General Electric Company

General Electric Company Polska Sp. Z O.o.

General Electric Deutschland Holding Gmbh

Piotr Jerzy Kulinski

Ashish Sharma

Scott Alan Schimmels

Adam Tomasz Pazinski

Tomasz Jan Bulsiewicz

Tomasz Edward Berdowski

Wendy Wenling Lin

Elzbieta Kryj-Kos

Raymond Floyd Martell

Lukasz Maciej Janczak

Patrick Keene Clements

Ruolong Ma

Pawel Adam Lewicki

Andrea Milli

Gunter Wilfert

A method of operating a gas turbine engine comprising: extracting a flow of air from a compressor section of the gas turbine engine into a first conduit; flowing the extracted flow of air through the first conduit to a first location at a turbine section of the turbine section, wherein a second conduit is in fluid communication with the turbine section at a second location; flowing a heat transfer fluid to a first heat exchanger positioned in thermal communication with the flow of air through the first conduit, the heat transfer fluid in thermal communication with the extracted flow of air through the first conduit via the first heat exchanger; and modulating, via a flow control device, a portion of the flow of air extracted from the first conduit to the second conduit downstream of the first heat exchanger.

Gas turbine engine with a fluid conduit system and a method of operating the same

A method of electroforming an airfoil comprising an airfoil body. The method comprising electroforming a metal edge shell over a filler, located at a leading edge of the airfoil body, and over the airfoil body. The filler can be encapsulated within the metal edge shell and the metal edge shell has a sculpted leading edge defining a non-linear pattern.

Engine airfoil metal edge

Methods and apparatus for gas turbine frame flow path hardware cooling are disclosed. An example engine fan case includes an outer band and an inner band, the outer band and the inner band connected using a double-walled vane, the vane including openings to pass cooling air flow from the outer band to an airfoil of the fairing, and an end segment seal, the seal formed on an edge of the fairing using an auxetic material.

Methods and apparatus for gas turbine frame flow path hardware cooling

An assembly for a turbine engine can include a monolithic body with an inner band and an outer band radially spaced from the inner band, a pocket surface in one of the inner or outer bands defining a recess, and an airfoil with a first end radially extending from the other of the inner or outer bands.

Turbine engine assembly

A gas turbine engine including: a first turbine rotor assembly including a plurality of first turbine rotor blades extended within a gas flowpath; and a casing surrounding the first turbine rotor assembly, wherein the casing comprises an outer casing wall extended around the first turbine rotor assembly; a plurality of vanes extended from the outer casing wall and within the gas flowpath at a location aft of the first turbine rotor assembly; and a thermal control ring positioned outward along a radial direction from the outer casing wall, and wherein the thermal control ring comprises a body and a plurality of pins, and wherein the plurality of pins extend between the outer casing wall and the body.

Gas turbine engine with clearance control system

An airfoil for a gas turbine engine defining a spanwise direction, a root end, a tip end, a leading edge end, and trailing edge end is provided. The airfoil includes: a body extending along the spanwise direction between the root end and the tip end, the body formed of a composite material; and a sculpted leading edge member attached to the body positioned at the leading edge end of the airfoil, the sculped leading edge member formed at least in part of a metal material and defining a non-linear patterned leading edge of the airfoil.

A gas turbine engine including a first turbine rotor assembly having a plurality of first turbine rotor blades extended within a gas flowpath, and a second turbine rotor assembly positioned aft along the gas flowpath of the first turbine rotor assembly. The second turbine rotor assembly is rotatably separate from the first turbine rotor assembly. A casing surrounds the first turbine rotor assembly. The casing has a unitary, integral outer casing wall extended forward of the first turbine rotor assembly and aft of the first turbine rotor assembly. The casing includes a plurality of vanes extended from the outer casing wall and through the gas flowpath aft of the first turbine rotor assembly and forward of the second turbine rotor assembly. The casing includes a plurality of walls forming thermal control rings extended outward along the radial direction from the outer casing wall. The outer casing wall and the thermal control rings is a unitary, integral structure.

Growing community of inventors

Warsaw, Poland

Piotr Jerzy Kulinski