OS-504 Research and Development of High Temperature Core Engine(Organized Session 5: HYPR-HST/SST Propulsion System)

• FUJIMURA Tetsuji

  Ishikawajima-Harima Heavy Industries Co., Ltd.

• TSUGUMI Shogo

  Ishikawajima-Harima Heavy Industries Co., Ltd.

• KIMURA Hideo

  Kawasaki Heavy Industries, Ltd.

• SHIMIZU Kunihiro

  Mitsubishi Heavy Industries, Ltd.

• CABE Jerry L.

  GE Aircraft Engines

• YANAGI Ryoji

  Nationl Aerospace Laboratory

抄録

Hypersonic Transport Propulsion System Research (HYPR) Program was launched in 1989 as a ten-year project. The objective of this program is to develop the technologies for the propulsion systems for a Mach 5 Hypersonic Civil Transport of the early 21st Century, which could be environmentally acceptable and economically viable. A engine being studied is a combined cycle engine composed of a turbo engine and a ramjet engine. The turbo engine operates from take off to Mach 3 and the ramjet operates over Mach 2.5 to Mach 5. To satisfy both requirements of low fuel consumption and high specific thrust, the challenging turbine inlet temperature of 1973K with high compressor discharge temperature was selected. To confirm a engine integration and heat resisted design, the High Temperature Core Engine (HTCE) which is a high pressure core of a turbo engine have been built and tested up to the Mach 3 operating conditions. Based on the results, the combined cycle engine has been built and will be tested at a altitude test facility in this winter. This paper describes the HTCE design and engine test results.

収録刊行物

• The International Gas Turbine Congress : book of abstracts

  The International Gas Turbine Congress : book of abstracts 1999 (1), 201-209, 1999-11-14

  公益社団法人日本ガスタービン学会

詳細情報

• CRID: 1573387452121932288
• NII論文ID: 110006692215
• NII書誌ID: AA12007658
• 本文言語コード: en
• データソース種別:
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