A seal assembly (176) for a gas turbine engine (20) according to an aspect of the present disclosure includes, among other things, a seal (69; 169; 269) including a main body (170) extending circumferentially between opposed mate faces (178; 278). The main...

An assembly (58) for a gas turbine engine (20) includes a compressor rotor (38), a turbine rotor (40) and a cooling circuit (60). The compressor rotor (38) includes a gas path surface (68). The turbine rotor (40) is rotatable with the compressor rotor (38)...

A turbine engine has: a compressor; a combustor; a turbine; a gaspath (90) passing downstream from the compressor through the combustor and then through the turbine; a fuel source; a fuel flowpath from the fuel source to the combustor; and a heat exchanger...

An ejector assembly (400; 500) for a cooling system (300; 600) of a gas turbine engine (110) may comprise: a tail cone (122; 410; 510) having a tail cone outlet (414; 518) in fluid communication with a cooling air flow of the cooling system; an ejector bod...

A hybrid-electric aircraft system (401) includes first and second hybrid-electric engines (410, 420), first and second ducting systems (430, 440) fluidly communicative with each other and with the first and second hybrid-electric engines (410, 420), respec...

An assembly (200) for mounting an auxiliary component (120) to an engine case (210) of a gas turbine engine (100) includes a support bracket (222), the support bracket (222) having a first end (230) configured for attachment to a first flange (232) of the ...