General Electric Company

Kevin Thomas McGovern

Robert Walter Coign

Gary Michael Itzel

Christopher Edward Wolfe

David Wayne Weber

Gregory Thomas Foster

Victor John Morgan

Richard Martin DiCintio

Douglas Frank Beadie

Matthew Stephen Casavant

Christopher Donald Porter

Robert Joseph Reed

Omprakash Samudrala

Kenneth Neil Whaling

Zachary James Taylor

Jesse Ellis Barton

Bryan David Lewis

Dipankar Pal

Bruce Loren Smith

Ravi Praveen Eluripati

David W Ball

Leissner F Poth

A sealing arrangement for sealing between a stage-one nozzle and an aft frame includes a seal comprising a flexible sealing element. The flexible sealing element includes an intermediate portion, a first outer portion on one side of the intermediate portion, and a second outer portion on the other side of the intermediate portion. The intermediate portion is mechanically loaded against the first stage nozzle and the aft frame, and the first outer portion and the second outer portion are pressure-loaded against the aft frame and the stage-one nozzle.

Pressure-loaded seals

Systems and devices configured to seal interfaces/gaps between stationary components of turbines and manipulate a flow of coolant about portions of the turbine during turbine operation are disclosed. In one embodiment, a seal element includes: a first surface shaped to be oriented toward a pressurized cavity of the turbine; a second surface oriented substantially opposite the first surface and shaped to sealingly engage a contact surface of the static components; and a first set of angular features disposed in the second surface, the first set of angular features fluidly connecting the pressurized cavity and the flowpath of the turbine.

Seal system including angular features for rotary machine components

A system configured to precisely control and/or modulate purge flow in a power plant system (e.g., a gas turbine) during operation is disclosed. In one embodiment, a system includes: at least one computing device adapted to control a purge flow in a gas turbine by performing actions comprising: obtaining operational data from the gas turbine; determining an inferred gas path pressure value for the gas turbine; determining an allowable purge flow for the gas turbine as a function of the operational data and the inferred gas path pressure value; and adjusting the purge flow based upon the allowable purge flow determination.

Turbine purge flow control system and related method of operation

A floating seal assembly for sealing two static parts is disclosed. Each static part has an opposing groove, and the opposing grooves define a seal cavity. Floating seal assembly includes a floating circumferential seal having a middle portion and opposing end portions, each opposing end portion is positioned within a groove in one of the static parts, wherein each end portion has a curved side facing a low pressure side of the seal cavity. The floating seal assembly according to embodiments of the invention is pressure driven in that each curved side of the end portions is configured to engage a low pressure side of the seal cavity in response to a pressure differential across the sealing cavity reaching a threshold value.

Floating seal

Shroud assembly for use in a turbine, having an outer shroud having a side proximate to flow of operative fluid of the turbine, the side having a boss and an outer shroud aperture extending through the boss. An inner shroud is located between the side of the outer shroud proximate to the flow of operative fluid and the operative fluid flow of the turbine, the inner shroud having an inner shroud aperture which is dimensioned to fit over the boss.

Ceramic matrix composite shroud attachment system

Second-stage nozzles have vanes including airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table I with the X, Y and Z values commencing at the radially innermost aerodynamic section of the airfoil and then made relative to that section for the Z coordinate values. The X, Y and Z values may be scaled as a function of the same constant or number to provide a scaled-up or scaled-down airfoil section for the nozzle.

Airfoil profile for a second stage turbine nozzle

A turbine cooling component comprising a circumferential leading edge, a circumferential trailing edge, a pair of spaced and opposed side panels connected to the leading and trailing edges, an arcuate base connected to the trailing and leading edges having a fore portion, a midsection portion, an aft portion, opposed side portions, an outer surface partially defining a cavity operative to receive pressurized air, and an arcuate inner surface in contact with a gas flow path of a turbine engine, a first side cooling air passage in the base extending along the first side portion from the fore portion to the aft portion, and a fore cooling air passage in the fore portion of the base communicative with the side cooling air passage and the cavity, operative to receive the pressurized air from the cavity.

Methods and apparatus involving shroud cooling

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.

Growing community of inventors

Simpsonville, SC, United States of America

Kevin Thomas McGovern