Embodiments of a Gas Turbine Engine ("GTE (20)") are provided, as are embodiments of a plasma flow-controlled intake system (22) for deployment on a GTE. In one embodiment, the GTE includes a turbine section (30), a combustion section (28) upstream of the ...

A compressor (20) for a gas turbine engine having a bleed air recirculation system includes a plurality of bleed holes (36) extending through a shroud (32) at a first axial location thereon substantially adjacent the rotor blade tips (28). The bleed holes ...

A gas turbine engine compressor (20) includes a rotor (24) defining a central axis of rotation and a plurality of blades (28) which project into an annular compressor gas flow passage (42), and a shroud (32) circumferentially surrounding the rotor (24) and...

A boundary layer control arrangement (10) comprises a pulse generator (14) communicating with a surface (20) having a fluid boundary layer thereacross. The boundary layer control arrangement (10) further includes a fluid supply means (12) for supplying a f...

The machine has a rotor with several rotor vanes (8) fixed on a rotating shaft whereby the means for removing the flow medium from at least one vane of one row are provided at non-axially symmetrical aerodynamically critical spots on the vane tips and ring...