1. 11/18/2018
Development of Cryogenic Engine for GSLV MkIII: Technological Challenges
RS Praveen, N Jayan, KS Bijukumar,
J Jayaprakash, V Narayanan, G Ayyappan
Liquid Propulsion System Centre
Vikram Sarabhai Space Centre
ISRO Propulsion Research Complex
Department of Space, INDIA
ICEC-26

2. Contents Introduction and Background
Cryogenic Engine Schematic and operational features
Technological Challenges and adopted approach methodology
Concluding remarks.
11/18/2018
ICEC-26, NEW DELHI

3. Introduction and Background
High thrust Upper Stage Cryogenic Engine and 2 MW Power
Liquid hydrogen fuel and Liquid oxygen oxidiser
Gas Generator Cycle for development easiness
Chilling requirement in ground and during flight prior to operation.
Regenerative Cooling
10 Hot tests cumulative duration of approximately 1900s
11/18/2018
ICEC-26, NEW DELHI

4. Technological Challenges
Design and realization of the sub systems viz the thrust chamber, the gas generator, the liquid hydrogen and liquid oxygen turbo pumps.
System engineering of the engine with given envelope constraints and mass budget in the launch vehicle.
Ignition of the engine thrust chamber in the tank head mode
Sustained and stable combustion.
Passive thrust control system using pressure regulator and cavitating venturi combination
Mixture Ratio Control using re-circulation flow
Boot strap mode starting using stored gaseous hydrogen.
Development of flight sequence including chilling requirements of feed circuits
Testing and qualification.
11/18/2018
ICEC-26, NEW DELHI

5. Sub-System Design and Realization
11/18/2018
ICEC-26, NEW DELHI

6. Thrust Chamber Development
11/18/2018
Thrust Chamber Development
Atomization and vaporization
Reaction and mixing
Thermal loads
Nozzle Performance
Stability
Testing
LH2 Inlet
Spacer Assembly
Thrust Chamber Assembly
LOX Inlet
High Pressure Valves
Cavitating Venturies
11/18/2018
ICEC-26, NEW DELHI
ICEC-26

7. Turbo Pump System Sizing Dual Stage for LH2 Single Stage for LOX
Independent Turbines and Power Management
Critical Speed
Bearings and Seals
Testing
11/18/2018
ICEC-26, NEW DELHI

8. Integrated Engine Envelope, mass and moment of inertia
Interface Joints
Start Sequence Development
Chilling Requirements
Testing
11/18/2018
ICEC-26, NEW DELHI

9. Concluding Remarks
This is the first time that a cryogenic engine that operates in gas generator cycle capable of delivering a thrust of 20T has been developed by ISRO.
The technological challenges faced during the various phases of development were briefly highlighted in the paper.
11/18/2018
ICEC-26, NEW DELHI

10. THANK YOU
11/18/2018
ICEC-26, NEW DELHI