Gas turbine engine vane end devices

• US 10,370,995 B2
• Filed: 11/28/2017
• Issued: 08/06/2019
• Est. Priority Date: 02/26/2013
• Status: Active Grant

• Current Assignee: Rolls-Royce Corporation (Rolls-Royce Holdings Plc), Rolls-Royce North American Technologies, Inc. (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce North American Technologies, Inc. (Rolls-Royce Holdings Plc)
• Inventors: Taketa, Linnea, Munson, John, Freeman, Ted J.
• Primary Examiner(s): Verdier, Christopher
• Application Number:
  US15/824,467
• Publication Number:
  US 20180156052A1
• Time in Patent Office: 616 Days
• Field of Search: 4151731, 4151732, 4151733, 4151741, 4151742, 4151701, 415230, 415231, 415148, 415150-151, 415159-166, 416 87, 416 88, 416 89
• CPC Class Codes: F01D 11/00 Preventing or minimising internal leakage of working-fluid, e.g. between stages sealings in general F16J ; sealing arrangements for transition ducts of combustor cans F01D9/023
• CPC Class Codes: F01D 11/005 Sealing means between non relatively rotating elements
• CPC Class Codes: F01D 11/02 by non-contact sealings, e.g. of labyrinth type for sealing space between rotor blade tips and stator F01D11/08
• CPC Class Codes: F01D 11/025 Seal clearance control; Floating assembly; Adaptation means to differential thermal dilatations
• CPC Class Codes: F01D 11/122 with erodable or abradable material blades having cutting or grinding tips F01D5/20
• CPC Class Codes: F01D 17/148 by means of rotatable members, e.g. butterfly valves
• CPC Class Codes: F01D 17/162 for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line F01D17/167 takes precedence
• CPC Class Codes: F01D 17/165 for radial flow, i.e. the vanes turning around axes which are essentially parallel to the rotor centre line F01D17/167 takes precedence
• CPC Class Codes: F01D 5/28 Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
• CPC Class Codes: F01D 9/041 using blades F01D5/148 takes precedence
• CPC Class Codes: F04D 19/02 Multi-stage pumps
• CPC Class Codes: F04D 27/002 by varying geometry within the pumps, e.g. by adjusting vanes
• CPC Class Codes: F04D 27/0246 by varying geometry within the pumps, e.g. by adjusting vanes
• CPC Class Codes: F04D 29/083 especially adapted for elastic fluid pumps
• CPC Class Codes: F04D 29/164 of an axial flow wheel
• CPC Class Codes: F05B 2240/571 Brush seals
• CPC Class Codes: F05D 2240/56 Brush seals
• CPC Class Codes: F16J 15/3288 Filamentary structures, e.g. brush seals

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.

Claims

1. 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 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 that defines 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,

wherein the fluid obstruction includes a first portion that is received within the internal opening and a second portion that has a convex rounded head configured to engage the wall of the gas turbine engine, the second portion extends away from the first portion beyond the internal opening toward a pressure side and a suction side of the gas turbine engine, and the seal is located between the surface that defines the internal opening and the first portion of the fluid obstruction.

2. The apparatus of claim 1, wherein the fluid obstruction extends along a portion of a chord of the rotatable airfoil member.

3. The apparatus of claim 1, wherein the seal discourages passage of air between a working flow path of the gas turbine engine and an internal space of the rotatable airfoil member and wherein the rotatable airfoil member is a variable turbine vane.

4. The apparatus of claim 1, wherein the seal is a rope seal and wherein the rotatable airfoil member is a turbine vane.

5. The apparatus of claim 1, wherein the rotatable airfoil member is formed to include a cutout that opens into the internal opening and the seal is received in the cutout.

6. 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 relative to an axis, 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 member that extends through the first end of the airfoil member into the interior, the member configured to provide fluid obstruction between the airfoil member and the wall,

wherein the airfoil member includes a pressure side and a suction side spaced apart from the pressure side, the member includes a piston that is located in the interior formed in the airfoil member and a head that is coupled to the piston, the head extends toward the pressure side and the suction side of the airfoil member, and the head has a convex-shaped outer surface when viewed circumferentially.

7. The apparatus of claim 6, wherein the airfoil member is a rotatable vane configured to assume a plurality of orientations relative to the wall.

8. The apparatus of claim 7, further comprising a seal located in the interior and disposed between the airfoil member and the piston and the seal are configured to discourage a flow of working fluid between the interior and a flow path of the gas turbine engine.

9. The apparatus of claim 8, wherein the seal is a rope seal.

10. The apparatus of claim 8, wherein the airfoil member is formed to include a cutout that opens into the interior and the seal is received in the cutout.