United Technologies Corporation

Pratt-Whitney Canada Corp

Rtx Corporation

Raytheon Technologies Corporation

Roger Gates

Tracy A Propheter-Hinckley

Paul M Lutjen

Gregory E Reinhardt

James Tilsley Auxier

Scott Daniel Virkler

Susan M Tholen

Franco Di Paola

Michael F Blair

Daniel Benjamin

David Richard Griffin

Richard W Hoff

Ian Alexander MacFarlane

John H Mosley

David Frederick Glasspoole

Richard H Page

Charles C Wu

James P Chrisikos

Brian C Lund

John J O'Connor

Franco DiPaola

David Glasspoole

Brian C Lung

A fastener assembly for affixing two flanges to a casing of a gas turbine engine is provided. The fastener assembly includes a bolt, a fastener, and first and second spacers. The bolt has a supporting shaft extending from a head and a thread portion. The supporting shaft has a diameter larger than a diameter of the thread portion. The fastener is configured to releasably mate with the thread portion. The first spacer surrounds a portion of the thread portion and is disposed between the fastener and a first flange. The second spacer surrounds the supporting shaft and is disposed between a second flange and the bolt head. The supporting shaft engages holes in the first flange, the casing, and the second flange. At least one of the first and second spacers absorbs a portion of a tensile load acting on the bolt.

Fastener assembly for a gas turbine engine

A chamfered stator vane rail is provided. The chamfered stator vane rail may comprise a forward rail and an aft rail axially opposite the forward rail. The aft rail may comprise a leading edge and a trailing edge located axially opposite and aft of the leading edge. The aft rail may comprise a chamfered edge on a radially outer surface. The chamfered edge may be oriented at an angle relative to an axis.

Chamfered stator vane rail

A cooling system for a gas turbine engine turbine section includes a rotor supporting a blade having a cooling passage. A disc is secured relative to the rotor and it forms a cavity between the rotor and the disc. A bleed air source is in fluid communication with the cavity. An impeller is arranged in the cavity. The impeller is configured to increase a fluid pressure within the cavity to drive bleed air from the bleed air source and thereby provide a pressurized cooling fluid to the cooling passage.

Gas turbine engine turbine impeller pressurization

A gas turbine engine has a plurality of compressor rotors, as well as a plurality of turbine rotors. A tie shaft of the engine is constrained to rotate with the compressor and turbine rotors during normal operating conditions. Further, an upstream hub is in threaded engagement with the tie shaft. The threads of the upstream hub are handed in a first manner when viewed from an upstream location. A downstream abutment member is positioned downstream of the turbine rotors and is also in threaded engagement with the tie shaft. Threads of the downstream abutment member are handed in the first manner when viewed from a downstream location. Accordingly, the compressor and turbine sections of the engine are reliably held together, and the tie shaft is substantially prevented from unwinding.

Assembly and method preventing tie shaft unwinding

An air seal assembly for a gas turbine engine includes a first cover plate with a radially extending knife edge seal defined about and axis of rotation. The first cover plate is mountable to a first rotor disk for rotation therewith, the first radially extending knife edge seal interfaces with a vane structure. A second cover plate with a second radially extending knife edge seal defined about the axis of rotation, the second cover plate mountable to the second rotor disk for rotation therewith. The second radially extending knife edge seal interfaces with the vane structure.

Cover plate with interstage seal for a gas turbine engine

A blade outer air seal (BOAS) support segment for supporting at least one BOAS segment of a static turbine shroud of a gas turbine engine, includes a radially and outwardly extending front leg for engagement with an outer case of the engine. The BOAS support segment further includes a pair of radially elongated rear prongs circumferentially spaced apart from each other and radially outwardly abutting the outer case.

Blade outer air seal support

A blade outer air seal (BOAS) casting core has first and second end portions and a plurality of legs. Of these legs, first legs each have: a proximal end joining the first end portion; a main body portion; and a free distal portion. Second legs each have: a proximal end joining the second end portion; a main body portion; and a free distal portion.

Blade outer air seal cores and manufacture methods

A cap for sealing an outer end of an oil filler tube of an engine where the oil filler tube has an inner end with ball valve having a float ball and mating valve seat for impeding any reverse flow of oil during engine operation. The cap includes a sealable plug mating the tube outer end; a rod extending from the plug toward the inner end of the tube; and a valve opening device mounted to the rod for dislodging the float ball from the valve seat.

Oil filter cap with ball valve anti-sticking device

Growing community of inventors

West Hartford, CT, United States of America

Roger Gates