United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Aytheon Technologies Corporation

Mark F Zelesky

Dominic J Mongillo, Jr

Thomas N Slavens

Tracy A Propheter-Hinckley

Joel H Wagner

Alexander Staroselsky

Atul Kohli

Brian D Merry

Edward F Pietraszkiewicz

Steven Bruce Gautschi

Scott D Lewis

Matthew S Gleiner

Bret M Teller

Gabriel L Suciu

Michael G McCaffrey

Sergey Mironets

JinQuan Xu

Thomas J Martin

Ricardo Trindade

Brandon W Spangler

Matthew A Devore

Daniel Bernard Kupratis

James Tilsley Auxier

Brooks E Snyder

Jeffrey S Beattie

Benjamin T Fisk

Paul M Lutjen

San Quach

Raymond C Surace

Carey J Clum

John Joseph Marcin

Timothy M Davis

Stephen Karl Kramer

Dennis M Moura

Tania Bhatia Kashyap

Thomas J Praisner

Xuan Liu

Timothy S Snyder

Bryan P Dube

James D Hill

Michael Winter

James B Hoke

Ioannis Alvanos

Timothy J Jennings

Glenn Levasseur

Michael D Greenberg

Andrew S Aggarwala

Charles W Haldeman

Michael F Blair

Shayan Ahmadian

Christopher J Hanlon

Becky E Rose

David A Krause

Andrew A Consiglio

James F Krenzer

Jeffrey Michael Jacques

Adam P Generale

Dustin Wayne Davis

Theodore W Hall

Kevin L Rugg

Parth Jariwala

Russell Deibel

Wolfgang Balzer

Brandon M Rapp

Benjamin Bellows

Arthur W Utay

Sebastian Martinez

Trevor Rudy

Christopher J Lehane

Gary D Steuber

Christopher T Bergman

Ben S Reinert

Thomas A Auxier

Stanislav Kostka, Jr

William Arthur Sowa

Edwin Otero

Richard Wesley Jackson

Dmitriy A Romanov

Richard Wesley Jackson, Iii

Dave J Hyland

Friedrich O Soechting

Daniel E Kane

Randal G McKinney

Andrew D Burdick

William L Plank

Eleanor D Kaufman

David J Candelori

Samuel R Miller, Jr

Mosheshe Camara-Khary Blake

Jesse R Christophel

Sean D Bradshaw

Paul E Coderre

David J Hyland

Kevin J Klinefelter

Markus W Fritch

Stephen D Doll

Richard L Sykes

Michael A Palumbo

Gaurav M Patel

Atul Kohil

An assembly is provided for a turbine engine. This assembly includes an engine core configured to drive rotation of a propulsor rotor. The engine core includes a first compressor section, a second compressor section, a flowpath, a bleed port, an inner passage and an outer passage. The first compressor section and the second compressor section are arranged axially along an axis. The flowpath extends longitudinally through the first compressor section and the second compressor section. The bleed port fluidly couples the flowpath to the inner passage and the outer passage in parallel. The bleed port is located longitudinally along the flowpath between the first compressor section and the second compressor section. The inner passage is arranged radially between the flowpath and the outer passage.

Bleeding core air from a turbine engine core flowpath

An inlet protector for a vane cooling air passage inlet including a vane including a vane cooling air inlet; an inlet protector fluidly coupled to the vane cooling air inlet, the inlet protector comprising a protector body having a discharge portion and a suction portion, an interior flow passage fluidly coupling the suction portion with the discharge portion; the discharge portion fluidly coupled with the vane cooling air inlet; and a suction inlet formed in the suction portion, wherein the suction inlet is located distally from the vane cooling air inlet.

Inlet protector for vane coupling hole

An assembly is provided for a turbine engine. This assembly includes an engine core extending along an axis. The engine core includes a first compressor section, a second compressor section, a flowpath, a bleed port, an inner passage, an outer passage and a flow diverter. The flowpath extends longitudinally through the first compressor section and the second compressor section. The bleed port fluidly couples the flowpath to the inner passage and the outer passage in parallel. The bleed port is located longitudinally along the flowpath between the first compressor section and the second compressor section. The flow diverter is located at an inlet into the bleed port from the flowpath. The flow diverter is configured to move between a first position and a second position.

Regulating core air bled from a turbine engine core flowpath

Disclosed is a method of reducing play in a vane arc segment. The vane arc segment includes an airfoil piece that defines first and second platforms and a hollow airfoil section that has an internal cavity and that extends between the first and second platforms. The first platform defines a gaspath side, a non-gaspath side, and a radial flange that projects from the non-gaspath side. Support hardware supports the airfoil piece via the radial flange, and a thermal insulation element is located adjacent the radial flange. The method includes performing a light scan of the radial flange to produce a digital three-dimensional model of the radial flange, and then machining the thermal insulation element in accordance with the digital three-dimensional model to provide a low-tolerance fit between the radial flange and the thermal insulation element that limits play between the airfoil piece and the thermal insulation element.

Vane arc segment with thermal insulation element

An airfoil includes an airfoil wall that defines a leading end, a trailing end, and suction and pressure sides that join the leading end and the trailing end. The airfoil wall is formed of a silicon-containing ceramic. A first environmental barrier topcoat is disposed on the suction side of the airfoil wall, and a second, different environmental barrier topcoat is disposed on the pressure side of the airfoil wall. The first topcoat is vaporization-resistant and the second topcoat is resistant to calcium-magnesium-aluminosilicate.

Airfoil having environmental barrier topcoats that vary in composition by location

An aspect includes a system for a gas turbine engine. The system includes one or more bleeds of the gas turbine engine and a control system configured to check one or more activation conditions of a dirt rejection mode in the gas turbine engine. A bleed control schedule of the gas turbine engine is adjusted to extend a time to hold the one or more bleeds of the gas turbine engine partially open at a power setting above a threshold based on the one or more activation conditions. One or more deactivation conditions of the dirt rejection mode in the gas turbine engine are checked. The dirt rejection mode is deactivated to fully close the one or more bleeds based on the one or more deactivation conditions.

Adaptive bleed schedule in a gas turbine engine

A vane arc segment includes an airfoil piece that defines first and second platforms and an airfoil section that extends between the first and second platforms. The first platform defines a gaspath side, a non-gaspath side, and a first platform radial flange that projects from the non-gaspath side. Support hardware supports the airfoil piece via the first platform radial flange. A thermal insulation element is situated adjacent the first platform radial flange. The support hardware supports the airfoil piece through the thermal insulation element.

A gas turbine engine includes a rotor carrying a blade, a ceramic vane adjacent the blade, a seal carried on the rotor adjacent the tip of the ceramic vane, and a cooling passage circuit extending through the blade, the seal, and the ceramic vane. The cooling passage circuit is configured to provide cooling air into the blade, then from the blade into the seal, and then from the seal into the ceramic vane.

Engine with cooling passage circuit extending through blade, seal, and ceramic vane

A method of measuring a gas turbine engine component of a gas turbine engine according to an example of the present disclosure includes, among other things, providing at least one gas turbine engine component including a coating on a substrate, detecting infrared radiation emitted from at least one localized region of the coating at a first wavelength in a first electromagnetic radiation frequency range, detecting infrared radiation emitted from the substrate corresponding to the at least one localized region at a second, different wavelength in a second electromagnetic radiation frequency range that differs from the first electromagnetic radiation frequency range, and determining a heat flux relating to the at least one localized region based upon a comparison of the first wavelength and the second wavelength.

Heat flux measurement system

An airfoil assembly includes an airfoil that has an exterior wall that defines an interior cavity. The exterior wall extends between a leading end and a trailing end and an open inboard end and an open outboard end. The exterior wall is formed of a high temperature-resistant material selected from refractory metal-based alloys, ceramic-based material or combinations thereof. A support frame extends in the interior cavity and protrudes from the interior cavity through at least one of the open inboard end and the open outboard end.

Airfoil assembly formed of high temperature-resistant material

An assembly for a gas turbine engine includes a vane assembly having an inner platform and an airfoil section extending from the inner platform. A first combustor panel extends at least partially along the vane from upstream of the vane, and a blade outer air seal extends at least partially along the vane from downstream of the vane. The first combustor panel and the blade outer air seal define a platform gap located between a leading edge of the airfoil section of the vane and a trailing edge of the airfoil section of the vane.

Gas turbine engine assembly with mid-vane outer platform gap

One exemplary embodiment of this disclosure relates to a gas turbine engine, including a component having a first portion formed using one of a casting and a forging process, and a second portion formed using an additive manufacturing process.

Multiple piece engine component

An aspect includes a dirt mitigation system for a gas turbine engine. The dirt mitigation system includes a plurality of bleeds of the gas turbine engine and a control system configured to determine a particulate ingestion estimate indicative of dirt ingested in the gas turbine engine. The control system is further configured to determine one or more operating parameters of the gas turbine engine and alter a bleed control schedule of the gas turbine engine to purge at least a portion of the dirt ingested in the gas turbine engine through one or more of the bleeds of the gas turbine engine based on the particulate ingestion estimate and the one or more operating parameters.

Dirt mitigation in a gas turbine engine

Growing community of inventors

Bolton, CT, United States of America

Mark F Zelesky