Rtx Corporation

Raytheon Technologies Corporation

Andrew V Schwendenmann

Joseph B Phelps

Benstone I Schwartz

Philip Andrew Varney

Alexander R Nelson

Armando Amador

Jacob Peter Mastro

Sean P McCutchan

Todd A Davis

Francis Parnin

Sean P McGee

Reade W James

Ryan William Lureau

Matthew Gomes

Ryan Lureau

Sean P Mcgee

Sean Mccutchan

A bearing assembly is provided that includes a frame, a magnetic bearing stator and a foil bearing. The frame extends axially along and circumferentially about an axis. The frame includes an inner bore and a plurality of channels arranged circumferentially about the axis. The magnetic bearing stator includes a stator body and a plurality of windings. The stator body circumscribes the frame. The stator body includes a plurality of stator protrusions arranged circumferentially about the axis. Each of the stator protrusions projects radially inward into a respective one of the channels. Each of the windings is wrapped around a respective one of the stator protrusions. The foil bearing is disposed within the inner bore and retained to the frame.

Frame for magnetic-foil bearing

A turbine engine is provided that includes a compressor section, a combustor section, a turbine section, a flowpath, a first rotating structure, a second rotating structure and a bearing system. The flowpath extends through the compressor section, the combustor section and the turbine section from an inlet to an exhaust. The combustor section includes a combustor. The first rotating structure includes a first compressor rotor within the compressor section and a first turbine rotor within the turbine section. The second rotating structure includes a second turbine rotor within the turbine section. The first turbine rotor is between the combustor and the second turbine rotor along the flowpath. The bearing system rotatably supports the first rotating structure. The bearing system includes an active magnetic bearing and a foil bearing.

Magnetic-foil bearing supporting turbine engine rotating structure

A bearing system is provided that includes a stationary structure, a rotating structure, a magnetic-foil bearing and a cooling jacket. The rotating structure is rotatable about an axis. The magnetic-foil bearing radially supports the rotating structure within the stationary structure. The magnetic-foil bearing includes a magnetic bearing stator, a magnetic bearing rotor and a foil bearing. The foil bearing is disposed radially between the magnetic bearing stator and the magnetic bearing rotor. The cooling jacket circumscribes and radially engages the magnetic bearing stator. A cooling circuit is configured to flow cooling fluid within the cooling jacket to cool the magnetic bearing stator.

Magnetic-foil bearing with cooling system

An apparatus has: a first member (); a shaft () rotatable relative to the first member about an axis; and a seal system (). The seal system has a seal carrier () having: an axially-extending wall () having an inner diameter (ID) surface (); and a radially-extending wall () having a first surface (). A seal () is carried by the first member and has: an outer diameter (OD) surface (); and a seal face (). A seat () is carried by the shaft and has a seat face () in sliding sealing engagement with the seal face. One or more springs () bias the seal carrier relative to the first member so as to bias the seal face against the seat face. A key () spans an interface between the seal carrier and the seal.

Carbon face seal

An apparatus has: a first member; a shaft rotatable relative to the first member about an axis; and a seal system. The seal system has a seal carrier having: an axially-extending wall having an inner diameter (ID) surface; and a radially-extending wall having a first surface. A seal is carried by the first member and has: an outer diameter (OD) surface; and a seal face. A seat is carried by the shaft and has a seat face in sliding sealing engagement with the seal face. One or more springs bias the seal carrier relative to the first member so as to bias the seal face against the seat face. At least one of the seal carrier inner diameter (ID) surface and seal outer diameter (OD) surface is formed by a coating.

A scupper suitable for a bearing compartment of a gas turbine engine includes a windage blocker in a gutter section upstream of a drain hole, the windage blocker extends from a wall of the gutter section. A method for capturing wept oil in a bearing compartment of a gas turbine engine includes positioning a windage blocker adjacent to a drain hole forming a passage space and increasing a pressure upstream of the windage blocker to generate a vortex downstream of the windage blocker creating an oil re-circulation zone promoting oil drainage into the drain hole.

Windage blocker for oil routing

A face seal assembly includes a seal carrier, a seal element supported by the seal carrier, a rotating seal plate interactive with the seal element to define a face seal, and a seal arrester configured to engage the seal carrier at a predetermined amount of wear of the seal element to stop wear of the seal element.

Face seal carrier arrester

A diffuser for an oil drainback system drain tube includes a flow chamber configured for attachment to an open end of a drain tube, wherein the flow chamber has a side wall and an end wall, and openings in at least the side wall.

Fluid diffusion device for sealed bearing compartment drainback system

A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a compressor section, a combustor section, a turbine section, and at least one rotatable shaft. The engine further includes a seal assembly having a seal plate mounted for rotation with the rotatable shaft, a face seal in contact with the seal plate at a contact area, and a seal carrier supporting the face seal. Further, in normal operating conditions, the seal plate includes a plurality of tabs configured to separate from a remainder of the seal plate in a worn seal condition in which the seal carrier contacts the seal plate.

Gas turbine engine including seal plate with separable tabs

A brush seal may comprise a bristle pack including at least one bristle made of a shape memory alloy. The bristle may be used in a sealing system. The brush seal may be disposed in a seal cavity. The brush seal may further comprise backing plate and a retention structure coupled to the bristle pack. The brush seal may be configured for passive clearance control during operation of a gas-turbine engine.

Brush seal with shape memory alloy

A gas turbine engine component includes a static component with at least one first flow channel. The labyrinth seal rotates relative to the static component. The labyrinth seal is spaced from the static component by a second flow channel. The flow passing between the labyrinth seal and the static component will have a first portion that travels through the at least one first flow channel and a second portion that travels through the second flow channel with the first portion of the flow being reintroduced into the second flow channel to create a flow restriction.

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Hampden, MA, United States of America

Andrew V Schwendenmann