A gas turbine engine (20) including a core having a compressor section (24) fluidly connected to a combustor (56) via a primary flowpath and a turbine section (28) connected to the combustor (56) via the core flow path (C). An assembly is disposed within t...

The ring (13) has two ring segments (18) holding guide vanes (16) and/or a heat shield plate (17) of a gas turbine, where the ring is fastened at a high pressure combustion chamber. The ring is segmented into regions of the guide vanes and/or the heat shie...

A reinforced structural guide vane system includes an outer casing (32); a center body (34) within the outer casing; a plurality of structural guide vanes (28) extending between and connected to the center body and the outer casing; and a plurality of stru...

A turbine engine shroud segment (10) comprises a body including an outer surface from and along which a segment projection extends away (36) from and in an axial direction. The segment projection includes circumferentially spaced apart segment support surf...

The device has a locking part (52) engaged between plates (34, 36) and between ends of sectors forming a spray ring. The ends are immobilized between the plates by the part, where the plates are parallel to circumferential orientation of an afterburner fla...

A low-pressure compressor exit stator assembly for a gas turbine includes a multiple of vanes (26) mounted between a full hoop outer shroud (34) and an inner shroud (36). The outer shroud (34) and inner shroud (36) are mounted to the intermediate case stru...

A bleed case assembly (46) is provided comprising an annular outer case (48) and an inner case (50). The inner case (50) comprises an annular shroud portion (60) having a radially outer surface opposite a radially inner surface, and a generally planar flan...