A feasibility study of a new ARTEX engine system of AFT-turbine configuration

Kousuke Isomura, Junsuke Omi, Nobuhiro Tanatsugu, Tetsuya Satou, Hiroaki Kobayashi

Research output: Contribution to journalArticle

4 Citations (Scopus)

Abstract

A feasibility of ATREX (Air-Turbo-Ram Expander cycle) engine with conventional aft-turbine configuration has been studied to be developed in about 10 years, if the development project has started under enough resources. The novel tip-turbine of the original ATREX engine is replaced by a conventional aft-turbine, and the maximum turbine inlet temperature (TIT) is reduced to 1200K, to realize the engine by only using approved metal technologies of modern jet engines. The capability of the performance has been shown by parametric studies by changing components' design parameters. The study shows that the performance of the ATREX engine is not less than that of pre-cooled turbo jet. Some technical issues on developing the new ATREX engine have been addressed. The most important issue would come from the transient total temperature change due to the rapid acceleration from sea level static (SLS) condition (288K) to Mach 6 at 30km of altitude (1680K) in 6 minutes. The deformation due to transient thermal expansion has to be controlled. Especially, the change of the tip clearance and the clearance between rotors and stators are pointed out to be important design issues. The ATREX engine, which has shorter axial length and simpler rotor, has structural advantage over turbo jet.

Original languageEnglish
Pages (from-to)153-160
Number of pages8
JournalActa Astronautica
Volume51
Issue number1-9
DOIs
Publication statusPublished - 2002 Jul
Externally publishedYes

Fingerprint

Turbines
Engines
Air
Rotors
Intake systems
Jet engines
Sea level
Stators
Mach number
Thermal expansion
Temperature
Metals

ASJC Scopus subject areas

  • Aerospace Engineering

Cite this

A feasibility study of a new ARTEX engine system of AFT-turbine configuration. / Isomura, Kousuke; Omi, Junsuke; Tanatsugu, Nobuhiro; Satou, Tetsuya; Kobayashi, Hiroaki.

In: Acta Astronautica, Vol. 51, No. 1-9, 07.2002, p. 153-160.

Research output: Contribution to journalArticle

Isomura, Kousuke ; Omi, Junsuke ; Tanatsugu, Nobuhiro ; Satou, Tetsuya ; Kobayashi, Hiroaki. / A feasibility study of a new ARTEX engine system of AFT-turbine configuration. In: Acta Astronautica. 2002 ; Vol. 51, No. 1-9. pp. 153-160.
@article{b6952c6cd88e413fa7140c8a48e9167e,
title = "A feasibility study of a new ARTEX engine system of AFT-turbine configuration",
abstract = "A feasibility of ATREX (Air-Turbo-Ram Expander cycle) engine with conventional aft-turbine configuration has been studied to be developed in about 10 years, if the development project has started under enough resources. The novel tip-turbine of the original ATREX engine is replaced by a conventional aft-turbine, and the maximum turbine inlet temperature (TIT) is reduced to 1200K, to realize the engine by only using approved metal technologies of modern jet engines. The capability of the performance has been shown by parametric studies by changing components' design parameters. The study shows that the performance of the ATREX engine is not less than that of pre-cooled turbo jet. Some technical issues on developing the new ATREX engine have been addressed. The most important issue would come from the transient total temperature change due to the rapid acceleration from sea level static (SLS) condition (288K) to Mach 6 at 30km of altitude (1680K) in 6 minutes. The deformation due to transient thermal expansion has to be controlled. Especially, the change of the tip clearance and the clearance between rotors and stators are pointed out to be important design issues. The ATREX engine, which has shorter axial length and simpler rotor, has structural advantage over turbo jet.",
author = "Kousuke Isomura and Junsuke Omi and Nobuhiro Tanatsugu and Tetsuya Satou and Hiroaki Kobayashi",
year = "2002",
month = "7",
doi = "10.1016/S0094-5765(02)00076-0",
language = "English",
volume = "51",
pages = "153--160",
journal = "Acta Astronautica",
issn = "0094-5765",
publisher = "Elsevier Limited",
number = "1-9",

}

TY - JOUR

T1 - A feasibility study of a new ARTEX engine system of AFT-turbine configuration

AU - Isomura, Kousuke

AU - Omi, Junsuke

AU - Tanatsugu, Nobuhiro

AU - Satou, Tetsuya

AU - Kobayashi, Hiroaki

PY - 2002/7

Y1 - 2002/7

N2 - A feasibility of ATREX (Air-Turbo-Ram Expander cycle) engine with conventional aft-turbine configuration has been studied to be developed in about 10 years, if the development project has started under enough resources. The novel tip-turbine of the original ATREX engine is replaced by a conventional aft-turbine, and the maximum turbine inlet temperature (TIT) is reduced to 1200K, to realize the engine by only using approved metal technologies of modern jet engines. The capability of the performance has been shown by parametric studies by changing components' design parameters. The study shows that the performance of the ATREX engine is not less than that of pre-cooled turbo jet. Some technical issues on developing the new ATREX engine have been addressed. The most important issue would come from the transient total temperature change due to the rapid acceleration from sea level static (SLS) condition (288K) to Mach 6 at 30km of altitude (1680K) in 6 minutes. The deformation due to transient thermal expansion has to be controlled. Especially, the change of the tip clearance and the clearance between rotors and stators are pointed out to be important design issues. The ATREX engine, which has shorter axial length and simpler rotor, has structural advantage over turbo jet.

AB - A feasibility of ATREX (Air-Turbo-Ram Expander cycle) engine with conventional aft-turbine configuration has been studied to be developed in about 10 years, if the development project has started under enough resources. The novel tip-turbine of the original ATREX engine is replaced by a conventional aft-turbine, and the maximum turbine inlet temperature (TIT) is reduced to 1200K, to realize the engine by only using approved metal technologies of modern jet engines. The capability of the performance has been shown by parametric studies by changing components' design parameters. The study shows that the performance of the ATREX engine is not less than that of pre-cooled turbo jet. Some technical issues on developing the new ATREX engine have been addressed. The most important issue would come from the transient total temperature change due to the rapid acceleration from sea level static (SLS) condition (288K) to Mach 6 at 30km of altitude (1680K) in 6 minutes. The deformation due to transient thermal expansion has to be controlled. Especially, the change of the tip clearance and the clearance between rotors and stators are pointed out to be important design issues. The ATREX engine, which has shorter axial length and simpler rotor, has structural advantage over turbo jet.

UR - http://www.scopus.com/inward/record.url?scp=10644283054&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=10644283054&partnerID=8YFLogxK

U2 - 10.1016/S0094-5765(02)00076-0

DO - 10.1016/S0094-5765(02)00076-0

M3 - Article

VL - 51

SP - 153

EP - 160

JO - Acta Astronautica

JF - Acta Astronautica

SN - 0094-5765

IS - 1-9

ER -