Ishikawajima-Harima Heavy Industries Co Ltd
Ishikawajima-Harima Heavy Industries Co Ltd
National Aerospace Laboratory
National Aerospace Laboratory
National Aerospace Laboratory
National Aerospace Laboratory
出版者
航空宇宙技術研究所
出版者（英）
National Aerospace Laboratory (NAL)
雑誌名
航空宇宙技術研究所特別資料
雑誌名(英)
Special Publication of National Aerospace Laboratory
巻
49T
ページ
109 - 114
発行年
2000-12
会議概要（会議名, 開催地, 会期, 主催者等）
航空宇宙技術研究所 17-19 Jan. 2000 東京 日本
会議概要（会議名, 開催地, 会期, 主催者等）（英）
National Aerospace Laboratory 17-19 Jan. 2000 Tokyo Japan
The SST propulsion system operates in the range from Mach 3 at takeoff to Mach 5 at hypersonic transport. The air temperatures and pressures at air inlet become very high at high-speed flight, requiring the engine materials to be cooled down to keep the engine operating satisfactorily. This paper describes the four examples of CFD (Computational Fluid Dynamics) simulation carried out in HYPR (Hypersonic Transport Propulsion System) project. The analysis of three-dimensional unsteady stage was conducted to investigate the detailed flow structure through a single stage high-pressure turbine with nonuniform temperature due to hot streaks from a combustor. The flow in the multiple rotating cavities was simulated using an axisymmetric Navier-Stokes code. In the first performance test, air temperature in low-pressure turbine rim cavity increased beyond expectations at the Mach 2.5 climb conditions. To understand the overheating, the flow in the low-pressure rim cavity was numerically simulated. Heat transfer to turbine disc is strongly influenced by the flow structure in the cavity. Three-dimensional steady flow in the cavity was analyzed. These results of simulations showed that the validity of the CFD code is useful for the understanding of phenomena occurred in the SST propulsion system.
CFD application to SST propulsion system
nalsp0049014.pdf
(3.37MB)
