Swirling midframe flow for gas turbine engine having advanced transitions [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: 266012
• Chủ đề: 1. 33 advanced propulsion systems; 2. 42 engineering

Tóm tắt

 A gas turbine engine can-annular combustion arrangement (10), including: an axial compressor (82) operable to rotate in a rotation direction (60)
  a diffuser (100, 110) configured to receive compressed air (16) from the axial compressor
  a plenum (22) configured to receive the compressed air from the diffuser
  a plurality of combustor cans (12) each having a combustor inlet (38) in fluid communication with the plenum, wherein each combustor can is tangentially oriented so that a respective combustor inlet is circumferentially offset from a respective combustor outlet in a direction opposite the rotation direction
  and an airflow guiding arrangement (80) configured to impart circumferential motion to the compressed air in the plenum in the direction opposite the rotation direction.