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CE-20

January 05, 2023

The CE-20 is a cryogenic rocket engine developed by the Liquid Propulsion Systems Centre, a subsidiary of Indian Space Research Organisation. It has been developed to power the upper stage of the LVM 3.[5] It is the first Indian cryogenic engine to feature a gas-generator cycle.[6] The high thrust cryogenic engine is the most powerful upper stage cryogenic engine in the world.[7]

CE-20
A computer model of CE-20
Country of originIndia
First flightJune 5, 2017
DesignerLPSC, ISRO
ManufacturerHAL[1]
ApplicationUpper stage booster
StatusActive
Liquid-fuel engine
PropellantLOX / LH2
Mixture ratio5.05
CycleGas Generator
Configuration
Chamber1
Nozzle ratio100
Performance
Thrust, vacuum186.36 kN (41,900 lbf)
Throttle range180–220 kN (40,000–49,000 lbf)
Chamber pressure6 MPa (870 psi)
Specific impulse, vacuum442 seconds (4.33 km/s)
Burn time640-800 seconds
Dimensions
Dry weight588 kg (1,296 lb)
Used in
Upper stage of LVM 3
References
References[2][3][4]

Overview

The CE-20 is the first Indian cryogenic engine to feature a gas-generator cycle.[8] The engine produces a nominal thrust of 200 kN, but has an operating thrust range between 180 kN to 220 kN and can be set to any fixed values between them. The combustion chamber burns liquid hydrogen and liquid oxygen at 6 MPa with 5.05 engine mixture ratio.[3][4] The engine has a thrust-to-weight ratio of 34.7 and a specific impulse of 442 seconds (4.33 km/s) in vacuum.[2]

Development and Testing

 
CE-20 during static testing at Cryo Main Engine and Static Test facility (CMEST) of ISRO Propulsion Complex (IPRC), Mahendragiri on 19 February 2016
  • On 28 April 2015, CE-20 cleared a 635 seconds long duration hot test at IPRC, Mahendragiri test facility. This test was preceded by two cold start tests and four short duration hot tests.[9]
  • On 16 July 2015, the first developmental CE-20 engine 'E1' was successfully endurance hot tested at ISRO Propulsion Complex, Mahendragiri for a duration of 800 seconds with Mixture Ratio Controller (MRC) in closed loop mode. This duration is approximately 25% more than the engine burn duration in flight. This was tenth development test for CE-20 [10]
  • On 10 August 2015, a short duration (5.7 seconds) hot test on the CE20 engine was done to demonstrate the successful engine ignition with tank pressure conditions as in flight.[11]
  • On 19 February 2016, the second developmental CE-20 engine 'E2'[12] was hot-tested for a duration of 640 seconds with Mixture Ratio Controller (MRC) in closed loop mode at ISRO Propulsion Complex, Mahendragiri.[13][14][15]
  • On 03 December 2016, flight acceptance test of 25 seconds in high altitude conditions was carried out on third developmental CE-20 engine (E3).[16][17][18] It was successfully flown on the first developmental flight 'D1' of the GSLV Mk-III on 5 June 2017.[19]
  • On 25 January 2017, CE-20 engine E2[18] integrated with development stage for GSLV Mk III, C25 'D' was tested for duration of 50 seconds.[20]
  • On 17 February 2017, CE-20 engine E2[18] integrated with development stage for GSLV Mk III, C25 'D' was tested for duration of 640 seconds.[21]
  • On 11 October 2018, CE-20 engine E6 completed 25 second long flight acceptance test in high altitude conditions for GSLV Mk III M1/Chandrayaan-2 mission[22]
  • On 16 December 2021, CE20 (E9 engine) was tested to demonstrate the repeatability of engine ignition with stable combustion. Two ignition trial tests of 3.2 seconds duration were conducted nominally followed by a nominal hot test of 50 seconds duration.[23]
  • On 12 January 2022, CE-20 engine E9 completed 720 second long qualification test for Gaganyaan programme.[24]
  • On 29 October 2022, CE-20 engine E11[25] completed flight acceptance hot test for 25 seconds. Test was conducted to check the integrity of hardware, subsystems' performance and tuning the engine for LVM 3 M3 mission.[26]
  • On 9 November 2022, CE-20 engine E9 was hot tested for 70 seconds. During this test the engine operated at thrust level of approximately 20 tonnes for the first 40 seconds and then switched to an uprated thrust regime of 21.8 tonnes lasting ~30 seconds. This uprated engine would increase payload capacity of LVM3 to GTO by up to 450 kg along an appropriate stage with additional propellant loading. As part of engine modification, Thrust Control Valve (TCV), 3D-printed LOX and LH2 turbine, and exhaust casings were introduced for the first time.[27]
  • On 23 December 2022, CE-20 engine E9 was hot tested for 650 second duration. For the first 40 seconds of test, the engine was operated at 20.2 tonne thrust level, after this engine was operated at 20 tonne off-nominal zones and then for 435 seconds it was operated at 22.2 tonne thrust level. With this test, the 'E9' engine has been qualified for induction in flight. The E9 engine with this hot test has undergone twelve hot tests with 3370 seconds cumulative burn duration at different thrust & mixture ratio levels.[28]

See also

References

  1. ^ "HAL to produce cryogenic engines for ISRO". The Hindu. 27 April 2013.
  2. ^ a b . ISRO. Archived from the original on 4 August 2022.
  3. ^ a b "LPSC Handouts at Aer India-2009". Specifications of CE-20. Liquid Propulsion Systems Centre. 13 March 2009. Retrieved 29 August 2009.
  4. ^ a b "Aero India 2009, LPSC specification sheet :: IMG_0159". Retrieved 2018-09-12.
  5. ^ "Indigenous Cryogenic Engine Tested Successfully". www.isro.gov.in.
  6. ^ K. S. Jayaram (22 February 2016). "India's heavy-lift rocket on track for December debut following engine test". Spacenews.
  7. ^ Praveen, RS; Jayan, N; Bijukumar, KS; Jayaprakash, J; Narayanan, V; Ayyappan, G (February 2017). "Development of Cryogenic Engine for GSLV MkIII: Technological Challenges". IOP Conference Series: Materials Science and Engineering. 171 (1): 012059. Bibcode:2017MS&E..171a2059P. doi:10.1088/1757-899X/171/1/012059.
  8. ^ R. Ramachandran (22 January 2014). "GSLV MkIII, the next milestone". Frontline.
  9. ^ Ram, Arun (29 April 2015). "Isro's desi cryogenic engine test successful - Times of India". The Times of India.
  10. ^ "Indigenously Developed High Thrust Cryogenic Rocket Engine Successfully Ground Tested for a duration for 800 seconds - ISRO". www.isro.gov.in.
  11. ^ "Year End Review: Achievements of Department of Space during the year 2015". Press Information Bureau, Government of India. Retrieved 12 February 2018.
  12. ^ "CE 20 Engine of GSLV MKIII successfully hot tested - ISRO". www.isro.gov.in. Retrieved 2018-02-12.
  13. ^ "ISRO upbeat as indigenous cryo engine passes test". The Hindu. 20 February 2016.
  14. ^ "ISRO successfully conducts hot test of Cryo CE 20 engine". The Hindu. Press Trust of India. 19 Feb 2016. Retrieved 12 February 2018.
  15. ^ "ISRO successfully conducts hot test of Cryo CE 20 engine". PTI. 19 Feb 2016. Retrieved 12 February 2018.
  16. ^ "High Altitude Flight Acceptance Test of CE20 Engine Conducted Successfully". Retrieved 12 February 2018.
  17. ^ "GSLV engine tested at Mahendragiri". The Hindu. 3 December 2016.
  18. ^ a b c "Department of Space Outcome Budget 2016-17" (PDF). Retrieved 12 October 2018.
  19. ^ Malik, Tariq (5 June 2017). "India Just Launched Its Heaviest & Most Powerful Rocket Yet". Space.com. Retrieved 7 June 2017.
  20. ^ "ISRO Successfully Tests C25 Cryogenic Upper Stage of GSLV MkIII - ISRO". www.isro.gov.in. Retrieved 2018-10-12.
  21. ^ "ISRO Successfully Tests its Cryogenic Stage (C25) for GSLV MkIII for the Flight Duration - ISRO". www.isro.gov.in. Retrieved 2018-10-12.
  22. ^ "ISRO successfully tests Cryogenic Engine (CE-20) for GSLV Mk-III / Chandrayaan-2 Mission - ISRO". www.isro.gov.in. Retrieved 2018-10-12.
  23. ^ (PDF). p. 108. Archived from the original (PDF) on 27 April 2022. Retrieved 10 November 2022.
  24. ^ . www.isro.gov.in. Archived from the original on 22 July 2022. Retrieved 2022-01-12.
  25. ^ "CE20 engine hot test video". www.isro.gov.in. Retrieved 2022-11-10.
  26. ^ Kumar, Chethan (29 October 2022). "Isro hot-tests CE-20 engine for GSLV-Mk3 to be used for next OneWeb launch". The Times of India. Retrieved 2022-10-29.
  27. ^ . Indian Space Research Organisation. 2022-11-09. Archived from the original on 2022-11-10. Retrieved 2022-11-10.
  28. ^ "Successful CE-20 Engine Hot Test with 20t off-nominal & 22.2t vacuum thrust". www.isro.gov.in. Retrieved 2022-12-24.

External links

 
Wikimedia Commons has media related to CE-20_(rocket_engine).
  • India test-fires indigenous cryo engine for 800 seconds
  • LPSC handouts during Aero India-2009 with Ce-20 specifications
  • LPSC handouts during Aero India-2009 with specifications of all Liquid-fueled engines of India
  • ISRO upbeat as indigenous cryo engine passes test

January 05, 2023
cryogenic, rocket, engine, developed, liquid, propulsion, systems, centre, subsidiary, indian, space, research, organisation, been, developed, power, upper, stage, first, indian, cryogenic, engine, feature, generator, cycle, high, thrust, cryogenic, engine, mo. The CE 20 is a cryogenic rocket engine developed by the Liquid Propulsion Systems Centre a subsidiary of Indian Space Research Organisation It has been developed to power the upper stage of the LVM 3 5 It is the first Indian cryogenic engine to feature a gas generator cycle 6 The high thrust cryogenic engine is the most powerful upper stage cryogenic engine in the world 7 CE 20A computer model of CE 20Country of originIndiaFirst flightJune 5 2017DesignerLPSC ISROManufacturerHAL 1 ApplicationUpper stage boosterStatusActiveLiquid fuel enginePropellantLOX LH2Mixture ratio5 05CycleGas GeneratorConfigurationChamber1Nozzle ratio100PerformanceThrust vacuum186 36 kN 41 900 lbf Throttle range180 220 kN 40 000 49 000 lbf Chamber pressure6 MPa 870 psi Specific impulse vacuum442 seconds 4 33 km s Burn time640 800 secondsDimensionsDry weight588 kg 1 296 lb Used inUpper stage of LVM 3ReferencesReferences 2 3 4 Contents 1 Overview 2 Development and Testing 3 See also 4 References 5 External linksOverview EditThe CE 20 is the first Indian cryogenic engine to feature a gas generator cycle 8 The engine produces a nominal thrust of 200 kN but has an operating thrust range between 180 kN to 220 kN and can be set to any fixed values between them The combustion chamber burns liquid hydrogen and liquid oxygen at 6 MPa with 5 05 engine mixture ratio 3 4 The engine has a thrust to weight ratio of 34 7 and a specific impulse of 442 seconds 4 33 km s in vacuum 2 Development and Testing Edit CE 20 during static testing at Cryo Main Engine and Static Test facility CMEST of ISRO Propulsion Complex IPRC Mahendragiri on 19 February 2016 On 28 April 2015 CE 20 cleared a 635 seconds long duration hot test at IPRC Mahendragiri test facility This test was preceded by two cold start tests and four short duration hot tests 9 On 16 July 2015 the first developmental CE 20 engine E1 was successfully endurance hot tested at ISRO Propulsion Complex Mahendragiri for a duration of 800 seconds with Mixture Ratio Controller MRC in closed loop mode This duration is approximately 25 more than the engine burn duration in flight This was tenth development test for CE 20 10 On 10 August 2015 a short duration 5 7 seconds hot test on the CE20 engine was done to demonstrate the successful engine ignition with tank pressure conditions as in flight 11 On 19 February 2016 the second developmental CE 20 engine E2 12 was hot tested for a duration of 640 seconds with Mixture Ratio Controller MRC in closed loop mode at ISRO Propulsion Complex Mahendragiri 13 14 15 On 03 December 2016 flight acceptance test of 25 seconds in high altitude conditions was carried out on third developmental CE 20 engine E3 16 17 18 It was successfully flown on the first developmental flight D1 of the GSLV Mk III on 5 June 2017 19 On 25 January 2017 CE 20 engine E2 18 integrated with development stage for GSLV Mk III C25 D was tested for duration of 50 seconds 20 On 17 February 2017 CE 20 engine E2 18 integrated with development stage for GSLV Mk III C25 D was tested for duration of 640 seconds 21 On 11 October 2018 CE 20 engine E6 completed 25 second long flight acceptance test in high altitude conditions for GSLV Mk III M1 Chandrayaan 2 mission 22 On 16 December 2021 CE20 E9 engine was tested to demonstrate the repeatability of engine ignition with stable combustion Two ignition trial tests of 3 2 seconds duration were conducted nominally followed by a nominal hot test of 50 seconds duration 23 On 12 January 2022 CE 20 engine E9 completed 720 second long qualification test for Gaganyaan programme 24 On 29 October 2022 CE 20 engine E11 25 completed flight acceptance hot test for 25 seconds Test was conducted to check the integrity of hardware subsystems performance and tuning the engine for LVM 3 M3 mission 26 On 9 November 2022 CE 20 engine E9 was hot tested for 70 seconds During this test the engine operated at thrust level of approximately 20 tonnes for the first 40 seconds and then switched to an uprated thrust regime of 21 8 tonnes lasting 30 seconds This uprated engine would increase payload capacity of LVM3 to GTO by up to 450 kg along an appropriate stage with additional propellant loading As part of engine modification Thrust Control Valve TCV 3D printed LOX and LH2 turbine and exhaust casings were introduced for the first time 27 On 23 December 2022 CE 20 engine E9 was hot tested for 650 second duration For the first 40 seconds of test the engine was operated at 20 2 tonne thrust level after this engine was operated at 20 tonne off nominal zones and then for 435 seconds it was operated at 22 2 tonne thrust level With this test the E9 engine has been qualified for induction in flight The E9 engine with this hot test has undergone twelve hot tests with 3370 seconds cumulative burn duration at different thrust amp mixture ratio levels 28 See also Edit India portal Rocketry portal Spaceflight portalCE 7 5 LVM 3 GSAT 14References Edit HAL to produce cryogenic engines for ISRO The Hindu 27 April 2013 a b ISRO successfully tests Cryogenic Engine CE 20 for GSLV Mk III Chandrayaan 2 Mission ISRO Archived from the original on 4 August 2022 a b LPSC Handouts at Aer India 2009 Specifications of CE 20 Liquid Propulsion Systems Centre 13 March 2009 Retrieved 29 August 2009 a b Aero India 2009 LPSC specification sheet IMG 0159 Retrieved 2018 09 12 Indigenous Cryogenic Engine Tested Successfully www isro gov in K S Jayaram 22 February 2016 India s heavy lift rocket on track for December debut following engine test Spacenews Praveen RS Jayan N Bijukumar KS Jayaprakash J Narayanan V Ayyappan G February 2017 Development of Cryogenic Engine for GSLV MkIII Technological Challenges IOP Conference Series Materials Science and Engineering 171 1 012059 Bibcode 2017MS amp E 171a2059P doi 10 1088 1757 899X 171 1 012059 R Ramachandran 22 January 2014 GSLV MkIII the next milestone Frontline Ram Arun 29 April 2015 Isro s desi cryogenic engine test successful Times of India The Times of India Indigenously Developed High Thrust Cryogenic Rocket Engine Successfully Ground Tested for a duration for 800 seconds ISRO www isro gov in Year End Review Achievements of Department of Space during the year 2015 Press Information Bureau Government of India Retrieved 12 February 2018 CE 20 Engine of GSLV MKIII successfully hot tested ISRO www isro gov in Retrieved 2018 02 12 ISRO upbeat as indigenous cryo engine passes test The Hindu 20 February 2016 ISRO successfully conducts hot test of Cryo CE 20 engine The Hindu Press Trust of India 19 Feb 2016 Retrieved 12 February 2018 ISRO successfully conducts hot test of Cryo CE 20 engine PTI 19 Feb 2016 Retrieved 12 February 2018 High Altitude Flight Acceptance Test of CE20 Engine Conducted Successfully Retrieved 12 February 2018 GSLV engine tested at Mahendragiri The Hindu 3 December 2016 a b c Department of Space Outcome Budget 2016 17 PDF Retrieved 12 October 2018 Malik Tariq 5 June 2017 India Just Launched Its Heaviest amp Most Powerful Rocket Yet Space com Retrieved 7 June 2017 ISRO Successfully Tests C25 Cryogenic Upper Stage of GSLV MkIII ISRO www isro gov in Retrieved 2018 10 12 ISRO Successfully Tests its Cryogenic Stage C25 for GSLV MkIII for the Flight Duration ISRO www isro gov in Retrieved 2018 10 12 ISRO successfully tests Cryogenic Engine CE 20 for GSLV Mk III Chandrayaan 2 Mission ISRO www isro gov in Retrieved 2018 10 12 Annual Report of Department of Space 2021 2022 PDF p 108 Archived from the original PDF on 27 April 2022 Retrieved 10 November 2022 Qualification testing of Cryogenic Engine for Gaganyaan Programme ISRO www isro gov in Archived from the original on 22 July 2022 Retrieved 2022 01 12 CE20 engine hot test video www isro gov in Retrieved 2022 11 10 Kumar Chethan 29 October 2022 Isro hot tests CE 20 engine for GSLV Mk3 to be used for next OneWeb launch The Times of India Retrieved 2022 10 29 Successful CE20 uprated Engine Hot Test with 21 8 T vacuum thrust Indian Space Research Organisation 2022 11 09 Archived from the original on 2022 11 10 Retrieved 2022 11 10 Successful CE 20 Engine Hot Test with 20t off nominal amp 22 2t vacuum thrust www isro gov in Retrieved 2022 12 24 External links Edit Wikimedia Commons has media related to CE 20 rocket engine India test fires indigenous cryo engine for 800 seconds LPSC handouts during Aero India 2009 with Ce 20 specifications LPSC handouts during Aero India 2009 with specifications of all Liquid fueled engines of India Status of CE 20 in Space Transportation GSLV Mk III of ISRO s 2008 09 Annual Report ISRO upbeat as indigenous cryo engine passes test Retrieved from https en wikipedia org w index php title CE 20 amp oldid 1129260746, wikipedia, wiki, book, books, library,

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