Segregated impeller shroud for clearance control in a centrifugal compressor

• US 10,408,226 B2
• Filed: 05/26/2016
• Issued: 09/10/2019
• 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: Ottow, Nathan, Acker, Jonathan, Cooper, Nate, Whitlock, Mark, Nesteroff, Michael
• Primary Examiner(s): Rivera, Carlos A
• Assistant Examiner(s): Haghighian, Behnoush
• Application Number:
  US15/165,728
• Publication Number:
  US 20170342995A1
• Time in Patent Office: 1,202 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 11/22 by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor
• CPC Class Codes: F01D 25/24 Casings modified for heating or cooling F01D25/14; Casing parts, e.g. diaphragms, casing fastenings casings for rotary machines or engines in general F16M ; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045
• 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: F05D 2220/3219 for the last stage of a compressor or a high pressure compressor
• CPC Class Codes: F05D 2240/11 Shroud seal segments
• CPC Class Codes: F05D 2250/281 threaded
• CPC Class Codes: F05D 2260/57 using servos, independent actuators, etc.
• CPC Class Codes: F05D 2270/3013 Outlet pressure
• CPC Class Codes: F05D 2270/305 Tolerances

Abstract

A system for controlling the clearance distance between an impeller blade tip of a centrifugal compressor and a radially inner surface of a segregated impeller shroud in a turbine engine. The system comprises a driving mechanism coupled to a portion of a segregated impeller shroud. The driving mechanism comprises a driving arm and threaded axial member configured to translate motion of an actuator ring into axially forward and aft motion of the portion of the segregated impeller shroud.

Claims

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

a static compressor casing;

an actuator carried by said casing, said actuator comprising a driving member extending along a radius of the axis of rotation of a rotatable centrifugal compressor and being rotatable about the axis, and a driving mechanism coupled to said driving member to rotate said driving member about the axis of rotation when said actuator is activated; and

an impeller shroud carried by said casing for encasing the rotatable centrifugal compressor, said shroud being threadably coupled to said driving member so that rotation of said driving member about the axis of rotation of the rotatable centrifugal compressor effects translation of at least a portion of said shroud relative to the rotatable centrifugal compressor in an axial direction while maintaining a radial alignment of said portion of said shroud.

2. The compressor shroud assembly of claim 1 wherein said threaded coupling between said driving member and said shroud comprises driving threads which rotate with said driving member while maintaining an axial alignment, and driven threads which translate axially with said portion of said shroud, and wherein said shroud forms a slidable coupling with said casing at a forward end thereof.

3. The compressor shroud assembly of claim 1 wherein said actuator comprises two or more driving members spaced around the axis of rotation of said driving members.

4. The compressor shroud assembly of claim 3 further comprising an actuating ring coupled to each of said driving members and to said driving mechanism.

5. The compressor shroud assembly of claim 1 wherein said shroud comprises a static inducer portion statically coupled to said casing, and an axially translatable exducer portion threadably coupled to said inducer portion and statically coupled to said driving member, the threaded coupling between said inducer portion and said exducer portion comprising static threads which maintain an axial alignment and moveable threads which rotate and axially translate with said driving member and said exducer portion to effect translation of said exducer portion relative to the rotatable centrifugal compressor in an axial direction.

6. The compressor shroud assembly of claim 5 wherein said actuator comprises two or more driving members spaced around the axis of rotation of said driving members.

7. The compressor shroud assembly of claim 6 further comprising an actuating ring coupled to each of said driving members and to said driving mechanism.

8. The compressor shroud assembly of claim 1 further comprising one or more sensors for measuring the clearance gap between said axially translatable portion of said shroud and the rotatable centrifugal compressor, said actuator being activated in response to the clearance gap measured by the one or more sensors.

9. The compressor shroud assembly of claim 1 further comprising one or more sensors for measuring discharge pressure of the rotatable centrifugal compressor, said actuator being activated in response to the measured pressure.

10. The compressor shroud assembly of claim 5 wherein said exducer portion comprises a first exducer portion threadably coupled to a second exducer portion, each of said exducer portions being axially translatable.

11. A compressor shroud assembly in a turbine engine, said compressor shroud assembly comprising:

a static compressor casing;

an actuator carried by said casing;

an impeller shroud for encasing a rotatable centrifugal compressor, said shroud comprising

an inducer portion mounted to said casing; and

an exducer portion coupled to said inducer portion and said actuator,

said actuator being operable to rotate about the axis of the centrifugal compressor to effect translation of said exducer portion relative to the rotatable centrifugal compressor in an axial direction while maintaining a radial alignment of said exducer portion.

12. The compressor assembly of claim 11 further comprising a threaded coupling between said inducer portion and said exducer portion wherein relative rotation about the axis of the compressor between said inducer portion and said exducer portion effects axial translation of said exducer portion.

13. The compressor assembly of claim 11 further comprising a threaded coupling between said exducer portion and said actuator, wherein relative rotation about the axis of the compressor between said exducer portion and said actuator effects axial translation of said exducer portion.

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

coupling an actuator to a static casing;

coupling an impeller shroud to the actuator by a threaded coupling, the impeller shroud being positioned to encase a rotatable centrifugal compressor; and

rotating the actuator about the rotation axis of the centrifugal compressor to thereby effect translation of at least a portion of the shroud relative to the centrifugal compressor in an axial direction.

15. The method of claim 14 comprising rotating the actuator relative to a portion of the shroud to effect axial translation of the portion of the shroud while maintaining the axial alignment of the actuator.

16. The method of claim 14 comprising rotating the actuator relative to a first portion of the shroud to effect axial translation of a second portion of the shroud while maintaining an axial alignment of the first portion of the shroud.

17. The method of claim 14 comprising activating the actuator responsive to sensing a clearance gap between the shroud and the compressor.

18. The method of claim 14 comprising activating the actuator responsive to sensing discharge pressure of the rotatable centrifugal compressor.

19. The method of claim 17 wherein the clearance gap is sensed by more than one clearance gap sensor positioned along the length of the shroud.

20. The method of claim 18 wherein the discharge pressure is sensed by a pressure sensor in fluid communication with a discharge plenum of the centrifugal compressor.

21. A compressor section in a gas turbine engine, said compressor section comprising:

a static casing;

a rotatable centrifugal compressor; and

a compressor shroud assembly comprising;

an actuator carried by said casing, said actuator comprising a driving member extending along a radius of the axis of rotation of a rotatable centrifugal compressor and being rotatable about the axis, and a driving mechanism coupled to said driving member to rotate said driving member about the axis of rotation when said actuator is activated; and

an impeller shroud carried by said casing for encasing said rotatable centrifugal compressor, said shroud being threadably coupled to said driving member so that rotation of said driving member about the axis of rotation of the rotatable centrifugal compressor effects translation of at least a portion of said shroud relative to the rotatable centrifugal compressor in an axial direction while maintaining a radial alignment of said portion of said shroud.