Raytheon Technologies Corporation

Rtx Corporation

United Technologies Corporation

David C Kiely

Todd A Davis

Russell B Witlicki

Christopher M Valva

Andrew Newton

Armando Amador

Nasr A Shuaib

Julie J Marquis

Brian Stahl

Christopher T Koetsch

Michael Voytovich

Jeffrey R Rigali

Ryan P Susca

Russel B Witlicki

Julie Marquis

A retrofit gas turbine engine includes a compressor, a combustor and a turbine. A tie shaft is connected to rotate by the turbine, and provide rotational drive into a gearbox. At least one fuel pump is connected to be driven by the gearbox. The at least one fuel pump delivers fuel downstream toward the combustor, and also has a return line. An added accessory turbine is positioned on the return line, and drives an added accessory which has been retrofit added to an existing gas turbine engine. A method is also disclosed.

Gas turbine engine with controlled return of fuel to power accessories and retrofitting method

A fluid system is provided that includes a first actuator, a second actuator and a valve system. The valve system includes a first control valve, a second control valve and a transfer valve. During a first mode of operation, the transfer valve is configured to fluidly couple the first control valve to the first actuator and fluidly couple the second control valve to the second actuator, and the transfer valve is also configured to fluidly decouple the first control valve from the second actuator and fluidly decouple the second control valve from the first actuator. During a second mode of operation, the transfer valve is configured to fluidly couple the first control valve to the first actuator and the second actuator, and the transfer valve is also configured to fluidly decouple the second control valve from the first actuator and the second actuator.

Fluid system with multi-mode transfer valve

A gas turbine engine component includes an inner support structure surrounding an engine center axis and fixed to an engine static structure, an outer support structure spaced radially outward of the inner support structure, and a curved beam comprised of a plurality of curved beam spring segments that are positioned adjacent to each other to form a ring. The inner and outer support structures are coupled together around the curved beam to enclose the curved beam therebetween and form an assembly. A bearing is spaced radially inward of the assembly.

Axially rigid curved beam with squeeze damper

A gas turbine engine component includes a bearing configured to support a shaft for rotation about an axis, wherein the bearing includes an outer race and an inner race, and a bearing housing spaced radially outwardly of the outer race. A curved beam centering spring is positioned between the outer race and the bearing housing. A cylindrical wall is radially outward of the bearing housing and engages the outer race and the bearing housing.

Curved beam centering spring for a thrust bearing

A gas turbine engine component includes a ring comprising a single-piece component having an outer peripheral surface and an inner peripheral surface that surrounds an engine center axis, a plurality of outer diameter pedestals formed in the outer peripheral surface and circumferentially spaced apart from each other, and a plurality of inner diameter pedestals formed in the inner peripheral surface and circumferentially spaced apart from each other. A plurality of recesses are formed in the outer peripheral surface and are circumferentially spaced apart from each other.

Unified curved beam bearing damper

A gas turbine engine includes a cover, a support, and a sealing member. The cover has a cover housing and a cover arm extending from the cover housing between a first arm end connected to the cover housing and a second arm end having a cover end surface. The support has a support body, a first support arm extending between a first support arm first end connected to the support body and a first support arm second end. The cover arm extends into the first support arm. The sealing member at least partially extends across a gap defined between the cover end surface and the first support arm.

Gas turbine engine having a sealing member

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Manchester, CT, United States of America

David C Kiely