Abstract: An airfoil for a gas turbine engine is disclosed. In various embodiments, the airfoil includes a cooling passage; an outer wall separating a core flow path from the cooling passage; a diffuser in fluid communication with the cooling passage and opening into the core flow path, the diffuser being characterized by a linear ridge on a downstream end of the diffuser; and a thermal barrier coating covering the outer wall and the linear ridge.

Abstract: An airfoil for a gas turbine engine is disclosed. In various embodiments, the airfoil includes a cooling passage; an outer wall separating a core flow path from the cooling passage; a diffuser in fluid communication with the cooling passage and opening into the core flow path, the diffuser being characterized by a linear ridge on a downstream end of the diffuser; and a thermal barrier coating covering the outer wall and the linear ridge.

Abstract: Disclosed is a vane stage for a variable area turbine, comprising vane platforms comprising a first vane platform and a second vane platform, one of the vane platforms being a radial inner vane platform and another of the vane platforms being a radial outer vane platform, and a space therebetween defining an air flowpath; a primary vane body secured at opposing radial ends to the first vane platform and the second vane platform, a secondary vane body movably secured at the first vane platform, the secondary vane body being movable between a stowed position, wherein the secondary vane body is outside of the air flow path, and a deployed position, wherein the secondary vane body is extended between the plurality of vane platforms to form a vane trailing edge extension.

Abstract: A system for circumferentially distributing debris in a gas turbine engine includes a component that defines a component cooling channel that has an opening and is configured to receive a cooling airflow. The system also includes a casing at least partially enclosing the component. The system also includes a debris distribution surface positioned radially between the casing and the opening.

Abstract: A system for reducing debris in a gas turbine engine includes a component that defines a component cooling channel for receiving a cooling airflow. The system also includes a casing at least partially enclosing the component. The system also includes a debris evacuation door coupled to the casing and having an open state in which the debris can exit the casing and a closed state.

Abstract: Disclosed is a vane stage for a variable area turbine, comprising vane platforms comprising a first vane platform and a second vane platform, one of the vane platforms being a radial inner vane platform and another of the vane platforms being a radial outer vane platform, and a space therebetween defining an air flowpath; a primary vane body secured at opposing radial ends to the first vane platform and the second vane platform, a secondary vane body movably secured at the first vane platform, the secondary vane body being movable between a stowed position, wherein the secondary vane body is outside of the air flow path, and a deployed position, wherein the secondary vane body is extended between the plurality of vane platforms to form a vane trailing edge extension.

Abstract: The systems and methods described herein adapt the orientation, position and/or diffusion angles of showerhead cooling holes depending on the external gas/streamline flow direction. In regions, for example, where the stagnation line is on the pressure side, the breakouts of the showerhead holes substantially face aft (e.g., primarily towards the suction side). The location and positioning of the holes may be oriented according to the direction of incoming gas flows.

Abstract: A system for reducing debris in a gas turbine engine includes a component that defines a component cooling channel for receiving a cooling airflow. The system also includes a casing at least partially enclosing the component. The system also includes a debris evacuation door coupled to the casing and having an open state in which the debris can exit the casing and a closed state.

Abstract: A system for circumferentially distributing debris in a gas turbine engine includes a component that defines a component cooling channel that has an opening and is configured to receive a cooling airflow. The system also includes a casing at least partially enclosing the component. The system also includes a debris distribution surface positioned radially between the casing and the opening.

Abstract: The systems and methods described herein adapt the orientation, position and/or diffusion angles of showerhead cooling holes depending on the external gas/streamline flow direction. In regions, for example, where the stagnation line is on the pressure side, the breakouts of the showerhead holes substantially face aft (e.g., primarily towards the suction side). The location and positioning of the holes may be oriented according to the direction of incoming gas flows.

Abstract: A method of forming a component for use in a gas turbine engine comprises the steps of determining a desired shape for a cooling hole on a gas turbine engine component, and determining the likely deposition of a coating to be provided on the component into the cooling hole. An intermediate cooling hole is formed that has an enlarged area from the desired shape to account for deposition of the coating. The component is then coated. A component and an intermediate component for use in a gas turbine engine are also disclosed.

Abstract: A blade for a gas turbine engine includes an airfoil that has a tip with a terminal end surface. The terminal end surface includes a recess that has a depth of less than 40 mils (1.016 mm). The recess is filled with a thermal barrier coating. The recess is without any cooling holes.

Abstract: If a refractory metal core (RMC) is punched, the punching asymmetry may be reflected in an asymmetry of the cast article features cast by the punched features. The punched features may have a shear zone and a fracture zone. The shear zone of the RMC will cast a relatively narrow portion of the post near one end; whereas the fracture zone will cast a relatively broader portion near the other end. The broader portion will also have a relatively shallow transition to the adjacent face of the slot-like passageway cast by the RMC. Where there is a stress asymmetry in the cast article in-use, the punching direction may be chosen so that the relatively broad portions of the post fall along the relatively higher stress face of the passageway.

Abstract: A coolable airfoil (25) for a gas turbine engine includes a leading edge portion (52) cooled by a combination of radial and impingement flows through internal passages (80) and (90) separated by an internal wall (95) which is imperforate along a radially inner portion (100) thereof and apertured along a radially outer portion (105) thereof

Abstract: Cooling air to the 1-2 turbine stage seal is supplied in parallel with air to the second vane from a plenum. A modulatable valve in the supply line to the plenum regulates air flow in response to a sensed temperature in the 1-2 seal area at high sensed speeds. Valve and thermocouples are checked for proper operation. Immediate alerts and maintenance messages are established along with fail safe operating conditions upon fault detection. Over cooling of the seal area during low power operation, in anticipation of a power increase, is used to improve low cycle fatigue life of the turbine disk and seal runner.

Abstract: Cooling air to the 1-2 turbine stage seal is supplied in parallel with air to the second vane surface from a plenum. A modulatable valve in the supply line to the plenum regulates air flow in response to a sensed temperature in the 1-2 seal area. A thermocouple is located in a bypass around a portion of the seal, being radially installed through a hollow vane and an opening in the seal shroud.

Abstract: A temperature controlled rotating seal (46) includes an annular runner (48) having knife edges (50) and a surrounding static shroud (44). Baffles (64, 66) extend radially from the adjacent rotor (10) and a static stator vane assembly (36), forming a plurality of annular mixing volumes (60, 62) disposed upstream of the seal (46). Cool air (70) is provided to the innermost mixing volume (62) thereby controlling the local gas temperatures at the rotor periphery (14).