General Electric Company

William F McGreehan

Robert Louis Ponziani

Neil Howes

Andrew J Lammas

Samuel H Davison

Bradley Willis Fintel

Sunil K Mishra

Laurence T Sherwood

To control disc temperature, provide blade tip clearance control, and purge the rotor bore of a high pressure compressor in a gas turbine engine, an axially elongated manifold is disposed coaxially in the rotor bore to distribute cooling air bleed from the compressor inlet airstream to selected cavities between successive rotor discs in amounts tailored to the particular cooling needs of the neighboring discs.

Compressor bore cooling manifold

A high pressure compressor flowpath bleed extraction slot is provided wherein an articulated portion of the outer band of the compressor forms a slot for providing efficient conversion of core air to diffuser air while retaining substantial pressure and velocity energies. The diffuser slot can be applied to an earlier compressor stage with improved performance.

High pressure compressor flowpath bleed valve extraction slot

An industrial gas turbine engine includes in serial flow relationship a first compressor, a second compressor, a combustor, a first turbine, and a second turbine. The first compressor and the second turbine are fixedly joined together by a first shaft, and a turbine rear frame having a hub is disposed downstream of the second turbine for rotatably supporting the first shaft. A balance piston is fixedly joined to the first shaft, and means for channeling a fluid first to the balance piston for balancing thrust force on the first shaft and then to the turbine rear frame for heating the hub are provided. The apparatus is effective for carrying out a method including channeling a fluid first to the balance piston for thrust balancing the first shaft and then channeling the fluid to the tubine rear frame for heating the frame hub.

Method for thrust balancing and frame heating

An industrial gas turbine engine includes in serial flow relationship a first compressor, a second compressor, a combustor, a first turbine, and a second turbine. The first compressor and the second turbine are fixedly joined together by a first shaft, and a turbine rear frame having a hub is disposed downstream of the second turbine for rotatably supporting the first shaft. A balance piston is fixedly joined to the first shaft, and means for channeling a fluid first to the balance piston for balancing thrust force on the first shaft and then to the turbine rear frame for heating the hub are provided. The apparatus is effective for carrying out a method including channeling a fluid first to the balance piston for thrust balancing the first shaft and then channeling the fluid to the turbine rear frame for heating the frame hub.

Apparatus for thrust balancing and frame heating

A method and system for controlling rotor blade tip clearances in a gas turbine engine is disclosed. A flow of heat transfer fluid is supplied to the rotor. The temperature of the flow is controlled as a function of the heat carrying capacity of the fluid.

Clearance control system

A system for controlling rotor blade tip clearances in a gas turbine engine supplies both heating air and cooling air to the rotor bore. The heating air flow is controlled by a valve and the cooling air flow is not controlled.

A method and apparatus for measuring the leakage flow rate through a labyrinth seal is disclosed. This is achieved by first injecting a tracer gas through a spray tube at an upstream region of the seal. The tracer gas mixes with the gas stream to form a mixed flow stream. The concentration of the tracer gas in the mixed flow stream is then measured, allowing the leakage flow rate to be calculated.

Growing community of inventors

West Chester, OH, United States of America

William F McGreehan