Rolls-royce Corporation

Rolls-royce North American Technologies Inc.

Kevin Sauer

Jack D Petty, Sr

John D Holdcraft

Keith McCormick

Christopher Dwayne DeBruhl

Duane Smith

Lewis Dailey

Russell N Bennett

Caleb Camara

Donald E Pinnick

Bradley A Lemke

Catherine Hidlebaugh

Kathryn M Dimon

David Stapleton

Christopher Debruhl

The disclosure describes a clutch assembly that includes a first clutch element coupled to an input shaft and including a first clutch element friction surface; a second clutch element coupled to an output shaft, and a brake clutch coupled to a stationary component. The second clutch element includes a first friction surface configured to engage the first clutch element friction surface and a second friction surface opposite the first friction surface. The second clutch element is configured to move relative to the first clutch element to engage and disengage the first friction surface and the first clutch element friction surface. The brake clutch includes a brake clutch friction surface configured to engage the second friction surface of the second clutch element when the first clutch element and the second clutch element are disengaged.

Clutch assembly brake

A combustor dome may be formed by way of additive layer manufacturing. The combustor dome may further include a raised outer surface and a recessed outer surface on a hot side of the combustor dome. The recessed outer surfaces may be closer to the cold side than the raised outer surfaces. The combustor dome may include a shadow surface defined between the raised outer surface and recessed outer surface. The shadow surface may define a corresponding cooling outlet in fluid communication with an internal cooling channel defined inside of the combustor dome. The cooling outlet may release air from the internal cooling channel to the hot axial side of the combustor dome.

Combustor dome via additive layer manufacturing

A system may be provided that includes a hot section component of a gas turbine engine. The hot section component includes a dual wall, which includes a first wall and a second wall. The first wall includes multiple impingement cooling holes extending through the first wall. The second wall is positioned adjacent the first wall. The first wall and the second wall together define a cooling passage between the first wall and the second wall. Multiple pockets are in a surface of the second wall. Each of the pockets is positioned opposite a respective one of the impingement cooling holes. Each of the pockets is configured to receive a cooling fluid from the respective one of the impingement cooling holes and direct the cooling fluid into the cooling passage. The cooling passage includes a single cooling passage into which the pockets are configured to direct the cooling fluid.

Impingement cooling dust pocket

Systems and methods are provided for a combustion liner assembly comprising at least a portion of a combustion liner of a combustor, the combustion liner defining a combustion chamber. A chute integral with at least the portion of the combustion liner is provided, the chute having an inlet, an outlet, and a body extending between the inlet and the outlet. The body of the chute extends towards a midline of the combustion chamber. The inlet is located in an outer surface of the combustion liner, and the outlet opens into the combustion chamber. A cooling channel is provided that extends from the outer surface of the combustion liner along the body of the chute.

Gas turbine combustor liner with integral chute made by additive manufacturing process

A combustor liner assembly is provided including an inlet wall, an inner wall, an outer wall, and a plurality of fasteners. The inlet wall has an opening into a combustion chamber. The inner wall is coupled to the inlet wall at a first end of the combustor liner. The inner wall defines a radially inner end of the combustion chamber. The outer wall includes a plurality of segments. The plurality of segments define a radially outer end of the combustion chamber. A first portion of the plurality of fasteners couples each of the plurality of segments to another of the plurality of segments. A second portion of the plurality of fasteners couples at least one of the plurality of segments to the inlet wall at the first end of the combustor liner.

Combustor bolted segmented architecture

A combustion section of a gas turbine engine may include a cassette configured to couple to an annular combustor dome arranged around a flow path for the gas turbine engine. The annular combustor dome may include a dome wall comprising a plurality of inlets configured to receive compressed air for a combustion chamber located downstream, relative to the flow path, from the annular combustor dome. The cassette may include a combustor wall extended away from the dome wall in a downstream direction. The cassette may further include a cowl integral to the combustor wall. At least a portion of the cowl may extend away from the dome wall in an upstream direction relative to the flow path. The cowl may receive compressed air from a diffusor and guide the compressed air to a space upstream from the inlets, relative to the flow path.

Cowl integration to combustor wall

A fuel injection system may include a fuel spray nozzle including a nozzle head and a nozzle stem. The nozzle head may include an air channel and a swirler in fluid communication with the air channel. The nozzle stem may extend into a compressor discharge pressure cavity and convey fuel to the air channel. The air channel may combine air from the swirler with the fuel from the nozzle stem and convey a mixture of fuel and air to a combustor. The fuel injection system may further include a scoop. The scoop may be coupled to the fuel spray nozzle. The scoop may receive air that flows into the compressor discharge pressure cavity from a diffusor. An outer surface of the fuel spray nozzle and an inner surface of the scoop define a duct in fluid communication with the swirler. The swirler may receive air from the duct.

Ram pressure recovery fuel nozzle with a scoop

An example system may include a computing device and an additive manufacturing tool. The computing device may define a digital representation of an inclined channel at least partially within a component, including an angle &#x3b8; based on a formula &#x3b8;=2 tan[tan(&#x3bb;/2)/sin(&#x3b1;)]. The inclined channel may define a longitudinal axis inclined at the angle &#x3b1; relative to a build direction, and may include a gabled roof configured to collapse into an arched roof. The angle &#x3bb; is a predetermined interior angle of the gabled roof measured in a plane substantially parallel to the build direction. The angle &#x3b8; is an interior angle of the gabled roof in a plane substantially normal to the inclined longitudinal axis. The computing device may control, based on the digital representation, the additive manufacturing tool to deposit a material along the build direction to fabricate the component including the inclined channel.

Additively manufactured components including channels

Crossover tubes for use with cans of a turbine engine. The crossover tubes include an outer member, an inner member that is adapted to move collinearly with the outer member. The crossover tubes also include a pair of flanges and a biasing member positioned between the flanges.

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Plainfield, IN, United States of America

Kevin Sauer