Multi-Spool Intercooled Recuperated Gas Turbine

• US 20090211260A1
• Filed: 05/05/2008
• Published: 08/27/2009
• Est. Priority Date: 05/03/2007
• Status: Abandoned Application

• Current Assignee: ICR Turbine Engine Corporation
• Original Assignee: Brayton Energy, LLC
• Inventors: Wolf, Thomas L., Kesseli, James B., Nash, James S.
• Application Number:
  US12/115,134
• Publication Number:
  US 20090211260A1
• Time in Patent Office: Days
• US Class Current: 60/786
• CPC Class Codes: F02C 1/02 the working fluid being an unheated pressurised gas
• CPC Class Codes: F02C 7/08 Heating air supply before combustion, e.g. by exhaust gases
• CPC Class Codes: F02C 7/27 Fluid drives turbine starters F02C7/277
• CPC Class Codes: F02C 7/275 Mechanical drives
• CPC Class Codes: F02C 7/277 the starter being a separate turbine
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A method and apparatus are disclosed for a gas turbine power plant with a variable area turbine nozzle and an integrated motor/alternator device for starting the gas turbine and power extraction after starting.

Claims

1. A gas turbine engine, comprising:

a high pressure spool having a high pressure compressor, a high pressure turbine, and a first rotatable shaft rotatably coupling the high pressure compressor and the high pressure turbine on a first pair of bearings;

a low pressure spool having a low pressure compressor, a low pressure turbine, and a second rotatable shaft rotatably coupling the low pressure compressor and the low pressure turbine;

a combustor for receiving a high pressure airflow from the high pressure compressor and delivering a heated airflow to the high pressure turbine to rotatably drive the first shaft and the high pressure compressor;

a free turbine spool comprising a free turbine and a free turbine shaft, said free turbine shaft rotatably coupling said free turbine to a load device selected from a mechanical load and an electrical load;

said high pressure turbine delivering a first reduced pressure airflow to said low pressure turbine to drive said second shaft and said low pressure compressor;

said low pressure turbine delivering a second reduced pressure airflow to said free turbine to drive said load device; and

a starter device for causing the rotation of said high pressure spool, said starter device integrally built into one or both of said first shaft and said high pressure compressor.

2. The gas turbine engine of claim 1, further comprising:

a heat exchanger; and

said free turbine delivering a third reduced pressure airflow to said heat exchanger for transferring heat from said third reduced pressure airflow to said high pressure airflow from said high pressure compressor.

3. The gas turbine engine of claim 1, further comprising:

said started device having a starter turbine and a source of motive fluid selectively fluidically coupled to said starter turbine for selectively delivering a motive fluid flow to said starter turbine; and

a valve controlled by a controller, said controller for generating a control signal, said valve configured to open and deliver said motive fluid to said starter turbine to start said gas turbine engine in response to said control signal.

4. The gas turbine engine of claim 3, where said motive fluid is selected from air and a hydraulic fluid.

5. The gas turbine engine of claim 1, wherein said high pressure compressor includes a rotor and said starter device includes a starter turbine including turbine buckets or turbine blades integrated with said rotor for causing rotation of the rotor in response to receiving a flow of said motive fluid.

6. The gas turbine engine of claim 5, wherein said motive fluid is air, said gas turbine engine further comprising air bearings on said first shaft supporting said starter turbine.

7. The gas turbine engine of claim 6, wherein said high pressure compressor includes a compressor impeller having an impeller face, a back face opposite the impeller face, and a plurality of turbine buckets formed on the back face, said turbine buckets adapted to cause rotation of the compressor impeller in response to receiving a flow of said air.

8. The gas turbine engine of claim 1, wherein said load device is connected to said free turbine, said load device selected from an alternator and a geared transmission.

9. The gas turbine engine of claim 1, further comprising:

said free turbine including a variable area turbine nozzle for controlling fuel consumption.

10. A gas turbine engine, comprising:

a high pressure spool having a high pressure compressor, a high pressure turbine, and a first rotatable shaft rotatably coupling the high pressure compressor and the high pressure turbine on a first pair of bearings;

a low pressure spool having a low pressure compressor, a low pressure turbine, and a second rotatable shaft rotatably coupling the low pressure compressor and the low pressure turbine;

a combustor for receiving a high pressure airflow from the high pressure compressor and delivering a heated airflow to the high pressure turbine to rotatably drive the first shaft and high pressure compressor;

a free turbine spool comprising a free turbine, and a free turbine shaft rotatably coupling said free turbine to a load device selected from a mechanical load and an electrical load;

said high pressure turbine delivering a first reduced pressure airflow to said low pressure turbine to drive said second shaft and said low pressure compressor;

said low pressure turbine delivering a second reduced pressure airflow to said free turbine to drive said load device; and

a combined motor and alternator device on said high pressure spool operable to drive said first rotatable shaft for starting said gas turbine engine, said combined motor and alternator device further operable to convert rotational energy of said first rotatable shaft to electrical energy.

11. The gas turbine engine of claim 10, further comprising:

a heat exchanger; and

said free turbine delivering a third reduced pressure airflow to said heat exchanger for transferring heat from said third reduced pressure airflow to said high pressure airflow from said high pressure compressor.

12. The gas turbine engine of claim 11, wherein said load device is connected to said free turbine, said load device is selected from an alternator and a geared transmission.

13. The gas turbine engine of claim 12, wherein said combined motor and alternator device is supported on said first rotatable shaft.

14. The gas turbine engine of claim 13, further comprising:

air bearings supporting said combined motor and alternator device on said first rotatable shaft.

15. The gas turbine engine of claim 10, wherein said combined motor and alternator device includes a magnetic rotor embedded within said first rotatable shaft.

16. The gas turbine engine of claim 10, where said combined motor and alternator device is disposed within a bearing system located on said first rotatable shaft between said high pressure turbine and said high pressure compressor.

17. The gas turbine engine of claim 10, wherein said combined motor and alternator device is coupled to said high pressure compressor.

18. The gas turbine engine according to claim 10, further comprising:

said free turbine including a variable area turbine nozzle for controlling fuel consumption.

19. The gas turbine engine of claim 10, where said combined motor and alternator device is electrically coupled to an electrical system of a vehicle.

20. A method of starting a gas turbine engine of a type having a high pressure spool, a low pressure spool, and a combustor for receiving high pressure airflow from a high pressure compressor of the high pressure spool and delivering a heated air flow to a high pressure turbine of said high pressure spool, said method comprising:

imparting rotation to a rotatable shaft rotatably coupling a rotor of the high pressure compressor and the high pressure turbine to start said gas turbine engine;

said step of imparting rotation selected from;

delivering a pressurized motive fluid to a starter turbine coupled to the rotatable shaft; and

delivering a rotational force to the first shaft using a combined motor and alternator device.

21. The method of claim 20, wherein said motive fluid is selected from the group consisting of air and a hydraulic fluid.

22. The method of claim 20, further comprising:

said step of imparting rotation including electrically coupling said combined motor and alternator device to a power supply of a vehicle; and

after starting said gas turbine engine, using said combined motor and alternator device to convert rotational energy of the rotatable shaft to electrical energy.