Presentacion Termodinamica 2
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Transcript of Presentacion Termodinamica 2
Staged Combustion CycleThermodynamics 2 Project
Nelson Ojeda
ME3120-22Presented: October 22, 2015
Prof. Ronaldo Sosa
ME Thermodynamics2
Statement of the Objective
General Objectives Thermodynamically Processes (P-V and T-S Diagrams) Advantages and disadvantages of the cycle Comparison with Carnot cycle Functionalities of the cycle Recent implementation and limitations
Staged Combustion Cycle
ME Thermodynamics 3
Originality Assessment1. Philip Graham, Hill, Carl Peterson; “
Mechanics and Thermodynamics of Propulsion”: Second Edition by Addison- Wesley Publishing (1992): Pages 467-478 & 469- 588 Print.
2. R. Douglas Archer, Maido Saarlas; “An Introduction to Aerospace Propulsion”: Second Edition by Prentice Hall, Inc. (1996): Pages- 28 & 433- 489 Print.
3. “Ideal Carnot Cycle” NASA informational page. Web. 12 Oct. 2015. <https://www.grc.nasa.gov/www/k-12/airplane/carnot.html>
4. “P-V liquid bipropellant description and representation” : Web. 13 Oct. 2015. <http://twt.mpei.ac.ru/TTHB/2/KiSyShe/eng/Chapter10/10-3-Reaction-engine-cycles.html>.
Needed previous knowledge
4
Liquid Propellant Rocket Engines• Propellant- means both fuel (e.g.,
alcohol, kerosene, hydrogen) and oxidizer (e.g., oxygen, nitric acid). – Cryogenic- liquid that is a gas at normal
temperature.
ME Thermodynamics
Propellant Boiling point [ᵒF/K]
Critical Pressure [psi/atm]
Critical Temp. [ᵒF/K]
Handling
Hydrogen -423/20 188/13 -400/33 FlammableAmmonia -28/240 1640/111 270/406 Toxic/
flammable
Oxygen -298/90 737/50 -182/155 GoodFluorine -307/85 800/54 -200/144 Very Toxic,
flammable
5
Liquid Propellant Rocket Engines– Storable liquid - stable over a wide range of
temperatures and pressures, which permits storage in closed containers for a long period of time(many months).
ME Thermodynamics
Propellant Boiling point [ᵒF/K]
Vapor Pressure [atm abs.]
Handling
Ethyl alcohol 173/352 0.8 Toxic/flammable
Hydrazine 235/386 1 Toxic/flammable
Nitrogen tetroxide
70/294 1.4 Toxic
Penta-borane 140/333 0.65 Toxic/Expl. In air
ME Thermodynamics 6
How does it work?
Gas Turbine
Staged Combustion Engine
1
2
3
4
Liquid HydrogenLiquid OxygenFuel rich mixture
7
Thermodynamic Process P-V Diagram
Staged Combustion Cycle
Carnot Cycle
V= c
onst
.
P= const.
Adiabatic expansion
Adiabatic expansion
Qout Qout
Qin
Qin
Adiabatic compression
Isothermalcompression
Isothermalexpansion
Isochoricprocess
ME Thermodynamics
ME Thermodynamics8
Thermodynamic Process T-S Diagram
Carnot CycleStaged Combustion Cycle
Isochoricprocess
P= const.
P= const.Adiabatic expansion Adiabatic
expansion
Isothermalexpansion
Isothermalcompression
Qin Qin
Qout Qout
ME Thermodynamics9
Staged Combustion EngineAdvantages
• All of the engine cycles' gases and heat go through the combustion chamber.• Abundance of power, which permits very high chamber pressures that allow
high expansion ratio nozzles. These nozzles give better efficiencies at low altitude.
• Has a wide application in rocketry and very often in aeronautical engineering.
Disadvantages• Development cost for this cycle is higher because the high pressures
complicate the development process. • Harsh turbine conditions.• High temperature piping required to carry hot gases.• A very complicated feedback and control design.
ME Thermodynamics10
Working ExampleSpace Shuttle Main Engine(SSME)
ME LABORATORY 11
Staged Combustion Engine
Source: NASA/ SSME video
Space Shuttle Main Engine(SSME) sketch
ME Thermodynamics12
Implementation • Integrate Powerhead Demonstration (IPD)
After 35 years without a major redesign, the liquid-fueled rocket engine is getting a facelift, courtesy of a team of engineers from NASA, the Air Force, Pratt & Whitney Rocketdyne, and Aerojet. – full-flow, staged-combustion rocket engine that uses liquid
hydrogen as fuel and liquid oxygen as the oxidizer. – better fuel efficiency– higher thrust-to weight ratios– higher Reliability– 250,000 pounds of thrust (twice the thrust of the Space Shuttle
main rocket engines)
ME LABORATORY 13
ImplementationFull-flow staged combustion
ME Thermodynamics14
Developments
SCE-200 engine
• Semi- cryogenic engine• Fuel- kerosene (RP-1)• Oxidizer- liquid oxygen• 460,000 pounds of thrustIn vacuum• Dry weight( 6,000lb)
ME Thermodynamics 15
Developments
RS-25 engine
• Cryogenic engine• Fuel- liquid hydrogen• Oxidizer- liquid oxygen• Configuration for a 70-metric-ton (77-ton)
lift capacity (targeted 130 metric tons (143 ton for the future))
• From 491,000 pounds of trust in vacuum to 510,000
• 1,500 gal/s
Source: NASA/ SSME video
ME Thermodynamics16
Test EnvironmentA-1 Test Stand at NASA’s Stennis Space Center
ME Thermodynamics 17
Questions
18
XCOR Aerospace(Piston Engine)
ME Thermodynamics
ME Thermodynamics19
Most Powerful Single Chamber
ME LABORATORY 20
Most Powerful(4 Chambers)
RD170
• 1773000 pounds of thrust in vacuum