Abstract: An air seal is provided which extends axially between a first side and a second side. The air seal includes an axial flange, a radial flange, a seal element, a retainer neck and a retainer head. The axial flange extends axially to the second side. The radial flange is connected to the axial flange at the second side. The radial flange projects radially outward from the axial flange to a distal end. The seal element projects radially outward from the distal end of the radial flange. The retainer neck is connected to the radial flange at the distal end of the radial flange. The retainer neck projects axially out from the radial flange towards the first side and then projects radially outward to the retainer head. The retainer head projects axially towards the first side and away from the retainer neck to an axial end of the retainer head.

Abstract: A vane has an airfoil extending between a radially outer platform and a radially inner platform. At least one of the platforms has nominally radially thinner portions, and a pad defining a radially thicker portion. The pad has a radial thickness that is greater than a thickness of the nominal radially thinner portions. The pad surrounds an outer periphery of the airfoil on a side of the radially outer platform. The pad has a varying radial thickness. A mid-turbine frame and a gas turbine engine are also disclosed.

Abstract: A vane for use in a gas turbine engine has an airfoil extending between a leading edge and a trailing edge, and is generally hollow. The vane has a radially outer platform and a radially inner platform. At least one of the radially inner and radially outer platforms has thicker portions circumferentially located beyond one of the leading edge and the trailing edge, and thinner portions circumferentially beyond circumferential edges of the airfoil. A mid-turbine frame and a gas turbine engine are also disclosed.

Abstract: A turbine vane includes an inner platform and an outer platform joined together by an airfoil. The airfoil has a leading edge and a trailing edge joined together by a pressure side and a suction side disposed opposite the pressure side. The inner platform defines a plurality of first inner cooling holes and a plurality of second inner cooling holes that are fluidly connected to an inner cooling passage. The plurality of first inner cooling holes are disposed proximate the leading edge and extend towards the suction side and the plurality of second inner cooling holes are disposed proximate the trailing edge and the suction side and extend towards the leading edge.

Abstract: An engine component for isolating a first pressure and/or first flow and a second pressure and/or second flow is provided. The engine component may comprise a body portion, a first seal element and a second seal element. The body portion may include a first standoff and a second standoff. The first seal element housed within the body portion. The second seal element may also be housed within the body portion. The second seal element may be coupled to the first seal element.

Abstract: An airfoil is disclosed, comprising an airfoil body and an internal cavity within the airfoil body. The internal cavity may comprise an outer edge comprising a first outer scallop and a second outer scallop, an inner edge opposite the outer edge, the inner edge comprising a first inner scallop and a second inner scallop, a leading edge spanning between the outer edge and the inner edge, and a trailing edge spanning between the outer edge and the inner edge and opposite the leading edge. Between the outer edge, the inner edge, the leading edge, and the trailing edge, the internal cavity may comprise eight columns of pedestals disposed axially relative to one another and axially between the leading edge and the trailing edge.

Abstract: An interface within a gas turbine engine includes a sealing surface defined by a portion of a vane platform. A seal is in contact with said sealing surface. A barrier is transverse to the sealing surface.

Abstract: A turbine vane includes an inner platform and an outer platform joined together by an airfoil. The airfoil has a leading edge and a trailing edge joined together by a pressure side and a suction side disposed opposite the pressure side. The inner platform defines a plurality of first inner cooling holes and a plurality of second inner cooling holes that are fluidly connected to an inner cooling passage. The plurality of first inner cooling holes are disposed proximate the leading edge and extend towards the suction side and the plurality of second inner cooling holes are disposed proximate the trailing edge and the suction side and extend towards the leading edge.

Abstract: An airfoil extends between radially inner and radially outer platforms. The airfoil extends between a leading edge and a trailing edge, and merges into facing surfaces of the radially inner and outer platforms. A variable fillet merges a facing surface of one of the radially inner and outer platforms into a wall of the airfoil. The variable fillet has a length extending away from a surface of the airfoil and a height extending away from the facing surface of at least one of the radially inner and outer platforms outwardly on to the airfoil. The variable fillet has a greater length at one of the leading edge and the trailing edge. A spaced portion has a shorter length at locations spaced from at least one of the leading and trailing edges. A mid-turbine frame and a gas turbine engine are also disclosed.

Abstract: An airfoil is disclosed, comprising an airfoil body and an internal cavity within the airfoil body. The internal cavity may comprise an outer edge comprising a first outer scallop and a second outer scallop, an inner edge opposite the outer edge, the inner edge comprising a first inner scallop and a second inner scallop, a leading edge spanning between the outer edge and the inner edge, and a trailing edge spanning between the outer edge and the inner edge and opposite the leading edge. Between the outer edge, the inner edge, the leading edge, and the trailing edge, the internal cavity may comprise eight columns of pedestals disposed axially relative to one another and axially between the leading edge and the trailing edge.

Abstract: A vane for use in a gas turbine engine has an airfoil extending between a leading edge and a trailing edge, a radially outer platform and a radially inner platform. A rib is on one of the radially inner and radially outer platforms, and is adjacent the trailing edge of the airfoil. A mid-turbine frame is also disclosed.

Abstract: An interface within a gas turbine engine includes a sealing surface defined by a portion of a vane platform. A seal is in contact with said sealing surface. A barrier is transverse to the sealing surface.

Abstract: An airfoil extends between radially inner and radially outer platforms. The airfoil extends between a leading edge and a trailing edge, and merges into facing surfaces of the radially inner and outer platforms. A variable fillet merges a facing surface of one of the radially inner and outer platforms into a wall of the airfoil. The variable fillet has a length extending away from a surface of the airfoil and a height extending away from the facing surface of at least one of the radially inner and outer platforms outwardly on to the airfoil. The variable fillet has a greater length at one of the leading edge and the trailing edge. A spaced portion has a shorter length at locations spaced from at least one of the leading and trailing edges. A mid-turbine frame and a gas turbine engine are also disclosed.

Abstract: A vane has an airfoil extending between a radially outer platform and a radially inner platform. At least one of the platforms has nominally radially thinner portions, and a pad defining a radially thicker portion. The pad has a radial thickness that is greater than a thickness of the nominal radially thinner portions. The pad surrounds an outer periphery of the airfoil on a side of the radially outer platform. The pad has a varying radial thickness. A mid-turbine frame and a gas turbine engine are also disclosed.

Abstract: A vane for use in a gas turbine engine has an airfoil extending between a leading edge and a trailing edge, and is generally hollow. The vane has a radially outer platform and a radially inner platform. At least one of the radially inner and radially outer platforms has thicker portions circumferentially located beyond one of the leading edge and the trailing edge, and thinner portions circumferentially beyond circumferential edges of the airfoil. A mid-turbine frame and a gas turbine engine are also disclosed.

Abstract: An engine component for isolating a first pressure and/or first flow and a second pressure and/or second flow is provided. The engine component may comprise a body portion, a first seal element and a second seal element. The body portion may include a first standoff and a second standoff. The first seal element housed within the body portion. The second seal element may also be housed within the body portion. The second seal element may be coupled to the first seal element.