Mid-section of a can-annular gas turbine engine with a radial air flow discharged from the compressor section [electronic resource]

• Ngôn ngữ: eng
• Ký hiệu phân loại: 629.13 Aeronautics
• Thông tin xuất bản: Oak Ridge, Tenn. : Distributed by the Office of Scientific and Technical Information, U.S. Dept. of Energy, 2016
• Mô tả vật lý: Medium: ED : , digital, PDF file.
• Bộ sưu tập: Metadata
• ID: 265974
• Chủ đề: 1. 33 advanced propulsion systems; 2. 42 engineering

Tóm tắt

A midframe portion (213) of a gas turbine engine (210) is presented, and includes a compressor section (212) configured to discharge an air flow (211) directed in a radial direction from an outlet of the compressor section (212). Additionally, the midframe portion (213) includes a manifold (214) to directly couple the air flow (211) from the compressor section (212) outlet to an inlet of a respective combustor head (218) of the midframe portion (213).