System for tuning a combustor of a gas turbine [electronic resource]

• Ngôn ngữ: eng
• Ký hiệu phân loại: 621.48 Nuclear engineering
• 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: 266665
• Chủ đề: 1. 33 advanced propulsion systems; 2. 42 engineering

Tóm tắt

A system for tuning a combustor of a gas turbine includes a flow sleeve having an annular main body. The main body includes an upstream end, a downstream end, an inner surface and an outer surface. A cooling channel extends along the inner surface of the main body. The cooling channel extends at least partially between the downstream end and the upstream end of the main body.