Gas-turbine installation

• US 20050086939A1
• Filed: 07/31/2004
• Published: 04/28/2005
• Est. Priority Date: 08/13/2003
• Status: Active Grant

• Current Assignee: Siemens AG
• Original Assignee: Siemens AG
• Inventors: Schmid, Udo
• Granted Patent: US 7,024,860 B2
• Time in Patent Office: Days
• US Class Current: 60/726
• CPC Class Codes: F01D 13/003 with at least two independent shafts, i.e. cross-compound
• CPC Class Codes: F02C 3/13 having variable working fluid interconnections between turbines or compressors or stages of different rotors controlling flow ratio between different flows of multi-flow jet-propulsion plant, e.g. ducted fan F02K3/075
• CPC Class Codes: F02C 7/185 Cooling means for reducing the temperature of the cooling air or gas
• CPC Class Codes: F02C 9/16 Control of working fluid flow F02C9/48 takes precedence; control of air-intake flow F02C7/057

Abstract

In a gas-turbine installation according to the invention there is provided, in order to increase the compressor mass flow, a separate turbo-compressor which is connected in parallel to the compressor of the gas turbine and which is preferably operated by means of an electric motor. By this means, the gas turbine is, at a current ambient temperature, operated with increased power output appropriate to a lower ambient temperature.

Claims

1-14. -14. (canceled)

15. A gas-turbine engine, comprising:

a turbine;

an air intake element;

an external air compressor having a shaft, operatively connected to the turbine;

a turbo-compressor connected to the air intake element and having a shaft arranged approximately parallel with the external air compressor shaft.

16. The gas-turbine engine according to claim 15, wherein the shaft of the turbo-compressor is rotated by an electric motor.

17. The gas-turbine engine according to claim 15, wherein the turbo-compressor supplies compressed air to the external air compressor.

18. The gas-turbine engine according to claim 17, wherein compressed air is supplied by a component selected from the group consisting of:

a blow-off line, a cooling-air line, an overflow line, combinations thereof, and the like.

19. The gas-turbine engine according to claim 15, wherein the gas-turbine engine is used in conjunction with a steam power engine.

20. The gas-turbine engine according to claim 15, wherein the turbo-compressor has a plurality of compressor stages.

21. The gas-turbine engine according to claim 20, wherein an intercooler is connected between two of the compressor stages.

22. The gas-turbine engine according to claim 21, wherein the intercooler functions as a fuel pre-heater.

23. The gas-turbine engine according to claim 22, wherein the intercooler is supplied with a coolant by a coolant supply associated with a generator or another component of the gas-turbine engine.

24. The gas-turbine engine according to claim 15, wherein the turbo-compressor is supplied with lubricating oil by a lubricating-oil supply associated with the gas turbine.

25. The gas-turbine engine according to claim 15, wherein the turbo-compressor is operated at nominal power during operation of the gas-turbine engine.

26. The gas-turbine engine according to claim 15, wherein the air compressed by the turbo-compressor is supplied through a control valve to the gas turbine and the control valve is opened and closed according to a control characteristic.

27. The gas-turbine engine according to claim 15, a return flow of the air compressed by the compressor to the turbo-compressor can be interrupted by means of a non-return valve.

28. The gas-turbine engine according to claim 27, wherein the non-return valve is actuated either hydraulically or pneumatically.