OS-507 R & D and Simulated Altitude Testing of HYPER Combined Cycle Engine(Organized Session 5: HYPR-HST/SST Propulsion System)

• MITSUOKA Takeo

  Ishikawajima-Harima Heavy Industries, Co., Ltd.

• NAKATA Yasushi

  Ishikawajima-Harima Heavy Industries, Co., Ltd.

• MIYAGI Hiroyuki

  Ishikawajima-Harima Heavy Industries, Co., Ltd.

• KIMURA Hideo

  Kawasaki Heavy Industries Co., Ltd.

• KISHI Kimihiro

  Mitsubishi Heavy Industries Co., Ltd.

• WELLS Gary

  United Technologies Pratt & Whitney

• CABE Jerry L.

  GE Aircraft Engines

• YANAGI Ryoji

  National Aerospace Laboratory

抄録

The Hypersonic Transport Propulsion System Research Project (HYPR) was launched in 1989 to develop technologies for the propulsion system of a Mach 5 hypersonic transport (HST) airplane. The engine being studied is the combined cycle engine composed of a turbo jet engine which can operate from take-off to Mach 3 and a ram jet engine which can operate over Mach 2.5 up to Mach 5. The mode transition from turbo to ram and reverse transition are assumed in the range of Mach 2.5 and 3. The combined cycle engine demonstrator was designed and manufactured in 1997. The first combined cycle engine test was carried out in February, 1998. Then the altitude test was performed to demonstrate turbo-ram mode transition capability from December, 1998 to March, 1999. This paper describes the design features and ATF test results of the combined cycle engine demonstrator focusing on turbo-ram mode transition.

収録刊行物

• The International Gas Turbine Congress : book of abstracts

  The International Gas Turbine Congress : book of abstracts 1999 (1), 225-232, 1999-11-14

  公益社団法人日本ガスタービン学会

詳細情報

• CRID: 1573387452121941888
• NII論文ID: 110006692218
• NII書誌ID: AA12007658
• 本文言語コード: en
• データソース種別:
  • CiNii Articles