Impeller shroud with thermal actuator for clearance control in a centrifugal compressor

• US 10,352,329 B2
• Filed: 05/26/2016
• Issued: 07/16/2019
• Est. Priority Date: 05/26/2016
• Status: Active Grant

• Current Assignee: Rolls-Royce Corporation (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce Corporation (Rolls-Royce Holdings Plc)
• Inventors: Nesteroff, Michael, Acker, Jonathan, Cooper, Nate, Ottow, Nathan
• Primary Examiner(s): Seabe, Justin D
• Assistant Examiner(s): Haghighian, Behnoush
• Application Number:
  US15/165,404
• Publication Number:
  US 20170342994A1
• Time in Patent Office: 1,146 Days
• CPC Class Codes: F01D 11/08 for sealing space between rotor blade tips and stator specially-shaped blade tips therefor F01D5/20
• CPC Class Codes: F01D 11/18 using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion
• 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 11/24 by selectively cooling-heating stator or rotor components
• CPC Class Codes: F04D 27/0246 by varying geometry within the pumps, e.g. by adjusting vanes
• CPC Class Codes: F04D 29/162 of a centrifugal flow wheel
• 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
• CPC Class Codes: F04D 29/624 especially adapted for elastic fluid pumps

Abstract

A system for controlling the clearance distance between an impeller blade tip of a centrifugal compressor and a radially inner surface of an impeller shroud in a turbine engine. The system comprises a thermal driver coupled between the impeller shroud and engine casing by hinged linkages. The thermal driver includes an annular ring and annular seal which together define thermal driver cavity. Relatively warm or relatively cool air supplied to the thermal driver cavity cause expansion and contraction, respectively, of the annular ring which is translated by linkages into axially forward and aft motion, respectively.

Claims

1. A compressor shroud assembly in a turbine engine comprising:

a static compressor casing;

a thermal actuator comprising;

one or more linkage assemblies mounted to said casing and being spaced around the circumference thereof;

an annular thermal drive member mounted to said linkage assemblies; and

an impeller shroud for encasing a rotatable centrifugal compressor and maintaining a clearance gap between the impeller shroud and the rotatable centrifugal compressor, wherein the impeller shroud is slidably coupled at a forward end to said casing and mounted to said linkage assemblies, said impeller shroud moving relative to the rotatable centrifugal compressor in an axial direction while substantially maintaining a radial alignment when said thermal actuator is actuated.

2. The compressor shroud assembly of claim 1 wherein said linkage assemblies each comprise a forward linkage pivotally mounted to said casing, an aft linkage pivotally mounted to said shroud, and a central linkage pivotally mounted to said forward and aft linkages.

3. The compressor shroud assembly of claim 2 wherein said annular thermal drive member is mounted to said central linkage and is adapted to radially expand or contract responsive to exposure to an actuating temperature, said annular thermal drive member expanding radially to effect movement of said shroud in an axially forward direction, said annular thermal drive member contracting radially to effect movement of said shroud in an axially aft direction.

4. The compressor shroud assembly of claim 3 wherein said annular thermal drive member is exposed to an actuating temperature by exposure to one or more of an actuating air, electrical heating elements, lubricant flow, or fluid flow.

5. The compressor shroud assembly of claim 4 wherein said annular thermal drive member is exposed to air drawn from the core air of the turbine engine.

6. The compressor shroud assembly of claim 2 further comprising an annular thermal drive ring coupled to the central linkage and adapted to axially expand or contract responsive to exposure to an actuating temperature, said annular thermal drive ring contracting axially to effect movement of said shroud in an axially forward direction, said annular thermal drive ring expanding axially to effect movement of said shroud in an axially aft direction.

7. The compressor shroud assembly of claim 6 wherein said annular thermal drive ring is exposed to an actuating temperature by exposure to one or more of an actuating air, electrical heating elements, lubricant flow, or fluid flow.

8. The compressor shroud assembly of claim 7 wherein said annular thermal drive ring is exposed to air drawn from the core air of the turbine engine.

9. The compressor shroud assembly of claim 1 wherein a slidable coupling between said shroud and said casing is dimensioned to maintain an air boundary during the full range of axial movement of said shroud.

10. The compressor shroud assembly of claim 3 further comprising one or more sensors for measuring the temperature in a cavity at least partly defined by said annular thermal drive member, said annular thermal drive member being exposed to warmer or cooler actuating temperatures in response to the measured temperature in said cavity.

11. The compressor shroud assembly of claim 10 further comprising one or more sensors for measuring the clearance gap between said shroud and the rotatable centrifugal compressor, said annular thermal drive member being exposed to warmer or cooler actuating temperatures in response to the clearance gap measure by the one or more sensors.

12. The compressor shroud assembly of claim 6 further comprising one or more sensors for measuring the temperature in a cavity at least partly defined by said annular thermal drive ring, said annular thermal drive ring being exposed to warmer or cooler actuating temperatures in response to the measured temperature in said cavity.

13. A compressor shroud assembly in a turbine engine comprising:

a static compressor casing;

a thermal actuator comprising;

one or more linkage assemblies mounted to said casing and being spaced around the circumference thereof;

a thermal drive member mounted to said linkage assemblies; and

an impeller shroud for encasing a rotatable centrifugal compressor and maintaining a clearance gap between the impeller shroud and the rotatable centrifugal compressor, wherein the impeller shroud is mounted at a forward end to said casing and mounted to said linkage assemblies, said impeller shroud moving relative to the rotatable centrifugal compressor in a cantilevered manner from said forward end thereof when said thermal actuator is actuated.

14. The compressor shroud assembly of claim 13 wherein said linkage assemblies each comprise a forward linkage pivotally mounted to said casing, an aft linkage pivotally mounted to said shroud, and a central linkage pivotally mounted to said forward and aft linkages;

and wherein said ring is mounted to said central linkage and adapted to radially expand or contract responsive to exposure to an actuating temperature, said ring expanding radially to effect movement of said shroud in an axially forward direction, said ring contracting radially to effect movement of said shroud in an axially aft direction.

15. A method of dynamically changing a clearance gap between a rotatable centrifugal compressor and a shroud encasing the rotatable centrifugal compressor, said method comprising:

mounting a thermal driver comprising a ring and a plurality of linkage assemblies to a static casing;

mounting a shroud to the thermal driver; and

actuating the thermal driver to thereby move the shroud relative to a rotatable centrifugal compressor.

16. The method of claim 15 further comprising providing actuating air to actuate the thermal driver.

17. The method of claim 16 wherein said actuating air is one of inducer air, exducer air, intermediate stage compressor air, or discharge air from the centrifugal compressor.

18. The method of claim 15 further comprising slidably coupling the forward end of the shroud to the casing, wherein the shroud moves relative to the rotatable centrifugal compressor in an axial direction while substantially maintaining a radial alignment when the thermal driver is actuated.

19. The method of claim 15 further comprising sensing the fluid temperature in a cavity at least partly defined by said thermal driver and actuating the thermal driver in response to the sensed fluid temperature.

20. The method of claim 15 further comprising sensing the clearance gap between the rotatable centrifugal compressor and the shroud and actuating the thermal driver in response to the sensed clearance gap.