Abstract: A cooling circuit for a gas turbine engine comprises a first wall having a first surface facing a first cavity and a second surface facing away from the first cavity. A second wall is spaced outwardly of the second surface of the first wall to provide at least one second cavity. Cooling fluid is configured to flow from the first cavity and exit to an external surface of the second wall via at least one hole to provide cooling to the external surface. A gas turbine engine and a method of forming a cooling circuit for a gas turbine engine are also disclosed.

Abstract: A gas turbine engine component includes a body with a wall surrounding an interior cavity. The wall has opposed interior and exterior surfaces. The interior surface has a plurality of coolant inlets and the exterior surface has a coolant outlet defined therein. A coolant conduit extends between the coolant inlets and the coolant outlet and is configured and adapted to induce secondary flow vortices in coolant traversing the coolant conduit and in an adherent coolant film over a portion of the exterior surface of component body.

Abstract: A gas turbine engine component includes a wall that provides an exterior surface and an interior flow path surface. A film cooling hole extends through the wall and is configured to fluidly connect the interior flow path surface to the exterior surface. The film cooling hole has a diffuser that is arranged downstream from a metering hole. The diffuser includes inner and outer diffuser surfaces opposite one another and respectively arranged on sides near the interior flow path surface and the exterior surface. A protrusion is arranged in the diffuser on the outer diffuser surface.

Abstract: A casting article according to another exemplary aspect of the present disclosure includes, among other things, a circuit forming portion including an interior channel and an outer shell body that surrounds the interior channel. An engineered failure feature is formed in the outer shell body and is configured to increase compressibility of the casting article during a casting process.

Abstract: A gas turbine engine component includes a wall that provides an exterior surface and an interior flow path surface. The wall has a wall thickness. A protrusion is arranged on the wall that extends a height beyond the wall thickness and provides a portion of the interior flow path surface. A film cooling hole that has an inlet is provided on the protrusion and extends to an exit on the exterior surface.

Abstract: A gas turbine engine component includes a wall that provides an exterior surface and an interior flow path surface. A film cooling hole extends through the wall and is configured to fluidly connect the interior flow path surface to the exterior surface. The film cooling hole has a pocket that faces the interior flow path and extends substantially in a longitudinal direction. The film cooling hole has a portion downstream from the pocket and is arranged at an angle relative to the longitudinal direction and extends to the exterior surface.

Abstract: An airfoil structure for a gas turbine engine includes an airfoil that includes a suction side cooling circuit with at least two segments that are connected by at least one impingement passage.

Abstract: A cooling circuit for a gas turbine engine comprises a gas turbine engine component having a first portion connected to a second portion via a curved surface. An inlet is formed in or near one of the first and second portions to receive a cooling air flow. An outlet is formed in or near the other of the first and second portions to direct cooling flow along a surface of the gas turbine engine component. At least one cooling path extends between the inlet and the outlet and has at least one cooling path portion that conforms in shape to the curved surface. A gas turbine engine and a method of forming a cooling circuit for a gas turbine engine are also disclosed.

Abstract: This disclosure relates to a gas turbine engine including a first engine component and a second engine component. The first engine component has a mate face adjacent a mate face of the second engine component. The engine further includes a seal provided between the mate face of the first engine component and the mate face of the second engine component. The seal includes least one trough.

Abstract: A cooling circuit for a gas turbine engine comprises a gas turbine engine component having a body with at least one internal cavity defined by a cavity wall. A plurality of cooling holes formed within the cavity wall, wherein each cooling hole is defined by a length extending from a cooling hole inlet to a cooling hole outlet, and wherein the cooling holes are positioned relative to each other such that a minimum allowable ligament distance is maintained between adjacent cooling holes along the entire length of each cooling hole. A gas turbine engine and a method of forming a cooling circuit for a gas turbine engine are also disclosed.

Abstract: A cooling system integrated into a stator assembly of a gas turbine engine has an on-board injector or cooling nozzle located for cooling of a rotor assembly. The nozzle may be generally annular and may contain a plurality of pivoting airfoils circumferentially spaced from one-another for directing cooling air flow from the nozzle and generally toward a plurality of holes in a cover of the rotor assembly. The pivoting airfoils are adapted to move between a spoiled state where the mass flow of cooling air is reduced, and to an optimal state where the mass flow is increased. The system may further include a plurality of fixed airfoils in the nozzle with adjacent fixed airfoils defining a discharge orifice in the nozzle. Each one of the plurality of pivoting airfoils may be located in a respective discharge orifice.

Abstract: A casting article according to an exemplary aspect of the present disclosure includes, among other things, a circuit forming portion and an interior channel formed inside of the circuit forming portion. The interior channel defines a leaching path that extends at least partially through the circuit forming portion.

Abstract: A component includes at least one thermal riser that extends from an exterior surface of the component. At least one cooling passage extends through a wall and adjoins an interior cooling passage and provides an exterior surface. At least one cooling passage is configured to direct cooling fluid through the wall adjacent to at least one thermocouple.

Abstract: A wall of a gas turbine engine is provided. The wall may comprise an external surface adjacent a gas path and an internal surface adjacent an internal flow path. A film hole may have an inlet at the internal surface and an outlet at the external surface. A flow accumulator adjacent the inlet may protrude from the internal surface. A method of making an engine component is also provided and comprises the step of forming a component wall comprising an accumulator on an internal surface and a film hole defined by the component wall. The film hole may include an opening adjacent the accumulator and defined by the internal surface.

Abstract: A cooling device for a gas turbine engine component comprises a gas turbine engine component having an upstream channel and a downstream channel that define a cooling flow path. A meter feature includes at least one hole to meter flow from the upstream channel to the downstream channel, and has an upstream side and a downstream side. An exit diffuser extends outwardly from the downstream side of the meter feature to control flow in a desired direction into the downstream channel. A gas turbine engine is also disclosed.

Abstract: A gas turbine engine component is described. The component includes a component wall having an internal surface that is adjacent a flow of coolant and an external surface that is adjacent a flow of gas. The component wall includes a cooling hole that has an inlet defined by the internal surface and an outlet defined by the external surface. The cooling holes also has a metering location having the smallest cross-section area of the cooling hole, an internal diffuser positioned between the inlet and the metering location, an accumulation diverter portion of the internal diffuser and an accumulator portion of the internal diffuser.

Abstract: An airfoil for a gas turbine engine, the airfoil includes a wall that has a leading edge and a trailing edge and at least partially defining a boundary of a leading edge cavity radially along the leading edge. A cooling jet structure is operatively associated with a portion of the wall proximate the leading edge and is configured to direct a cooling fluid tangent to the portion of the wall.

Abstract: An example gas turbine engine component includes an airfoil having a leading edge area, a first circuit to cool a first section of the leading edge area, and a second circuit to cool a second section of the leading edge area. The first circuit separate and distinct from the second circuit within the airfoil.

Abstract: An article includes a body that has a first section and a second section bonded with the first section. The first section is formed with a first material that has a first microstructure and the second section is formed of a second material that has a second, different microstructure.

Abstract: An airfoil includes an airfoil body having an internal cavity. A thermostatic valve is located at least partially within the internal cavity. The thermostatic valve is configured to passively control fluid flow into the internal cavity in response to a temperature within the internal cavity.