United Technologies Corporation

Raytheon Technologies Corporation

Alstom Technology Limited

General Electric Technology Gmbh

Ansaldo Energia Switzerland Ag

Brian K Richardson

Peter Stuttaford

Sumit Soni

Kevin B Powell

Russell B Hanson

Eric J Ward

Nicolas Demougeot

Khalid Oumejjoud

Alfredo Cires

John Henriquez

Daniel J Sullivan

Marc Paskin

Chiluwata Lungu

Justin Bosnoian

John Thomas Cutright

Jeffrey D Dickens

Nikki McMullen

Richard Parker

Luiz Claudio Fernandes

David Schlamp

Brandon Hill

A system for an engine defined about an axial centerline includes an inner case that includes a bushing, a duct case radially outward of the inner case with respect to the axial centerline, and a seal located on the duct case. The system further includes a borescope plug assembly that traverses the seal and the bushing in mounting to the inner case. The borescope plug assembly includes a spring, a housing sleeve, and a washer sleeve at least partially nested within the housing sleeve. The spring is isolated from the seal by the housing sleeve and the washer sleeve such that the spring is contact-free with respect to the seal.

Borescope plug assembly

The present invention discloses a novel apparatus and way for directing a supply of compressed air into a fuel nozzle assembly for mixing with a fuel source. The apparatus comprises a fuel nozzle assembly having a plurality of coaxial tubes and radially-extending swirler vanes for directing a supply of fuel to a mixing tube. Compressed air is directed to flow in a primarily axial direction by passing through a hemispherically-shaped dome portion at an air inlet region of the fuel nozzle assembly. The hemispherically-shaped dome includes a plurality of openings for directing air into the fuel nozzle assembly in a direction having a radial and axial component.

Fuel nozzle with hemispherical dome air inlet

A system and method for improving the cooling to a portion of a combustion liner of a gas turbine combustor is disclosed. The combustion liner is cooled by supplying air through a plurality of cooling holes arranged in axially spaced rows in an upper and lower portion of the liner. The cooling holes are spaced accordingly so as to direct additional cooling flow to an area of the combustion liner not receiving sufficient flow due to maldistributions of air from the compressor discharge.

Combustion liner with bias effusion cooling

A gas turbine combustion liner having a novel and improved system for receiving a peripheral device through a floating collar is disclosed. The retaining collar assembly provides planar movement for receiving the peripheral device while preventing the floating collar from rotational movement through an anti-rotation tab on the collar and a collar cap, resulting in reduced wear to the peripheral device. The collar cap can include different configurations for reducing any vibratory effects caused by an oncoming airflow directly contacting the floating collar.

Retaining collar for a gas turbine combustion liner

A mounting arrangement for a gas turbine engine blade having a root employs a lightweight, simple and economical leaf spring spacer which biases the blade root in a radially outward direction to minimize unwanted movement of the root within a conforming slot in a blade hub under conditions such as windmilling when centrifugal force alone is inadequate to tightly seal the root within the slot.

Gas turbine engine blade mounting arrangement

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Jupiter, FL, United States of America

Brian K Richardson