General Electric Company

Richard Francis Gutta

Roger C Walker

Fernando Jorge Casanova

James Michael Forrester

John Herbert Dimmick

Sanjeev Kumar Jha

Charles E Steckle

Nicholas Simon Graham

Ronald Stuart Denmark

Raymond Andrew Vincent

Srinivas Ravi

Ravi Meenaksh

Robert Craig Akin

Arthur J Piekarski

Prem Navin Dhayanandam

Vasantharuban Subramanian

Tushar S Desai

Robert Crag Akin

Roger Clayton Walker

Fernando Casanova

Fernando J Casanova

Ravi Meenaks

An airfoil and shroud assembly includes an airfoil including a root end, a free end and a tenon extending from the free end, the tenon including a base and an externally threaded stud extending from the base. A shroud includes an opening configured to receive the base of the tenon. A nut is configured to be threadably coupled to the externally threaded stud on the tenon on the airfoil to couple the shroud to the airfoil.

Airfoil shroud assembly using tenon with externally threaded stud and nut

Load couplings, power trains, and methods for adjusting torsional natural frequencies of power trains are provided. In one embodiment, a load coupling includes a first flange, a second flange, and a shaft extending between the first flange and the second flange. The load coupling further includes an annular ring extending radially outward from one of the first flange, the second flange, or the shaft, the annular ring including a plurality of bore holes defined therein, each of the plurality of bore holes including a first opening. The load coupling further includes a first cap connected within one of the plurality of bore holes proximate the first opening, the first cap deformable such that an interference fit is created with the one of the plurality of bore holes.

Load coupling and method for adjusting torsional natural frequency of power train

A method facilitates assembling a turbine. The method includes coupling buckets to a turbine wheel. The method also includes coupling a first end of a cover plate to the turbine wheel such that at least one projection extending from the turbine wheel retains the cover plate in position relative to the turbine wheel and inserting a fastening mechanism through an opening defined in the turbine wheel to secure the cover plate against the turbine wheel. The cover plate facilitates reducing dovetail leakage across the buckets coupled to the turbine wheel.

Method and apparatus to facilitate increasing turbine rotor efficiency

A cooling circuit serves to provide cooling air in a rotor having a compressor rotor and a turbine rotor. The cooling circuit includes a first cooling path through the compressor rotor in series with a second cooling path through the turbine rotor such that one amount of cooling air is used for cooling both the compressor rotor and the turbine rotor. The construction enables a reduction in cooling air requirements, thereby increasing power plant efficiency.

Rotor cooling circuit

An air duct assembly for a gas turbine compressor rotor in a gas turbine engine is described. The rotor includes a compressor spool shaft and at least one stage disk, and the air duct assembly includes an elongate hollow cylindrical air duct configured to couple to a stage disk at a first end of the air duct. The second end of the air duct is configured to couple to the spool shaft. The second end of the air duct includes a plurality of lobes depending radially inward, a spool shaft insert configured to fit into an opening in the spool shaft, and a plurality of pins coupled to the spool shaft insert and configured to extend from the insert and to engage the lobes of the second end of the air duct.

Trilobe mounting with anti-rotation apparatus for an air duct in a gas

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Greer, SC, United States of America

Richard Francis Gutta