General Electric Company

Kenneth Neil Whaling

David Wesley Ball, Jr

Hua Zhang

Dean Matthew Erickson

David W Ball

Kevin Wayne Kinzie

Gunnar Leif Siden

Carl Gerard Schott

John Joseph Lynch

Christina Renee Pompey

Ravi Praveen S Eluripati

Ravi Praveen Eluripati

Eric Stephen Kaufman

James L Davis

William Michael Starr

Ronald Scott Bunker

Christopher Edward Wolfe

David Martin Johnson

Douglas Scott Byrd

Douglas Frank Beadie

Omprakash Samudrala

Jason Allen Seale

Kevin Thomas McGovern

Alan Meier Truesdale

Ajit Singh Sengar

Priscilla Childers

Michael Savale

Mark Disch

Michael Francis Michalski

Nattamai Venkataraman Saravanan

Curtis Newton, Iii

Jr David Wesley Ball

An ejector system and method of operation for combining high and low pressure fluid flow streams is disclosed. A nozzle chamber communicates with a high pressure fluid flow stream and a suction chamber communicates with a low pressure fluid flow stream. The outlet of the nozzle chamber exit into the suction chamber and include multiple nozzles such that the high pressure flow stream exits the nozzle chamber in multiple flow streams having multiple surface areas for interlayer drag between the flows. The low pressure fluid flow stream is entrained by the high pressure fluid flow streams exiting the multiple nozzles to define an intermediate pressure flow stream.

Gas turbine ejector and method of operation

A method of assembling an ejector is provided, wherein the method includes providing a motive nozzle tip having a centerline axis and including a nozzle tip edge having at least one protrusion extending through a plane substantially normal to the centerline axis. The method also includes coupling the motive nozzle tip to the ejector.

Methods and apparatus for assembling a low noise ejector motive nozzle

A method for controlling the generation of turbine cooling air from air extracted from a compressor of a gas turbine including: extracting compressed air from a low pressure and a high pressure stage of the compressor; adding in an ejector the compressed air from the low pressure stage to the air from the high pressure stage and discharging the combined air as turbine cooling air; bypassing the ejector with a bypass portion of the extracted compressed air from the high pressure stage; in response to turning on the flow of extracted compressed air from the low pressure stage, changing a set point for an actual pressure ratio that includes a pressure of the turbine cooling air, and adjusting the bypass flow in response to the changed set point to cause the actual pressure ratio to approach the changed set point.

Method and system for controlling a set point for extracting air from a compressor to provide turbine cooling air in a gas turbine

A turbine includes: a plurality of turbine blades arranged within a casing, the arrangement including a clearance between tips of the blades and the casing; a plurality of manifolds disposed proximate to the casing opposite the clearance, wherein each of the manifolds includes a plurality of impingement holes in the surface thereof; a source of clearance information; and a source of cooling air for supplying cooling air through a plurality of flow control devices to selected ones of the manifolds according to the clearance information. A system and a method are also provided.

Apparatus and method for reducing eccentricity and out-of-roundness in turbines

An ejector for a turbine engine is described herein. The ejector may include a variable geometry motive nozzle and a variable geometry mixing tube positioned downstream of the variable geometry motive nozzle.

Variable geometry ejector

An ejector comprising a motive inlet, a motive nozzle separably secured to the motive inlet, a suction chamber about the motive nozzle, a suction fluid inlet to the suction chamber, a mixing tube in fluid communication with the suction chamber and the motive nozzle, a diffuser in fluid communication with the mixing tube and distal the suction chamber and the motive nozzle, and an outlet from the diffuser is provided. A nozzle comprising at least two concentric arc nozzle portions is also provided. An ejector comprising a mixing tube including a flexible layer adapted to compress or stretch, thereby allowing a mixing tube diameter to change is further provided.

Ejectors with separably secured nozzles, adjustable size nozzles, or adjustable size mixing tubes

A system is provided for directing air from plural compressor ports to provide cooling and/or sealing air to an associated turbine site. A first flow from a pressure stage of the compressor has a first pressure and temperature. A second flow from another pressure stage of the compressor has a second pressure and temperature. The first and second pressures/temperatures are different. An ejector has two inlets for receiving the first and second flows, and output for combining the first and second flows into a third flow. The pressure and temperature of the third flow are different from the first and second pressures and temperatures. A bypass line is connected between the first flow and the third flow, and provides a bypass flow. A mixer combines the bypass flow and the third flow into a fourth flow. The fourth flow has a pressure and temperature intermediate the pressure and temperature of the bypass flow and the third flow. The mixer comprises inner and outer sections. The inner section is generally cylindrical in cross section and has a plurality of holes therein. The angle between the direction of the bypass flow and the direction of the third flow, when the bypass flow meets the third flow in the mixer, is less than about 90 degrees.

Mixer for cooling and sealing air system of turbomachinery

A system for mixing flows from a compressor is provided. The system comprises an ejector that combines a first flow and a second flow, from the compressor, into a third flow. A bypass flow is connected between the first flow and the third flow. A mixer combines the bypass flow and the third flow into a fourth flow. The fourth flow has a pressure and temperature intermediate the respective pressures and temperatures of the bypass flow and the third flow.

Mixer for cooling and sealing air system for turbomachinery

A method of assembling a combustor assembly is provided, wherein the method includes providing a combustor liner having a centerline axis and defining a combustion chamber therein, and coupling an annular flowsleeve radially outward from the combustor liner such that an annular flow path is defined substantially circumferentially between the flowsleeve and the combustor liner. The method also includes orienting the flowsleeve such that a plurality of inlets formed within the flowsleeve are positioned to inject cooling air in a substantially axial direction into the annular flow path to facilitate cooling the combustor liner.

Methods and system for reducing pressure losses in gas turbine engines

A gas turbine engine system. The system includes a compressor with a first compressor stage and a second compressor stage, a turbine with a first turbine stage and a second turbine stage, a first flow path connecting the first compressor stage and the first turbine stage, a second flow path connecting the second compressor stage and the second turbine stage, a crossover flow path connecting the first flow path and the second flow path, and an ejector positioned about the crossover flow path and the first flow path. The ejector may be a variable motive nozzle ejector.

Variable motive nozzle ejector for use with turbine engines

A method for analyzing a system for safety to personnel or other systems is disclosed comprising: identifying at least one operating parameter of a first subcomponent of said product; identifying an inherent hazard of said first subcomponents based on an analysis of the at least one operating parameter; identifying features of the structure or operation of the subcomponent corresponding to the inherent hazard; identifying modifications or controls for the identified features which would mitigate the inherent hazard; prioritizing the identified features with respect to the effect that each of said features has on safety of the product; and determining whether an unsafe condition could result from the inherent hazard.

Method for performing a hazard review and safety analysis of a product or system

Growing community of inventors

Simpsonville, SC, United States of America

Kenneth Neil Whaling