Multi-shaft reheat turbine mechanism for generating power

• US 6,141,953 A
• Filed: 03/04/1998
• Issued: 11/07/2000
• Est. Priority Date: 03/04/1998
• Status: Expired due to Fees

• Current Assignee: Solo Energy Corporation
• Original Assignee: Solo Energy Corporation
• Inventors: Dibble, Robert W., Mongia, Rajiv K., Buckley, Steven G., Touchton, George L., Neuhaus, Peter D.
• Primary Examiner(s): FREAY, CHARLES GRANT
• Application Number:
  US09/034,101
• Time in Patent Office: 979 Days
• Field of Search: 60/39.04, 60/39.161, 60/39.17, 60/39.511, 60/39.512, 60/723
• US Class Current: 60/774
• CPC Class Codes: F02C 3/22 the fuel or oxidant being gaseous at standard temperature and pressure F02C3/28 takes precedence
• CPC Class Codes: F02C 3/36 Open cycles
• CPC Class Codes: F02C 6/003 Gas-turbine plants with heaters between turbine stages
• CPC Class Codes: F02G 2254/11 Catalytic burners
• CPC Class Codes: F05D 2260/211 by intercooling, e.g. during a compression cycle
• CPC Class Codes: Y02E 20/14 Combined heat and power generation [CHP]
• CPC Class Codes: Y02E 20/16 Combined cycle power plant [CCPP], or combined cycle gas turbine [CCGT]
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A multi-shaft reheat turbine mechanism includes multiple turbines mounted on respective compressor shafts, and catalytic reactors feeding respective ones of the turbines. Fuel is introduced into a low pressure compressor, whereby there is no need to pressurize the fuel. The compressor side of the mechanism emits a compressed air/fuel flow, portions of which are combusted in respective ones of the catalytic reactors. The air/fuel flow traveling from the compressor side to the turbine side passes through a regenerator in heat exchanging relationship with exhaust gas from a low pressure turbine.

Claims

1. A multi-shaft reheat turbine mechanism comprising:

a plurality of shafts, expansion turbines connected respectively to all shafts, and compressors connected respectively to at least two shafts for compressing air and fuel;

means for supplying air and fuel into the compressor side to be compressed thereby;

an intercooler disposed in a line extending between an outlet of one of the compressors and an inlet of another of the compressors for cooling compressed air/fuel traveling between those compressors;

the compressors constituting a compressor side of the mechanism for compressing air/fuel, and the turbines constituting a turbine side of the mechanism for driving the compressors;

at least one electrical generator operably connected to the turbine side to be powered thereby;

a heat exchanger for conducting compressed air/fuel from the compressor side in heat exchange relationship with hot exhaust gas from the turbine side, to heat the compressed air/fuel;

the turbine side further including combustors for combusting compressed air/fuel, each combustor disposed upstream of an associated turbine, and including an outlet for conducting combusted air/fuel to its respective turbine;

a first of the turbines being disposed upstream of a second of the turbines, with an exhaust outlet of the first turbine connected to a second of the combustors, the second combustor being associated with the second turbine; and

a conduit arrangement for conducting a first portion of the heated compressed air/fuel to a first of the combustors, the first combustor being associated with the first turbine, and for conducting the exhaust gas from the first combustor, together with a second portion of the heated compressed air/fuel, to the first turbine to be expanded therein.

2. The turbine mechanism according to claim 1 further comprising an additional conduit arrangement communicating with an outlet of the first turbine for conducting a portion of expanded exhaust from the first turbine to the second combustor, and for conducting another portion of expanded exhaust from the first turbine to the second turbine.

3. The turbine mechanism according to claim 2 wherein the turbine side further includes a power turbine connected to a shaft to which no compressor is attached and to which an electrical generator is attached, the power turbine disposed downstream of all turbines mounted on shafts to which compressors are attached.

4. The turbine mechanism according to claim 3, further including an additional combustor arranged upstream of the power turbine.

5. The turbine mechanism according to claim 3 wherein the turbines further include a third turbine mounted to a shaft to which a compressor is attached;

a third combustor associated with the third turbine and located between the second and third turbines;

another conduit arrangement provided for conducting a portion of expanded exhaust from the second turbine to the third combustor, and another portion of expanded exhaust from the second turbine to the third turbine;

the combustor associated with the power turbine being connected to the third turbine for receiving exhaust gas therefrom.

6. The turbine mechanism according to claim 1 wherein the heat exchanger is a regenerator having a core movable through separate paths in which the compressed air/fuel flow, and hot exhaust gas from the turbine side are conducted, respectively.

7. The turbine mechanism according to claim 6 wherein each of the combustors is a catalytic reactor.

8. The turbine mechanism according to claim 1 wherein each of the combustors is a catalytic reactor.

9. The turbine mechanism according to claim 1 wherein the means for introducing air and fuel comprises means for introducing air and fuel directly and separately into a first of the compressors.

10. A turbine mechanism comprising:

a spool comprising a shaft, a compressor connected to the shaft, and a first expansion turbine connected to the shaft;

the compressor comprising a compressor side of the mechanism for compressing air/fuel, and the turbine comprising a turbine-side of the mechanism for driving the compressor;

means for supplying air and fuel to the compressor side to be compressed thereby;

at least one electrical generator operably connected to the turbine side to be powered thereby;

a heat exchanger for conducting compressed air/fuel from the compressor side in heat exchange relationship with hot exhaust gas from the turbine side, to heat the compressed air/fuel;

the turbine side including a first combustor disposed upstream of first turbine, a second combustor disposed downstream of the first turbine, and a second turbine disposed downstream of the second combustor; and

a conduit arrangement for conducting a first portion of the heated compressed air to the first combustor, and for conducting products of combustion from the first combustor, together with a second portion of the heated compressed air/fuel, to the first turbine.

11. A method of producing energy, utilizing a multi-shaft reheat turbine mechanism comprising a plurality of shafts, expansion turbines connected respectively to all shafts, and compressors connected respectively to at least two shafts, the compressors constituting a compressor side, and the turbines constituting a turbine side;

the method comprising the steps of;

A. delivering air and fuel one of the compressors which emits compressed air/fuel;

B. cooling the compressed air/fuel in an intercooler;

thereafter

C. delivering the cooled air/fuel from the intercooler to another of the compressors;

thereafter

D. passing the cooled air/fuel through a heat exchanger in heat exchanging relationship with exhaust gas from the turbine side of the mechanism subsequent to step C, to produce a heated compressed air/fuel flow;

thereafter

E. reacting only a portion of the fuel of the flow in a combustor and then delivering the flow, including unreacted fuel, to one of the turbines of the turbine side;

thereafter

F. reacting expanded exhaust from the one turbine, including unreacted fuel, in another combustor, and then delivering the flow, including expanded exhaust, to another turbine disposed downstream thereof; and

G. driving an electrical generator operably connected to the turbine side.

12. The method according to claim 11 wherein step D comprises passing compressed air/fuel through a cold side of a regenerator while conducting the exhaust gas through a hot side thereof, and moving a heat-exchange core through the hot and cold paths.

13. The method according to claim 11 wherein the combustors are catalytic reactors.

14. The method according to claim 11, wherein step E comprises passing the flow through a combustor with a residence time insufficient for reacting all of the fuel in the flow passing therethrough.

15. The method according to claim 11 wherein step E comprises passing the flow through a combustor having an insufficient capacity for reacting all of the fuel passing therethrough.

16. The method according to claim 11 wherein step E comprises passing only some of the flow through a combustor and causing some of the flow to bypass the combustor and be delivered directly to a turbine disposed downstream thereof.

17. The method according to claim 11 wherein step A comprises delivering air and fuel directly and separately into the one compressor.

18. The method according to claim 11 wherein step A comprises delivering all of the air and fuel to the one compressor.