![• “Cryogenic Rocket Engine.” Wikipedia, The Free Encyclopedia, 24 Oct. 2023,
en.wikipedia.org/wiki/Cryogenic_rocket_engine.
• Lakshmanan, Gokul. NASA SLS Cryogenic Engine - Complete Explanation. SlideShare, n.d.
Web. Accessed [Date].
• Sivolella, D. (2014). Power to orbit: The main engines. In To orbit and back again.
Springer.
Reference
• “YouTube.” Cryogenic Engines | The complete physics.
https://www.youtube.com/watch?v=3isXaIQ3Lkk.
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Cryogenic Rocket Engines & its Principle By Ranjith
- 1. Cryogenic Rocket Engines Ranjith .S Sastra Deemed University
- 2. Topics of Discussion • Introduction • Working Principle • Construction • Rocket Engine Power Cycles • Conclusion Page 2
- 3. INTRODUCTIO N • The word 'cryogenic' is derived from Greek, meaning "production of freezing cold". Cryogenics is the study of the production and behaviour of materials at very low temperature below -150°C or 123 K. • Oxygen liquifies at -183°C (90k) • Hydrogen liquifies at -253°C (20k) Fuel + Oxidizer = Propellant Page 3
- 4. Working Principle The basic principle driving a cryogenic rocket engine are: Newton third law of motion Law of conservation of momentum Cryogenic rocket engine derives thrust like all other rocket engines by accelerating an impulse carrier to high speeds. The chemical energy stored in the fuel is converted into kinetic energy by burning the fuel in the combustion chamber and subsequent expansion in the nozzle to produce thrust. Page 4
- 5. Construction The major components of a cryogenic rocket engine are: • Combustion chamber • Pyrotechnic initiator (igniter): zirconium - potassium perchlorate mixture • Fuel injector and fuel pumps • Oxidizer pumps • Gas turbine • Fuel tanks • nozzle Page 5
- 6. Page 6
- 7. Construction (Cont.) Specific Impulse Fuel Injector Page 7
- 8. Rocket Engine Power Cycles • Propellant tanks are pressurized to supply fuel and oxidizer to the engine, eliminating the need for turbo pumps. • Pressurized Helium is often used Pressure-Fed Engine: Page 8
- 9. Power cycles (Cont.) Expander Cycle: • Heat from the nozzle and combustion chamber powers the fuel and oxidizer pumps. • Uses a gas generator of some kind to start the turbine and run the engine until the heat input from the thrust chamber and nozzle skirt in sufficient enough to run the turbine Page 9
- 10. Power cycles (Cont.) Gas Generated (GG) Cycle: • To overcome this gas generated cycle is used. Some of the fuel and oxidizer is burned separately (pre-burner chamber) to power the pumps and then discarded. • Most gas-generator engines use the fuel for nozzle and combustion chamber cooling. • Disadvantage: this cycle is also not very efficient as some exhaust is totally lost. Page 10
- 11. Power cycles (Cont.) Staged Combustion Cycle: • The efficiency can be increased by diverting this exhaust from the turbine to the combustion chamber. All of the fuel and a portion of the oxidizer are fed through the pre-burner, generating fuel-rich gas. After being run through a turbine the gas is injected into the combustion chamber and burned. • Advantage: No loss of heat compared to gas generator cycle. • Disadvantage: This engine type gives the highest thrust and specific impulse however the pressure inside the combustion chamber is very high therefore it needs very powerful and expensive parts. • Used in space launch systems. Page 11
- 13. • “Cryogenic Rocket Engine.” Wikipedia, The Free Encyclopedia, 24 Oct. 2023, en.wikipedia.org/wiki/Cryogenic_rocket_engine. • Lakshmanan, Gokul. NASA SLS Cryogenic Engine - Complete Explanation. SlideShare, n.d. Web. Accessed [Date]. • Sivolella, D. (2014). Power to orbit: The main engines. In To orbit and back again. Springer. Reference • “YouTube.” Cryogenic Engines | The complete physics. https://www.youtube.com/watch?v=3isXaIQ3Lkk. Page 13