Gas Turbine Generator

• US 20130056982A1
• Filed: 12/16/2010
• Published: 03/07/2013
• Est. Priority Date: 12/17/2009
• Status: Abandoned Application

• Current Assignee: Richard Gozdawa
• Original Assignee: Richard Gozdawa
• Inventors: Gozdawa, Richard
• Application Number:
  US13/516,738
• Publication Number:
  US 20130056982A1
• Time in Patent Office: Days
• US Class Current: 290/7
• CPC Class Codes: F01D 15/10 Adaptations for driving, or combinations with, electric generators
• CPC Class Codes: F02C 7/32 Arrangement, mounting, or driving, of auxiliaries
• CPC Class Codes: F02C 7/36 Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user F02C3/107 - F02C3/13 and F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H
• CPC Class Codes: F05D 2220/768 equipped with permanent magnets
• CPC Class Codes: F05D 2240/40 Use of a multiplicity of similar components
• CPC Class Codes: F05D 2250/312 the axes being parallel to each other
• CPC Class Codes: F05D 2260/4031 as in toothed gearing

Abstract

A gas turbine generator 1 comprising a combustor (2), a turbine (4), a compressor (6), a drive shaft (7) and at least one generator. The turbine (4) is driven by the combustor (6). The drive shaft (7) links the turbine (4) and the compressor (6) along a common rotational drive axis. The at least one electrical generator comprises a rotor and a stator, and the rotational axis of the generator rotor is radially offset from the drive axis. Drive means is provided which connects the generator rotor to the drive shaft (7) such that rotation of the drive shaft (7) causes rotation of the generator rotor.

Claims

1. A gas turbine generator comprising:

a combustor,

a turbine driven by the combustor,

a compressor;

a drive shaft linking the turbine and the compressor along a common rotational drive axis; and

at least one electrical generator comprising a rotor and a stator;

wherein the rotational axis of the generator rotor is radially offset from the drive axis, and drive means is provided which connects the generator rotor to the drive shaft such that rotation of the drive shaft causes rotation of the generator rotor.

2. The gas turbine generator of claim 1, wherein the rotor comprises a permanent magnet secured to a rotor shaft.

3. The gas turbine generator of claim 2, wherein the permanent magnet is at least partially surrounded by a sleeve configured to urge the magnet against the rotor shaft.

4. The gas turbine generator of claim 1, wherein the rotational axis of the generator rotor is oriented substantially parallel to the drive axis.

5. The gas turbine generator of claim 1, wherein the drive means comprises a drive gear connected to and axially aligned with the drive shaft, and a rotor gear connected to the at least one generator rotor and linked to the drive gear such that rotation of the drive gear by the drive shaft causes rotation of the rotor gear and hence the rotor.

6. The gas turbine generator of claim 5 further comprising an idler gear intermediate the drive gear and the rotor gear.

7. The gas turbine generator of claim 6, wherein the idler gear is mounted on a flexible gear support configured to permit self-alignment of the idler gear.

8. The gas turbine generator of claim 1, wherein the at least one generator comprises a plurality of electrical generators.

9. The gas turbine generator of claim 8, wherein the rotational axes of the plurality of generators are radially spaced from the drive axis.

10. The gas turbine generator of claim 9, wherein the plurality of generators are axially positioned in line with at least a portion of the drive shaft.

11. The gas turbine generator of claim 8, wherein each of the plurality of electrical generators may be selectively and independently deactivated to vary the total electrical power output of the gas turbine generator.

12. The gas turbine generator of claim 10, wherein each of the plurality of electrical generators is provided with a dedicated power control unit which is used to selectively deactivate the electrical generator

13. The gas turbine generator of claim 12 further comprising a controller connected to each of the power control units and configured to cause the power control units to selectively deactivate one or more of the electrical generators based on a required power output for the gas turbine generator.

14. A gas turbine generator comprising:

a combustor;

a turbine driven by the combustor;

a compressor driven by the turbine; and

a plurality of electrical generators driven by the turbine.

15. The gas turbine generator of claim 14, wherein the plurality of generators are driven by the turbine via a drive train.

16. The gas turbine generator of claim 14, wherein each of the plurality of electrical generators may be selectively and independently deactivated to vary the total electrical power output of the gas turbine generator.

17. The gas turbine generator of claim 16, wherein each of the plurality of electrical generators is provided with a dedicated power control unit which is used to selectively deactivate the electrical generator

18. The gas turbine generator of claim 17 further comprising a controller connected to each of the power control units and configured to cause the power control units to selectively deactivate one or more of the electrical generators based on a required power output for the gas turbine generator.

19. The gas turbine generator of claim 15, wherein each of the electrical generators is removably coupled to the drive train such that it may be selectively mechanically decoupled from the drive train.

20. A gas turbine generator comprising:

a combustor;

a turbine driven by the combustor;

a compressor;

an electrical generator driven by the turbine, and

a drive shaft for linking the turbine and the compressor, the drive shaft having a first end configured for connection to the turbine and an opposing second end configured for connection the compressor, wherein at least one of the first and second ends comprises a mechanically interlocking connector configured to allow sliding disengagement of the drive shaft from at least one of the turbine and the compressor respectively.

21. The gas turbine generator of claim 20, wherein the mechanically interlocking connector comprises a spline formed on one of the drive shaft and the at least one of the turbine and the compressor which is configured to be received within a corresponding mating section on the other of the drive shaft and the at least one of the turbine and the compressor.

22. The gas turbine generator of claim 21, wherein both the first and second ends of the drive shaft comprise splines configured to be received within corresponding mating sections on the turbine and the compressor respectively.

23. The gas turbine generator of claim 20, wherein the generator is driven by the turbine via a drive train and the generator is connected to the drive train by to an interlocking mechanical connector which enables sliding disengagement of the generator from the drive train.

24. The gas turbine generator of claim 23, wherein the interlocking mechanical connector comprises a plurality of spigots extending from one of the generator and the drive train which are received within corresponding apertures on the other of the generator and the drive train enabling sliding disengagement of the two.

25. (canceled)