Airfoil cooling with internal cavity displacement features [electronic resource]

• Ngôn ngữ: eng
• Ký hiệu phân loại: 629.132 Mechanics of flight; flying and related topics
• Thông tin xuất bản: Oak Ridge, Tenn. : Distributed by the Office of Scientific and Technical Information, U.S. Dept. of Energy, 2019
• Mô tả vật lý: Medium: ED : , digital, PDF file.
• Bộ sưu tập: Metadata
• ID: 265776
• Chủ đề: 1. 33 advanced propulsion systems

Tóm tắt

A turbine airfoil including a central cavity defined by an outer wall including pressure and suction sides extending between and joined at leading and trailing edges, and a chordal axis extends generally centrally between the pressure and suction sides. Rib structures located in the central cavity define radial central channels extending across the chordal axis. Radial near wall passages are defined between the rib structures and each of the pressure and suction sides of the outer wall. The radial near wall passages are each open to an adjacent central channel along a radial extent of both the near wall passages and the adjacent central channel to define a radial flow pass associated with each central channel. The flow passes are connected in series to form a serpentine cooling path extending in the direction of the chordal axis.