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Development of Turbopump Systems for Cryogenic and Semicryogenic Propulsion Systems of ISRO

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Abstract

In Indian Space Research Organization (ISRO), the studies for the development of cryogenic propulsion were initiated in early 1980’s. The first cryogenic turbopump design (C12) in ISRO was made for 12 tonne (T) thrust engine identified for Geosynchronous Satellite Launch Vehicle (GSLV). The C12 turbopumps have undergone only initial developmental and design validation tests. The specific objective of attaining indigenous capability to launch Indian National Satellite-II (INSAT-II 2.5 T) spacecraft to geo transfer orbit (GTO) led to the need for developing a high-performance stage combustion (SC) cycle cryogenic engine. This cryogenic upper stage (CUS) engine forms the third stage of GSLV-MarkII (GSLV-MkII) launch vehicle (LV). The design check, development, extensive qualification and acceptance tests for these turbopumps were carried out and turbopumps are being used in GSLV-MkII LV. The need for launching 4 T class satellite to GTO led to the development of a high thrust 20 T cryogenic engine (CE-20). The design and development of these turbopumps were indigenously carried out. These turbopumps are rotor dynamically configured and its bearings and seals were indigenously developed. Turbopumps for CE-20 engine has successfully undergone development, qualification and acceptance tests and is being used in GSLV-MkIII vehicle. CE-20 engine turbopumps are the first indigenously designed, realised and qualified high speed turbopump in ISRO. To increase the payload capability of GSLV-MkIII LV and to meet ISRO’s future LV programme, Liquid Propulsion Systems Centre (LPSC), has taken up the development of a 200 T semicryogenic engine (SE-2000). Preliminary design review (PDR) of turbopumps are completed, hardware realisation and developmental tests are in progress.

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Abbreviations

ISRO:

Indian Space Research Organisation

LPSC:

Liquid Propulsion Systems Centre

GSLV:

Geosynchronous Satellite Launch Vehicle

INSAT:

Indian National Satellite

GTO:

Geo transfer orbit

CUS:

Cryogenic upper stage

GG:

Gas generator

SC:

Stage combustion

C12:

12 Tonne thrust engine

CE-20:

20 Tonne cryogenic engine

SE-2000:

200 Tonne semicryogenic engine

LOX:

Liquid oxygen

LH2 :

Liquid hydrogen

LN2 :

Liquid nitrogen

GN2 :

Gaseous nitrogen

PDR:

Preliminary design review

NPSH:

Net positive suction head

R&D:

Research and development

References

  • Abraham AM, Panigrahi S, Suresh MS (2017) Effect of pre-inducer in reducing net positive suction head requirement of a pump. J Propuls Power. https://doi.org/10.2514/1.B35514

    Article  Google Scholar 

  • Abraham AM, Unnikrishnan Nair P, Suresh MS (2020) Effect of blade configuration on performance of a high speed axial flow pump inducer. 71st IAC—The Cyber Space Edition

  • Choukekar KD, Nandi TK, George Paul P, Suresh MS (2009) Hydrostatic journal bearings for cryogenic rocket engine turbopumps: a review on the developments. Aerosp J Inst Eng (I) 90:3–8

    Google Scholar 

  • Huzel DK, Huang DH (2002) Modern Engineering for design of Liquid-Propellant Rocket Engines. AIAA, Washington DC, pp 155–218

    Google Scholar 

  • Kiran R, Sunil R, Harikumar K, Panigrahi S, Jayan N (2020) Effect of floating ring seal clearance on the performance of centrifugal pump used in liquid rocket engine. 71st IAC-The Cyber Space Edition

  • Narayanan V, Dathan MC, Sivan K, Suresh MS, Karthikesan D, Kartha NRV, Jose P (2014) Flight testing of Indian Cryogenic Upper Stage. IAF, Toronto

    Google Scholar 

  • Narayanan V, Dathan MC, Suresh MS, Jayan N, George M, Philip M, Ramesh G, Ganesh Pillai M (2014) Development Status of a 200 kN thrust Cryogenic Upper Stage Engine for ISRO’s next generation launch vehicle. IAF, Toronto

    Google Scholar 

  • Sanand TV, Deepak D, Unnikrishnan Nair P, Suresh MS (2011) Technological challenges and new techniques involved in the development of turbopumps for the semi-cryo engine of ISRO. ASET Conference, Mahendragiri

  • Sutton GP (2006) Turbopumps, a historical perspective. 42nd joint propulsion conference and exhibition, California

  • Sutton GP, Biblarz O (2001) Rocket propulsion elements. Wiley, NewYork, pp 197–239

    Google Scholar 

Download references

Acknowledgement

Author wish to express sincere gratitude to Dr.K. Sivan Chairman, ISRO and Dr.V. Narayanan, Director, LPSC for their continuous support and guidance during developmental activities. Author also like to express sincere gratitude to assembly and testing team at ISRO Propulsion Complex (IPRC), Mahendragiri without their continuing support the development activities would not have been possible. The contributions of N.K.Gupta, T.M. Philip, P. Unnikrishnan Nair, Paul P. George, Sridhar Panigrahi and their team members are greatly acknowledged.

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  1. Semicryogenic Propulsion Systems Project, Liquid Propulsion Systems Centre, Indian Space Research Organisation, Thiruvananthapuram, Kerala, India

    M. S. Suresh

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  1. M. S. Suresh
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Correspondence to M. S. Suresh.

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Suresh, M.S. Development of Turbopump Systems for Cryogenic and Semicryogenic Propulsion Systems of ISRO. Trans Indian Natl. Acad. Eng. 6, 229–241 (2021). https://doi.org/10.1007/s41403-020-00189-5

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  • DOI: https://doi.org/10.1007/s41403-020-00189-5

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