General Electric Company

Raymond Henry Goetze

Alston Ilford Scipio

Sanji Ekanayake

Kenneth Damon Black

Surinder Singh Pabla

Eklavya Calla

Ian David Wilson

Henry Grady Ballard, Jr

Bradley James Miller

Peter Samuel King

Andrew Ray Kneeland

Stephen Christopher Chieco

Douglas Corbin Warwick

Kenneth David Black

An assembly and method are provided for sealing a compressor in a gas turbine engine. The method comprises forming an annular groove in a compressor casing such that the groove extends circumferentially about a rotor that is housed within the casing. The compressor casing is then coupled to the rotor such that the compressor casing extends circumferentially about the rotor. A plurality of arcuate seal segments are then inserted into the annular groove without removing the rotor from the compressor casing such that the plurality of seal segments extend circumferentially about the rotor to facilitate sealing a gap that is defined between the rotor and the compressor casing.

Replaceable seals for turbine engine components and methods for installing the same

A method of repairing a damaged rotor comprising: (a) preparing a locally damaged portion of the rotor; (b) cold spraying alloy powder particles onto the locally damaged portion; (c) controlling the cold spraying in step (b) to restore the locally damaged portion to form a repaired portion having substantially the same properties and shape as originally manufactured; and (d) heat treating at least the repaired portion.

Method of repairing a turbine rotor using cold spraying

A method of manufacturing a rotor includes: (a) providing a core shaft; (b) cold spraying alloy powder particles onto the core shaft; (c) controlling the cold spraying to form sections at least of different shape along the core shaft to thereby form a near-net shape rotor; and (d) heat treating the near-net shape rotor to relieve stresses and to form diffusion bonding across interfaces between individual powder particles and the core shaft, and finish-shaping said near-net shape rotor.

Turbine rotor fabrication using cold spraying

A method operates a gas turbine that includes a compressor section, a turbine section and an extraction cooling system. The method includes monitoring an operation of the gas turbine, directing a cooling air flow through the extraction cooling system from the compressor section to the turbine section in response to normal operation of the gas turbine, and directing a warming air flow through the extraction cooling system to the compressor section and the turbine section in response to shutdown of the gas turbine.

Systems and methods of reducing heat loss from a gas turbine during shutdown

Growing community of inventors

Simpsonville, SC, United States of America

Raymond Henry Goetze