United Technologies Corporation

Raytheon Technologies Corporation

Meggan Harris

James P Allore

Marc J Muldoon

Jorge I Farah

Robert T Brooks

Tor W Sherwood

Curtis C Cowan

Seth A Max

Christopher Drake

Stephen A Paul

Steven Wayne Burd

Michael Joseph Murphy

John T Ols

Alexander W Williams

Michael J Giering

Gregory S Hagen

Christopher Treat

Timothy Dale

Ozgur Erdinc

Paul Attridge

Alexander I Khibnik

Jaime A Arbona

Yiqing Lin

Stephanie Ernst

William G Askey

Steven J Laporte

Sheree R Swenson-Dodge

Stephanie Milbury

Curtis Cowan

A combustor assembly for a gas turbine engine includes a TOBI module that includes a TOBI housing. The TOBI housing has a slot. A vane includes a dovetail removably received within the slot. The TOBI housing includes an axially extending TOBI nozzle array. The TOBI housing includes a plenum. A cooling passage fluidly connects the plenum to the vane. The TOBI housing includes passages configured to provide cooling fluid to the vane. The TOBI housing includes a first passageway further connecting the TOBI nozzle to the plenum.

Gas turbine engine with dove-tailed TOBI vane

A fuel fitting assembly includes a monolithic fuel fitting formed by additive manufacturing. The fitting includes a first end, a second end, a conduit extending axially through the fitting from the first end to the second end, and a first sealing element. The first end is to be connected to a fuel line. The second end is to be connected to a device requiring or providing fuel. The first sealing element includes a sealing seat circumferentially surrounding the conduit at the second end of the fitting. The fuel fitting is integrally formed as a stack of layers of material.

Fuel fitting

A cooling arrangement for a turbine engine includes a cooling source and first and second structures. A ceramic-based composite cooling tube fluidly provides a fluid connection between the first and second structures. The cooling tube is configured to transfer a cooling fluid from the cooling source to the second structure.

Gas turbine engine cooling fluid composite tube

A disclosed lock washer includes a first opening spaced apart from a second opening for receiving fasteners and preventing rotation. A first set of tabs is associated with the first opening and a second set of tabs is associated with the second opening. Each of the first and second set of tabs are bendable to a lock position preventing rotation of a fastener received within a corresponding one of the first opening and the second opening.

Self-anti-rotating dual lock washer

A swirler for a combustor of a gas turbine engine includes a swirler outer body with a swirler threaded section defined around a swirler central longitudinal axis. A bulkhead support shell for a combustor of a gas turbine engine includes a swirler boss with a boss threaded section defined around a swirler central longitudinal axis. A combustor of a gas turbine engine includes a bulkhead support shell with a swirler boss. The combustor also includes a swirler mountable to the swirler boss at a threaded interface defined around a swirler central longitudinal axis.

Swirler mount interface for gas turbine engine combustor

A divergent flap includes a hinge joint to connect the divergent flap to a convergent flap, a plow structure, a first wall, a second wall, and two side walls. The plow structure is at a plow end of the flap opposite the hinge joint. The first wall and the second wall each extend from the hinge joint to the plow end. The second wall is spaced apart from the first wall by the two side walls to form at least one cooling channel extending between the hinge joint and the plow end. The divergent flap is integrally formed in layer-by-layer fashion as a single piece.

Divergent flap

A combustor assembly for a gas turbine engine includes a TOBI module which includes a TOBI housing. The TOBI housing has a slot. A vane including a dovetail is removably received within the slot.

A structural panel for use with a gas turbine engine includes a first exterior wall, a second exterior wall, and interior walls. The first exterior wall includes a first exterior surface and a first interior surface parallel to the first exterior surface. The second exterior wall includes a second exterior surface and a second interior surface parallel to the second exterior surface. The interior walls extend from the first interior surface to the second interior surface. The interior walls are arranged to form a pattern of hexagonal cells. The pattern of hexagonal cells includes cell groups having a variation in structural strength such that at least one of the cell groups has a structural strength that is not the same as the remaining cell groups.

Structural honeycomb panel

A swirler is provided for a gas turbine engine. The swirler includes a swirler body with a threaded section and a multiple of circumferentially arranged tabs operable to flex radially outward. The multiple of circumferentially arranged tabs are radially displaced from the threaded section.

A unitary one-piece hub has first and second rings and a midsection arranged between the first and second rings. The midsection includes a plurality of windows configured to receive a plurality of cross members. The windows include a lip configured to surround the cross members. A gas turbine engine and a method of providing a hub for a gas turbine engine are also disclosed.

Gas turbine hub

A turbine engine includes multiple tierod supports. Each of the tierod supports is connected to an inner frame case of the turbine engine via multiple fasteners and at least one self anti-rotating bushing component.

Turbine engine support assembly including self anti-rotating bushing

A variable outer air seal support system according to an exemplary aspect of the present disclosure includes, among other things, a case having a plurality of slots, and an extension of a variable outer air seal segment. The extension provides at least one extension aperture. A connector pin is configured to move within the slot to move the variable outer air seal segment from a first position to a second position. The variable outer air seal segment overlaps a circumferentially adjacent variable outer air seal segment more in the first position than in the second position.

Variable outer air seal support

An example turbomachine system includes a first variable outer air seal including at least one channel. The first variable outer air seal configured to selectively communicate a fluid in response to movement of a second variable outer air seal relative to the first variable outer air seal. An example fluid control method includes selectively covering a channel inlet using a variable outer air seal to control flow through the channel.

Variable outer air seal fluid control

A system for a turbofan has a variable outer air seal, an actuator coupled to the variable outer air seal, a sensor positioned inside the turbofan for sensing an engine parameter, and a flight controller connected to the turbofan for receiving the parameter from the sensor. The flight controller directs the actuator to regulate the position of the actuator based on the flight condition resulting form the received parameter.

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Colchester, CT, United States of America

Meggan Harris