Power Systems Mfg., LLC

Other

United Technologies Corporation

Siemens Energy, Inc.

Alstom Technology Limited

Richard Seleski

Michael G McCaffrey

Jonathan Jeffery Eastwood

David James Wiebe

Graham Ryan Philbrick

Joseph F Englehart

Henry K Webster

Jerome H Katy

Benjamin G Hettinger

Thomas K Churbuck

Robert P Moore

Adam Wallace

ChaiDee Woods Brown

Tom Brooks

Thomas E Brew, Jr

Dale Lee Cox

Remo Chiurato

A turbine section for a gas turbine engine includes blade outer air seals and stator vanes that provide a core flow path. A turbine case supports blade outer air seals and stator vanes. An annular cavity is provided between an interior surface of the turbine case and the blade outer air seals and the stator vanes. A hole extends through the turbine case from an exterior surface to the interior surface. The annular cavity extends axially to an exit. A manifold circumscribes the exterior surface of the turbine case and provides an annular space therebetween. The annular space is in fluid communication with the exit of the annular cavity via the hole.

Gas turbine engine active clearance control system using inlet particle separator

A turbine assembly having an outer casing (), an inner structural ring (), and an annular gas path () defined between outer and inner flow path walls () for conducting a gas flow through the turbine assembly. A plurality of structural struts () are spaced apart in a circumferential direction, each strut () including a strut body () extending in a radial direction for supporting the inner structural ring () to the outer casing (). A first strut end () at a radially outer end of the strut body () is detachably attached to the outer casing () with a first fastener structure () engaging the outer casing (), and a second strut end () at a radially inner end of the strut body () is detachably attached to the inner structural ring () with a second fastener structure () engaging the inner structural ring ().

Turbine assembly with detachable struts

A shroud for use with a turbine blade is disclosed wherein the shroud provides at least one knife edge with at least one tooth for cutting a groove in a compliant rub strip that minimizes wear on the knife edge. The tooth is positioned along the knife edge inward of the ends of the knife edge and a distance from an airfoil stackline such that the moment created by the tooth mass and its effect on shroud bending stress is significantly reduced, thereby resulting in increased turbine blade durability.

Turbine blade shroud cutter tip

The present invention seeks to provide a turbine blade with increased creep capability for both uncooled and cooled turbine blades while generally maintaining operating stress levels at an interface region between the turbine blade and a turbine disk. A turbine blade is disclosed having an attachment, a neck, a platform, and an airfoil. Extending radially outward from the attachment, through the neck, and terminating radially inward of the platform is a plurality of first cavities. The turbine blade in accordance with the preferred embodiment of the present invention is cast from a high density nickel base alloy with high temperature capability and improved creep capability. A plurality of first cavities are placed in the attachment and neck region to reduce excess weight of the turbine blade due to the higher density, greater creep capable alloy. Reducing the weight of the blade in this region provides increased creep capability in the turbine blade airfoil while maintaining operating stress levels.

Turbine blade attachment lightening holes

There is provided a gas turbine vane with an airfoil cooling circuit incorporating multiple generally radially extending rows of pedestals generally bisected by a plurality of axially extending ribs with the ribs containing a plurality of recessed cavities. The recessed cavities are positioned immediately adjacent pedestals located closest to the ribs such that a cavity passageway is formed to pass sufficient cooling air between the rib and pedestal to increase overall heat transfer and reduce pressure loss of the cooling fluid.

Vane enhanced trailing edge cooling design

An improved gas turbine blade is disclosed that utilizes a blade tip shroud with tapered shroud pockets to remove excess weight from the shroud while not compromising shroud bending stresses. Excess shroud weight removed by the tapered pockets reduces overall blade pull while maintaining material necessary to increase shroud stiffness. The resulting rib created between the tapered pockets provides a surface, away from possible areas of stress concentration, for drilling radial cooling holes.

Turbine blade pocket shroud

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Palm Beach Gardens, FL, United States of America

Richard Seleski