United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Jorn Axel Glahn

Gabriel L Suciu

Frederick M Schwarz

Brian D Merry

Christopher Marc Dye

Peter M Munsell

Clifton J Crawley, Jr

William K Ackermann

Philip S Stripinis

Denman H James

Matthew R Feulner

John P Virtue

Matthew D Teicholz

Ethan K Stearns

Jason B Solomonides

Brian M Fentress

Daniel J McKaveney

Jeffrey W Sutliff

William H Greene, Jr

Kenneth J White

Philip D Hoover

Victor M Pinedo

William G Sheridan

Gary D Roberge

Nathan A Snape

Charles E Lents

Steven B Johnson

Andrew P Berryann

Gregory M Dooley

Collin P Fitzgerald

Todd A Davis

Francis Parnin

Armando Amador

Allan R Penda

Amy Rose Grace

Brian F Hilbert

Timothy J Castaldo

Cheng-Zhang Wang

Anthony Spagnoletti

Justin W Heiss

Matthew J Howlett

Robert Newman

David F Cloud

Taryn Narrow

Charles Joseph Banas

Sin Chien Siw

Michelle Diana Stearns

Matthew G Dixon

Christoper M Dye

Frederick W Schwarz

Anthony Sr Demitraszek

A hydraulically supported seal including a seal plate operatively coupled with a seal, the seal being supported by a seal carrier within a housing; a piston having a piston shaft, the piston being in operative communication with the seal opposite the seal plate, the piston shaft being disposed through the housing through a piston receiver formed in the housing; a cylinder operatively coupled to the piston opposite the seal; and wherein the piston is hydraulically biased by a hydraulic fluid within the cylinder.

Hydraulically supported face seal

An assembly is provided for a turbine engine. This assembly includes a rotating structure rotatable about an axis, a stationary structure and a bearing. The stationary structure forms a bearing compartment, a buffer cavity, a low pressure cavity and a high pressure cavity with the rotating structure. The buffer cavity surrounds the bearing compartment. The low pressure cavity surrounds the buffer cavity. The high pressure cavity surrounds the low pressure cavity. The bearing is within the bearing compartment. The bearing rotatably couples the rotating structure to the stationary structure.

Buffer air system for a bearing compartment

A gas turbine engine includes a fan rotor, a compressor section, a combustor section, and a turbine section. The turbine section is positioned downstream of the combustor section. A fan drive turbine in the turbine section, and a shaft connects the fan drive turbine to the fan rotor. An inlet duct is connected to a cooling air source and connected to a cooling compressor downstream of the fan drive turbine. The cooling compressor is connected to an air source, and connected to a turning duct for passing compressed air in an upstream direction through the shaft. A method is also disclosed.

Thermal management of a gas turbine engine shaft

A method of operation is provided during which buffer air flows into a buffer cavity in a turbine engine. The buffer cavity surrounds a bearing compartment in the turbine engine. Leakage air flows across a buffer seal device in the turbine engine. The buffer air and the leakage air are combined to provide combined air. The combined air is vented to a pressure sink such that: a pressure of the buffer air within the buffer cavity is maintained at or below a maximum buffer air threshold during operation of the turbine engine; and a flowrate of the leakage air across the buffer seal device is maintained at or above a minimum leakage air threshold during the operation of the turbine engine.

Buffer air method and system for a bearing compartment

A hydrostatic seal configured to be disposed between relatively rotatable components. The hydrostatic seal includes a seal carrier. The hydrostatic seal also includes a beam extending axially from a forward end to an aft end, the beam cantilevered to the seal carrier at one of the forward end and the aft end, the beam free at the other end. The hydrostatic seal further includes a bellows seal operatively coupled to the seal carrier and in contact with the beam.

Bellows secondary seal for cantilevered hydrostatic advanced low leakage seal

A rotating seal rotatable about a rotational axis is provided. The rotating seal includes a body having a first surface disposable to face the rotational axis and a second surface disposable to contact with a stationary element. The body defines a cooling channel including one or more entrance channels respectively extending from the first surface, one or more exit channels and a plenum. The plenum extends circumferentially through the body and has a hot side adjacent to the second surface. The plenum is fluidly interposed between the one or more entrance channels and the one or more exit channels whereby fluid exiting the one or more entrance channels and entering the plenum impinges against the hot side.

Impingement cooled rotating seal

This disclosure relates to a buffer system for a gas turbine engine. An exemplary gas turbine engine includes, among other features, a buffer manifold in an intershaft region. The buffer manifold is configured to direct a flow of air between a first air seal and a first oil seal, and to direct another flow of air between a second air seal and a second oil seal.

Buffer system for gas turbine engine

According to an aspect, a method includes predicting, by a processor, a projected oil-wetted metal temperature in a lubrication system of a gas turbine engine at shutdown based on one or more thermal models prior to shutdown of the gas turbine engine. The processor determines a coking index based on the projected oil-wetted metal temperature and a coking limit threshold associated with one or more engine components. An oil coking mitigation action is triggered as a shutdown management event of the gas turbine engine based on the coking index.

Oil coking mitigation in a gas turbine engine

A gas turbine engine includes a first tap connected to a compressor section to deliver air at a first pressure. A heat exchanger is downstream of the first tap. A cooling air valve selectively blocks flow of cooling air across the heat exchanger. A cooling compressor is downstream of the heat exchanger and pressurizes the air from the first tap to a greater second pressure. A shut off valve selectively stops flow of the air between the heat exchanger and the cooling compressor. A controller controls the cooling air valve, the shut off valve, and the cooling compressor such that the flow of the air is stopped between the heat exchanger and the cooling compressor only after the controller has stopped the cooling compressor. A monitoring system communicates with the controller and includes a pressure sensor and a temperature sensor downstream of the cooling compressor.

Failure mitigation and failure detection of intercooled cooling air systems

A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a shaft and first and second bearing structures that support the shaft. Each of the first bearing structure and the second bearing structure includes a bearing compartment that contains a lubricant and a seal that contains the lubricant within the bearing compartments. A buffer system is configured to pressurize the seals to prevent the lubricant from escaping the bearing compartments. The buffer system includes a first circuit configured to supply a first buffer supply air to the first bearing structure, a second circuit configured to supply a second buffer supply air to the second bearing structure, and a controller configured to select between at least two bleed air supplies to communicate the first buffer supply air and the second buffer supply air.

Multi-circuit buffer system for a gas turbine engine

A system for starting a gas turbine engine of an aircraft is provided. The system includes a pneumatic starter motor, a discrete starter valve switchable between an on-state and an off-state, and a controller operable to perform a starting sequence for the gas turbine engine. The starting sequence includes alternating on and off commands to an electromechanical device coupled to the discrete starter valve to achieve a partially open position of the discrete starter valve to control a flow from a starter air supply to the pneumatic starter motor to drive rotation of a starting spool of the gas turbine engine below an engine idle speed, where the controller modulates a duty cycle of the discrete starter valve via pulse width modulation.

Modified start sequence of a gas turbine engine

A gas turbine engine according to an example of the present disclosure includes a shaft rotatable about an axis, a bearing disposed about the shaft and within a bearing compartment, and a seal assembly positioned to seal the bearing compartment. The seal assembly includes a fixed seal and a seal runner rotatable with the shaft. The first axial face and a second axial face axially opposite the first axial face with respect to the axis. The first axial face includes a first surface rotatable against the seal, and the second axial face includes a trough portion. A second surface is angled relative to a radial baseline plane defined perpendicular to the axis, and a dam between the trough portion and the second surface. An oil source is positioned to provide oil into the trough portion.

Gas turbine engine seal assemblies

A seal seat includes an annular body and an extension. The annular body is disposed about a centerline axis. The extension is connected to and extends radially outward from the annular body. The extension includes first, second, and third portions. The first portion is connected to the annular body and is defined by axially opposed upstream and downstream wall faces. The first portion includes a fin connected to the upstream wall face. The second portion is connected to the first portion and extends substantially parallel to the annular body. The third portion is connected to the second portion and extends substantially parallel to the second portion.

Carbon face seal seat thin wall design

A system for controlling a start sequence of a gas turbine engine includes an electronic engine control system, a thermal model, memory, a model for determining a time period (t), and a controller. The thermal model synthesizes a heat state of the gas turbine engine. The memory records the current heat state at shutdown and a shutdown time of the gas turbine engine. The model for determining the time period is for motoring the gas turbine engine at a predetermined speed Nthat is less than a speed to start the gas turbine engine, where tis a function of the heat state recorded at engine shutdown and an elapsed time of an engine start request relative to a previous shutdown time. The controller modulates a starter valve to maintain the gas turbine engine within a predetermined speed range of Nto Nfor homogenizing engine temperatures.

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Manchester, CT, United States of America

Jorn Axel Glahn