Abstract: The present invention provides coolable exhaust nozzle flap and seal assemblies having liners that are spaced inward and apart from their respective flap and seal cool walls, to form a cooling passage therebetween that converges in the axial downstream flow direction. One embodiment provides single wall multi-hole film cooled nozzle flap and seal liners particularly for use individually or in combination on convergent and divergent hollow flaps and seals for variable exhaust nozzles. Flap and seal coolable assemblies may be unitary structures that are integrally fabricated or formed such as by casting.

Abstract: The present invention provides coolable exhaust nozzle flap and seal assemblies having liners that are spaced inward and apart from their respective flap and seal cool walls, to form a cooling passage therebetween that converges in the axial downstream flow direction. One embodiment provides single wall multi-hole film cooled nozzle flap and seal liners particularly for use individually or in combination on convergent and divergent hollow flaps and seals for variable exhaust nozzles. Flap and seal coolable assemblies may be unitary structures that are integrally fabricated or formed such as by casting.

Abstract: An afterburning, gas turbine aircraft engine with an annular duct for carrying bypass airflow is provided with a sliding valve type of rear Variable Area Bypass Injector (VABI) system. This rear VABI varies the direction and volume of the flow of bypass air into separate regions at an afterburning section of the engine. The system includes a sliding valve mounted in the bypass duct that is translated axially to open and close slots leading to core engine exhaust flow in the afterburning section. The unique structure of the injector system enables the axial translation of this sliding valve to simultaneously control bypass airflow into: first, a mixer just upstream of the afterburning section; second, a plurality of slots leading to the afterburning section; and third, an exhaust nozzle cooling liner that is cooled with the remaining portion of the bypass air.

Abstract: Airflow exiting a centrifugal compressor is diffused in multiple shaped passages tangential to the compressor impeller dumped into a plenum to reduce its Mach number and then directed through deswirl vanes to the entrance of a combustor. Deswirl at reduced Mach number significantly reduces pressure losses resulting in reduced complexity and manufacturing cost for the diffuser deswirl system.

Abstract: A flameholder for the afterburner of an aircraft gas turbine engine is provided which comprises a pair of concentric rings forming an annular flow passage therebetween which has a continuous annular inlet for receiving the gas flow from the turbine exhaust. A plurality of discrete pilot fuel jets eject pilot fuel into the passage. A plurality of flow vanes are positioned within and around the circumference of the annular flow passage in order to impart a circumferential swirl to the fuel-air mixture and thereby improve the mixing and vaporizing thereof. An igniter of the spark type is positioned downstream of the swirl vanes. The outer annular wall of the flow passage extends downstream of and diverges conically outward from the inner wall of the flow passage. An annular V-shaped gutter is secured to the downstream end of the inner wall of the annular flow passage in order to provide a stable flameholding surface. The pre-mixed, vaporized fuel recirculates into the V-gutter to provide combustion stability.