Dynamic control of a gas turbine engine compressor during rapid transients

• US 20100281875A1
• Filed: 10/15/2007
• Published: 11/11/2010
• Est. Priority Date: 10/13/2006
• Status: Active Grant

• Current Assignee: Rolls-Royce Power Engineering PLC (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce Power Engineering PLC (Rolls-Royce Holdings Plc)
• Inventors: Price, Brian John, Demers, Louis
• Granted Patent: US 8,302,405 B2
• Time in Patent Office: Days
• US Class Current: 60/772
• 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: F02C 3/107 with two or more rotors connected by power transmission
• CPC Class Codes: F02C 7/057 Control or regulation conjointly with fuel supply control F02C9/50, with nozzle area control F02K1/16
• CPC Class Codes: F05D 2240/40 Use of a multiplicity of similar components
• CPC Class Codes: F05D 2240/61 Hollow
• CPC Class Codes: F05D 2270/023 of different spools or shafts
• CPC Class Codes: F05D 2270/304 Spool rotational speed
• CPC Class Codes: F05D 2270/44 active, predictive, or anticipative

Abstract

A gas turbine engine is disclosed that has with two or more compressors. A first one of the compressors include a compressor variable geometry mechanism that may be in the form of adjustable vanes, bleed valves, or the like. A first one of the compressors is turned at a first speed and the second one of the compressors is turned at a second speed. The first speed is maintained approximately constant while the second speed varies and position of the compressor variable geometry mechanism is modulated in accordance with the second speed of the second one of the compressors to regulate surge margin for the first one of the compressors.

Claims

1. A method, comprising:

driving an electric power generator with a gas turbine engine including two or more compressors to produce AC electricity, a first one of the compressors including a compressor variable geometry mechanism;

regulating operation of the first one of the compressors to a desired surge margin, which includes;

determining rotational speed of a second one of the compressors;

adjusting the compressor variable geometry mechanism to a target position as a function of the rotational speed of the second one of the compressors.

2. The method of claim 1, wherein the second one of the compressors is downstream of the first one of the compressors, and the determining of the rotational speed includes correcting for ambient temperature.

3. The method of claim 1, wherein the compressor variable geometry mechanism includes at least one of a variable position vane and a compressor bleed device.

4. The method of claim 1, which includes rotating the first one of the compressors at a rotational speed less than the rotational speed of the second one of the compressors, the electric power generator being mechanically connected to the first one of the compressors to turn therewith.

5. The method of claim 4, which includes varying the rotational speed of the first one of the compressors over a range while the rotational speed of the first one of the compressors remains generally constant in proportion to a target frequency of the AC electricity.

6. The method of claim 1, which includes:

performing the regulating of the first one of the compressors to address a transient state operation;

during steady state operation, changing regulation of the first one of the compressors to a different mode than the regulating of the first one of the compressors for the transient state operation.

7. The method of claim 1, wherein the compressor variable geometry mechanism is one of a plurality to variable mechanisms including a number of bleed off valves and a number of variable inlet guide vanes and further comprising:

adjusting position of the variable inlet guide vanes in response to the transient operating condition based on the rotational speed of the second one of the compressors.

8. The method of claim 1, wherein the regulating of the operation of the first one of the compressors includes biasing the target position to account for a time lag between actual and observed speed of the second one of the compressors.

9. The method of claim 1, wherein the second one of the compressors includes one or more adjustable compressor mechanisms and the regulating of the operation of the first one of the compressors includes accounting for operation of the one or more adjustable compressor mechanisms.

10. A method, comprising:

operating a gas turbine engine with two or more compressors, a first one of the compressors including a compressor variable geometry mechanism;

turning a first one of the compressors at a first speed and a second one of the compressors at a second speed;

maintaining the first speed approximately constant while the second speed varies; and

modulating position of the compressor variable geometry mechanism in accordance with the second speed to regulate surge margin.

11. The method of claim 10, wherein the second one of the compressors is downstream of the first one of the compressors and includes a number of other compressor variable geometry mechanisms, and the modulating of the position of the compressor variable geometry mechanism includes determining an adjustment that accounts for a time lag between actual and observed speed of the second one of the compressors and for positioning of the other compressor variable geometry mechanisms.

12. The method of claim 10, wherein the compressor variable geometry mechanism includes at least one of a variable position vane and a compressor bleed device.

13. The method of claim 10, which includes driving an electric power generator with the gas turbine engine to provide AC electricity.

14. The method of claim 13, wherein the first one of the compressors is mechanically coupled to the electric power generator to turn therewith, and the first speed being in proportion to a target frequency of AC electricity, and the first speed being less than the second speed.

15. The method of claim 10, wherein the modulating of the position of the compressor variable geometry mechanism is included in a transient state mode of regulation of the first one of the compressors, and further comprising:

during steady state operation, changing to a steady state mode of regulation of the first one of the compressors different than the transient state mode.

16. The method of claim 10, wherein the compressor variable geometry mechanism a plurality to variable mechanisms including a number of bleed off valves and a number of variable inlet guide vanes.

17. An apparatus, comprising:

a gas turbine engine including two or more compressors, a first one of the compressors including a compressor variable geometry mechanism;

a sensor to provide one or more sensor signals corresponding to rotational speed of a second one of the compressors;

a controller operatively coupled to the sensor, the controller including operating logic responsive to the signal to regulate surge margin of the first one of the compressors, the operating logic being structured to select a target position of the compressor variable geometry mechanism as a function of the one or more sensor signals and generate one or more corresponding output signals; and

wherein the compressor variable geometry mechanism is responsive to the one or more corresponding output signals to adjust to the target position.

18. The apparatus of claim 17, further comprising means for accounting for a time lag between actual and observed speed of the second one of the compressors.

19. The apparatus of claim 17, wherein the second one of the compressors includes one or more other compressor variable geometry mechanisms and further comprising means for accounting for position of the one or more other compressor variable geometry mechanisms.

20. The apparatus of claim 17, further comprising an electric power generator mechanically coupled to the first one of the compressors to turn therewith.

21. The apparatus of claim 20, wherein the compressor variable geometry mechanism includes at least one of a bleed off valve and the variable inlet guide vane.

22. The apparatus of claim 21, wherein the gas turbine engine is of a multispool arrangement with the first one of the compressors being a lower pressure type than the second one of the compressors.

23. The apparatus of claim 17, further comprising another sensor to detect ambient temperature, the controller being structured to correct the one or more sensor signals in accordance with the ambient temperature.