Abstract: A dual-wall airfoil comprises a spar including pressure and suction side walls with raised features on outer surfaces thereof. A pressure side coversheet has an inner surface in contact with the raised features on the outer surface of the pressure side wall so as to define pressure side flow pathways between the pressure side wall and the pressure side coversheet, and a suction side coversheet has an inner surface in contact with the raised features on the outer surface of the suction side wall so as to define suction side flow pathways between the suction side wall and the suction side coversheet. The raised features on the outer surface of the pressure and/or suction side wall include an arrangement of pedestals, where each pedestal comprises an aspect ratio in a range from about 1:1 to about 5:1. The aspect ratio of the pedestals is varied within the arrangement.

Abstract: An airfoil including a spar and a cover sheet that are configured for cooling. The spar includes standoffs and a leading edge wall. The standoffs are disposed along a pressure and/or suction side. A pressure-side panel and a suction-side panel are coupled to the standoffs and/or the leading edge wall. Leading ends of the pressure-side panel and the suction-side panel are disposed adjacent to one another proximate to the leading edge. The standoffs extend beyond the pressure-side leading end toward the leading edge wall. At least one of the leading ends of the pressure-side and suction-side panels defines a notch to form an outlet port at the leading edge. Standoffs may be disposed to define grooves in between in communication with the outlet port.

Abstract: A blade used in a gas turbine engine includes a pair of pedestals and an airfoil coupled between the pedestals. The airfoil includes cooling features to cool the airfoil.

Abstract: An airfoil for use in a gas turbine engine is disclosed herein. The airfoil includes a pressure side wall, a suction side wall, and a cooling air distribution system. The suction side wall is arranged opposite the pressure side wall. The cooling air distribution system is formed internal to at least one of the pressure side wall and the suction side wall. The cooling air distribution system is configured to distribute cooling air through the airfoil to cool the airfoil.

Abstract: An airfoil including a spar and a cover sheet. Standoffs, a leading edge wall, and a separator wall extend away from an outer surface of the spar. The standoffs are arranged to define leading grooves disposed at the pressure side of the leading edge. The cover sheet is coupled to the leading edge wall and the standoffs over the leading grooves to define cooling passageways. The cooling passageways are in communication with one or more inlet ports formed in the spar, which are in communication with a plenum disposed within the spar. The cover sheet is arranged to define outlet ports or a slot in communication with the cooling passageway. Cooling air is delivered from the cooling air plenum through the inlet port for impingement cooling at the cover sheet, and traverses downstream through the cooling passageway to the outlet ports or slot for film cooling of the leading edge.

Abstract: A turbine assembly for a gas turbine engine is disclosed herein. The turbine assembly includes a turbine vane and an annular turbine shroud. The turbine vane has an airfoil extending through a primary gas path and is formed to include cooling passages sized to conduct cooling air from an inlet aperture to a discharge aperture. The turbine shroud is adapted to extend around a bladed turbine wheel to resist gasses from passing over turbine blades without interacting with the turbine blades. The turbine shroud includes a ceramic matrix composite blade track having a radially-inwardly facing inner surface arranged in confronting relation with the primary gas path.

Abstract: An airfoil including a spar and a cover sheet that are configured for cooling. The spar includes standoffs and a leading edge wall. The standoffs are disposed along a pressure and/or suction side. A pressure-side panel and a suction-side panel are coupled to the standoffs and/or the leading edge wall. Leading ends of the pressure-side panel and the suction-side panel are disposed adjacent to one another proximate to the leading edge. The standoffs extend beyond the pressure-side leading end toward the leading edge wall. At least one of the leading ends of the pressure-side and suction-side panels defines a notch to form an outlet port at the leading edge. Standoffs may be disposed to define grooves in between in communication with the outlet port.

Abstract: An airfoil including a spar and a cover sheet that are configured for cooling. The spar includes standoffs and a leading edge wall. The standoffs are disposed along a pressure and/or suction side. A pressure-side panel and a suction-side panel are coupled to the standoffs and/or the leading edge wall. Leading ends of the pressure-side panel and the suction-side panel are disposed adjacent to one another proximate to the leading edge. The standoffs extend beyond the pressure-side leading end toward the leading edge wall. At least one of the leading ends of the pressure-side and suction-side panels defines a notch to form an outlet port at the leading edge. Standoffs may be disposed to define grooves in between in communication with the outlet port.

Abstract: An airfoil with dual wall cooling for a gas turbine engine comprises a spar having pressure and suction side walls that meet at leading and trailing edges of the airfoil, with a tip extending therebetween. An interior of the spar includes a coolant cavity, and each of the pressure and suction side walls includes an arrangement of pedestals on an outer surface thereof and a plurality of cooling holes in fluid communication with the coolant cavity. A pressure side coversheet overlies the pressure side wall and terminates in a radial direction short of the tip of the spar to form a shelf extending along a chordal direction. Flow channels between the pressure side wall and coversheet are configured to direct coolant from the cooling holes to radial flow outlets adjacent to the shelf. A suction side coversheet overlies the suction side wall, and a coolant circuit between the suction side wall and coversheet does not include radial coolant outlets.

Abstract: A blade used in a gas turbine engine includes a pair of pedestals and an airfoil coupled between the pedestals. The airfoil includes cooling features to cool the airfoil.

Abstract: A blade used in a gas turbine engine includes a pair of pedestals and an airfoil coupled between the pedestals. The airfoil includes cooling features to cool the airfoil.

Abstract: An airfoil with dual wall cooling for a gas turbine engine comprises a spar having pressure and suction side walls that meet at leading and trailing edges of the airfoil, with a tip extending therebetween. An interior of the spar includes a coolant cavity, and each of the pressure and suction side walls includes an arrangement of pedestals on an outer surface thereof and a plurality of cooling holes in fluid communication with the coolant cavity. A pressure side coversheet overlies the pressure side wall and terminates in a radial direction short of the tip of the spar to form a shelf extending along a chordal direction. Flow channels between the pressure side wall and coversheet are configured to direct coolant from the cooling holes to radial flow outlets adjacent to the shelf. A suction side coversheet overlies the suction side wall, and a coolant circuit between the suction side wall and coversheet does not include radial coolant outlets.

Abstract: An airfoil for use in a gas turbine engine is disclosed herein. The airfoil includes a pressure side wall, a suction side wall, and a cooling air distribution system. The suction side wall is arranged opposite the pressure side wall. The cooling air distribution system is formed internal to at least one of the pressure side wall and the suction side wall. The cooling air distribution system is configured to distribute cooling air through the airfoil to cool the airfoil.

Abstract: An airfoil including a spar and a cover sheet that are configured for cooling. The spar includes standoffs and a leading edge wall. The standoffs are disposed along a pressure and/or suction side. A pressure-side panel and a suction-side panel are coupled to the standoffs and/or the leading edge wall. Leading ends of the pressure-side panel and the suction-side panel are disposed adjacent to one another proximate to the leading edge. The standoffs extend beyond the pressure-side leading end toward the leading edge wall. At least one of the leading ends of the pressure-side and suction-side panels defines a notch to form an outlet port at the leading edge. Standoffs may be disposed to define grooves in between in communication with the outlet port.

Abstract: An airfoil including a spar and a cover sheet. Standoffs, a leading edge wall, and a separator wall extend away from an outer surface of the spar. The standoffs are arranged to define leading grooves disposed at the pressure side of the leading edge. The cover sheet is coupled to the leading edge wall and the standoffs over the leading grooves to define cooling passageways. The cooling passageways are in communication with one or more inlet ports formed in the spar, which are in communication with a plenum disposed within the spar. The cover sheet is arranged to define outlet ports or a slot in communication with the cooling passageway. Cooling air is delivered from the cooling air plenum through the inlet port for impingement cooling at the cover sheet, and traverses downstream through the cooling passageway to the outlet ports or slot for film cooling of the leading edge.

Abstract: A turbine assembly for a gas turbine engine is disclosed herein. The turbine assembly includes a turbine vane and an annular turbine shroud. The turbine vane has an airfoil extending through a primary gas path and is formed to include cooling passages sized to conduct cooling air from an inlet aperture to a discharge aperture. The turbine shroud is adapted to extend around a bladed turbine wheel to resist gasses from passing over turbine blades without interacting with the turbine blades. The turbine shroud includes a ceramic matrix composite blade track having a radially-inwardly facing inner surface arranged in confronting relation with the primary gas path.

Abstract: A gas turbine engine component is provided that can be cooled with a cooling media such as air using a variety of passages. In one form, cooling fluid is routed through a hole that exits at least partially through a pedestal formed between walls. A plurality of cooling holes can be provided through a trench face and in some forms can include a diffusion through a divergence in the hole exit. J-Hook passages can be provided through a trench face, and, in some forms, multiple trenches can be provided. A cooling hole having a neck portion can be provided, as can a cooling hole with one or more turns to reduce a total pressure. In one form, a corrugated cooling passage can be provided.

Abstract: A blade used in a gas turbine engine includes a pair of pedestals and an airfoil coupled between the pedestals. The airfoil includes cooling features to cool the airfoil.

Abstract: A seal may be used in a shroud ring of a turbine. The seal includes a first strip, a second strip, and a flow-control band that extends between and interconnects the first and second strips to control the flow of a fluid through the seal.

Abstract: A gas turbine engine component is provided that can be cooled with a cooling media such as air using a variety of passages. In one form, cooling fluid is routed through a hole that exits at least partially through a pedestal formed between walls. A plurality of cooling holes can be provided through a trench face and in some forms can include a diffusion through a divergence in the hole exit. J-Hook passages can be provided through a trench face, and, in some forms, multiple trenches can be provided. A cooling hole having a neck portion can be provided, as can a cooling hole with one or more turns to reduce a total pressure. In one form, a corrugated cooling passage can be provided.