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
211 - 212
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
Inlet air temperatures and pressures become very high when an SST (Supersonic Transport) propulsion system operates at high speed, and heat transfer to the turbine disc is strongly influenced by the airflow structure in the cavity. In this study, a simulation of airflow in a turbine disc cavity was made using a three-dimensional Reynolds-averaged Navier-Stokes code. The study focused on the effect of bolts in the cavity on the flowfield and resultant heat transfer. There are 30 bolts located on the rotating wall surface of the turbine disc. The one-thirtieth domain of the annulus, which contains one bolt, was calculated under the periodic boundary conditions. The velocity vectors, temperature distribution and swirl ratio inside the turbine disc cavity were calculated. These results showed that flows inside the cavity were strongly influenced by bolts. The bolts caused large differences in temperatures and swirl velocities between the fluid and the heated surface of the cavity. Thermal conductivity calculated using numerical results in the disc cavity with bolts was 1.3 times larger than that in the cavity without bolts. These results indicate that heat transfer is strongly influenced by the detailed shape of the surface inside the cavity.
CFD application to SST propulsion system
nalsp0049030.pdf
(181.56KB)
