公开(公告)号：US5740674A

公开(公告)日：1998-04-21

申请号：US698064

申请日：1996-08-15

申请人： Bruno Beutin ,  Jean-Louis Charbonnel ,  Andre Collot ,  Claude Dejaune ,  Alain Espenel ,  Philippe Fessou ,  Jean-Claude Gregoire ,  Daniel Martin ,  Herve Paitre ,  Jean-Francois Ranvier ,  Monique Thore

发明人： Bruno Beutin ,  Jean-Louis Charbonnel ,  Andre Collot ,  Claude Dejaune ,  Alain Espenel ,  Philippe Fessou ,  Jean-Claude Gregoire ,  Daniel Martin ,  Herve Paitre ,  Jean-Francois Ranvier ,  Monique Thore

IPC分类号： F01D9/04 ,  F02C7/00

CPC分类号： F01D9/042 ,  Y02T50/672 ,  Y02T50/673

摘要： The arrangement of a gas turbine engine suitable for high bypass ratio aircraft engines in which gases circulate in a primary air channel (7) and a secondary channel (8) concentric to said primary air channel, is characterized in that structural vanes (22) connecting the channel delimitation casings (2, 10, 14, 5) with each other, alternate with aerodynamic vanes (20) for guiding the gases on a common circumference of the engine bypass air channel (8), and in that the structural channels branch out between the two channels. The resulting advantages are simplicity of construction associated with a reduction in the space required for housing the channels and good resistance without notable increase of the total mass.

摘要翻译： 适用于高旁通比飞行器发动机的燃气涡轮发动机的布置，其中气体在主空气通道（7）和与所述主空气通道同心的第二通道（8）中循环，其特征在于，连接 通道分隔壳体（2,10,14,5）彼此相交，与用于将气体引导到发动机旁通空气通道（8）的公共圆周上的气动叶片（20）交替，并且结构通道分支 两个通道之间。 所产生的优点是结构简单，与减少用于容纳通道所需的空间和良好的阻力相关联，而不显着增加总质量。