General Electric Company

Siemens Energy, Inc.

Siemens Aktiengesellschaft

Bruce Loren Smith

Gunnar Leif Siden

Robert Romany By

David James Wiebe

Robert Alan Brittingham

Brian Peter Arness

Matthew D Montgomery

Daniel David Snook

Kevin Thomas McGovern

Peter Gaines Cleveland

Carlos Alberto Collado

Charles Andrew Malinowski

Peter Christopher Selent

Poornathresan Krishnakumar

Leissner F Poth

An airfoil () including an internal cooling circuit () to direct cooling fluid () through an interior of the airfoil. The airfoil also includes a trailing edge (') defining plugged holes () and cooling holes () along a radial direction (). A selective group () of the cooling and plugged holes are based on a reduced cooling fluid requirement at the trailing edge (&#x2032;) resulting from an improved thermal barrier coating (). A process () is also provided including removing () an airfoil from service in a gas turbine engine and adding or improving () a thermal barrier coating on the airfoil. The process also includes selectively () plugging holes in the airfoil in response to a reduced cooling fluid required through the airfoil as a result of the added or improved thermal barrier coating.

Trailing edge cooling arrangement for an airfoil of a gas turbine engine

An airfoil assembly including an endwall and an airfoil extending from the into a gas flow path. The endwall includes upstream and downstream edges, and is defined on a platform structure having a front surface extending radially in a direction of a thickness of the platform structure. At least one fluid injection passage extends through the platform structure in a direction from the upstream edge toward the downstream edge of the endwall. The fluid injection passage has an outlet opening defined at the endwall and an inlet opening in fluid communication with a pressurized fluid source. The fluid injection passage extends at a shallow angle relative to a plane of the endwall wherein the fluid injection passage defines a passage axis passing through the front surface and the endwall for effecting energization of a boundary layer between the outlet opening and the airfoil leading edge.

Airfoil assembly including vortex reducing at an airfoil leading edge

An apparatus () is presented for controlling a boundary layer () in a diffusing flow path () of a power generating machine (). The apparatus includes a passage () in the power generating machine with an inlet () and an outlet (). The apparatus also includes a fluid source () coupled to the inlet to transmit fluid into the passage. The apparatus also includes a vortex generator () within the passage effective to generate a vortex fluid () at the outlet. The outlet is positioned to inject the vortex fluid into the diffusing flow path of the power generating machine in order to control the boundary layer of the diffusing flow path. An apparatus is also provided to enhance the diffusion of a flow path within a power generating machine.

Apparatus for controlling a boundary layer in a diffusing flow path of a power generating machine

A turbine bucket including an airfoil, the airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 as contained herein wherein the Z values are non-dimensional values from approximately 0 to 1 convertible to Z distances in inches by multiplying the Z values by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by substantially smooth continuing arcs, define airfoil profile sections at each distance Z, the profile sections at the Z distances being joined substantially smoothly with one another to form a complete airfoil shape.

Airfoil shape for a turbine bucket

A turbine engine that includes a vortex protrusion disposed upon a component that rotates during operation of the turbine engine; wherein the vortex protrusion includes an outer surface that is configured to induce a vortex flow pattern as the component rotates during operation.

Systems and apparatus relating to turbine engines and seals for turbine engines

Second-stage nozzles have vanes including airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table I with the X, Y and Z values commencing at the radially innermost aerodynamic section of the airfoil and then made relative to that section for the Z coordinate values. The X, Y and Z values may be scaled as a function of the same constant or number to provide a scaled-up or scaled-down airfoil section for the nozzle.

Airfoil profile for a second stage turbine nozzle

The third stage nozzle has an airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein X and Y values are in inches and define airfoil profile sections at each distance Z and Z are non-dimensional values within a range from 0.1 to 0.9 convertible to Z distances in inches by multiplying the Z values of Table I within the range by a height of the airfoil in inches. The profile sections at the Z distances are joined smoothly with one another to form the nozzle airfoil shape. The X and Y distances may be scalable to provide a scaled-up or scaled-down airfoil for the nozzle. The nominal airfoil given by the X, Y and Z distances lies within an envelope of &#xb1;0.160 inches.

Airfoil shape for a turbine nozzle

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 values are non-dimensional values from 0.03 span to 0.95 span convertible to Z distances in inches by multiplying the Z values by the height of the airfoil in inches. 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 the bucket 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 envelop of &#xb1;0.150 inches in directions normal to the surface of the airfoil.

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Greer, SC, United States of America

Bruce Loren Smith