Rolls-Royce Corporation

Rolls-Royce North American Technologies Inc.

John D Holdcraft

Jack D Petty, Sr

Kevin Sauer

James Carl Loebig

Christopher Dwayne DeBruhl

Duane Smith

David Stapleton

Christopher D Debruhl

Sr Jack D Petty

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 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

A gas turbine engine includes a combustor having a combustor tile assembly with improved cooling air flow channels and enhanced cooling efficiency. A method of manufacturing same is provided which increases production capabilities and the geometric configurations of the exit ports which in turn improve the hot side operating temperature of the tiles in the combustion chamber.

Combustor tile

A combustion chamber includes an inner wall, an outer wall surrounding the inner wall, and a flow passage between the inner wall and outer wall that permits forward flow and restricts reverse flow. The inner wall has a plurality of effusion holes in fluid communication with the inside of the combustion chamber. The outer wall has a plurality of cooling side holes in fluid communication with a cooling source. The inner wall and the outer wall define a flow passage therebetween that fluidly connects one or more of the cooling side holes with one or more of the effusion holes. The flow passage has a geometric configuration to permit forward flow of gases through the flow passage from the cooling source to the inside of the combustion chamber and to restrict reverse flow of gases through the flow passage from the inside of the combustion chamber to the cooling source. The permitted flow rate is greater than the restricted flow rate.

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Carmel, IN, United States of America

John D Holdcraft