Design Study and Component Tests on a Subscale Precooled Turbojet Engine for Flight Experiment
- Paper number
IAC-05-C4.5.02
- Author
Dr. Hideyuki Taguchi, Japan Aerospace Exploration Agency (JAXA), Japan
- Coauthor
Dr. Kazuhisa Fujita, Japan Aerospace Exploration Agency (ISTA/JAXA), Japan
- Coauthor
Mr. Hiroaki Kobayashi, Japan Aerospace Exploration Agency (ISTA/JAXA), Japan
- Coauthor
Dr. Keiichi Okai, Japan Aerospace Exploration Agency (ISTA/JAXA), Japan
- Year
2005
- Abstract
Components of the small scale precooled turbojet engine such as variable intake, air precooler, core engine, ram combustor and variable nozzle are designed and tested for the flight experiment and high enthalpy wind tunnel tests. The engine is expected to be operative from lift-off to Mach 6 by applying the precooling system and using LH2 as a fuel. Length of the engine is 2m. Hypersonic and supersonic wind tunnel experiments were conducted to acquire and improve the intake aerodynamic performances. Total pressure recovery of the intake was 0.22 at Mach 5. Variable intake whose main structure is advanced composite material is designed to realize the intake without cooling under Mach 6 flight condition. The shape of the intake and the precooler is designed using FEM analysis. Mixed compression type compressor was designed by CFD. Component test of the main combustor is performed using gaseous hydrogen. Temperature of the combustor could achieve 1273 K. A variable mechanism and cooling mechanism of the rectangular nozzle is designed. After the wind tunnel and combustion tests of the engine components, total engine system is designed by 3 dimensional CAD. The weight of the engine could satisfy the requirement of the flight test.
- Abstract document
- Manuscript document
IAC-05-C4.5.02.pdf (🔒 authorized access only).
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