Blade clearance control for gas turbine engine

• US 9,587,507 B2
• Filed: 12/30/2013
• Issued: 03/07/2017
• Est. Priority Date: 02/23/2013
• Status: Active Grant

• Current Assignee: Rolls-Royce North American Technologies, Inc. (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce North American Technologies, Inc. (Rolls-Royce Holdings Plc)
• Inventors: Ottow, Nathan W.
• Primary Examiner(s): Kershteyn, Igor
• Application Number:
  US14/143,567
• Publication Number:
  US 20150016946A1
• Time in Patent Office: 1,163 Days
• US Class Current: 1/1
• CPC Class Codes: F01D 11/22 by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor
• CPC Class Codes: F01D 5/043 of the axial inlet- radial outlet, or vice versa, type
• CPC Class Codes: F04D 29/4206 especially adapted for elastic fluid pumps
• CPC Class Codes: F04D 29/622 Adjusting the clearances between rotary and stationary parts

Abstract

An apparatus and method for controlling a clearance between the blades of a turbomachinery component and flow forming surface are disclosed herein, and includes controlling the clearance by moving the surface axially relative to the turbomachinery component. In one embodiment the apparatus includes an impeller rotatable about a first axis, a shroud encircling the impeller, and a first ring encircling the first axis. An actuator is operably engaged with the first ring to pivot the first ring about the first axis. The apparatus also includes at least one cam engaged with the first ring and at least one cam follower engaged with the shroud. Pivoting movement of the first ring about the first axis results in the at least one cam urging the at least one cam follower and the shroud along the first axis to vary a distance between the plurality of blades and the shroud.

Claims

1. An apparatus comprising:

a gas turbine engine bladed turbomachinery component centered on a first axis and operable to rotate about said first axis, said bladed turbomachinery component including an inner base and a plurality of blades extending radially outward from said inner base and also extending along said first axis, wherein a plurality of fluid channels are respectively defined between adjacent pairs of said plurality of blades;

a flow path forming component encircling said bladed turbomachinery component and substantially enclosing a radially outward side of said blades along said first axis;

a pivoting member circumferentially extending about said first axis and adjacent to at least part of said flow path forming component along said first axis;

an actuator operably engaged with said pivoting member to pivot said pivoting member about said first axis;

at least one cam engaged with said pivoting member; and

at least one cam follower engaged with said flow path forming component, wherein pivoting movement of said pivoting member about said first axis results in said at least one cam urging said at least one cam follower and said flow path forming component along said first axis to vary a distance between said plurality of blades and said flow path forming component.

2. The apparatus of claim 1, wherein the bladed turbomachinery component is an impeller, wherein each of said plurality of channels includes a fluid channel exit directed radially outward relative to said first axis, wherein one of said at least one cam and said at least one cam follower is a wheel rotatable about a second axis extending transverse to said first axis and wherein the other of said at least one cam and at least one cam follower is a ramp having a bottom edge and a top edge spaced from one another about said first axis and also along said first axis.

3. The apparatus of claim 1, wherein the pivoting member is a first ring, and further comprising:

a second ring circumferentially extending about said first axis and extending between first and second ends, wherein said first end is fixed said flow path forming component, said ring being elastically deformable in response to said cam urging said cam follower and said flow path forming component along said first axis to vary a distance between said plurality of blades and said flow path forming component; and

wherein the flow path forming component is a shroud, and wherein the turbomachinery component is an impeller.

4. The apparatus of claim 3, wherein said first end and said second end are radially spaced from one another relative to said first axis.

5. The apparatus of claim 3, wherein said second ring includes a bulbous portion between said first and second ends, and wherein said actuator is at least partially received in said bulbous portion.

6. The apparatus of claim 1, wherein the cam and cam follower are in sliding engagement.

7. The apparatus of claim 6, wherein the sliding engagement is defined by a threaded engagement and wherein the cam and cam follower are annular.

8. A method comprising:

spinning a gas turbine engine bladed component within a flow path surface about a first axis to change a pressure of a working fluid;

moving a pivoting member about the first axis in a circumferential direction;

interacting a cam and a cam follower as the pivoting member moves circumferentially; and

axially adjusting the flow path surface to adjust a clearance between the flow path surface and the gas turbine engine bladed component as a result of the interacting.

9. The method of claim 8, further comprising:

actuating a shaft to cause the moving;

wherein the cam takes the form of one of a wheel and a ramp; and

wherein the gas turbine engine bladed component is a centrifugal impeller.

10. The method of claim 8, further comprising:

wherein the axially adjusting includes biasing the flow path surface away from the gas turbine engine bladed component with a plate extending fully around the first axis and fixed to the flow path surface at a radially inner end;

wherein the flow path surface is a shroud; and

wherein the gas turbine engine bladed component is a gas turbine engine impeller.

11. The method of claim 10, further comprising:

engaging the pivoting member to a static engine structure through a roller; and

interconnecting a radially-outer end of the plate with a static structure.

12. The method of claim 8, wherein:

the interacting includes slidingly interacting the cam and cam follower.

13. A turbine engine comprising:

a gas turbine engine bladed turbomachinery component centered on a first axis and operable to rotate about said first axis, said bladed turbomachinery component including a base and plurality of blades extending radially outward from said base and also extending along said first axis, wherein a plurality of fluid channels are respectively defined between adjacent pairs of said plurality of blades;

a flow path forming surface encircling said bladed turbomachinery component and substantially enclosing an outward side of said blades;

a pivoting member encircling said first axis and adjacent to at least part of said flow path forming surface along said first axis;

an actuator operably engaged with said pivoting member to pivot said pivoting member about said first axis;

a plurality of cams engaged with and spaced from one another about said pivoting member; and

a plurality of cam followers engaged with and spaced from one another about said flow path forming surface, wherein pivoting movement of said pivoting member about said first axis results in each of said plurality of cams urging a corresponding one of said plurality of cam followers and said flow path forming surface along said first axis to vary a distance between said plurality of blades and said flow path forming surface.

14. The turbine engine of claim 13, wherein the pivoting member is a ring, and wherein each of said plurality of cams are respective wheels rotatable about individual second axes extending transverse to said first axis, wherein the flow path forming surface is a shroud, and wherein each of said plurality of channels includes a fluid channel exit directed radially outward relative to said first axis.

15. The turbine engine of claim 13, further comprising:

a first casing member defining a cylindrical surface and an annular flange projecting radially outward from said cylindrical surface, wherein said pivoting member encircles said cylindrical surface and abuts said annular flange;

a first plurality of rollers mounted on said pivoting member and riding along said cylindrical surface; and

a second plurality of rollers mounted on said pivoting member and riding along said annular flange;

wherein the gas turbine engine bladed turbomachinery component is an impeller.

16. The turbine engine of claim 13, further comprising:

a first casing member defining a cylindrical surface and a first annular flange projecting radially outward from said cylindrical surface, wherein said pivoting member encircles and rotates about said cylindrical surface and abuts said first annular flange;

a second casing member fixed to said first casing member at a first axial end and extending away from said first axial end along said first axis to second axial end;

a spring fixed at a radially-outer end to said second axial end of said second casing member and fixed at a radially-inner end to said flow path forming surface, said spring operable to generate a biasing force urging said flow path forming surface against said pivoting member; and

wherein the gas turbine engine bladed turbomachinery component is an impeller.

17. The turbine engine of claim 16, further comprising:

a plurality of rollers mounted on said pivoting member and riding along said first annular flange, each of said plurality of rollers radially aligned with one of said plurality of cams.

18. The turbine engine of claim 17, wherein said flow path forming surface includes a second annular flange confronting said first annular flange and wherein each of said plurality of cam followers is further defined as a ramp formed in said second annular flange and facing toward said first annular flange, and wherein said actuator is disposed in an annular cavity defined by said first casing member, said second casing member, and said spring.

19. The turbine engine of claim 13, wherein the plurality of cams and plurality of cam followers are distributed axially along the first pivoting member.

20. The turbine engine of claim 19, wherein the plurality of cams and plurality of cam followers are defined by a threaded interengagement that helically wraps circumferentially around the first pivoting member.