Design study on a small pre-cooled turbojet engine for flight experiments

Hideyuki Taguchi, Tetsuya Satou, Hiroaki Kobayashi, Takayuki Kojima, Keiichi Okai, Kazuhisa Fujita, Toyohiko Ohta

Research output: Chapter in Book/Report/Conference proceedingConference contribution

8 Citations (Scopus)

Abstract

Design aspects of a small pre-cooled turbojet engine for flight experiments are investigated in this study. Pre-cooled turbojet engine is a hypersonic engine suitable for Two Stage To Orbit (TSTO) Space Planes and other hypersonic cruise vehicles. The engine has a capability to accelerate vehicles with a flight speed range between Mach 0 and 6. The payload injection capability of the vehicle appeared to be higher than that with rocket engines, in the former analysis. Some component models for the engine have been tested under simulated conditions. Aerodynamic performances of a variable air intake have been investigated by wind tunnel tests. Anti-frosting technology has been established by using a light weight pre-cooler. System performance of pre-cooling cycle under sea level static condition has been obtained. High temperature structure for a ram combustor and a variable exhaust nozzle has been examined by firing tests. A small pre-cooled turbojet engine for flight experiments is designed based on the component models. The engine will be used for the experiments to obtain thenno-dynamic data of the pre-cooled cycle with the designed flight speed range. Results of thermo-dynamic analyses, CFD analyses and component tests are described in this study. Those results are used to determine the final scale and shape of each component

Original languageEnglish
Title of host publicationA Collection of Technical Papers - 13th AIAA/CIRA International Space Planes and Hypersonic Systems and Technologies Conference
Pages1914-1922
Number of pages9
Volume3
Publication statusPublished - 2005
Externally publishedYes
Event13th AIAA/CIRA International Space Planes and Hypersonic Systems and Technologies Conference - Capua
Duration: 2005 May 162005 May 20

Other

Other13th AIAA/CIRA International Space Planes and Hypersonic Systems and Technologies Conference
CityCapua
Period05/5/1605/5/20

Fingerprint

Turbojet engines
Engines
Hypersonic aerodynamics
Experiments
Air intakes
Rocket engines
Sea level
Combustors
Mach number
Wind tunnels
Nozzles
Aerodynamics
Computational fluid dynamics
Orbits
Cooling
Temperature

ASJC Scopus subject areas

  • Engineering(all)

Cite this

Taguchi, H., Satou, T., Kobayashi, H., Kojima, T., Okai, K., Fujita, K., & Ohta, T. (2005). Design study on a small pre-cooled turbojet engine for flight experiments. In A Collection of Technical Papers - 13th AIAA/CIRA International Space Planes and Hypersonic Systems and Technologies Conference (Vol. 3, pp. 1914-1922)

Design study on a small pre-cooled turbojet engine for flight experiments. / Taguchi, Hideyuki; Satou, Tetsuya; Kobayashi, Hiroaki; Kojima, Takayuki; Okai, Keiichi; Fujita, Kazuhisa; Ohta, Toyohiko.

A Collection of Technical Papers - 13th AIAA/CIRA International Space Planes and Hypersonic Systems and Technologies Conference. Vol. 3 2005. p. 1914-1922.

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Taguchi, H, Satou, T, Kobayashi, H, Kojima, T, Okai, K, Fujita, K & Ohta, T 2005, Design study on a small pre-cooled turbojet engine for flight experiments. in A Collection of Technical Papers - 13th AIAA/CIRA International Space Planes and Hypersonic Systems and Technologies Conference. vol. 3, pp. 1914-1922, 13th AIAA/CIRA International Space Planes and Hypersonic Systems and Technologies Conference, Capua, 05/5/16.
Taguchi H, Satou T, Kobayashi H, Kojima T, Okai K, Fujita K et al. Design study on a small pre-cooled turbojet engine for flight experiments. In A Collection of Technical Papers - 13th AIAA/CIRA International Space Planes and Hypersonic Systems and Technologies Conference. Vol. 3. 2005. p. 1914-1922
Taguchi, Hideyuki ; Satou, Tetsuya ; Kobayashi, Hiroaki ; Kojima, Takayuki ; Okai, Keiichi ; Fujita, Kazuhisa ; Ohta, Toyohiko. / Design study on a small pre-cooled turbojet engine for flight experiments. A Collection of Technical Papers - 13th AIAA/CIRA International Space Planes and Hypersonic Systems and Technologies Conference. Vol. 3 2005. pp. 1914-1922
@inproceedings{656999b84afe4a0c8298f56a88e828d1,
title = "Design study on a small pre-cooled turbojet engine for flight experiments",
abstract = "Design aspects of a small pre-cooled turbojet engine for flight experiments are investigated in this study. Pre-cooled turbojet engine is a hypersonic engine suitable for Two Stage To Orbit (TSTO) Space Planes and other hypersonic cruise vehicles. The engine has a capability to accelerate vehicles with a flight speed range between Mach 0 and 6. The payload injection capability of the vehicle appeared to be higher than that with rocket engines, in the former analysis. Some component models for the engine have been tested under simulated conditions. Aerodynamic performances of a variable air intake have been investigated by wind tunnel tests. Anti-frosting technology has been established by using a light weight pre-cooler. System performance of pre-cooling cycle under sea level static condition has been obtained. High temperature structure for a ram combustor and a variable exhaust nozzle has been examined by firing tests. A small pre-cooled turbojet engine for flight experiments is designed based on the component models. The engine will be used for the experiments to obtain thenno-dynamic data of the pre-cooled cycle with the designed flight speed range. Results of thermo-dynamic analyses, CFD analyses and component tests are described in this study. Those results are used to determine the final scale and shape of each component",
author = "Hideyuki Taguchi and Tetsuya Satou and Hiroaki Kobayashi and Takayuki Kojima and Keiichi Okai and Kazuhisa Fujita and Toyohiko Ohta",
year = "2005",
language = "English",
isbn = "1563477297",
volume = "3",
pages = "1914--1922",
booktitle = "A Collection of Technical Papers - 13th AIAA/CIRA International Space Planes and Hypersonic Systems and Technologies Conference",

}

TY - GEN

T1 - Design study on a small pre-cooled turbojet engine for flight experiments

AU - Taguchi, Hideyuki

AU - Satou, Tetsuya

AU - Kobayashi, Hiroaki

AU - Kojima, Takayuki

AU - Okai, Keiichi

AU - Fujita, Kazuhisa

AU - Ohta, Toyohiko

PY - 2005

Y1 - 2005

N2 - Design aspects of a small pre-cooled turbojet engine for flight experiments are investigated in this study. Pre-cooled turbojet engine is a hypersonic engine suitable for Two Stage To Orbit (TSTO) Space Planes and other hypersonic cruise vehicles. The engine has a capability to accelerate vehicles with a flight speed range between Mach 0 and 6. The payload injection capability of the vehicle appeared to be higher than that with rocket engines, in the former analysis. Some component models for the engine have been tested under simulated conditions. Aerodynamic performances of a variable air intake have been investigated by wind tunnel tests. Anti-frosting technology has been established by using a light weight pre-cooler. System performance of pre-cooling cycle under sea level static condition has been obtained. High temperature structure for a ram combustor and a variable exhaust nozzle has been examined by firing tests. A small pre-cooled turbojet engine for flight experiments is designed based on the component models. The engine will be used for the experiments to obtain thenno-dynamic data of the pre-cooled cycle with the designed flight speed range. Results of thermo-dynamic analyses, CFD analyses and component tests are described in this study. Those results are used to determine the final scale and shape of each component

AB - Design aspects of a small pre-cooled turbojet engine for flight experiments are investigated in this study. Pre-cooled turbojet engine is a hypersonic engine suitable for Two Stage To Orbit (TSTO) Space Planes and other hypersonic cruise vehicles. The engine has a capability to accelerate vehicles with a flight speed range between Mach 0 and 6. The payload injection capability of the vehicle appeared to be higher than that with rocket engines, in the former analysis. Some component models for the engine have been tested under simulated conditions. Aerodynamic performances of a variable air intake have been investigated by wind tunnel tests. Anti-frosting technology has been established by using a light weight pre-cooler. System performance of pre-cooling cycle under sea level static condition has been obtained. High temperature structure for a ram combustor and a variable exhaust nozzle has been examined by firing tests. A small pre-cooled turbojet engine for flight experiments is designed based on the component models. The engine will be used for the experiments to obtain thenno-dynamic data of the pre-cooled cycle with the designed flight speed range. Results of thermo-dynamic analyses, CFD analyses and component tests are described in this study. Those results are used to determine the final scale and shape of each component

UR - http://www.scopus.com/inward/record.url?scp=29044441429&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=29044441429&partnerID=8YFLogxK

M3 - Conference contribution

SN - 1563477297

SN - 9781563477294

VL - 3

SP - 1914

EP - 1922

BT - A Collection of Technical Papers - 13th AIAA/CIRA International Space Planes and Hypersonic Systems and Technologies Conference

ER -