United Technologies Corporation

Raytheon Technologies Corporation

Siemens Westinghouse Power Corporation

United Technologies Corporaton

Frank J Cunha

Stanislav Kostka, Jr

Nurhak Erbas-Sen

William Abdel-Messeh

Timothy S Snyder

Edward F Pietraszkiewicz

Keith A Santeler

Om Parkash Sharma

Bret M Teller

Jason Edward Albert

Randal G McKinney

Young H Chon

Eric L Couch

Matthew T Dahmer

Stanislav Kostka

Dominic J Mongillo, Jr

Bryan P Dube

James B Hoke

Eric A Hudson

Albert K Cheung

James P Bangerter

Christopher Drake

Scott W Gayman

Russell B Hanson

Jeffrey R Levine

Alexander W Williams

Kevin Joseph Low

Andreas Sadil

Raymond Scott Nordlund

Christopher R Joe

Jonathan M Jause

Eric P Letizia

Torence P Brogan

Christos Adamopoulos

David Michael Kontrovitz

Barry Lee McKinley

Nicholas Mule

Michael A Palumbo

Thomas Malow

Anthony L Schiavo, Jr

Dominic Mongillo

Jr Stanislav Kostka

Stanislav Kostka Jr

Timothy S Synder

Randal G Mckinney

David M Kontrovitz

Young Chon

Christopher Joe

Keith Santeler

An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall including a shell and a heat shield. The combustor wall defines first and second cavities between the shell and the heat shield. The heat shield defines a first outlet and an elongated second outlet. The first outlet is fluidly coupled with the first cavity. The second outlet is fluidly coupled with the second cavity. The combustor wall defines one of the cavities with a tapered geometry.

Film cooling a combustor wall of a turbine engine

An assembly for a turbine engine is provided. This turbine engine assembly includes a shell and a heat shield with a cooling cavity between the shell and the heat shield. The heat shield defines a plurality of cooling apertures and an indentation in a side of the heat shield opposite the cooling cavity. The cooling apertures are fluidly coupled with the cooling cavity. The indentation is configured such that cooling air, directed from a first of the cooling apertures, at least partially circulates against the side of the heat shield.

Film-cooled multi-walled structure with one or more indentations

An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall. The combustor wall includes a shell, a heat shield and an annular body. The annular body extends through the combustor wall and at least partially defines a quench aperture along a centerline through the combustor wall. The shell defines a first cooling aperture radially outwards of the annular body relative to the centerline and is configured to direct air to impinge against a portion of the annular body between the heat shield and the shell.

Combustor quench aperture cooling

A wall assembly for use in a combustor of a gas turbine engine includes a support shell with a first inner periphery along an axis and a liner panel with a second inner periphery along the axis. The second inner periphery is smaller than the first inner periphery. Another wall assembly for use in a combustor of a gas turbine engine includes an annular grommet mounted between the support shell and the liner panel. The annular grommet defines a contoured inner wall.

Contoured dilution passages for gas turbine engine combustor

An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall. The combustor wall includes a shell, a heat shield and an annular body. The body extends laterally between an inner surface and an outer surface. The inner surface defines an igniter aperture in the combustor wall. The outer surface is vertically between the heat shield and the shell. The shell defines a first cooling aperture through which air is directed to impinge against the outer surface.

Cooling an igniter body of a combustor wall

A combustor wall is provided for a turbine engine. The combustor wall includes a combustor shell and a combustor heat shield that is attached to the shell. The heat shield includes a first panel and a second panel that sealingly engages the first panel in an overlap joint. A cooling cavity extends between the shell and the heat shield and fluidly couples a plurality of apertures in the shell with a plurality of apertures in the heat shield.

Heat shield panels with overlap joints for a turbine engine combustor

An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall with a shell and a heat shield. The combustor wall defines a quench aperture therethrough. The combustor wall also defines a cavity between the shell and the heat shield. The shell defines a first aperture through which air is directed into the cavity. The heat shield includes a rail that at least partially defines a second aperture configured to direct at least some of the air within the cavity out of the combustor wall and towards the quench aperture.

Stepped heat shield for a turbine engine combustor

A structure is provided for a turbine engine. The structure includes a shell with a first surface, and a heat shield with a textured second surface and a textured third surface. The texture of a portion of the second surface is different than the texture of a portion of the third surface. The first surface and the second surface define a first cooling cavity between the shell and the heat shield. The first surface and the third surface define a second cooling cavity between the shell and the heat shield.

Turbine engine multi-walled structure with internal cooling element(s)

An assembly is provided for a turbine engine. A combustor wall of the turbine engine assembly includes a shell and a heat shield. The combustor wall defines a quench aperture through the shell and the heat shield. The heat shield defines an effusion outlet a distance from the quench aperture equal to between about twenty-five times and about seventy-five times a width of the effusion outlet.

Cooling a combustor heat shield proximate a quench aperture

A fuel injector guide is provided for a turbine engine combustor. The fuel injector guide includes a tubular base, an annular flange, a plurality of ribs and a flow turbulator. The base extends along an axis between first and second ends. The flange extends radially out from the base at the second end. The ribs are disposed around the base and extend axially out from the flange towards the first end. The flow turbulator is disposed between an adjacent pair of the ribs.

Fuel injector guide(s) for a turbine engine combustor

A liner panel for a combustor of a gas turbine engine includes a multiple of heat transfer augmentors which extend from a cold side thereof. At least one of the multiple of heat transfer augmentors includes a first heat transfer augmentation feature with a second heat transfer augmentation feature stacked thereon.

Gas turbine engine combustor liner panel

A wall assembly for a combustor of a gas turbine engine is provided. The wall assembly includes a support shell with a contoured region to define at least one convergent passage between the support shell and a multiple of liner panels. A method of cooling a wall assembly for a combustor of a gas turbine engine is also provided. This method includes a step of directing cooling air into at least one convergent passage between the support shell and a multiple of liner panels.

Gas turbine engine wall assembly with support shell contour regions

An assembly for a turbine engine is provided that includes a combustor wall, which includes an aperture body between a shell and a heat shield. The aperture body at least partially forms a cavity and an aperture that extends through the combustor wall. An inlet passage extends in the combustor wall to the cavity. An outlet passage extends in the combustor wall from the cavity to the aperture.

Combustor wall aperture body with cooling circuit

Film cooled multi-walled structure with one or more indentations

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Avon, CT, United States of America

Frank J Cunha