Patent ID: 7584615
Filing Date: 2009-09-08
Classification: F02K

Abstract:
1. A method of improving the ignition performance of an after-burner device for a bypass turbojet, the after-burner device receiving a “hot” central primary flow coming from an exhaust enclosure of the turbine of the turbojet, and a “cold” peripheral secondary flow flowing peripherally outside the exhaust enclosure, and having an after-burner ignition zone situated in the secondary flow reaching the after-burner device such that the ignition function is kept in the secondary flow, comprising: providing an ignitor member located in the ignition zone; and conveying a portion of the primary flow into the after-burner ignition zone through a feed duct connected at one end to a flame catcher ring that borders the ignition zone and connected at its other end to the exhaust enclosure in order to raise the temperature in this zone to a value that is higher than the temperature of the secondary flow so as to encourage after-burner ignition.