General Electric Company

Scott Francis Johnson

Matthew Troy Hafner

Vivek Venugopal Badami

Guanghua Wang

Sandip Dutta

Craig Allen Bielek

Joseph Anthony Weber

Mark Stewart Schroder

Nilesh Tralshawala

James Murray

Benjamin Arnette LaGrange

Paul Joseph Martin

Michael James O'Connor

Jon Robert DeLong

Tommy Dee Hayes

Daniel Francesco Driscoll

James Joseph Murray

A turbine apparatus is disclosed including a first article and a second article disposed between the first article and a hot gas path of a turbine. The first article includes at least one first article cooling channel in fluid communication with and downstream from a cooling fluid source, and the second article includes at least one second article cooling channel in fluid communication with and downstream from the at least one first article cooling channel. A method for redundant cooling of the turbine apparatus is disclosed including flowing a cooling fluid from the cooling fluid source through at least one first article cooling channel, exhausting the cooling fluid from the at least one first article cooling channel into at least one second article cooling channel, and flowing the cooling fluid through the at least one second article cooling channel.

Turbine apparatus and method for redundant cooling of a turbine apparatus

The present disclosure is directed to a cooling system for a turbomachine. The cooling system includes a turbomachine component defining a turbomachine component cavity. The cooling system also includes an insert positioned within the turbomachine component cavity for cooling the turbomachine component. The insert includes an insert body and a spring body. The spring body includes a first portion fixedly coupled to the insert body, a second portion in sliding engagement with the turbomachine component, and a third portion in sliding engagement with the insert body.

Turbomachine cooling system

Various embodiments include systems and apparatuses adapted for detecting two-dimensional turbomachine exhaust temperature. In some embodiments, a system includes a two-dimensional grid sized to mount within an exhaust path of a gas turbomachine, a radiation detection device for detecting radiation emitted from the two-dimensional grid at a plurality of points on the two-dimensional grid, the radiation detection device being mountable proximate the exhaust path and the two-dimensional grid and at least one computing device connected with the radiation detection device, the at least one computing device configured to generate a planar map of the temperature of the exhaust from the gas turbomachine based upon the intensity of the radiation emitted from two-dimensional grid detected at the plurality of points on the two-dimensional grid.

Systems and methods for planar temperature measurement

A power plant control system determines an augmented operating parameter set point responsive to a life cycle cost (LCC) objective function responsive to a LCC model. The augmented operating parameter value may be responsive to an initial set point determined by a controls model and a performance indicator determined by a performance model. The power plant may include a thermal generator, such as a gas turbine or other fuel-burning generator, and the operating parameter may include firing temperature, fuel flow rate, steam pressure/temperature/flow rate, and/or another suitable operating parameter. An offer curve is generated responsive to the augmented operating parameter.

Power plant operation enhancement

Third stage turbine buckets have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z' set forth Table I wherein X and Y values are in inches and the Z&#x2032; values are non-dimensional values from 0 to 1 convertible to Z distances in inches by multiplying the Z&#x2032; values by the height of the airfoil in inches and adding the radius of the airfoil base. The X and Y values are distances which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape. The X, Y and Z distances may be scalable as a function of the same constant or number to provide a scaled up or scaled down airfoil section for the bucket. The nominal airfoil given by the X, Y and Z distances lies within an envelope of +/&#x2212;0.0.060 inches in directions normal to the surface of the airfoil.

Airfoil shape for a turbine bucket and turbine incorporating same

Growing community of inventors

Simpsonville, SC, United States of America

Scott Francis Johnson