Gas turbine engine assembling method for aircraft, involves forming axially aligned slots that extend radially via outer and inner casings, coupling flameholder within augmenter, and coupling augmentor within gas turbine engine

摘要

The method involves coupling a set of turning vanes (42) between a radially outer casing (36) and a radially inner casing (38) to form a flameholder assembly (30). Axially aligned slots extending radially through the outer and the inner casings are formed. A flameholder is coupled within an augmenter. The augmentor is coupled within a gas turbine engine. Flow restrictors are coupled between the outer and the inner casings. The vanes are coupled between the outer and the inner casings so that the vanes are positioned between the slots. Independent claims are also included for the following: (1) an augmenter for a gas turbine engine, comprising a flameholder with a radially outer casing (2) a gas turbine engine comprising flameholder coupled within an augmenter.