Design study of hypersonic components for precooled turbojet engine

Takayuki Kojima; Hiroaki Kobayashi; Hideyuki Taguchi; Katsuyoshi Fukiba; Kazuhisa Fujita; Hiroshi Hatta; Ken Goto; Takuya Aoki; Tetsuya Sato

Design study of hypersonic components for precooled turbojet engine

Takayuki Kojima^*, Hiroaki Kobayashi, Hideyuki Taguchi, Katsuyoshi Fukiba, Kazuhisa Fujita, Hiroshi Hatta, Ken Goto, Takuya Aoki, Tetsuya Sato

^*Corresponding author for this work

School of Fundamental Science and Engineering

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

7 Citations (Scopus)

Abstract

Recent studies about variable nozzles, that are a rectangular type nozzle and an axisymmetric type nozzle, of the precooled turbojet engine (S-engine) which are developed for the demonstration of the key technologies for the propulsion system of the hypersonic airplane and the first stage propulsion of the TSTO space plane are described in this paper. For the rectangular nozzle, three types of C-shaped carbon/carbon composite cowls which includes subscale model of the precooled turbojet engine are fabricated and the fine attachment to the ramp is confirmed. For the firing of the S-engine, stainless steel cowl with concrete heat insulator are fabricated and tested for 20 sec. Axisymmetric variable plug nozzle which is made of C/C material is fabricated and pressurized by the cold flow test. The axisymmetric plug nozzle can be operative up to 0.57 MPa of nozzle inlet pressure.

Original language	English
Title of host publication	15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference
Publication status	Published - 2008 Dec 1
Event	15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference - Dayton, OH, United States Duration: 2008 Apr 28 → 2008 May 1

Publication series

Name	15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

Conference

Conference	15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference
Country/Territory	United States
City	Dayton, OH
Period	08/4/28 → 08/5/1

ASJC Scopus subject areas

Engineering(all)

Cite this

Kojima, T., Kobayashi, H., Taguchi, H., Fukiba, K., Fujita, K., Hatta, H., Goto, K., Aoki, T., & Sato, T. (2008). Design study of hypersonic components for precooled turbojet engine. In 15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference [2008-2504] (15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference).

Design study of hypersonic components for precooled turbojet engine. / Kojima, Takayuki; Kobayashi, Hiroaki; Taguchi, Hideyuki et al.

15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference. 2008. 2008-2504 (15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference).

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

Kojima, T, Kobayashi, H, Taguchi, H, Fukiba, K, Fujita, K, Hatta, H, Goto, K, Aoki, T & Sato, T 2008, Design study of hypersonic components for precooled turbojet engine. in 15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference., 2008-2504, 15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, Dayton, OH, United States, 08/4/28.

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abstract = "Recent studies about variable nozzles, that are a rectangular type nozzle and an axisymmetric type nozzle, of the precooled turbojet engine (S-engine) which are developed for the demonstration of the key technologies for the propulsion system of the hypersonic airplane and the first stage propulsion of the TSTO space plane are described in this paper. For the rectangular nozzle, three types of C-shaped carbon/carbon composite cowls which includes subscale model of the precooled turbojet engine are fabricated and the fine attachment to the ramp is confirmed. For the firing of the S-engine, stainless steel cowl with concrete heat insulator are fabricated and tested for 20 sec. Axisymmetric variable plug nozzle which is made of C/C material is fabricated and pressurized by the cold flow test. The axisymmetric plug nozzle can be operative up to 0.57 MPa of nozzle inlet pressure.",

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AU - Fujita, Kazuhisa

AU - Hatta, Hiroshi

AU - Goto, Ken

AU - Aoki, Takuya

AU - Sato, Tetsuya

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Design study of hypersonic components for precooled turbojet engine

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