = 25.4mm [30]

(a) Mach 12.5

17

(b) Mach 10.5

1-21 DCAF [30]1Btu/inch2s = 163.4W/cm2

3. S. Ueda 2006 Mach 6

RANS 1-22[31]

1-23

1-23

1-22 [31]

18

1-23 CFD [31]MVSV

4. Paul J. Kennedy Jason R. Trelewicz 2011 Direc t

Write Technology 1-24 Mach 5

24kPa 48kPa 0.60.8 1.0 [29] [32]

1-24 ABCD

1-25

( 4 )

1-24 [29]

19

1-25 [29]

5. Gardon

1-26 7 Mach 2.5 1.4kg/s 1300K

1800K 0.70.8 1.1 1-27

[33]

1

20

1-26 mm [33]

(a) (b)

1-27 [33]

[33]

21

1.3.1.2

[34]

1.3.2

CFD

1.3.2.1 CFD

--

y+=1

CFD --

CFD

1. G. Bobskill 1991 HYPULSE CFD

1-28 NS

NS NS

CFD [35]

22

1-28 HYPULSE [35]

2. S. Ueda 2006 Mach 6

RANS [31] 1-23

3. C. Fureby 2013 HyShot II

1-14 RANS LES

1-29 HyShot II [36, 37]

1-30 LES

HyShot II 28km 33km

RANS 28km[36, 37]

23

1-30 HyShot II CFD [37]

4. [38]

(CARDC-AHL) AHL3D

(a) (b)

1-31 CFD[38]

5. NS

RANS[39] 1-32

24

Mach 2.5 1600K 9.1bar 1000K

147mm 10mm 0.8 0.1

0.8

1-33

1-32

1-33 RANS[39]

CFD

Validation

1.3.2.2

[40]

[13]

[41]

25

1.3.2.2.1

1. W. H. Heiser 1-34

[41]

1-34 ab[41]

2. NASP Richard M. Traci VITMAC

[30] Mach 6

1-19

3. SPIRITECH G. Eric SRHEATTMScramjet/Ramjet Heat

Exchanger Analysis Tool

[42]

4. X-shock

-

[43]

5. W. H. Heiser

[44] 1-35

26

1-35 /

6.

[45-47]

1.3.2.2.2

1. W. H. Heiser

[41]

2.

[40]

3.

[48]

4.

2000K

[49]

27

[33]

1-36[50]

1-36 [50]

[51]

[52]

1.3.3

[53] [54]/

[51][55, 56]-

[57]/Mach [58]

[59][60]

1-37

3300-8300 W/cm2[41]

28

1-37[53]

1-38

1-38 [53] [61]

29

1.3.4

CFD

1.4

CFD

3 14

( 77320 K Mach 2.0 2.5

1305K 1701K 2.0kg/s 3.0kg/s 0.52 0.88

DES CFD

30

8 CFD

CFD

31

[62-64]

2.1

2-1 [62-64]

2-1 [33]

2-2 Gardon q

Tc-Tb

32

2-2 Gardon

Gardon Gardon

2-3 2-4

2-3 Gardon [33]

33

q

K

E

2-4

2.2

1. 1/3

2.

3.

4.

5.

1.

2. 4.110-5/K

1.6710-5/K

3.

34

4.

2.3

1Cr18Ni9Ti

25 W/mK 20W/mK

M450 2-5

450

35

2-5 M450

2-1

, []

315 SnPbAg 312

SD-585T Sn99Bi0.3Ag0.7 227 230 30-40

SD-510T Sn64Bi35Ag1 172 190 30-40

2-6

36

18

27

227

312700

2-6

2.3.1

30 25 85%

2-7 3

K1 12.452.84W/cm2/mV K2 35.312.5K/mV

8.231.20s 3-16

37

0 5 10 15 20 25 30 35 400

20

40

60

80

100

120

140

160

180

200

New structure

Original structure

K2(

K/m

V )

K1(W/cm

2/mV)

2-7

2.4

15

2.4.1

2-8

38

M

Cooling

WatermL/sHB484N

mVXMZ600B

degCXMZ600B

degCXMZ600B

NI USB 6009

degCXMZ600B

WHB404W-ZB

1.

2. 3.

4.

5. 6.

7. 9.

8.

10. -

11. -

12. -

17 -

18. -

13.

14.

15.

16.

2-8

1. (1,2,3,4,5,13)(8,9,16,7)(9,10,11,12,17,18,14,15)

(6)

2. (1)(3)(2)(4)

(5)(13)

3. (8)(9)(16, 2-12)

(7)

4. (9)(10,11,18)(12)

(17)(14)(15) 2-9

5. P

Qwater E Tb Twater

Th

6. P

2-14 2-15(2-1) K1 K2

1 2

4PK

D E (2-1)

39

2h bT TK

E

(2-2)

2-9

2-10

40

2-11

2-12 0.25mm K

OMEGA CHAL-010-BW

LabVIEW

2-12

LabVIEW 2-13

41

2-13 LabVIEW

2.4.2

10s

35s

LabVIEW 2-14 2-15 excel

42

2-14

wsf 11:05 2013/12/5 s217

c:\Documents andSettings\Administrator\MyDocuments\\\time_data_13-12-05_1053_001.lvm

c:\Documents andSettings\Administrator\MyDocuments\\\calibration_data_13-12-05_1053_001.lvm

43

2-15

2-16

7%

44

0.0 0.8 1.6 2.4 3.2 4.0 4.8 5.6 6.4 7.2 8.00

20

40

60

80

100H

ea

t flu

x (

W/c

m2)

Output Voltage (mV)

Heat Flux (EHM)

Heat Flux (HTBBRM)

Linear fit

Linear fit

0.0 0.8 1.6 2.4 3.2 4.0 4.8 5.6 6.40

20

40

60

80

100

120

140

160

180

Te

mp

era

ture

diffe

ren

ce

(d

eg

C)

Output Voltage (mV)

Temperature difference

Linear fit

(a) (b)

2-16 EHM HTBBRM

2.5

45

3.1

3.1.1

3-1

O2 H2

Fuel Tank

Cooling Water

Gas Valve

System

Water Pump

Air Heater Combustor AssemblyNozzleP-2P-4

Air

P-5

Water Valve

SystemP-6

P-8P-9

P-10

P-44

Two-Stage Fuel Heater

P-11

P-12

P-45

DAQ

&

Control

Pressure Measurement System

P-14P-15P-16P-35P-36P-37P-38P-39P-40P-41P-42P-43

Heat Flux Measurement System

P-7P-8P-9P-10P-11P-12

P-26P-27P-28P-29P-30P-31P-32P-33P-34

Sonic Nozzle

3-1

0.6-4.0MPa

700-2200 K 5.0 kg/s 60 s Vitiated air

0.1% CYB-10S

B

1%

3.1.2

3-2 1Cr18Ni9Ti

46

0.72.0 5.3

20mm 2mm 3mm

5mm Ra=3.2

34 1mm 24 18mm

3-2 12mm 7 50

64mm 4 2.65mm

8mm 9 0.4mm 9

1mm

3-2

3.1.3

MicroMaster440SamHydraulik 3-3

[65]

47

[66]

7685 K 2.87 4.56 MPa

11

3-3

3.1.4

3-2 0.1% Motorola MPX2200

3-4

48

P-17

DAQNI PCI 6225

P-15

P-55

TC-K

3-4

3-5

3-4 200L (WILO

MVI410-1/16/E/3-380-50-2 10bar) SS-

33S6FNU.ER.T-1.6mm-G1/4 SNS-APU6*4

CN 203519207U

49

[67], 3-7 18 mm

12% Ra3.2

2.4

10s

18

27

3-6

50

3-7

E Tb(Contronix CH6)

(NI PCI 6225) 10 Hz

LabVIEW Excel

30 mL/s

3.1.5

2mm 1mm

0.8 1.2 mm 1.0mm0.5mm 0.1mm

0.1mm

51

(a)

(b)

3-8

3.1.6

1.

2. 1

10 3

35 18 35 20

35 3-9

15

3.

52

0 10 20 30 40 50 600

5

10

15

20

25

30

35

40

Total Pressure

Fuel PressureP

ressure

[bar]

Time [s]

0

200

400

600

800

1000

1200

combustion

heating

Total Temperature

Tem

pera

ture

[K

]

Exp No.7

aerodynamic

heating

3-9 7

3.1.7

qm T0 P0 H2, kerosene

Mach , 3-1

3-10

4 3-11

53

0 500 1000 1500 20000

20

40

60

80

100

120

140

160

180

Sta

tic P

ressu

re[k

Pa

A]

Axial Position [mm]

6 7

8 9

10 11

12 13

14 15

16 17

18 19

20 21

22 23

24 25

26 27

28 29

30 31

32 33

34 35

Mean(cold)

Mean(hot)

2014011601 Static Pressure

3-10

70 80 90 100 1100

1

2

3

4

5

6

7

channel 1

channel 2

channel 3

channel 4

channel 5

channel 6

channel 7

channel 8

channel 9

channel 10

channel 11

channel 12

channel 13

channel 14

channel 15

channel 16

channel 17

channel 18

channel 19

channel 20

Heat flux s

ensor

sig

nal E

[m

V]

Time [s]

Sensor 19

N = 59

Mean = 6.76704

SD = 0.02964

3-11

[41] Mach

54

3.1.8

14 3-1

Mach 5

3-2

3-1

Mach

Exp.

No. DataSet ID Ma T0 (K)

P0

(bar)

qm

(g/s) kerosene H2 Comment

1 2014011401 2.5 1605 9.66 3086 0 0

2 2014011402 2.5 1608 9.6 3075 0 0

3 2014011601 2.5 1595 9.53 3074 0.56 0.189

4 2014012702 2.5 1619 9.51 3091 0.55 0.149

5 2014022501 2.5 1622 8 2578 0 0

6 2014031101 2.5 1627 8.01 2568 0.72 0.095

7 2014031701 2.5 1701 8.11 2580 0.59 0

8 2014031802 2 1289 4.16 2574 0.69 0.094

9 2014032001 2 1308 4.15 2579 0.88 0.098

10 2014032002 2 1308 4.15 2577 0.52 0.095

11 2014032103 2 1314 3.76 2008 0.71 0.096

12 2014032105 2 1306 4.94 3061 0.7 0.091

13 2014032402 2 1469 4.45 2556 0.7 0.093

14 2014032502 2 1686 4.75 2539 0.7 0.093

3-2

0 1,2 - 1 6,14 Mach 2.52.0 2 11,8,12 2.0, 2.5, 3.0 kg/s 3 10,8,9 0.5, 0.7, 0.9 4 8,13,14 1300, 1500, 1700 K

3.2

A B

55

Exp.No.##x## 3-1 ##

x c x h

3.2.1

5 3-12

1

20km 5kPa

2 3.7 4.7

3 3-16 5% 95% 8.231.20

15

56

0 200 400 600 800 1000 1200 1400 1600 1800 20000

40

80

120

160

200

240

280 Static Pressure

Exp No. 1

Exp No. 2

Sta

tic P

ressure

[kP

a]

x, [mm]

0

1

2

3

4

Mach Number

Exp No. 1

Exp No. 2

Calc

ula

ted

Ma

ch

Nu

mb

er

1

3-12 1, Mach

0 200 400 600 800 1000 1200 1400 1600 1800 20000

10

20

30

40

50

60

70 Exp.No.1

Exp.No.2

Heat flux [W

/cm

2]

x, [mm]

3-13 1,

57

0 200 400 600 800 1000 1200 1400 1600 1800 20000

10

20

30

40

50

60

70

Exp.No.1

Exp.No.2

Heat flux [W

/cm

2]

x, [mm]

vertical distribution:

increase from upper wall to lower wall

3-14 1,

0 200 400 600 800 1000 1200 1400 1600 1800 20000

10

20

30

40

50

60

70

Exp.No.1

Exp.No.2

Heat flux [W

/cm

2]

x, [mm]

3-15 1,

58

70 80 90 100 1100

1

2

3

4

5

6

7

channel 1

channel 2

channel 3

channel 4

channel 5

channel 6

channel 7

channel 8

channel 9

channel 10

channel 11

channel 12

channel 13

channel 14

channel 15

channel 16

channel 17

channel 18

channel 19

channel 20

Heat flux s

ensor

sig

nal E

[m

V]

Time [s]

Sensor 19

Rise Time=7.71482

Rise Range=6.05045

3-16 Origin 5%-95%.

3.2.2

3-20 Mach

6

5

1900 mm

3-19

2.5 1.2

1400mm 1500mm

3.3

59

0 200 400 600 800 1000 1200 1400 1600 1800 20000

50

100

150

200

250

300

Static Pressure

Exp No. 12c

Exp No. 12h

Sta

tic P

ressure

[kP

a]

x, [mm]

10.0

0.5

1.0

1.5

2.0

2.5

3.0

3.5

4.0

Mach Number

Exp No. 12c

Exp No. 12h

Calc

ula

ted

Ma

ch

Nu

mb

er

3-17 No.12 Mach

0 200 400 600 800 1000 1200 1400 1600 1800 20000

25

50

75

100

125

Exp.No.12 w/o combustion

Exp.No.12 with combustion

Heat flux [W

/cm

2]

x, [mm]

3-18 No.12

60

0 200 400 600 800 1000 1200 1400 1600 1800 20000

25

50

75

100

125



Heat flux [W

/cm

2]

x, [mm]

vertical distribution flipped

after combustion

3-19 No.12

0 200 400 600 800 1000 1200 1400 1600 1800 20000

25

50

75

100

125



Heat flux [W

/cm

2]

x, [mm]

3-20 No.12

3.2.3

3 kerosene 0.52 0.88

61

3-21- 3-24 3-21 kerosene

0 200 400 600 800 1000 1200 1400 1600 1800 20000

50

100

150

200

250

300

Static Pressure

Exp No. 10h

Exp No. 8h

Exp No. 9h

S

tatic P

ressure

[kP

a]

x, [mm]

0.0

0.5

1.0

1.5

2.0

2.5

3.0

Mach Number

Exp No. 10h

Exp No. 8h

Exp No. 9h

Calc

ula

ted M

ach N

um

ber

3-21 3: kerosene0.5, 0.7, 0.9, T01300K, qm2.5 kg/s, H2 0.1. Mach

0 200 400 600 800 1000 1200 1400 1600 1800 20000

25

50

75

100

125

Exp.No.10 kerosene

=0.52

Exp.No.8 kerosene

=0.69

Exp.No.9 kerosene

=0.88

Heat flux [W

/cm

2]

x, [mm]


62

0 200 400 600 800 1000 1200 1400 1600 1800 20000

10

20

30

40

50

60

70

80

Exp.No.10 kerosene

=0.52

Exp.No.8 kerosene

=0.69

Exp.No.9 kerosene

=0.88

Heat flux [W

/cm

2]

x, [mm]


0 200 400 600 800 1000 1200 1400 1600 1800 20000

25

50

75

100

125

Exp.No.10 kerosene

=0.52

Exp.No.8 kerosene

=0.69

Exp.No.9 kerosene

=0.88

Heat flux [W

/cm

2]

Location, [mm]


[23]

2.230.01 kg/s

63

3-25

0 10 20 30 40 500

5

10

15

20

25

30

35

coolin

g w

ate

r outlet te

mpera

ture

ris

e (

degC

)

Time (s)

exp. 10 combustor

exp. 8 combustor

exp. 9 combustor

3-25

9

9

64

3.2.4

2 3-29 Mach

Mach q qm0.8

[41]

2/5

0.8

1/5Pr R

0

e

.0287 mp p m

quc T c Tt

Aq qS (3-1)

0 200 400 600 800 1000 1200 1400 1600 1800 20000

50

100

150

200

250

300

Static Pressure

Exp No. 11h

Exp No. 8h

Exp No. 12h

Sta

tic P

ressure

[kP

a]

x, [mm]

0

1

2

3

Mach Number

Exp No. 11h

Exp No. 8h

Exp No. 12h

Calc

ula

ted

Ma

ch

Nu

mb

er

3-26 2: qm 2.0 kg/s 3.0 kg/s T01300K, kerosene0.7, H20.1 Mach

65

0 200 400 600 800 1000 1200 1400 1600 1800 20000

25

50

75

100

125

Exp.No.11 qm=2008 g/s



Heat flux [W

/cm

2]

x, [mm]


0 200 400 600 800 1000 1200 1400 1600 1800 20000

10

20

30

40

50

60

70

80




Heat flux [W

/cm

2]

x, [mm]


66

0 200 400 600 800 1000 1200 1400 1600 1800 20000

25

50

75

100

125




Heat flux [W

/cm

2]

x, [mm]


3.2.5

4 3-33 qm

T0 P0 T0 0.5

67

0 200 400 600 800 1000 1200 1400 1600 1800 20000

50

100

150

200

250

Static Pressure

Exp No. 8h

Exp No. 13h

Exp No. 14h

Sta

tic P

ressure

[kP

a]

x, [mm]

0

1

2

3

Mach Number

Exp No. 8h

Exp No. 13h

Exp No. 14h

Calc

ula

ted

Ma

ch

Nu

mb

er

3-30 4: T0 1289K 1687K qm 2.5 kg/s, kerosene0.7, H20.1 Mach

0 200 400 600 800 1000 1200 1400 1600 1800 20000

25

50

75

100

125

Exp.No.8 T0=1289 K

Exp.No.13 T0=1469 K

Exp.No.14 T0=1687 K

Hea

t flu

x [

W/c

m2]

x, [mm]

3-31 4: T0 1289K 1687K qm 2.5 kg/s, kerosene0.7, H20.1

68

0 200 400 600 800 1000 1200 1400 1600 1800 20000

15

30

45

60

75

Exp.No.8 T0=1289 K

Exp.No.13 T0=1469 K

Exp.No.14 T0=1687 K

Hea

t flu

x [

W/c

m2]

x, [mm]


0 200 400 600 800 1000 1200 1400 1600 1800 20000

25

50

75

100

125

Exp.No.8 T0=1289 K

Exp.No.13 T0=1469 K

Exp.No.14 T0=1687 K

Heat flux [W

/cm

2]

x, [mm]


3.2.6 Mach

Mach 4 3-37

69

Mach 2.5

Mach Mach 2.5

Mach 2.0

Mach 2.5 Mach 2.0

Mach 2.5 Mach 2.0 Mach

0 200 400 600 800 1000 1200 1400 1600 1800 20000

50

100

150

200

250

300

Static Pressure

Exp No. 6h

Exp No. 14h

Sta

tic P

ressure

[kP

a]

x, [mm]

0.0

0.5

1.0

1.5

2.0

2.5

3.0

3.5

4.0

Mach Number

Exp No. 6h

Exp No. 14h

Calc

ula

ted

Ma

ch

Nu

mb

er

3-34 1 Mach 2.5 2.0, T0 1650K, qm 2.5kg/s, kerosene0.7, H20.1

Mach

70

0 200 400 600 800 1000 1200 1400 1600 1800 20000

25

50

75

100

125

Exp.No.6 Ma=2.5

Exp.No.14 Ma=2.0

Heat flux [W

/cm

2]

x, [mm]


0 200 400 600 800 1000 1200 1400 1600 1800 20000

10

20

30

40

50

60

70

80

Exp.No.6 Ma=2.5

Exp.No.14 Ma=2.0

Heat flux [W

/cm

2]

x, [mm]


71

0 200 400 600 800 1000 1200 1400 1600 1800 20000

25

50

75

100

125

Exp.No.6 Ma=2.5

Exp.No.14 Ma=2.0

Heat flux [W

/cm

2]

x, [mm]


3.3

10%

[15, 16]

( ) ( )aw w rad aw wq h hT T q T T (3-2)

h Tw Taw

[41]:

3 * 2

23 *

02

1 Pr1

Pr2

11

aw

p

Ma

T Tu

cMa

T

(3-3)

1000K 3000K Pr* 0.73 1.33

0(0.93 0.0 for Ma [1,4]1)aw TT (3-4)

Taw T0 Mach

0(0.93T T )wq h (3-5)

72

Tw T0

h T0

0

0

0.93

0.93 wq

Tq h

h T T

(3-6)

T0

Stanton

12 4

h

2/5 1/5 2/5

0.2

0.8 0.8 0.20.02870.028

StPr R

7

e Prx

pmp p m

cuc c q

A

qh xA

(3-7)

h x-0.2

1

[53] p3/p1

3

.8

1

0

peak

ref

q p

q p

(3-8)

T0 h

3.3.1

T0, Ma qm

(3-5) (3-7) (3-9) Mach

0.8 20( ) Ma1mK cq q T b (3-9)

73

3-3 (3-10)

20.8

20T27.03 0.653 1 0.05766[W/ cm ] 1000[K]

Ma[kg/ s]

mqq

(3-10)

3-38 3-498%(3-9)

3-3

Exp.No. Ma T0 qm qavg,isolator q

1000K kg/s W/cm2 W/cm2

1 2.5 1.605 3.086 39.59 40.56

2 2.5 1.608 3.075 40.22 40.57

3 2.5 1.595 3.074 38.78 39.99

4 2.5 1.619 3.091 40.74 41.18

5 2.5 1.622 2.578 36.91 35.72

6 2.5 1.627 2.568 37.47 35.81

7 2.5 1.701 2.58 39.15 38.68

8 2 1.289 2.574 28.73 28.18

9 2 1.308 2.579 29.16 29.05

10 2 1.308 2.577 29.05 29.07

11 2 1.314 2.008 23.11 24.03

12 2 1.306 3.061 33.67 33.22

13 2 1.469 2.556 35.58 35.94

14 2 1.686 2.539 45.29 45.25

74

20 25 30 35 40 4520.0

22.5

25.0

27.5

30.0

32.5

35.0

37.5

40.0

42.5

45.0

47.5

Fitted data Points

y=x

y=(15%)x

Isolator Heat Flux Average at Cold State (W/cm^2)

Fitte

d d

ata

Poin

ts

20.8

20T27.03 0.653 1 0.05766[W/ cm ] 1000[K

Ma[k / ]g s]

mqq

3-38

3-4 R2

K K c c b b

2 R2

27.02864 1.94519 0.6529 0.0408 -0.05766 0.00394 3.12408 0.9787

3-40 3-41 3-41 3-42

Mach 2.0

Mach 2.0 Mach 2.5

Mach 2.0 x=1000mm

Mach 2.0

Mach2.5

75

0 200 400 600 800 1000 1200 1400 1600 1800 20000.0

0.2

0.4

0.6

0.8

1.0

1.2

1.4

1.6

1.8

2.0

convergence

Mach 2.0 cases w/o combustion

Upper Wall

Lower Wall

Norm

aliz

ed H

eat flux

x, [mm]

divergence

3-39 Mach 2.0

0 200 400 600 800 1000 1200 1400 1600 1800 20000.0

0.2

0.4

0.6

0.8

1.0

1.2

1.4

1.6

1.8

2.0

Mach 2.5 cases w/o combustion

Upper Wall

Lower Wall

Norm

aliz

ed H

eat flux

x, [mm]

divergence

convergence

3-40 Mach 2.5

76

0 200 400 600 800 1000 1200 1400 1600 1800 20000.0

0.5

1.0

1.5

2.0

2.5

3.0

3.5

4.0

Mach 2.0 cases

with combustion

Upper Wall

Lower WallN

orm

aliz

ed H

eat flux

x, [mm]

3-41 Mach 2.0

0 200 400 600 800 1000 1200 1400 1600 1800 20000.0

0.5

1.0

1.5

2.0

2.5

3.0

3.5

4.0

Mach 2.5 cases

with combustion

Upper Wall

Lower Wall

Norm

aliz

ed H

eat flux

x, [mm]

Dashed line:

Liquid fuel

Solid line:

Supercritical fuel

3-42 Mach 2.5

77

3.4

Mach 2.0 2.5

1300K 1600K 2.0 3.0kg/s 0.5 0.9

1.

4

2.

0.3

2.35

3.40 5.0 7.8

4-5

2MW/m2 4.0

3.

0.8

Mach

4.

Mach 2.0

78

4.1

VerificationValidation[68]

Guide: Guide for the

Verification and Validation of Computational Fluid Dynamics Simulations AIAA G-077-1998

VerificationValidation

Verification: The process of determining that a model implementation

accurately represents the developer's conceptual description of the model and

the solution to the model.

Validation: The process of determining the degree to which a model is an

accurate representation of the real world from the perspective of the intended

uses of the model.

Detached Eddy Simulation, DES CFD

Validation

4.2

79

4.2.1

[33]

4-1

Cf

4-1

1. , ( )m fuelq x

2. ,m inletq

3. , , ( )( )m m inlet m fuelq q q xx

4. ( ), 1,2,3...m ip x i N p(x)

5. A(x) Cw(x)

6. u0 T0

7. cf =0inju

80

(4-1) u(x)

( ) (x)2

( ) ( ) ( )f m

m inj m w

cd q u x p

q ux A x u dqx dA C dx

Ap (4-1)

8. 0( 0)u x u u(x)

9. F

m moutlet inletF q u pA q u pA (4-2)

10.

mq uA (4-3)

( )x

11.

u

inlet

R Tp

MW (4-4)

T(x)

12.

, ( )s s inleth h T (4-5)

13.

2

2st sh h

u (4-6)

14. ( )wT x Eckert

hawStanton St cf

15. 7

16. ( )q x

17.

81

, , , ,0

,

cos-

xw

m st m inlet st inlet m fuel st fuel

m fuel

q h q hqC

dxq h

q LHV

(4-7)

LHV ,st fuelh

tan/

wC

dA dx (4-8)

4.2.2

[33] 4-2

250mm 250mm 1000mm

1000mm

0 500 1000 1500 20000

10

20

30

40

50

60

70

80

Exp. No. (2), Ma = 2.5, T0=1608.1[K], qm=3075[g/s],

Kerosene=0,

H2=0

Wa

ll H

ea

t F

lux(W

/cm

2)

x (mm)

Upper Wall

West Wall

Lower Wall

Quasi-1d heat flux

4-2 2

4.2.3

6 7

Mach 2.5

82

4-3 4-4

0 400 800 1200 1600 20000

25

50

75

100

125

Exp. No. (6h), Ma = 2.5, T0=1626.8[K], qm=2567.7[g/s],

Kerosene=0.72,

H2=0.095

Heat F

lux (

W/c

m2)

x (mm)

Exp. No. 6h

Calculated Value

Upper Wall

West Wall

Lower Wall

4-3 6

0 400 800 1200 1600 20000

25

50

75

100

125

Exp. No. (7h), Ma = 2.5, T0=1701[K], qm=2580.3[g/s],

Kerosene=0.59,

H2=0

Heat F

lux (

W/c

m2)

x (mm)

Exp. No. 7h

Calculated Value

Upper Wall

West Wall

Lower Wall

4-4 7

83

Mach 2.0 8 4-5

Mach

0 500 1000 1500 20000

10

20

30

40

50

60

70

80

90

100

110

120

25

50

75

100

125

150

175

200

225

Exp. No. (8h), Ma = 2, T0=1288.9[K], qm=2574.1[g/s],

Kerosene=0.69,

H2=0.094

Wall

Heat F

lux(W

/cm

2)

Location (mm)

Upper Wall

West Wall

Lower Wall

Quasi-1d

heat flux

Static Pressure

Sta

tic P

ressure

(kP

aA

)

4-5 8

84

0 400 800 1200 1600 20000

500

1000

1500

2000

2500

3000

0

10

20

30

40

50

60

70

80

90

(K)

x (mm)

(W/c

m2)

4-6 8

DES 4-10

4.3 CFD

CFD 8

[69] CFD

OpenFOAM

DES LES

S-A RANS

directed relation

graph-aided sensitivity analysis, DRGEPSA RP-3 48

/197

(Partially-Stirred Reactor, PaSR)

85

(In Situ Adaptive Tabulation, ISAT)

2000

4-7

0 200 400 600 800 1000 1200 1400 1600 1800 20000

50

100

150

200

250

Sta

tic P

ressure

(kP

a)

x (mm)

DES Pmean

Measurement

4-7 DES

4-9

1ms

CFD

86

0 200 400 600 800 1000 1200 1400 1600 1800 20000

25

50

75

100

125

150

175

200

Exp. No. (8h), Ma = 2, T0=1288.9[K], q

m=2.57[kg/s],

Kerosene=0.69,

H2=0.094

Heat F

lux (

W/c

m2)

x (m)

DES upper wall

Upper

4-8 DES

0 200 400 600 800 1000 1200 1400 1600 1800 20000

25

50

75

100

125

150

175

200

Exp. No. (8h), Ma = 2, T0=1288.9[K], q

m=2.57[kg/s],

Kerosene=0.69,

H2=0.094

Heat F

lux (

W/c

m2)

x (m)

DES lower wall

Lower

4-9 DES

DES

87

4-10 50mm X

X

200mm 600mm

9

4-11

4-10

900mm 1100mm

1400mm

1400mm

4-10 DES

88

4-11 DES

4-11 4-12

4-13

4-12

89

4-13 DES

4.4

DES CFD

8 DES

DES

1/3DES

DES

90

[6, 70]

CFD

VerificationValidation

Validation

Verification CFD

CFD CFD

5.1

[71]

91

//(Conserved Mass/Momentum/Energy Method,

CMME)//(Conserved Mass/Energy/Entropy Method, CMES)

(Langley Distortion Methodology, LDM)

CMME CMMS

CFD LDM

distortion parameters/

CMME

5.1.1

CFD

3

1

i i i i

i

y x yx

0i iV A

dV u n dAt

(5-1)

( )i i j ij ij j iV A V

u dV u u n dA dVpt

f

(5-2)

2 2

i i i is s

V A

i i ij i j

V V A A

u u u ue dV h dA

t

dV QdV n dA qdf u u A

(5-3)

V A in

iu se sh ij if

Q q ij

Kronecker delta(5-4)

92

0,

1,ij

i j

i j

(5-4)

(5-1)-(5-3)

CFD

p T

uRp

TMW

(5-5)

( , )ih h T x (5-6)

AiAe Aw

Control Volume

pTu,v,wh

AwAe

A i n

inflow outflow

x

y

fvqv

z

5-1 (Control Volume)

0t

(5-7)

0i iA

u n dA (5-8)

93

( )i j ij ij j iA V

u u n dAp dVf (5-9)

2

i ii i s i i ij i j i i

A V V A A

f uu u

u n h dA dV QdV n dA nu q dA

(5-10)

i i

A

i iA

u n dA

u n dA

V

V

dV

dV

Ai Ae

advective transport rate

Pe 1diffusive transport rate

(5-11)

A

i w eA AA A (5-12)

e i w

i iA A AudA udA dAnu (5-13)

22

= cos si

+

ne i

w w w

A A

i i w w w w i iA A A V

p p

n

u dA u dA

u udA pdA dA f u dV (5-14)

e i w w

st st i i st w i iA A A A V Vu dA uh dA u n h dA q dA QdVh f u dV (5-15)

1Fru

fL (5-16)

e i w

i iA A A

udA udA dAnu (5-17)

22

= co

+

s sin

e i

w w w

A A

i i w w w wA A A

p pu dA u dA

u udA pdA An d

(5-18)

e i w w

st st i i st wA A A A V

u dA uh dA u n h dA q dA dh Q V (5-19)

94

5.1.2

m

Aq udA (5-20)

, , ,m e m i m wq q q (5-21)

2

= A

m

uu

q

dA (5-22)

AA

ppd

A

(5-23)

, ,, ( )e i i i m w inj wm e e e m i we iq u p q u p q u p FA A A A (5-24)

wp p (5-25)

, ,, ( )e i i i m w injm e e m i wie eq u p q u p uA FA q p A A (5-26)

sh sth

=s

As

m

uhh

q

dA (5-27)

=st

Ast

m

uhh

q

dA (5-28)

,, , ,=ste sti m w st injm e m i w bq q q h Q Qh h (5-29)

dx 0

,m m wdq dq (5-30)

95

( )m inj wmd q u pA u dq dAp dF (5-31)

,( )m st st inj m w bq h h q dd dQd Q (5-32)

=mA

vA

u dA q

qudA

(5-33)

MW

m A

n

A

udAqMW

uqdA

MW

(5-34)

T

u

pMWT

R (5-35)

5.1.3

2

f m w

w

c uxd d

q CF

A (5-36)

( )

cos

aw w w mw

h h CdQ

A

qSt dx

(5-37)

,b m fuelQ q LHV (5-38)

96

fc Darcy LHV bQ

CFD

( )- -m inj mw d q u pA u dq dAdF

dx

p

dx

(5-39)

2 ( )- -m inj mf

m w

A d q u pA u d dA

q

q pc

u dxC

(5-40)

(5-41)

,( )m t t inj m wq h h dq Qd d (5-41)

Stanton

,= ( )-w

w m t t inj m

qC dxddQ q h h dq

cos (5-42)

,

( )

( )( ) - ( ) -A x

A x inlw m t m t t injetinlet

mQ q h q h h dq (5-43)

,( ) co(

s

)

m t t inj m

aw w w m

q h h dqASt

h h

d

dxqC

(5-44)

haw

2

3 Pr2

aw hhu

(5-45)

(5-32)(5-41)

, -o ob m st t f n fi j m mdQ d dq h h h dq q h (5-46)

, ,

( )

,

-( )

+inlet

o o o

f inj m fuel f fA A x

m fuel

h q uh dA uh dAx

q LHV

(5-47)

97

5.2 CFD

5-2 CFD

CFD

5-2 CFD

5.2.1 CFD

OpenFOAM DES

[39] CFD

5-3 mm 80mm

Mach 2.5 1600K 9.1bar 0.9

1000K Fluent 6.3 k

SST AUSM

Euler [72]

[73]

p(x)

_avg(x)_1d(x)

CFD/

(x,y,z,t)(x,y,z,t)

98

~ 1miny

paraview 4.3.1 3

5.2.2

ptop

CFD

0 200 400 600 800 1000 1200 14000

20

40

60

80

100

120

140

160

p_avg

(kP

a)

x (mm)

p_avg

p_top

p_side

5-4

80mm 5-5

99

0 200 400 600 800 1000 1200 14000

20

40

60

80

100

120

140

160

p_avg

(kP

a)

x(mm)

p_avg

p_side

16 pts AAv smooth of "p_side"

5-5

5.2.3

5-6

2%

Mach

100

0 200 400 600 800 1000 1200 14000

500

1000

1500

u_1d(m

/s)

x(mm)

u_1d(m/s)

u_avg

5-6(u_1d)(u_avg)

5.2.4

5-7

101

0 200 400 600 800 1000 1200 14000.0

0.1

0.2

0.3

0.4

rho_1d

(kg/m

3)

x(mm)

rho_1d

rho_avg

5-7

vA

v

A

udA qu

dA A

(5-48)

(5-49)

m vq u A (5-49)

vu (5-22)u

Hypersonic Air-breathing Propulsion[41]

Ac

(5-33)

102

mI pq u A

(5-50)

(5-22)

mcA

q

u (5-51)

Ac

0 200 400 600 800 1000 1200 14000.0

1.0E-3

2.0E-3

3.0E-3

A (

m2)

x(mm)

A

Ac

A_1d

5-8 (Ac)

5-8

Ac /

/ Ac

103

5.2.5

5-9

5%

0 200 400 600 800 1000 1200 14000

500

1000

1500

T_1d(K

)

x(mm)

T_1d

T_avg

5-9 (T_1d)(T_avg)

(4-4)

5-10

4%[48]

104

0 200 400 600 800 1000 1200 14000

5

10

15

20

25

30

Mean M

ole

cula

r W

eig

ht (k

g/k

mol)

x(mm)

MW_1d

MW_avg

5-10 MW_avg(MW_1d)

5.2.6

105

0 200 400 600 800 1000 1200 14000.0

0.2

0.4

0.6

0.8

1.0

1.2

1.4

1.6

1.8

hs_1d

(MJ/k

g)

x(mm)

hs_1d

hs_avg

5-11(hs_1d)(hs_avg)

5.2.7

5-12

106

0 200 400 600 800 1000 1200 14000.0

0.5

1.0

1.5

2.0

2.5

hst_

1d

(M

J/k

g)

x(mm)

hst_1d

hst_avg

5-12(hs_1d) (hs_avg)

2 2 2

2 2 2 2 2

1 2 3

2

( ) + ( )22 2

=

st s

s s s

st

u v wh h

u u uh T

vh T

wh

h

(5-52)

x x

CFD

107

0 200 400 600 800 1000 1200 1400

-0.04

-0.02

0.00

0.02

0.04

0.06

x(mm)

1

2

3

5-13

5-11 5-13

5.2.8

(5-39) 5-14

CFD

108

0 200 400 600 800 1000 1200 14000

50

100

150

200

250

F_1d (

N/m

)

x(mm)

F_1d

F_avg

5-14 (F_avg)(F_1d)

5.2.9

Stanton

5-15

CFD DES

109

0 200 400 600 800 1000 1200 14000

20

40

60

80

100

120

140

160

180

200

220

240

260

Integrate Qw_1d

Integrate Qw_avg

Inte

gra

teQ

w_1d

(kW

)

x(mm)

5-15 (Integrate Qw_avg)(Integrate Qw _1d)

5.3

CFD

/

RANS

1.

2.

3. 3%

4. CFD 24%

24%

5.

5% 8% 5% 10%

110

6.

CFD CFD

111

6.1

Mach2.02.5

1300K 1600K 2.0 3.0kg/s77320

K 0.5 0.9 0.1 14 5

Mach

Mach

Detached Eddy Simulation

CFD

8 DES

112

DES

1/3DES

DES

CFD

6.2

1. 1.5

1/8

2.

Validation

3. CFD

6.3

1.

3D 2.

3.

1.

2.

113

3.

4.

CFD

115

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A:

119

A:

14 A A-2 A-1

Exp.No.##x## 3-1 ## x c

x h

3-2

A:

121

A:

123

A-1

1 2 3c 3h 4c 4h 5 6c 6h 7c 7h 8c 8h 9c 9h 10c 10h 11c 11h 12c 12h 13c 13h 14c 14h mm W/cm^2 W/cm^2 W/cm^2 W/cm^2 W/cm^2 W/cm^2 W/cm^2 W/cm^2 W/cm^2 W/cm^2 W/cm^2 W/cm^2 W/cm^2 W/cm^2 W/cm^2 W/cm^2 W/cm^2 W/cm^2 W/cm^2 W/cm^2 W/cm^2 W/cm^2 W/cm^2 W/cm^2 W/cm^2

(K) 1605 1608 1595 1595 1619 1619 1622 1627 1627 1701 1701 1289 1289 1308 1308 1308 1308 1314 1314 1306 1306 1469 1469 1686 1686(bar) 9.66 9.6 9.53 9.53 9.51 9.51 8 8.01 8.01 8.11 8.11 4.16 4.16 4.15 4.15 4.15 4.15 3.76 3.76 4.94 4.94 4.45 4.45 4.75 4.75Mach 2.5 2.5 2.5 2.5 2.5 2.5 2.5 2.5 2.5 2.5 2.5 2 2 2 2 2 2 2 2 2 2 2 2 2 2 0 0 0 0.56 0 0.55 0 0 0.72 0 0.59 0 0.69 0 0.88 0 0.52 0 0.71 0 0.7 0 0.7 0 0.7H2 0 0 0 0.189 0 0.149 0 0 0.095 0 0 0 0.094 0 0.098 0 0.095 0 0.096 0 0.091 0 0.093 0 0.093

(g/s) 3086 3075 3074 3074 3091 3091 2578 2568 2568 2580 2580 2574 2574 2579 2579 2577 2577 2008 2008 3061 3061 2556 2556 2539 253980 38.5 38.8 35.0 35.9 36.5 37.5 32.4 33.0 33.7 36.5 38.2 27.5 29.3 27.6 32.3 27.6 29.6 18.4 17.2 33.5 36.8 33.5 36.5 44.3 48.8520 38.7 38.8 38.1 39.2 39.8 40.7 35.4 36.1 47.8 37.3 39.0 27.6 50.0 28.2 51.6 28.1 51.6 23.3 43.0 32.9 57.4 34.8 61.7 43.6 67.6871 18.9 19.3 17.4 45.2 19.0 71.4 21.8 21.8 106.2 23.6 71.1 15.7 102.0 16.3 105.6 16.4 110.5 13.1 86.0 19.6 104.3 19.6 103.2 24.9 115.81046 29.5 29.9 27.1 80.5 -- -- 27.1 27.9 110.5 30.7 95.9 21.1 93.9 21.5 90.2 24.4 92.5 19.9 83.1 29.6 110.7 31.3 101.1 38.0 110.51221 13.9 -- 26.9 87.0 24.1 92.0 20.8 22.6 112.8 18.0 103.4 12.4 84.6 11.9 87.3 12.2 71.6 9.5 64.9 16.3 111.4 16.1 99.1 18.9 119.51321 33.9 34.4 32.1 113.2 27.9 100.4 25.2 16.4 64.1 5.1 58.3 -- -- 16.6 95.2 16.1 81.6 13.0 76.9 20.3 106.9 20.5 99.4 25.8 107.31550 18.8 19.3 18.7 61.0 20.2 58.9 25.6 25.4 55.5 25.2 57.2 17.0 45.8 17.1 40.8 16.9 44.0 16.3 36.2 14.9 50.0 18.1 43.7 19.8 46.61900 13.2 13.8 12.4 65.9 -- -- -- 17.1 69.2 18.1 76.7 21.2 62.5 22.0 63.6 22.5 62.2 27.4 66.2 15.9 75.0 20.3 67.5 19.0 73.21046 27.2 27.7 30.5 86.3 29.5 77.9 25.0 25.6 68.0 24.5 65.9 18.4 49.2 18.7 42.8 19.4 52.7 15.8 45.8 22.8 54.5 23.7 60.8 28.5 56.51321 42.1 43.4 30.9 99.9 32.2 98.1 27.0 15.4 50.8 6.3 63.0 4.9 32.1 5.2 27.0 5.1 32.9 7.1 28.2 18.9 64.1 -- -- -- --1900 18.8 19.6 19.8 65.1 20.2 61.8 22.0 24.3 65.9 25.1 70.4 20.2 59.0 20.8 60.3 20.9 59.6 22.0 59.9 21.8 65.4 23.1 59.7 28.6 59.01900 45.0 44.5 44.6 76.8 43.1 73.3 40.2 41.8 63.4 42.3 72.3 25.7 57.0 25.9 50.6 25.6 62.9 22.6 55.4 29.1 62.4 31.5 58.7 38.5 64.980 42.7 43.7 43.7 45.8 46.4 47.8 43.2 43.3 45.0 44.4 46.3 32.0 32.7 32.5 50.3 32.5 33.6 27.9 29.2 37.2 38.2 40.1 41.1 50.8 52.4520 38.4 39.5 38.3 38.9 40.2 40.4 36.6 37.5 49.4 38.3 38.7 27.8 48.3 28.3 46.1 28.0 49.2 22.9 43.0 31.2 53.9 33.9 60.0 42.4 68.4736 33.2 33.8 32.8 40.4 35.1 38.9 32.3 -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- -- --871 25.8 28.0 32.2 55.8 32.2 52.9 28.4 29.4 67.2 27.9 39.3 20.1 33.5 20.4 31.6 20.5 37.1 16.6 31.5 22.6 34.5 23.9 42.7 29.0 50.4971 30.7 31.2 29.5 72.0 32.3 74.0 32.1 30.3 92.5 31.7 87.1 25.4 50.7 25.8 55.2 26.4 61.9 21.1 49.8 30.3 53.7 31.7 65.8 39.1 78.21221 16.7 17.6 17.6 123.1 18.2 128.0 15.1 16.0 101.0 15.2 118.4 10.8 89.7 11.2 87.9 10.9 89.2 8.9 78.1 12.9 97.2 13.4 93.7 16.8 99.51550 28.4 29.0 27.8 153.7 28.9 149.0 33.0 31.6 107.9 29.4 89.9 28.0 79.6 29.0 77.9 28.4 67.0 30.9 61.9 24.6 79.7 25.9 76.4 26.7 85.71900 61.5 51.1 59.3 80.0 63.1 81.8 66.6 64.6 78.7 64.2 72.7 37.2 62.5 37.9 53.1 37.7 62.1 29.7 55.6 39.6 65.7 45.3 63.8 52.7 69.0

124

A-2

1 2 3c 3h 4c 4h 5 6c 6h 7c 7h 8c 8h 9c 9h 10c 10h 11c 11h 12c 12h 13c 13h 14c 14h mm kPa kPa kPa kPa kPa kPa kPa kPa kPa kPa kPa kPa kPa kPa kPa kPa kPa kPa kPa kPa kPa kPa kPa kPa kPa

(K) 1605 1608 1595 1595 1619 1619 1622 1627 1627 1701 1701 1289 1289 1308 1308 1308 1308 1314 1314 1306 1306 1469 1469 1686 1686(bar) 9.66 9.6 9.53 9.53 9.51 9.51 8 8.01 8.01 8.11 8.11 4.16 4.16 4.15 4.15 4.15 4.15 3.76 3.76 4.94 4.94 4.45 4.45 4.75 4.75Mach 2.5 2.5 2.5 2.5 2.5 2.5 2.5 2.5 2.5 2.5 2.5 2 2 2 2 2 2 2 2 2 2 2 2 2 2 0 0 0 0.56 0 0.55 0 0 0.72 0 0.59 0 0.69 0 0.88 0 0.52 0 0.71 0 0.7 0 0.7 0 0.7H2 0 0 0 0.189 0 0.149 0 0 0.095 0 0 0 0.094 0 0.098 0 0.095 0 0.096 0 0.091 0 0.093 0 0.093

(g/s) 3086 3075 3074 3074 3091 3091 2578 2568 2568 2580 2580 2574 2574 2579 2579 2577 2577 2008 2008 3061 3061 2556 2556 2539 253975 40.99 40.98 41.05 41.61 42.55 42.53 34.75 35.97 35.60 37.25 37.32 44.16 43.82 43.69 62.99 43.90 43.69 35.00 34.68 52.91 52.73 49.22 48.84 53.98 53.51125 61.53 61.48 61.54 61.91 62.82 62.88 51.69 52.98 53.27 54.89 55.23 57.86 58.13 57.61 126.37 57.91 57.77 46.03 49.17 69.64 76.93 64.52 64.21 70.66 70.87175 38.40 38.59 38.83 39.16 39.94 39.98 32.80 33.80 33.91 35.67 35.88 38.80 54.06 38.16 101.38 38.55 38.16 30.98 66.48 46.35 91.49 43.52 45.79 47.89 47.11225 41.89 42.66 42.73 43.12 45.57 45.75 37.76 39.84 40.27 41.09 41.38 43.07 96.94 42.36 118.40 42.69 42.80 36.05 91.22 51.39 127.29 47.63 79.70 51.96 51.60275 30.94 30.84 30.98 31.51 32.40 32.48 25.88 27.12 27.09 28.15 28.40 33.50 110.44 33.25 150.68 33.48 76.79 26.30 100.90 40.64 146.44 37.82 121.70 42.18 44.40325 46.35 46.22 45.99 46.40 47.47 47.59 39.03 39.95 39.63 40.96 41.30 42.06 118.16 41.52 145.86 41.81 44.14 33.45 104.33 50.34 150.06 46.63 110.47 51.11 50.61375 41.14 41.12 41.63 42.04 44.02 44.44 36.96 38.53 39.14 39.69 40.37 42.49 130.04 41.82 169.17 41.92 107.36 34.87 109.46 49.89 175.53 46.71 140.06 50.95 70.65425 41.35 41.21 41.16 41.40 42.82 42.82 35.17 36.28 36.13 37.51 37.91 41.61 152.39 41.33 181.20 41.52 120.36 33.16 115.61 49.72 197.02 46.60 147.38 51.32 87.08475 36.23 36.14 36.27 36.66 37.67 37.68 30.74 32.27 31.96 33.03 33.17 34.94 160.41 34.62 190.13 34.62 126.06 27.86 119.09 41.81 205.59 38.85 147.97 42.84 113.89525 38.94 38.98 38.93 39.37 40.50 42.25 33.19 41.81 45.64 34.92 35.10 36.46 171.43 35.81 192.59 36.27 128.66 29.21 123.29 43.38 215.99 41.69 151.74 46.31 121.70675 42.99 43.15 43.53 102.62 41.40 54.43 36.99 38.74 124.16 39.88 40.04 41.99 193.60 42.14 206.71 42.61 152.30 34.36 142.06 50.57 236.69 47.62 180.74 52.17 164.31725 37.47 37.08 37.57 118.57 34.56 97.73 31.17 32.33 123.14 34.04 36.16 39.45 198.79 39.09 208.44 39.71 161.13 31.94 147.86 48.71 242.21 44.86 188.46 49.65 174.99775 38.98 39.05 39.37 126.25 36.43 121.60 33.08 35.19 135.63 37.20 61.12 39.15 171.99 -- -- 37.50 165.64 30.23 149.79 45.32 243.01 -- -- 45.96 184.20825 36.00 36.19 36.32 138.00 33.23 121.55 30.02 31.86 130.05 33.25 98.72 35.97 201.90 35.59 211.81 35.86 167.83 28.63 151.59 43.87 244.85 40.37 195.17 44.32 185.05875 36.03 36.16 36.59 136.13 33.80 125.83 30.82 31.91 131.75 34.32 103.63 39.49 199.04 39.37 209.29 39.73 170.04 31.28 150.77 47.17 242.38 44.15 195.60 47.88 183.36925 35.07 35.14 34.82 128.96 33.70 122.55 28.52 28.25 139.47 29.92 107.94 32.15 182.73 31.87 194.82 32.12 153.32 26.28 138.43 38.52 222.30 36.46 175.56 40.16 171.54975 35.66 35.48 36.03 145.05 34.74 136.68 30.54 31.24 119.21 32.28 118.99 38.16 173.52 37.89 186.71 38.40 146.80 30.93 131.36 46.21 211.40 43.12 167.45 47.57 165.581025 34.58 34.71 35.76 147.82 34.32 144.90 31.27 32.62 103.10 34.32 120.58 35.32 165.75 34.71 177.77 35.48 141.84 28.52 124.20 42.48 201.49 39.32 160.41 44.12 165.691075 32.44 32.40 32.45 145.12 32.74 139.23 27.68 31.66 131.01 33.17 127.89 34.69 165.44 34.11 175.34 34.52 147.82 27.23 126.34 42.57 200.61 38.52 164.87 42.30 167.231125 29.30 29.33 29.56 158.27 30.27 152.48 25.14 -- -- 28.62 133.81 26.94 157.24 26.62 165.83 33.47 145.20 21.76 120.10 32.96 191.35 31.11 160.67 34.87 164.551175 33.15 32.93 33.67 160.76 34.92 158.46 28.07 28.73 119.96 30.25 135.34 29.59 156.98 29.15 161.54 29.38 143.49 23.94 118.62 36.03 191.06 33.94 159.12 37.52 164.971225 27.83 27.70 28.11 164.07 29.15 163.25 23.80 26.36 120.10 27.31 126.68 34.25 139.57 33.64 141.78 33.96 128.81 28.45 105.01 41.82 168.54 38.33 143.00 42.04 145.131275 32.95 32.89 33.59 146.09 34.90 142.69 26.15 24.98 133.59 26.40 140.85 29.44 154.12 29.25 158.86 29.62 143.34 24.14 117.55 35.93 187.08 33.78 159.02 38.02 164.581325 30.65 30.50 30.61 142.55 32.18 141.78 26.54 28.23 104.57 29.35 110.94 31.24 126.79 31.04 128.65 31.41 116.86 29.97 94.98 38.40 152.48 35.80 129.91 40.27 130.791475 30.15 29.63 29.94 102.83 31.21 100.38 40.55 50.34 87.44 41.94 87.01 48.50 91.48 48.06 94.63 48.68 84.35 60.76 70.27 34.51 110.62 42.22 93.10 35.31 92.731525 39.11 37.84 39.23 94.01 37.57 94.68 62.67 70.53 80.04 67.88 77.92 58.81 80.67 60.74 82.24 61.33 72.89 65.09 61.49 39.24 97.23 57.47 80.10 40.80 81.531575 56.97 65.92 67.43 79.35 64.21 78.51 70.42 72.35 71.08 73.42 66.82 67.18 72.40 67.21 74.92 67.03 66.58 70.38 56.88 60.76 88.18 69.74 72.73 72.47 69.871625 74.54 78.29 79.59 79.38 73.09 78.75 71.33 72.35 68.12 71.47 65.92 74.45 69.06 73.78 71.30 73.70 61.90 75.43 64.48 75.58 83.91 75.64 68.14 79.07 68.861675 78.54 79.37 78.62 72.06 81.62 71.85 75.99 80.66 64.35 77.71 61.77 78.74 66.54 78.96 69.18 78.23 60.09 79.63 82.80 76.48 80.27 80.40 66.24 77.79 64.211725 72.82 74.36 74.17 66.50 75.26 65.09 80.71 81.84 59.71 81.41 54.74 82.5

Experimental study on thermal environment of scramjet combustor

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Transcript of Experimental study on thermal environment of scramjet combustor