A thermal management system for an aircraft comprises a first gas turbine engine, a first thermal bus, a first heat exchanger, and a chiller. The first thermal bus comprises a first heat transfer fluid, with the first heat transfer fluid being in fluid com...

The invention discloses a method for operating a gas turbine (10) with sequential combustion (14, 15, 17, 19), which gas turbine (10) comprises a compressor (13), a first combustor (14, 17) with a first combustion chamber (14) and first burners (17), which...

The shield (15) has heat shield bricks fastened to a supporting structure (16) when a cooling air groove is partially covered along a longitudinal direction (7). A channel-shaped groove section (8) is formed into which a cooling air duct (9) opens, where c...

A heat exchanger assembly (130) comprises a heat exchanger body (202) including a first fluid circuit (100) and a second fluid circuit (102). The first circuit includes a first bypass valve (136) in flow communication with a first fluid circuit inlet chann...

Systems for cooling turbine components via fluid filled conduits 17 are disclosed. Various embodiments include a system having: a set of fan systems 6 for cooling a set of conduits 17, the set of conduits 17 fluidly connected with a turbine component 12; a...

A system for supplying turbine cooling air flow includes a turbofan engine, a heat exchanger, and a door. The turbofan engine includes an engine case that has an inner volume within which at least a gas turbine engine is mounted, and a bypass flow passage ...

The load raising process is applied to components (40) of the gas turbine subject to great heat. These components, which are usually cooled by air (KL), are replaced by steam-cooled components (61, 62, 73). These include at least one component (62) in the ...

An aviation turbomachine comprising, downstream from the turbine, a post-combustion chamber extended by at least one nozzle, said chamber being defined radially by a thermal protection lining dispsoed inside a casing, said casing and said lining together d...

A connector segment (22) for connecting a combustor liner (24) and a transition piece (20) in a gas turbine has a substantially cylindrical shape and is of double-walled construction including inner and outer walls (32, 34) and a plurality of cooling chann...

A cooling air cooling system (40) is selectively operable to reduce fuel gum deposits within the cooling system when a gas turbine engine (10) operates above a predefined percentage of rated engine power. The cooling system includes a re-circulating loop (...