General Electric Company

Yang Liu

Hua Zhang

Gary Michael Itzel

Roger C Walker

Dwight Eric Davidson

Michael Adelbert Sullivan

Sivaraman Vedhagiri

William Andrew Parker

Philip Michael Caruso

Ravichandran Meenakshisundaram

Mahesh Madhukar Athavale

A segment of a component for use in a gas turbine includes a leading edge; a trailing edge; a pair of opposed lateral sides between the leading and trailing edges; and a seal slot provided in each lateral side. The seal slot includes a surface having a channel extending in an axial direction defined from the leading edge to the trailing edge, at least one inlet to the channel, and at least one outlet from the channel. The at least one outlet is spaced downstream from the at least one inlet in the axial direction. The segment may be an inner shroud segment or a nozzle segment.

Cooling gas turbine components with seal slot channels

A gas turbine engine is provided comprising a compressor with an insulated cooling circuit. The compressor comprises a compressor casing having a compression chamber and at least one stator and at least one rotor disposed in the compression chamber, the at least one stator comprising a stator body having a plurality of tubes for transporting cooling air through passages in the stator body into the compression chamber. The plurality of tubes are surrounded by an air gap for insulating the tubes from the stator body.

Gas turbine engine with insulated cooling circuit

The turbine section of the turbine engine is provided with a flow of cooling air which is taken from a compressor section of the turbine engine. The air received from the compressor section is itself cooled before the air is delivered to the turbine. Heat is removed from the flow of air by a plurality of heat pipes which conduct heat away from the flow of air to lower the temperature of the air before it is provided to the turbine.

Apparatus and method for cooling a turbine using heat pipes

A turbine bucket for a turbomachine includes a main body portion having a base portion and an airfoil portion, the base portion includes a bucket cavity forward region and a shank cavity. The turbine bucket also includes a cooling channel that extends through the main body portion. At least one flow passage extends between one of the cooling channel and the shank cavity, toward the bucket cavity forward region. The at least one flow passage delivers a flow of cooling gas toward the bucket cavity forward region. The flow of cooling gas limits ingestion of hot gases into the bucket cavity forward region.

Turbine bucket for a turbomachine and method of reducing bow wave effects at a turbine bucket

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Simpsonville, SC, United States of America

Yang Liu