Cryogenic Rocket Engine
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Cryogenics is the study of the operations at very low temperature (below −150 °C, −238 °F or 123 K) and the behaviour of materials at these temperatures.
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Cryogenic Rocket Engine
- 2. 2 Presented By: Vivek D Pawan Rama Mali Sreyas prabhu Samrat G N Gaurav Karki
- 3. CONTENTS • What is CRYOGENICS • Propellants used in CRE* • Construction of CRE • CRE around the world • Challenges in CRE • CONCLUSION * CRE: Cryogenic Rocket Engine
- 4. PRINCIPLE OF ROCKET ENGINE The basic principle driving a rocket engine are: Newton’s third law of motion Law of conservation of momentum Derives thrust like all other rocket engines by accelerating an impulse carrier to high speeds Chemical energy Kinetic energy
- 6. What is Cryogenics ? • Greek words “Kyros” - cold or freezing and “genes” - born or produced • Cryonics is NOT the same as Cryogenics • In physics, Cryogenics is the study of the operations at very low temperature (below −150 °C, −238 °F or 123 K) and the behaviour of materials at these temperatures.
- 7. • Propulsion system • Isp of different propulsion systems: Solid propulsion = 265 s Earth-storable liquid propulsion = 285 s Cryogenic propulsion = 450 s
- 8. ALSO, BECAUSE SATELLITES ARE BECOMING HEAVIER…. INSAT 1A [1982] –1150 kg INSAT 2A [1992] –1900 Kg INSAT 3C [2002] –2750 Kg INSAT 4A [2005] –3080 kg
- 9. IN ROCKET ENGINES • Cryogenic technology involves the use of rocket propellants at extremely low temperatures. • Liquid Oxygen (LOX) & Liquid Hydrogen (LH2) • Oxygen remains at liquid only at temperatures below -183 ° C and hydrogen below - 253 ° C.
- 10. THE FIRST OPREATIONAL CRE
- 11. THE FIRST OPREATIONAL CRE First successful flight in 1963 and is still used on the Atlas V rocket. The Japanese LE-5 engine flew in 1977 French HM-7 in 1979 Chinese YF-73 in 1984 The Soviet Union in 1987 (AMERICAN) - ATLAS V
- 12. CRYOGENIC PROPELLANTS • Combination of Cryogenic fuel and oxidizer. • Cryogenic fuel- Storage at extremely low temperature in a liquid state such as Liquid Hydrogen. • Storage of propellant is difficult task. Eg: LH2 and LOX
- 13. FACTORS FOR SELECTING THE PROPELLANT • Ease of operation • Cost • Hazards • Performance
- 14. CRYOGENIC FUEL- OXIDIZER COMBINATION • Liquid hydrogen and Liquid oxygen • Kerosene(RP-1) and Liquid oxygen • Unsymmetrical dimethyl hydrazine and Nitrogen tetra oxide • Hydrazine and Aerozine-50
- 15. DISADVANTAGES OF CRYOGENIC PROPELLANTS • Difficult to store, so less desirable for usage. • Liquid hydrogen has low density as compare to other liquid propellant. • Kerosene is more damaging than hydrogen. • Lithium and fluorine are both extremely corrosive and toxic.
- 16. PERFORMANCE OF PROPELLANTS Propellant mix Vacuum Isp (seconds) Effective exhaust velocity (m/s) Liquid hydrogen/ Liquid oxygen 455 4462 Kerosene(RP-1)/ Liquid oxygen 358 3510 Unsymmetrical dimethyl hydrazine/ Nitrogen tetra oxide 333 3369 Hydrazine/ Aerozine-50 312 3126
- 17. CONSTRUCTION OF CRE • Combustion chamber • Pyrotechnic igniters • Fuel injector • Fuel and Oxidizer Cryo-pumps • Gas turbine • Cryo-valves • Regulators • External fuel tanks • Nozzle
- 20. Fuel injector
- 23. Pre-burners and thrust control system
- 24. Schematic Diagram of CRE
- 26. CRE AROUND THE WORLD RL-10 First flight-27 November1962 Upper stage engine centaur Thrust- 110 KN Isp- 450 seconds J-2 First flight-26 June 1966 Upper stage engine of AS-201 Thrust- 1033.1 KN Isp- 421 seconds UNITED STATES
- 27. RS-25 • First flight- 1981 • Space shuttle main engine RS-68 • First flight- 1998 • First stage engine of delta 4 rocket UNITED STATES
- 28. LE-7 • First flight- 1977 • H-2 satellite launch vehicle • Thrust - 1078 KN • Isp- 446 seconds LE-5 • Thrust -102.9 KN • Isp -450seconds JAPAN
- 29. VULCAIN First flight-1996 Main stage Thrust- 1015 KN Isp- 440 seconds FRANCE HM7 First flight-1979 Upper stage Thrust- 64.8 KN Isp- 446 seconds
- 30. YF-73 First flight- 1984 Long march Thrust- 44.15 KN Isp- 432 sec YF-75 First flight- 1994 Thrust-78.45 KN Isp- 437 sce CHINA
- 31. RD-0146 First flight- 2001 Upper stage of booster Thrust- 98100 KN Isp- 463 sec RD-0120 First flight- 1987 Expendable launch system Thrust- 1961 KN Isp- 455 sec RUSSIA
- 32. C E 7.5 • The specifications and key characteristics of the engine are: • Propellant Combination – LOX / LH2 • Maximum thrust (Vacuum) – 75 kN • Operating Thrust Range (as demonstrated during GSLV Mk2 D5 flight) – 73.55 kN to 82 kN • Engine Specific Impulse - 454 seconds • Steering during thrust: provided by two gimballed steering engines
- 33. C E 20 • Propellant Combination - LOX / LH2 • Thrust Nominal (Vacuum) - 200 kN • Operating Thrust Range - 180 kN to 220 kN • Engine Specific Impulse - 443 seconds
- 34. DEVELOPMENTS IN ISRO YEARS EVENTS 1986 Launch a program to develop 1 ton cryogenic engine 1987 Second generation INSAT- 2 series 1989 France offered 7 ton HM7 1990 India approved an offer with Soviet Union’s 1993 Soviet Union’s backed out of the deal with India 2001-2007 Development GSLV-D1 and cryogenic upper stage project speeded up
- 35. YEARS EVENTS 2008 First indigenous cryogenic engine tested for 200 seconds 2009 GSLV-D3 successfully tested for 800 seconds 2010 Failure if GSLV-D3 with GSAT-4 2011 Fuel booster turbo pump modified 2012 ISRO test cryogenic engine under vacuum 2013 Assembly of GSLV-D5 started 2014 Successfully launch of GSLV-D5 DEVELOPMENTS IN ISRO
- 36. OTHER APPLICATIONS OF CRYOGENICS ► Cryosurgery ► Electric power transmission ► Frozen food ► Blood banks ► Infrared Sensors ► Electronics
- 37. CHALLENGES Thermal contraction Storage problems High density Highly reactive gases Overall cost of propellants relatively high
- 38. CHALLENGES Leakage problems Boil off rate Hydrogen embrittlement Zero gravity conditions
- 39. FUTURE TRENDS OF CRYOGENIC MATERIALS • Computationally designed materials and processing • Unique nano-phase materials systems for new applications at low temperatures • Smart materials and systems based on new alloys • Durability and performance • Quality assurance and testing
- 40. CONCLUSION
- 41. Any Queries
- 43. Thank you
Editor's Notes
- PERMISSION
- Time – Introduction
- The basic principle driving a rocket engine are: Newton third law of motion Law of conservation of momentum(momentum are the product of the units of mass and velocity) In principle, 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 thrust chamber and subsequent expansion in the nozzle to produce thrust
- Basically Rocket engines are Reaction engines. Spacecraft propulsion is any method used to accelerate spacecraft and artificial satellites. Rocket Engines Interplanetary vehicles mostly use chemical rockets as well.
- Cryogenics originated from two Greek words “Kyros” which means cold or freezing and “genes” which means born or produced Cryonics (from Greek κρύος 'kryos-' meaning 'icy cold') is the low-temperature preservation of animals (including humans) who cannot be sustained by contemporary medicine, with the hope that healing may be possible in the future. Cryogenics is the study of very low temperatures In physics, Cryogenics is the study of the operations at very low temperature (below −150 °C, −238 °F or 123 K) and the behaviour of materials at these temperatures.
- Propulsion system: The power Centre of a launcher and it increases the sp impulse of rocket Specific Impulse (Isp): Index of efficiency of a propulsion system. Isp= Thrust / Weight flow rate of propellants. Traditionally expressed in seconds. Isp of different propulsion systems (sea-level) Solid propulsion –265 s Earth-storable liquid propulsion –285 s Cryogenic propulsion –450 s
- Cryogenic technology involves the use of rocket propellants at extremely low temperatures. The combination:- Liquid Oxygen (LOX) & Liquid Hydrogen (LH2) offers the highest energy efficiency for rocket engines. Oxygen remains at liquid only at temperatures below -183 ° C and hydrogen below - 253 ° C.
- American and Soviet engineers independently, all discovered that rocket engines need high mass flow rate of both oxidizer and fuel to generate a sufficient thrust. At that time oxygen and low molecular weight hydrocarbons were used as oxidizer and fuel pair. At room temperature and pressure, both are in gaseous state. Hypothetically, if propellants had been stored as pressurized gases, the size and mass of fuel tanks themselves would severely decrease rocket efficiency. Therefore, to get the required mass flow rate, the only option was to cool the propellants down to cryogenic temperatures (below −150 °C, −238 °F), converting them to liquid form. Hence, all cryogenic rocket engines are also, by definition, either liquid-propellant rocket engines or hybrid rocket engines
- The first operational cryogenic rocket engine RL10 rocket engine. The United States was the first country to develop cryogenic rocket engines. with RL-10 engines, registered its first successful flight in 1963 and is still used on the Atlas V rocket. Then The Japanese LE-5 engine flew in 1977 ,French HM-7 in 1979 , Chinese YF-73 in 1984 . The Soviet Union, first country to put a satellite and later a human in space, successfully launched a rocket with a cryogenic engine only in 1987.
- *In cre cryogenic propellant is a combination of cryogenic fuel and oxidizer which are in liquid forms. *cryogenic fuels are fuels that require storage at extremely low temp. in order to maintain them in a liquid state. cryogenic fuels often constitute liquifide gases such as liquid hydrogen. To store prop. Onboard a rocket is very diff. task as they have low densities. Thus by cooling and compressing the into liquids we can vastly increase their density and make it possible to store them in large quantity in small tanks.
- The combination of LH2 and LOX is one of the most widely used. When burned this combination have one of the highest enthalpy releases by combustion, producing specific impulse upto 455 sec. It is the cleanest cryogenic fuel & oxidizer combination. When liquid hydrogen used with lox, by product is only water. This water is thrown out of nozzle in form of hot vapour. It is economical. Lox costs less than gasoline. Reaction time and storability are not too critical.
- Bcs of low temp. cryogenic propellant are difficult to store over long period of time. For this reason they are less desirable for use in millatry rockets. Even as a liqud, hydrogen has low density requiring large tanks, pumps and extreme cold requires tank insulation. Most rockets that use lh2 fuel use it in upper stage only. In the case of kerosene launch pad fires due to spilled kerosene are more damaging than hydrogen fires. Highest specific impulse ever test fired in rocket engine was li and f with hydrogen added to improve the exhaust thermodynamics. Isp= 542 sec in vaccume equivalent to exhaust vel. Of 5320 m/s. But we don’t use this exotic prop. Bcs li and f are both extremely corrosive. Li ignites on contact with air. F ignites on contact with most fuels including hydrogen. F and hf in the exhaust are very toxic. Which makes working around the launch pad difficult and damages the environment.
- RL-10 CENTAUR IS USE AS UPPER STAGE S-4 IS SECOND STAGE OF SATURN -1 DCSS –DELTA CRUOGENIC SECOND STAGE J-2 AS-201- UNMANED TEST FIHHT OF APOLLLO SPACECRAFT Saturn -2 stage & third stage
- RS-83 LE-7A -FIRST SATGE OF H2 LAUNCH VEHICLE
- VINCI- under development Upperstage liquid rocket booster
- China’s academy of launch vehicle technology Long march 3- 3(chinese orbital carrier rocket) YF-77-long march 5- heavy lift launch system yf-50t under development RD-0120 DESIGNETED AS 11D122
- RD-0146- RUS-M LAUNCH VEHICLE TO CARRY FUTURE PPTS-PROPSPECTIVE PILOTED TRANSPORT SYSTEM PARTIALLY REUSABLE CAPSULE MANNED SPACECRAFT CE-7.5 IT REPLACED RUSSIAN KVD-1 ENGINE NOMIAL THRUST OF 200KN THE VALUE CAN FIXED BETWEEN THIS RANGR
- 1986- COST OF 12 CRORE TO LEARN HOW TO HANDLE CRYOGENIC FLUID 1987-INSAT-2 WEIGHING 2TONE- GTO- US OFFERED 800 MILLION DOLLER FOR 2 ENGINE 1989-HM7- 1200 MILLION DOLLER-2 7 TONE ENGINE, TRANSFER OF TECHNOLGY & SET UP OF MANUFAC FACILITIES IN INDIA 1990-8 SCIENTIST WENT TO MOSCOW- 15 MONTHS
- 2010- FAILURE OF GSLV-D3 WITH GSAT-4 – FAIL TO SUSTAIN IGNITION BCZ OF TURBO PUMP STOPPED DECEMBER 2010- EXPLOSION DUE TECHNICAL SNAG FIRST STAGE GSLV-D5 TARGETED TO BE LAUCHED IN JUNE ABORTED DUE LEAK IN THE FUEL TANK 05 JAN -2014-SATISH DHAWAN SPACE CENTRE SHAR, SRIHARIKOTA
- Cryosurgery (also called cryo therapy) is the use of extreme cold produced by liquid to destroy abnormal tissue. Cryosurgery is used to treat external tumors, such as those on the skin. For internal tumors, liquid nitrogen is circulated through a hollow instrument called a cryoprobe. Cryosurgery has been used for many years in the treatment of skin cancer Frozen food When very large quantities of food must be transported to regions like war zones, earthquake hit regions, etc., they must be stored for a long time, so cryogenic food freezing is used. Blood banking Certain rare blood groups are stored at low temperatures, such as -165 degrees C. Forward looking infrared (FLIR) Many infra-red cameras require their detectors to be cryogenically cooled. The super conducting electronic devices like SQUID (Super conducting quantum interference device) are used in sensitive digital magnetometers and voltmeters. Zero friction bearings use magnetic field instead of oil or air, derived from the Meissner effect associated with super conductivity. Super conducting electric motors are constructed approaching zero electric loses.
- Low density of liquid Hydrogen –more structural mass Low temperature of propellants -Complex storage & transfer systems and operations Hazards related to cryogens High density requires larger tanks Overall cost of propellants relatively high Need for ignition system. Cryogens are highly concentrated gases and have a very high reactivity. Liquid oxygen, which is used as an oxidizer, combines with most of the organic materials to form explosive compounds. So lots of care must be taken to ensure safety
- One of the most major concerns is leakage. At cryogenic temperatures, which are roughly below 150 degrees Kelvin or equivalently (-190) degrees Fahrenheit, the seals of the container used for storing the propellants lose the ability to maintain a seal properly. Hydrogen, being the smallest element, has a tendency to leak past seals or materials. The "Boil off rate" usually refers to the amount of liquid vaporized by heat leaking into the tank per unit time. In a way it indicates that to maintain the same pressure in the tank you need to vent at least this amount of equivalent liquid or vapor. Less and you will build pressure, more will result in a drop in pressure in the tank, unless you have a vaporizer. Hydrogen Embrittlement It is the process by which various metals, most importantly high-strength steel, become brittle and fracture following exposure to hydrogen. Need for ignition system. Zero Gravity conditions The condition of real or apparent weightlessness occurring when any gravitational forces acting on a body meet with no resistance sothe body is allowed to accelerate freely.
- There are several trends today that can help us look into the future of cryogenics materials Simulation of materials characteristics using this approach will include modeling of microstructure, defects, surface structure, interface properties, prediction of adhesion and bonding, thermodynamic properties, and general mechanical behaviour.
- The future of cryogenics will be very exciting and dynamic. It will be driven by traditions, trends, costs, performance, legislation. Of these, the most critical issue is costs. Logical, creative and innovative ideas will have little chance of success if the economics are not positive. Cryogenics materials will be part of the dynamic future. By considering the entire cryogenics materials, we are not limited to just one type of materials, but metal materials, composites and fluorinated polymers will remain the major materials for applications at very low temperatures. We are no longer limited by shape, density, size, composition, we are only limited by our imagination and our knowledge and OUR understanding of how to achieve the highest level of performance from cryogenics materials. We must not only continue to make incremental improvements in present materials but develop whole new technologies of manufacturing and processing for to achieve the highest performance in THIS field.