Gas turbine engine vane end devices
First Claim
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1. An apparatus comprising:
- a rotatable airfoil member for a gas turbine engine having an end structured to contact a wall of the gas turbine engine, the end having an abradable coating configured to wear according to a contact between the abradable coating and the wall of the gas turbine engine,wherein the rotatable airfoil member is disposed adjacent a rotatable blade and the rotatable airfoil member is configured to turn a working fluid, the rotatable blade configured to rotate around a central axis of the gas turbine engine, and the rotatable airfoil member is rotatable about a rotation axis that extends perpendicularly from the central axis,wherein the end of the rotatable airfoil member defines two squealer tips integrally formed with the rotatable airfoil member such that the two squealer tips are blocked from moving radially relative to the rotatable airfoil member, the two squealer tips spaced apart from each other, wherein the abradable coating is applied to a radial outer tip of each of the two squealer tips, and the two squealer tips engage the wall of the gas turbine engine, andwherein the rotatable airfoil member is a turbine vane, and the turbine vane includes a cooling hole disposed between the two squealer tips.
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Abstract
A turbomachinery component of a gas turbine engine is disclosed having a number of techniques of reducing the effects of a gap flow between an airfoil member of the gas turbine engine and a wall of the gas turbine engine. The airfoil member can be variable and in one form is a variable turbine vane. In one embodiment a brush seal is included between the vane and the wall. In another form a wear surface is disposed between the vane and the wall. In yet another form a moveable member capable of being actuated to change position can be disposed between the vane and the wall to alter the size of a gap between the two.
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Citations
18 Claims
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1. An apparatus comprising:
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a rotatable airfoil member for a gas turbine engine having an end structured to contact a wall of the gas turbine engine, the end having an abradable coating configured to wear according to a contact between the abradable coating and the wall of the gas turbine engine, wherein the rotatable airfoil member is disposed adjacent a rotatable blade and the rotatable airfoil member is configured to turn a working fluid, the rotatable blade configured to rotate around a central axis of the gas turbine engine, and the rotatable airfoil member is rotatable about a rotation axis that extends perpendicularly from the central axis, wherein the end of the rotatable airfoil member defines two squealer tips integrally formed with the rotatable airfoil member such that the two squealer tips are blocked from moving radially relative to the rotatable airfoil member, the two squealer tips spaced apart from each other, wherein the abradable coating is applied to a radial outer tip of each of the two squealer tips, and the two squealer tips engage the wall of the gas turbine engine, and wherein the rotatable airfoil member is a turbine vane, and the turbine vane includes a cooling hole disposed between the two squealer tips. - View Dependent Claims (2, 3, 4, 5)
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6. An apparatus comprising:
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a rotatable airfoil member for a gas turbine engine, the rotatable airfoil member having a first end and a second end spaced apart radially from the first end relative to a central axis of the gas turbine engine such that the rotatable airfoil member extends radially relative to the central axis, the first end of the rotatable airfoil member formed to include a first squealer member that is integrally formed with the first end so that the first squealer member is blocked from moving radially relative to the first end, and wherein the first squealer member extends radially outward away from the first end relative to the central axis, the rotatable airfoil member configured to rotate about a rotation axis that extends radially through the rotatable airfoil member, and the rotation axis is perpendicular to the central axis; and a wall arranged circumferentially around the first end of the rotatable airfoil member relative to the central axis; wherein the rotatable airfoil member further includes a first wear surface disposed on a radial terminating tip of the first squealer member, the first wear surface configured to engage the wall in response to the rotatable airfoil member rotating about the rotation axis, and the first wear surface is configured to be abraded when relative movement between the rotatable airfoil member and the wall causes the rotatable airfoil member and the wall to contact each other. - View Dependent Claims (7, 8, 9, 10, 11, 12, 13, 14, 15, 16, 17, 18)
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Specification