Development of Cryogenic Engine for GSLV MkIII: Technological Challenges

Abstract

View the article online for updates and enhancements. Abstract. Cryogenic engine capable of delivering 200 kN thrust is being developed for the first time in the country by ISRO for powering the upper stage of GSLV Mk-III, the next generation launch vehicle of ISRO capable of launching four tonne class satellites to Geosynchronous Transfer Orbit(GTO). Development of this engine started a decade ago when various sub-systems development and testing were taken up. Starting with injector element development, the design, realization and testing of the major sub-systems viz the gas generator, turbopumps, start-up system and thrust chamber have been successfully done in a phased manner before conducting a series of developmental tests in the integrated engine mode. Apart from the major sub-systems, many critical components like the igniter, control components etc were independently developed and qualified. During the development program many challenges were faced in almost all areas of propulsion engineering. Systems engineering of the engine was another key challenge in the realization. This paper gives an outlook on various technological challenges faced in the key areas related to the engine development, insight to the solutions and measures taken to overcome the challenges.

A Review on Advancements and Characteristics of Cryogenic Propulsion Rocket Engine

“…Here, a twin circuit was used to regeneratively cool the chamber in which the throat would be cooled with LH2, while the nozzle would be cooled with LOx, so as to improve chamber life and thereby to increase the engine thrust. In addition to this, during the development stages of ISRO's in-house GSLV Mk 3 project 23,24) , its LOX/LH2 based upper stage engine(CE20) was revolutionary at the time to operate in the gas generator cycle and was sufficient to attain a specific impulse of 443 seconds in a vacuum and operating thrust range between 180 kN to 220 kN, which was indeed a ground-breaking news to the aerospace community. All key elements like as atomization, vaporisation, reaction, mixing, thermal loads, nozzle performance, and engine stability were taken into consideration while designing the CE20's thrust chamber.…”

Common Bulkhead Tank Design for Cryogenic Stage of an Indian Launch Vehicle

“…A cryogenic propulsion system provides approximately 80% higher specific impulse than a solid propulsion system 1 . India has made significant progress from tiny Rohini sounding rocket in the 1960s to the current GSLV MkIII with cryogenic stages 1,2 .…”

“…ISRO uses Liquid Hydrogen (LH2) as fuel and Liquid Oxygen (LOX) as the oxidizer in their cryogenic stages 2 . These are stored in propellant tanks which are arranged in tandem with the intertank structure in the middle.…”