Raytheon Technologies Corporation

United Technologies Corporation

Lee Edward Bouldin

Dennis M Moura

Jonathan Jeffery Eastwood

Monica Pacheco-Tougas

Joshua Daniel Winn

Edward A Krystowski

An assembly for a turbine engine includes a combustor wall. The combustor wall includes a shell, a heat shield and an annular land. The heat shield is attached to the shell. The land extends vertically between the shell and the heat shield. The land extends laterally between a land outer surface and an inner surface, which at least partially defines a quench aperture in the combustor wall. A lateral distance between the land outer surface and the inner surface varies around the quench aperture.

Quench aperture body for a turbine engine combustor

A combustor for use in a gas turbine engine has a combustor outer shell. A panel has an inner face which will face hot products of combustion, and a boss surrounding a feature, with the boss extending to an outer end. A spacing surface is spaced from the boss, and is at an outer position that is inward of the outer end of the boss. The spacing surface spaces the panel from the outer shell. A trough is intermediate the boss and the spacing surface. The trough extends to an outer end which is inward of the outer position of the spacing surface. A gas turbine engine is also disclosed.

Boss for combustor panel

A combustor of a gas turbine engine includes a multiple of liner panels mounted to the support shell, at least one of the multiple of liner panels includes a first impingement cavity that operates at a first pressure and a second impingement cavity that operates at a second pressure different than the first pressure. A method of cooling a wall assembly within a combustor of a gas turbine engine includes directing air through a support shell and a liner panel that defines a first impingement cavity and a second impingement cavity. The first impingement cavity operates at a first pressure and the second impingement cavity operates at a second pressure that is different than the first pressure.

Controlled variation of pressure drop through effusion cooling in a double walled combustor of a gas turbine engine

A combustor wall is provided for a turbine engine. The combustor wall includes a shell and a heat shield that is attacked to the shell. The heat shield includes a rail and a cooling element connected to the rail in a cavity. The cavity extends in a vertical direction between the shell and the heat shield. The cavity fluidly couples a plurality of apertures in the shell with a plurality of apertures in the heat shield.

Turbine engine combustor heat shield with one or more cooling elements

An annular grommet is provided for a wall assembly of a combustor section of a gas turbine engine. The annular grommet includes a wall that at least partially defines a chamber. A wall assembly within a gas turbine engine includes a liner panel with a hot side and a cold side. The wall assembly also includes an annular grommet with a passage wall and a flange wall transverse to the passage wall. The annular grommet includes a chamber therein. A method of cooling a wall assembly within a gas turbine engine includes injecting air through a chamber in an annular grommet.

Passage geometry for gas turbine engine combustor

A liner panel is provided for use in a combustor of a gas turbine engine. The liner panel includes a major dilution passage having a lip and a first seal boss. The liner panel also includes a minor dilution passage having a second seal boss adjacent the first seal boss.

Dilution passage arrangement for gas turbine engine combustor

A wall assembly for use in a combustor of a gas turbine engine includes a transverse structure with at least one effusion passage that extends at an angle &#x3b1; therethrough. The effusion passage includes an inlet in an outer periphery of a wall. A wall assembly within a gas turbine engine include a liner panel generally parallel to a support shell and a transverse structure with at least one effusion passage that extends at an angle &#x3b1; therethrough. The effusion passage includes an inlet in an outer periphery of a wall that is transverse to the liner panel and the support shell.

Angled combustor liner cooling holes through transverse structure within a gas turbine engine combustor

A combustor for a turbine engine is provided that includes a combustor wall. The combustor wall includes a shell and heat shield, which is attached to the shell. One or more cooling cavities are defined between the shell and the heat shield, and fluidly couple a plurality of apertures defined in the shell with a plurality of apertures defined in the heat shield. The apertures in the heat shield include a first aperture and a second aperture. An angle of incidence between the first aperture and a surface of the heat shield is different than an angle of incidence between the second aperture and the surface.

Turbine engine combustor heat shield with multi-angled cooling apertures

A system for collaborating on a component according to an exemplary aspect of the present disclosure includes, among other things, a computing device configured to execute an editing module. The editing module is configured to generate at least one developed feature of the component design in response to executing at least one global command relating to a multi-user CAx command set, and to generate at least one undeveloped feature of the component design in response to executing at least one local command relating to a local CAx command set.

Support of undeveloped features in multi-user CAx environment

A system for collaborating on a component includes a computing device having a memory and a processor, the computing device configured to execute a first multi-user CAx environment, a data module configured to access data corresponding to a component design having at least one feature corresponding to a group of feature types from at least one current state database in a memory storage device, and a time stamp tool included in the multi-user CAx environment and configured to cause at least one computing device executing the multi-user CAx environment to apply a timestamp to each revision of a part model and save each revision including the timestamp to a revision database.

Growing community of inventors

Woodbridge, CT, United States of America

Lee Edward Bouldin