General Electric Company

Hardev Singh

Gerard Anthony Rinck

Ching-Pang Lee

Steven Robert Brassfield

Mark Edward Stegemiller

John Howard Starkweather

Monty Lee Shelton

Jonathan Philip Clarke

Chander Prakash

Michael Joseph Danowski

Brian Alan Norton

Johan Michael Reimann

Atanu Talukdar

Guruprasad Srinivasan

William Randolph Shinkle

Kotesh Kummamuri Rao

Venkatesh Kattigari Madyastha

Yan Chen

Jose Leon Vega

Jose Mendoza

David Michael Boudreaux

A controller includes a processor and memory. The memory stores instructions that, when executed, are configured to cause the processor to receive measurements pertaining to a measured operation parameter of at least a portion of a turbine system. The instructions are also configured to cause the processor to generate a customized model for the at least the portion of the turbine system. Moreover, the instructions are configured to cause the processor to estimate an estimated value using the received measurements. The estimated value pertains to a parameter of the turbine system. Furthermore, the instructions are configured to cause the processor to using the customized model, reduce or remove at least some environmental conditions from a corrected estimated value derived from the estimated value.

Model-based performance estimation

A system, includes machinery; and a protection monitoring system, comprising a processor configured to: analyze a trend of one or more data measurements of the machinery for one or more patterns indicative of a potential future fault within the machinery in the trend; and provide a fault prediction based upon the analysis of the trend.

Systems and methods for fault analysis

An airfoil for a gas turbine engine has opposed pressure and suction sidewalls extending between a leading edge and a trailing edge. The airfoil includes an array of radially-spaced apart longitudinally-extending lands which define a plurality of trailing edge slots therebetween. Each of the trailing edge slots has an inlet in fluid communication with an interior of the airfoil and an exit in fluid communication with the trailing edge. At least one of the lands is tapered such that a width of the land measured in a radial direction decreases from the suction sidewall to the pressure sidewall.

Turbine nozzle with trailing edge convection and film cooling

A gas turbine engine turbine blade includes a hollow airfoil extending radially from a blade root to a radially outer airfoil tip. The airfoil includes an airfoil outer wall having transversely spaced apart pressure and suction side walls meeting along chordally spaced apart leading and trailing edges of the airfoil. A radially extending cooling air supply channel within the airfoil includes a bank of pins integral with and extending transversely between the pressure and suction side walls. The bank of the pins is tuned such that a natural frequency of the blade associated with an engine forced driving mode of the blade is sufficiently away from a steady state engine operating frequency to substantially avoid natural frequency resonance of the blade during steady state engine operation. The bank of the pins is tuned by locations of the pins within the cooling air supply channel.

Turbine blade frequency tuned pin bank

A turbine blade for a gas turbine engine. An existing blade was found to exhibit bowing, or a concave configuration facing the pressure side, along its trailing edge. The invention reduces bowing by ( ) changing tilt, ( ) changing lean, ( ) reducing the number of cooling holes, while ( ) changing the diameters of the cooling holes, to maintaining the total cooling flow unchanged.

Gas turbine engine blade

A rotor blade for a gas turbine engine including a tip region that facilitates reducing operating temperatures of the rotor blade is described. The tip region includes a first tip wall and a second tip wall extending radially outward from a tip plate of an airfoil. The tip walls extend from adjacent a leading edge of the airfoil to connect at a trailing edge of the airfoil. A notch is defined between the first and second tip walls at the airfoil leading edge. At least a portion of the second tip wall is recessed to define a tip shelf.

Method and apparatus for reducing turbine blade tip temperatures

Growing community of inventors

Mason, OH, United States of America

Hardev Singh