Gas turbine engine vane end devices
AssigneesRolls-Royce North American Technologies Inc., ROLLS-ROYCE plc
InventorsLinnea Taketa, John Munson, Ted J. Freeman
Life of this patent
Estimating the term…
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.
Claims20
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 coating and the wall of the gas turbine engine.
An apparatus comprising:
- a rotatable airfoil member of a gas turbine engine having a surface that defines an internal opening, the rotatable airfoil capable of being positioned at a plurality of orientations, the rotatable airfoil member operable to be disposed within a flow path of the gas turbine engine;
- a fluid obstruction received within the internal opening and configured to adjust toward and away from the internal opening to engage a wall of the gas turbine engine as the rotatable airfoil member is positioned at the plurality of orientations;
- and
- a seal disposed between the surface of the internal opening and the fluid obstruction, the seal structured to discourage a flow of working fluid between the internal opening of the rotatable airfoil member and the flow path of the gas turbine engine.
An apparatus comprising:
- an airfoil member for a gas turbine engine, the airfoil member having a first end and a second end spaced apart radially from the first end, the airfoil member formed to include an interior that opens into the first end;
- a wall arranged circumferentially around the first end of the airfoil member;
- and
- a movable member that extends through the first end of the airfoil member into the interior, the movable member configured to move radially toward the wall relative to the airfoil member to provide fluid obstruction between the airfoil member and the wall in response to a relative pressure difference between the interior of the airfoil member and an exterior of the airfoil member.
Dependencies are inferred from the claim text.