General Electric Company Polska Sp. Z O.o.

Dariusz Olczak

Leszek Marek Rzeszutek

Tomasz Jan Bulsiewicz

Jaroslaw Stec

Grzegorz Maciej Kaczmarek

Maciej Michal Stanczyk

Tomasz Bulsiewics

Maciej Michal Stańczyk

Adam Tralewski

A compressor comprises a rotor shaft including a forward end portion. The forward end portion defines an outer surface. A first row of compressor rotor blades is coupled to the rotor shaft downstream from the forward end portion. An outer casing at least partially surrounds the first row of compressor rotor blades and the outer surface of the forward end portion of the rotor shaft. The outer casing at least partially defines an inlet to the compressor. An inlet guide vane comprises a mounting portion, a tip portion, a leading-edge portion, and a trailing-edge portion. The mounting portion is coupled to the outer casing upstream from the first row of compressor rotor blades. The tip portion extends towards the outer surface of the forward end portion of the rotor shaft. A radial gap is defined between the tip portion and the outer surface.

Compressor with anti-ice inlet

A nozzle segment for a gas turbine engine comprises an outer band having a cooling air inlet, an inner band having a first cooling air outlet, and a nozzle airfoil comprising a cooling flow passage arranged to receive the cooling air as a cooling air stream. A first channel and a second channel are arranged within the cooling flow passage. A deflector is arranged to divide the cooling air stream into a first cooling air stream in the first channel and a second cooling air stream in the second channel, respectively. The deflector deflects the first cooling air stream obliquely to a suction sidewall in the first channel, wherein the first channel is configured to transport the first cooling air stream along the first channel in a swirly flow.

Turbine nozzle segment and a turbine nozzle comprising such a turbine nozzle segment

A turbine engine that includes an engine casing including a fluid supply plenum, a mating surface, and a nozzle supply passage and a cavity flow passage that both extend between the fluid supply plenum and the mating surface. The turbine engine further includes a turbine nozzle assembly including a mating band. The mating band includes an inlet scoop in flow communication with the nozzle supply passage. An interface is defined between the mating band and a first portion of the mating surface, and a band cavity is defined between the mating band and a second portion of the mating surface. The cavity flow passage couples the fluid supply plenum in flow communication with the band cavity.

Turbine engine and components for use therein

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Warsaw, Poland

Dariusz Olczak