An engine component assembly includes a first engine component having a hot surface in thermal communication with a hot combustion gas flow and a cooling surface with at least one cavity. A second engine component is spaced from the cooling surface, and includes at least one cooling aperture. The cooling aperture is arranged such that cooling fluid impinges on the cooling surface at an angle.

An engine component assembly includes a first engine component having a hot surface in thermal communication with a hot combustion gas flow and a cooling surface with at least one cavity. A second engine component is spaced from the cooling surface, and includes at least one cooling aperture. The cooling aperture is arranged such that cooling fluid impinges on the cooling surface at an angle.

A gas turbine engine component has a component body configured to be positioned within a flow path of a gas turbine engine, wherein the component body includes at least one internal cavity. At least one inlet opening is formed in an outer surface of the component body to direct flow into the at least one internal cavity. At least one outlet from the internal cavity, wherein the at least one outlet is located at a lower pressure area in the internal cavity than the at least one inlet opening such that flow is drawn into the internal cavity from the at least one inlet opening and expelled out the at least one outlet. A gas turbine engine and a method of enhancing laminar flow for a gas turbine engine component are also disclosed.

A gas turbine engine, including: a diffuser case defining an inner shroud and an outer shroud; and a combustor housed within the diffuser case between the inner shroud and the outer shroud, the combustor including: a shell; a forward dome attached to the shell at a forward end of the combustor; and a deflector attached to the forward dome and extending away from the forward dome.

A gas turbine engine, including: a diffuser case defining an inner shroud and an outer shroud; and a combustor housed within the diffuser case between the inner shroud and the outer shroud, the combustor including: a shell; a forward dome attached to the shell at a forward end of the combustor; and a deflector attached to the forward dome and extending away from the forward dome.

A combustor may comprise an outer wall defining, at least, a portion of a combustion chamber. A dilution chute may extend from an interior surface of the outer wall. A support structure may extend between the dilution chute and the interior surface of the outer wall. A spall plate may extend from the interior surface of the outer wall. The spall plate may be located between the support structure and an outlet of the combustion chamber.

A diffuser of a thermal energy machine, in particular of a gas turbine, has a diffuser inlet, a diffuser outlet, and a plurality of air-guiding elements, wherein an air mass flow enters the diffuser through the diffuser inlet, and wherein the air mass flow that has entered the diffuser exits the diffuser through the diffuser outlet and flows off as a plurality of partial air mass flows by the air-guiding elements. At least two immediately adjacent air-guiding elements of the plurality of air-guiding elements are designed in such a way that the flow-off angles thereof with respect to the circumferential surface formed by the outlet opening of the diffuser outlet extending circumferentially in the circumferential direction differ from each other.

A diffuser of a thermal energy machine, in particular of a gas turbine, has a diffuser inlet, a diffuser outlet, and a plurality of air-guiding elements, wherein an air mass flow enters the diffuser through the diffuser inlet, and wherein the air mass flow that has entered the diffuser exits the diffuser through the diffuser outlet and flows off as a plurality of partial air mass flows by the air-guiding elements. At least two immediately adjacent air-guiding elements of the plurality of air-guiding elements are designed in such a way that the flow-off angles thereof with respect to the circumferential surface formed by the outlet opening of the diffuser outlet extending circumferentially in the circumferential direction differ from each other.

A turbine combustor section has a flow conditioner including a plurality of conduits arranged to convey pressurized air to an air chamber for entrance into a plurality of fuel nozzles. Each conduit includes an inlet configured to receive the pressurized air from an annular passage and an outlet configured to deliver the pressurized air to the air chamber. A cross-sectional area of each conduit varies between the inlet and the outlet so as to reduce a pressure drop across the flow conditioner.

A grommet for a combustor of a gas turbine engine is disclosed. The grommet includes a lower platform and a raised platform. The lower platform includes a plurality of top slots located in the top surface and a plurality of bottom slots located in the bottom surface. Each top slot and bottom slot may extend radially along the lower platform. The plurality of top slots may be spaced equidistantly from one another along the circumference of the lower platform. The plurality of bottom slots may be spaced equidistantly from one another along the circumference of the lower platform.