United Technologies Corporation

Raytheon Technologies Corporation

United Technologies Corporaton

Stanislav Kostka, Jr

Frank J Cunha

Timothy S Snyder

Randal G McKinney

Tracy A Propheter-Hinckley

Dominic J Mongillo, Jr

Christopher Drake

Mark F Zelesky

James B Hoke

Joel H Wagner

Albert K Cheung

Hoyt Y Chang

Andreas Sadil

Christos Adamopoulos

Timothy S Synder

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

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

Film cooled multi-walled structure with one or more indentations

An assembly is provided for a turbine engine. A combustor wall of the turbine engine assembly includes a shell, a heat shield and an annular body engaged with the shell and the heat shield. The annular body extends through the combustor wall. The annular body at least partially defines a quench aperture along a centerline through the combustor wall. The annular body also at least partially defines a cooling aperture in fluid communication with the quench aperture. At least a portion of the cooling aperture extends radially outward from the quench aperture relative to the centerline.

Cooling a quench aperture body of a combustor wall

A cooled wall for lining a combustor of a gas turbine engine includes an annular outer wall defining a radial passage extending therethrough, an inner wall spaced radially from the outer wall to define an axial channel in fluid communication with the radial passage, and a connecting wall joining the inner wall to the outer wall. A method of making the cooled wall includes providing a three-dimensional computer model of the cooled wall, depositing a uniform thickness layer of material on a substrate, using a laser or electron beam to melt or sinter the material to form a cross section, repeating the depositing and cross section steps to form the cooled wall, and heat treating the cooled wall.

Combustor wall cooling channel formed by additive manufacturing

A grommet assembly and method of design to enhance the flow coefficient, thereof, includes a shell having a first side and an opposite second side, and a chamfered grommet projecting through the shell along a centerline and including an annular first end surface spaced outward from the first side and a conical face spanning axially and radially inward from the annular first end surface and axially beyond the second side. The assembly may further include a panel spaced from the shell and defining a cooling cavity therebetween with the conical surface defining at least in-part a hole in fluid communication through the shell and panel and isolated from the cooling cavity. A plurality of cooling channels in the grommet are in fluid communication with the cooling cavity and communicate through the panel. The combination of the conical face and the cooling channels improve the discharge coefficient of the grommet while enhancing grommet cooling.

Growing community of inventors

Shrewsbury, MA, United States of America

Stanislav Kostka, Jr