Rolls-royce Corporation

Rolls-royce Deutschland Ltd & Co. Kg

Anthony Pidcock

Desmond Close

Michael Paul Spooner

Paul Ian Chandler

William C Kwan

Miklos Gerendas

George Pask

Geoffrey M Dailey

William B Wright

John S Richardson

Volker Herzog

Simon Cross

Lance P Bell

Peter Fry

Andrew P Wray

Stephen M Cooper

Neil Gater

A lean burn combustor includes a first wall and a second wall spaced from the first annular wall. Angularly spaced axially extending coolant collection manifolds collect coolant from the space between the first and second walls. A plurality of rows of axially spaced apertures extend through the first wall to supply coolant into the space between the first and second walls and one row of aperture is positioned between each pair of adjacent manifolds. The second wall extends the full length of the combustor. The second wall has a circumferentially extending wall extending towards and contacting the first wall and the wall is spaced from the downstream end of the second wall. An annular supply manifold supplies coolant to the space between the first and second walls downstream of the circumferentially extending wall and the manifolds supply coolant to the manifold. A film of coolant is discharged from the space.

Combustion chamber having axially extending and annular coolant manifolds

A liner element for a gas turbine combustor having a structural wall with fixing apertures provided therethrough. The liner element has a unitary construction defining a cooling side and combustion side, and a plurality of effusion holes extending between a cooling side surface of the element and a combustion side surface of the element. The liner element is configured to be affixed to the structural wall of a combustor with its cooling side surface spaced from the wall to define a chamber between the cooling side surface and the wall, and the liner element further includes integrally formed and non-threaded protuberances on its cooling side, the protuberances being arranged to engage and extend through respective fixing apertures in the combustor wall. Also disclosed is a method of thermally insulating the liner element.

Liner element for a combustor, and a related method

A combustion chamber arrangement comprises an annular combustion chamber arranged radially between an inner casing and an outer casing. The combustion chamber comprises a metering wall arranged upstream of an upstream wall and the upstream wall and the metering wall each have a plurality of circumferentially spaced apertures. Each aperture in the metering wall is aligned with a respective one of the apertures in the upstream wall. A fuel injector is arranged in each of the apertures in the upstream wall. An air swirler is aligned with a respective one of the fuel injectors. Each air swirler is arranged between the upstream wall and the metering wall. The metering wall has a plurality of metering holes arranged to provide a controlled supply of air to each of the air swirlers and the combustion chamber is secured to the inner casing by a mounting feature.

Combustion chamber arrangement

There is disclosed a liner element in the form of an impingement/effusion tile for a gas turbine combustor having a structural wall. The liner element has a unitary construction defining a cooling side and combustion side, and a plurality of effusion holes extending between a cooling side surface of the element and a combustion side surface of the element. The liner element is configured to be affixed to the structural wall of a combustor with its cooling side surface spaced from the structural wall to define a chamber between the cooling side surface and the structural wall, and the liner element further includes integrally formed and internally threaded protuberances on its cooling side, the protuberances being arranged to engage the structural wall.

Liner element for a combustor

A fuel manifold and fuel injector arrangement has a fuel manifold and at least one fuel injector. The fuel injector has main and pilot fuel nozzles. The fuel manifold has at least one fuel pipe segment and each fuel pipe segment has an outer pipe, an intermediate pipe arranged within the outer pipe and an inner pipe arranged within the intermediate pipe. A thermally insulating medium is provided in a chamber defined between the outer pipe and the intermediate pipe. The chamber between the intermediate pipe and the inner pipe is fluidly connected to a first fuel supply and the chamber within the inner pipe is fluidly connected to a second fuel supply. The at least one pilot fuel nozzle is fluidly connected to the chamber between the intermediate pipe and the inner pipe and the main fuel nozzle is fluidly connected to the chamber within the inner pipe.

Fuel manifold and fuel injector arrangement

A combustion chamber comprises an outer wall and an inner wall spaced from the outer wall. The outer wall has at least one mounting aperture extending there-through and the inner wall has threaded studs extending there-from. The threaded studs extend through the mounting apertures in the outer wall. Cooperating nuts locate on the studs and washers are positioned between the outer wall and the cooperating nuts. Each washer has a rim and a bore. The washers have one or more passages extending there-through from the rim to the bore of the washer to provide a flow of coolant through the passages in the washers, the mounting apertures in the outer wall and around the threaded studs to cool the threaded studs to increase the working life of the inner wall. Other cooling arrangements for the threaded studs are disclosed.

Combustion chamber with cooling passage in fastener arrangement joining inner and outer walls

A gas turbine engine combustion chamber includes a first wall and a second wall. The second wall is arranged within and spaced from the first wall to define a cavity between the first wall and the second wall. The first wall has a plurality of impingement apertures extending there-through and the second wall has a plurality of effusion apertures extending there-through. The impingement apertures have a first diameter, a first pitch, and a first area. The effusion apertures have a second diameter, a second pitch, and a second area. The ratio of the first diameter to the second diameter is at least 3, the ratio of the first pitch to the second pitch is at least 4 and the ratio of the first area to the second area is at least 9. This arrangement increases the cooling performance of the effusion apertures in the second wall.

Cooled double walled article

A cooling arrangement for a surface of a wall in a gas turbine engine, the wall having a plurality of effusion holes each with an outlet onto the surface for supplying an effusion flow to the surface and an inlet, the inlets of the effusion holes being arranged at the peripheries of groups tessellated on an opposing surface of the wall, each inlet being located on the peripheries of three groups. The arrangement comprises a second wall spaced apart from the opposing surface having impingement orifices each for directing a flow of air in use to a respective impingement location on the opposing surface, each group having a centrally positioned impingement location.

Cooling arrangement for a combustion chamber

A fuel injector head for a gas turbine engine the head comprising a pilot injector and a main injector located radially outwardly of the pilot injector. A concentric separates the pilot injector from the main injector and bounding a duct through which in use a fuel injected by the pilot injector flows. The splitter is hollow to improve cooling and has a radially inner surface which defines a first portion which tapers radially inwardly to a throat and a second portion which tapers radially outwardly from the throat with the angle of the radially outwards taper being such that a flow of air in use over the radially inner surface remains attached over the length of the surface.

Fuel injector

A gas turbine engine pre-diffuseris generally annular, including radially inner and radially outer wallsandand a generally cylindrical midlinedefined between the walls. The pre-diffuserincludes a central memberwhich forces air flowing through the pre-diffuserto separate, initially to be directed away from the midlinebefore subsequently being allowed to diffuse back towards the midline. The majority of the diffusion takes place on the walls of the central member and is thus in an inner region of the annulus of air ejected from the pre-diffuser to pass to the combustor. Any boundary losses therefore do not significantly effect air at the extremities of this annulus, this air being destined for the annuli of the combustor and requiring relatively high energy levels.

Diffuser for gas turbine engine

A wall element () for a wall structure () of a gas turbine engine combustor (). The wall element () comprises a main member () with an upstream edge region () and a downstream edge region (). A plurality of heat removal members () are provided on the main member (). The downstream edge () of the wall element and/or the downstream facing surface of the heat removal members closest to the downstream edge () are provided with a thermally resistant coating.

Wall elements for gas turbine engine combustors

A gas diffusion arrangement () for a gas turbine engine () is disclosed. The gas diffusion arrangement () has an inlet () and an outlet () for the gas, and comprises diffusion means () having an upstream region () and a downstream region (). Distribution means () is arranged between the downstream region () and the outlet () to distribute the gas into a desired flow pattern. The area ratio of the cross-sectional area of the downstream region () to the cross-sectional area of the upstream region () is greater than 1.5 to 1.

Gas diffusion arrangement

A seal arrangement for a combustor is disclosed. The seal arrangement comprises a seal defining a first aperture, an inner combustor wall defining a second aperture, and an outer combustor wall defining a third aperture. The first and second apertures are arranged in line with each other to receive an article therethrough. The seal is arranged between the inner and outer combustor walls.

Sealing arrangement

A wall element for use as part of an inner wall of a gas turbine engine combustor wall structure is of cast construction and includes a plurality of cooling apertures provided therethrough and formed during the casting process. The cooling apertures may be located in positions where they could not be conventionally formed by laser drilling.

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Derby, United Kingdom

Anthony Pidcock