Development Study of A Precooled Turbojet Engine

Paper number

IAC-08.C4.5.4

Author

Prof. Tetsuya Sato, Waseda University, Japan

Coauthor

Dr. Hideyuki Taguchi, Japan Aerospace Exploration Agency (JAXA), Japan

Coauthor

Mr. Hiroaki Kobayashi, Japan Aerospace Exploration Agency (JAXA), Japan

Coauthor

Mr. Takayuki Kojima, Japan Aerospace Exploration Agency (JAXA), Japan

Coauthor

Dr. Katsuyoshi Fukiba, Japan Aerospace Exploration Agency (JAXA), Japan

Coauthor

Dr. Daisaku Masaki, Japan Aerospace Exploration Agency (JAXA), Japan

Coauthor

Dr. Keiichi Okai, Japan Aerospace Exploration Agency (JAXA), Japan

Coauthor

Dr. Kazuhisa Fujita, Japan Aerospace Exploration Agency (JAXA), Japan

Coauthor

Mr. Motoyuki Hongoh, Japan Aerospace Exploration Agency (JAXA), Japan

Coauthor

Dr. Shujiro Sawai, Japan Aerospace Exploration Agency (JAXA), Japan

Year

2008

Abstract

This paper describes a development study of a hypersonic turbojet engine developed in Japan Aerospace Exploration Agency, JAXA. From the result of the trade-off study, the precooled cycle turbojet (PCTJ) was selected. PCTJ can operate from take-off to Mach 6 at 26 km of altitude by using the cryogenic performance of fuel liquid hydrogen.

A sub-scale engine  (S-engine) has 23 cm x 23 cm of rectangular cross section, 2.6 m of the overall length and about 100 kg of the target weight employing composite materials for a variable-geometry rectangular inlet and nozzle. The design thrust and specific impulse at SLS are 1.2 kN and 2060 sec respectively.

The aerodynamic design and component tests have been finished using wind tunnel models of an air-intake, precooler, compressor, combustor and nozzle. A prototype engine made of metal for the Mach2 flight demonstration is now under development. 

Two series of the ground system firing tests of S-engine were conducted in March and October 2007. These tests verified the precooled cycle, component performance and healthiness, start-up and acceleration control sequences. Maximum rotational speed of 70,000 rpm was attained in this test (design speed is 80,000 rpm). Next firing test is to be conducted in this summer. This test is more similar to the flight test, that is, it uses the fuel supplying system of the flight model (a tank, valves and control and measurement systems) and finally the engine will be attached to the vehicle.

The flight demonstration using a high-altitude observation balloon will be conducted in 2009 at Taiki town in Hokkaido.

Abstract document

IAC-08.C4.5.4.pdf

Manuscript document

IAC-08.C4.5.4.pdf (🔒 authorized access only).

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