General Electric Company

Wei Ning

Gunnar Leif Siden

Michael Ericson Friedman

John Franklin Ryman

Achalesh Kumar Pandey

Bradley Taylor Boyer

Scott Mordin Hoyte

James William Vehr

Dennis Paul Dry

Luke John Ammann

Stephen William Tesh

Yoon Seok Choi

Mullahalli Venkataramaniah Srinivas

Jagmeet Singh

In one aspect the present subject matter is directed to a system for cooling a turbine engine. The system includes a cooling medium source, a stator vane having an internal flow passage that is in fluid communication with the cooling medium source and a turbine shroud assembly having an internal flow passage that is in fluid communication with the internal flow passage of the stator vane. The system allows for reduced peak thermal gradients between a cooling medium provided by the cooling medium source and various turbine hardware components such as the turbine shroud assembly.

System for cooling a turbine engine

A method of decreasing the operational stresses acting on a target airfoil row in a turbine engine; wherein the target airfoil row is bordered on each side by a first upstream airfoil row and a first downstream airfoil row; the first upstream airfoil row and the first downstream airfoil row having substantially the same number of similar airfoils and both comprising one of a row of rotor blades and a row of stator blades, and the target airfoil row comprising the other; the method comprising the step of: configuring the circumferential position of the airfoils of the first upstream airfoil row and the airfoils of first downstream airfoil row such that at least a portion of the airfoils of the first upstream airfoil row and at least a portion of the airfoils of the first downstream airfoil row comprise a clocking relationship of between 25% and 75% pitch.

Turbine airfoil clocking

An assembly of airfoils in a turbine engine, the assembly comprising: at least three successive axially stacked rows of airfoils in one of a compressor and a turbine: a first airfoil row, a second airfoil row, and a third airfoil row; wherein the first airfoil row and the third airfoil row each comprise one of a row of rotor blades and a row of stator blades, and the second airfoil row comprises the other; and wherein at least a majority of the mid-channel points of the airfoils in the third airfoil row are positioned circumferentially within +/&#x2212;25% pitch of the third airfoil row with respect to the location at which a wake flow during a selected operating condition from the first airfoil row is determined to enter the third airfoil row.

Disclosed is a turbine blade or vane including a blade or vane body including a leading edge and a trailing edge, a plurality of cooling openings disposed along the trailing edge, a first width of the trailing edge, the first width being disposed across the cooling openings, and a second width of the trailing edge the second width being disposed between the cooling openings, wherein the second width is smaller than the first width.

Turbine blade or vane with improved cooling

A system for creating a risk analysis for at least one turbomachine includes a database storing characteristics of one or more turbomachines and a processing module coupled to the database that receives the characteristics from the database and creates the risk analysis. The processing module includes a modeling module that creates a representation of the amount of rocking in a particular turbomachine based on the characteristics and a performance modeler coupled to the modeling module and that, based on the representation of the amount of rocking, creates the risk analysis.

Turbomachine airfoil life management system and method

A method of operating a turbine engine, wherein the turbine engine includes a compressor, a combustor, a turbine, a plurality of successive axially stacked stages that include a row of circumferentially spaced stator blades and circumferentially spaced rotor blades, and a plurality of circumferentially spaced injection ports disposed upstream of a first row of stator blades in the turbine; the injection ports comprising a port through which cooling air is injected into the hot-gas path of the turbine, the method comprising: configuring the stator blades in the first row of stator blades such that the circumferential position of a leading edge of one of the stator blades is located within +/&#x2212;15% pitch of the first row of stator blades of the circumferential location of the injection port midpoint of at least a plurality of the injection ports.

Methods, apparatus and systems concerning the circumferential clocking of turbine airfoils in relation to combustor cans and the flow of cooling air through the turbine hot gas flowpath

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Greenville, SC, United States of America

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