Structure of output section of jet propulsion engine or gas turbine
Номер патента: CA2208113A1
Опубликовано: 09-02-1998
Автор(ы): Keisuke Hashimoto
Принадлежит: Kawasaki Jukogyo KK
Опубликовано: 09-02-1998
Автор(ы): Keisuke Hashimoto
Принадлежит: Kawasaki Jukogyo KK
Реферат: A tandem blade lattice having characteristics enhanced is provided. In a high pressure ratio blade lattice, inevitable generation of an shock wave is shifted, as much as possible, toward a rear portion of an upper surface of a front blade to inhibit separation from a blade surface from being caused by interference of theshock wave and a boundary layer, and boundary layer control is performed such that a speed, a momentum and the like of a jet flowing from a trailing edge of alower surface of the front blade onto an upper surface of a rear blade are regulated to obtain a flow along the upper surface of the rear blade, so that separation of the boundary layer on the upper surface of the rear blade is restricted to a vicinity of a trailing edge.
Damper assembly for a strut in a jet propulsion engine
Номер патента: US5056738A. Автор: Gary D. Mercer,Kurt T. Hildebrand. Владелец: General Electric Co. Дата публикации: 1991-10-15.