United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Paul W Duesler

Frederick M Schwarz

Brian D Merry

Michael Joseph Murphy

Allan R Penda

Curtis C Cowan

Matthew D Nicolson

Constantino V Loffredo

Richard J Pawlaczyk

C Vincent Loffredo

William S Pratt

Joseph W Bridges, Jr

Edward J Hovan

Robert F Brodell

Michael R Thomas

Douglas A Welch

Marc Samit

Richard W Rosborough

Paul Filewich

Joseph N Cerino

Michael L Vukovinsky

Wendell R Loso

Frank B Manning

Patrick D Markham

Steven T Selfors

Harold T Prosser, Jr

Andrew Yanaros

Christopher W Jones

Joseph W Bridges Jr

Frederick M Schawrz

Richard Rosborough

Michael Vukovinsky

A heat exchanger (HEX) for cooling air in a gas turbine engine is provided. An adjustable damper is provided. The adjustable damper may be for damping a movement of the HEX relative to the gas turbine engine. An adjustable damper may comprise: a first tube; a second tube located at least partially within the first tube; a housing coupled to the second tube; a moveable member, the moveable member comprising a contacting surface in contact with the second tube; an adjusting member adjustably coupled to the housing; and a spring member located between the moveable member and the adjusting member, the spring member configured to at least one of compress or decompress in response to adjusting member moving relative to the housing.

Heat exchanger for cooled cooling air with adjustable damper

A heat exchanger (HEX) for cooling air in a gas turbine engine is provided. The HEX may comprise a central manifold comprising an inlet portion, a first outlet portion, and a second outlet portion. The HEX may further comprise a plurality of tubes coupled to the central manifold, the plurality of tubes comprising at least a first tube, a second tube, a third tube, and a fourth tube, a shroud at least partially encasing said plurality of tubes, and a cooling air flow path defined by at least one of the shroud, the plurality of tubes, and an outer surface of the central manifold, wherein the cooling air flow path is orthogonal to said plurality of tubes.

Folded heat exchanger for cooled cooling air

A heat exchanger array includes a first row of heat exchangers, a second row of heat exchangers, and side curtains. The first row heat exchangers are spaced apart to define first gaps. The second row heat exchangers are spaced apart to define second gaps and are positioned downstream of and staggered from the first row heat exchangers such that the second row heat exchangers are aligned with the first gaps and the first row heat exchangers are aligned with the second gaps. Each side curtain is in close proximity to a first row heat exchanger and a second row heat exchanger. The side curtains define a neck region upstream of and aligned with each first row heat exchanger and each second row heat exchanger. Each neck region has a neck area that is less than a frontal area of the heat exchanger with which it is aligned.

Staggered heat exchanger array with side curtains

A gas turbine engine may include a rotor overspeed protection (ROP) assembly. The ROP assembly may include an annular blade outer air seal (BOAS) assembly including a ROP segment. The ROP assembly may include a stator vane coupled with the BOAS assembly/. The stator vane may include a stator flange disposed about a forward edge portion of the stator vane. The ROP segment may include a ROP flange extending in an axially aft direction from a main body of the ROP segment toward the stator vane, wherein the ROP flange is disposed radially inward of the stator flange.

Rotor overspeed protection assembly

An assembly is provided for a turbine engine with an axial centerline. This assembly includes a turbine engine structure and a valve assembly. The turbine engine structure includes an outer duct wall, an inner duct wall, a first flow path and a second flow path. The inner duct wall is radially inward of the outer duct wall. The first flow path is radially inward of the inner duct wall. The second flow path is radially outward of the inner duct wall and is radially inward of the outer duct wall. The valve assembly includes a valve element and a valve actuator. The valve element is configured to regulate flow of fluid between the first flow path and the second flow path. The valve actuator is configured to move the valve element. The valve actuator is positioned entirely radially outward of the outer duct wall.

Externally replaceable valve assembly for a turbine engine

Aspects of the disclosure are directed to a heat exchanger comprising: a first plurality of channels configured to convey a first medium at a first set of temperatures along a first span of the first plurality of channels, the first set of temperatures including a first inlet temperature and a first outlet temperature, a second plurality of channels configured to convey a second medium at a second set of temperatures along a second span of the second plurality of channels, the second set of temperatures being at least partially different from the first set of temperatures and including a second inlet temperature and a second outlet temperature, and a core region where the first plurality of channels and the second plurality of channels are co-mingled with respect to one another.

Heat exchanger for cooling medium temperature reduction

A gas turbine engine has a compressor section including a lower pressure compressor and a higher pressure compressor, and a turbine section. A core engine housing surrounds the compressor section and the turbine section. An outer intermediate housing wall defines an internal chamber between the core housing and the outer intermediate housing. A fan rotor and a fan casing surround the fan rotor to define a bypass duct between the fan case and the outer intermediate housing. A heat exchanger is mounted in the internal chamber and receives high pressure air for cooling the high pressure air and delivering the high pressure air into the core engine housing to be utilized as cooling air for a component. Air from the lower pressure compressor is utilized to cool the higher pressure air in the heat exchanger.

Heat exchanger for gas turbine engine mounted in intermediate case

A cam isolation system for a gas turbine engine compressor actuator includes a torque tube. The system also includes a cam bracket operatively coupled to an engine case structure, the cam bracket defining a slot. The system further includes an actuator bracket operatively coupled to the torque tube at a first end of the actuator bracket, the actuator bracket having a pin disposed within the slot of the cam bracket.

Cam isolation system for gas turbine engine compressor section

An exemplary gas turbine engine includes a fan bypass duct defined between a fan nacelle and core cowl of an engine core. The engine core includes a cooled cooling air system configured to receive cooling air from a primary flowpath bleed at a diffuser within the engine core and configured to provide cooled cooling air to at least one component within the engine core. The cooled cooling air system including an air-air heat exchanger.

Cooled cooling air system for a turbofan engine

Heat exchanger array

A heat exchanger for use in a gas turbine engine has a central body including an inlet manifold and at least one tube providing an outlet manifold, and a plurality of tubes communicating holes in an outer periphery of the inlet manifold to holes in an outer periphery of the outlet manifold, and passages for cooling air to pass across the tubes. A gas turbine engine is also disclosed.

Heat exchanger with heat resistant center body

A gas turbine engine has a core engine with a compressor section and a turbine section. The compressor section includes a low pressure compressor and a high pressure compressor. A cooling air system taps compressed air and passes the compressed air through a heat exchanger. Cooling air passes over the heat exchanger to cool the compressed air, which is returned to the core engine to provide a cooling function. The heat exchanger is mounted through a flexible mount allowing movement between a static structure and the heat exchanger.

Heat exchanger for gas turbine engine with support damper mounting

A heat exchanger (HEX) for cooling air in a gas turbine engine is provided. An adjustable damper is provided. The adjustable damper may be for damping a movement of the HEX relative to the gas turbing engine. An adjustable damper may comprise: a first tube; a second tube located at least partially within the first tube; a housing coupled to the second tube; a moveable member, the moveable member comprising a contacting surface in contact with the second tube; an adjusting member adjustably coupled to the housing; and a spring member located between the moveable member and the adjusting member, the spring member configured to at least one of compress or decompress in response to adjusting member moving relative to the housing.

A heat exchanger (HEX) arrangement for cooling air in a gas turbine engine is provided. The HEX arrangement may include a heat exchanger coupled to a plurality of ducts comprising a hot-side inlet duct and a hot-side outlet duct. The hot-side outlet duct may be in fluid communication with a compressor section of the gas turbine engine and in mechanical communication with a diffuser case. The HEX arrangement may further include a plurality of supporting links coupled between the heat exchanger and the gas turbine engine for securing the heat exchanger relative to the gas turbine engine. The supporting links may comprise a statically determined system. A spring rate ratio of between 1% and 30% may exist between the plurality of ducts and the plurality of supporting links.

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Manchester, CT, United States of America

Paul W Duesler