Thermal linear actuator for rotor air flow control in a gas turbine

• US 5,054,996 A
• Filed: 07/27/1990
• Issued: 10/08/1991
• Est. Priority Date: 07/27/1990
• Status: Expired due to Fees

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Carreno, Diether
• Primary Examiner(s): Look, Edward K.
• Assistant Examiner(s): Verdier, Christopher M.
• Application Number:
  US07/558,450
• Time in Patent Office: 438 Days
• Field of Search: 415/47, 415/48, 415/115, 415/116, 415/134, 415/12, 415/146, 416/96 R, 416/97 R, 60/39.75
• US Class Current: 415/115
• 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 5/08 Heating, heat-insulating or cooling means specially adapted for radial flow machines or engines F01D5/04

Abstract

A gas turbine rotor assembly includes axially spaced rotor discs carried on a shaft, together with first and second generally cylindrical actuators mounted at each of their opposite ends to the shaft and extending toward one another to overlap at their distal ends. The actuators lie within the interior surface of the rotor discs and have openings in their overlapped portions. Upon a transient condition, the forward actuator thermally expands in an axial direction to register at least in part its openings with the openings of the second actuator to provide air flow through the partially aligned openings to opposite sides of an aft rotor disc. The second actuator thermally expands in a forward axial direction to increase the registration of the openings and, hence, the flow-through area, affording increased air flow. When approaching steady state operation, the rotor assembly expands axially to displace the openings of the second actuator into misalignment with the openings of the first actuator to prevent the flow of air through the openings, whereby cooling losses during steady state operation are avoided.

Claims

1. A gas turbine rotor assembly, comprising:

a rotatable shaft;

a plurality of turbine rotors each including a disc mounted on said shaft;

turbine buckets on said discs along their outer rims;

a pair of cylindrical actuators having opposite ends thereof secured respectively to said shaft and adjoining ends free and overlapping concentrically one within the other radially inwardly of said discs, at least one of said actuators being responsive to a change in temperature to expand in one axial direction relative to the other of said actuators, said actuators having at least one opening each therethrough and in said overlapping portions; and

means for supplying compressor extraction air within the cylindrical actuators for communication through said openings, said one actuator being movable in said one axial direction in response to a change in temperature during transient turbine operation to register at least in part its opening with the opening of said other actuator to enable air to flow from within said actuators through the registered openings to opposite sides of at least one of said rotor discs.

2. An assembly according to claim 1 wherein said other actuator is movable in an opposite axial direction in response to a change in temperature during transient operation to displace its opening to increase the area of registration of and the flow of air through the registering openings.

3. An assembly according to claim 1, wherein, at turbine rotor start-up, the openings in the overlapping actuator portions lie out of registration to preclude communication through the overlapped portions of the actuators.

4. An assembly according to claim 3 wherein said other actuator is movable in an opposite axial direction in response to a change in temperature during transient operation to displace its opening to increase the area of registration of and the flow of air through the registering openings.

5. An assembly according to claim 1 including means responsive to temperature changes during transient operation for displacing said actuators relative to one another to decrease the area of registration of and the aggregate flow of cooling air through the registering openings.

6. An assembly according to claim 5 wherein said other actuator is movable in an opposite axial direction in response to a change in temperature during transient operation to displace its openings to increase the area of registration of and the aggregate flow of air through the registering openings.

7. An assembly according to claim 6, wherein, at turbine rotor start-up, the openings in the overlapping actuator portions lie out of registration to preclude communication through the overlapped portions of the actuators.

8. An assembly according to claim 1 including a seal carried by said other actuator and sealing against the inner surface of said one disc, at least a pair of axially spaced openings carried by each said actuator.

9. An assembly according to claim 8 wherein said openings through said other actuator lie on opposite sides of said seal to enable air to flow along opposite sides of said one disc.

10. A gas turbine rotor assembly, comprising:

a rotatable shaft;

a plurality of turbine rotors each including a disc mounted on said shaft;

turbine buckets on said discs along their outer rims;

a pair of cylindrical actuators having opposite ends thereof secured respectively to said shaft and adjoining ends free and overlapping concentrically one within the other radially inwardly of said discs, at least one of said actuators being responsive to a change in temperature to expand in one axial direction relative to the other of said actuators;

said actuators having at least one opening each therethrough and in said overlapping portions, said openings at least partially registering one with the other;

means for supplying compressor extraction air within the cylindrical actuators for communication through said registering openings, said one actuator being movable in said one axial direction in response to a change in temperature during transient turbine operation to change the extent of registration of said openings relative to one another thereby to alter the flow of air from within said actuators through the registering openings to opposite sides of one of said rotor discs.

11. An assembly according to claim 10 wherein said other actuator is movable in an opposite axial direction in response to a change in temperature during transient operation to displace its opening to increase the area of registration of and the flow of air through the registering openings.

12. An assembly according to claim 10 including means responsive to temperature changes during transient operation for displacing said actuators relative to one another to decrease the area of registration of and the flow of cooling air through the registering openings.

13. A method of operating a gas turbine rotor assembly having a rotatable shaft, a plurality of turbine rotors mounted on said shaft, each including a disc with buckets along its outer rim, and a pair of cylindrical actuators defining an air channel and overlapping portions with openings therethrough for supplying air to said rotors, comprising the steps of:

(a) thermally expanding one of said actuators in one axial direction to register at least part of the openings through said one actuator with the openings through the other actuator to enable flow of air from said channel to at least one rotor; and

(b) thermally expanding the other of said actuators in an axial direction to change the extent of registration of said openings and alter the flow of air from said channel through said registering openings to said rotor.

14. A method according to claim 13 including displacing said other actuator relative to said one actuator in said one direction to alter the flow of air through said registering openings in said actuators.

15. A method according to claim 13 including displacing said other actuator to misalign the openings thereof relative to the openings in the one actuator thereby to prevent flow of air from said channel through said openings.

16. A method according to claim 13 including thermally expanding the other of said actuators in an axial direction opposite to the axial direction of thermal expansion of said one actuator to increase the extent of registration of said openings and increase the flow of air from said channel through said registering openings.

17. A method according to claim 16 including displacing said other actuator relative to said one actuator in said one direction to decrease the flow of air through said registering openings in said actuators.

18. A method according to claim 16 wherein said gas turbine has start-up and steady state operations, prior to turbine start-up operation, said actuator openings are misaligned, and including performing step (a) after start-up operation and before steady state operation.

19. A method according to claim 18 including performing step (b) before steady state operation occurs.

20. A method according to claim 19 including displacing said other actuator, prior to steady state operation, to misalign the openings thereof relative to the openings in the one actuator thereby to choke the flow, wholly or in part, from said channel through said openings.

21. A method according to claim 20 wherein the openings are misaligned and flow through the openings is choked off during steady state operation.