EP0769098A1 - Gas turbine plant with additional compressor - Google Patents

Gas turbine plant with additional compressor

Info

Publication number
EP0769098A1
EP0769098A1 EP93919753A EP93919753A EP0769098A1 EP 0769098 A1 EP0769098 A1 EP 0769098A1 EP 93919753 A EP93919753 A EP 93919753A EP 93919753 A EP93919753 A EP 93919753A EP 0769098 A1 EP0769098 A1 EP 0769098A1
Authority
EP
European Patent Office
Prior art keywords
compressor
combustor
air
gas turbine
additional
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP93919753A
Other languages
German (de)
French (fr)
Inventor
Agnar Skog
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Alstom Power Carbon AB
Original Assignee
ABB Carbon AB
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by ABB Carbon AB filed Critical ABB Carbon AB
Publication of EP0769098A1 publication Critical patent/EP0769098A1/en
Withdrawn legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/16—Control of working fluid flow
    • F02C9/18—Control of working fluid flow by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/107—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with two or more rotors connected by power transmission
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/13—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor having variable working fluid interconnections between turbines or compressors or stages of different rotors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/36—Open cycles

Definitions

  • the present invention relates to a gas turbine plant comprising a compressor, a gas turbine and a pressurized combustor.
  • combustion gases are generated which drive a gas turbine.
  • This gas turbine drives a compressor which compresses air for pressurizing the combus- tor.
  • the compressed air is at the same time utilized as com ⁇ bustion air during the combustion.
  • the gas turbine is divided into a high-pressure and a low-pressure turbine. With such a division of the gas turbine, the low-pressure turbine can then, on a separate first shaft, drive a low- pressure compressor for compression of the air in a first stage.
  • the high-pressure turbine then drives, via a second separate shaft, a high-pressure compressor in which air is compressed in a second stage before the air is supplied to the combustor.
  • a cooler may be provided for cooling the air after the first stage in the compression.
  • the fuel which is supplied to the combustor consists of gaseous, liquid or solid fuels, for example natural gas, oil or coal, in dependence on the nature of the plant.
  • a PFBC power plant is an example of a plant comprising a gas tur ⁇ bine cycle according to the configuration described above in which a solid fuel, usually pulverized coal, is burnt in a fluidized bed in the combustor.
  • an electric generator for generating useful energy is usually connected to the high-pressure tur ⁇ bine by way of a gear.
  • the generator Upon start-up of the plant, it is possible to utilize the generator as electric motor to run up the compressor and hence pressurize the combustor.
  • a compressor size is usually chosen which provides optimal air flow at a low exterior air temperature known to the site of the plant.
  • the density of the air will be lower, whereby the air flow through the compressor is reduced.
  • the invention relates to a method and a device for supplying additional air to a combustor in a gas turbine plant with the aid of an additional compressor for additional air, which means that air is compressed in the additional com ⁇ pressor and supplied to the combustor by passing the com ⁇ pressed air wholly or partially past the ordinary compressor which delivers air to the compressor for pressurizing the combustor and for maintenance of a combustion in the com ⁇ bustor.
  • the additional compressor is driven by the gas turbine. If the latter is divided into a high-pressure and a low- pressure turbine, the additional compressor is suitably driven by the high-pressure turbine.
  • the operation of the additional compressor can be performed via a gear or by mounting it on the same shaft as the turbine.
  • Another alternative mode of operation is to mount the additional compressor on the same shaft as the generator via a clutch.
  • a still further variant for operation of the additional compressor is to provide it with its own electric motor.
  • the possi ⁇ bility of adaptation to other components in the plant and to the necessary air flow, caused by these components, to the combustion process in the combustor is improved.
  • a possi ⁇ bility is also provided of compensating for the power reduc- tion in the plant caused by the reduced air flow to the combustor at higher exterior air temperatures.
  • Figures la-lc schematically illustrates a number of general variants of a gas turbine plant wherein additional air is supplied to a combustor from an additional compressor.
  • Figure 2 shows the supply of additional air from an addi ⁇ tional compressor to a combustor in a gas turbine plant, in which the gas turbine and the compressor are divided into high-pressure and low-pressure units.
  • BK designates a combustor in which a fuel is fired under high pressure.
  • the high pressure is accomplished by means of a compressor C, which compresses air which is supplied to the combustor BK via an intercept and bypass valve V. Air to the compressor is admitted via the air conduit 8.
  • the combustion gases which are generated in the combustor BK are passed via the inter ⁇ cept and bypass valve V to a gas turbine GT to utilize the energy in the combustion gases, whereupon the consumed waste gases are removed via a waste gas conduit 10.
  • the gas tur ⁇ bine GT is mounted on the same shaft A as the compressor C and thus drives the compressor.
  • the intercept and bypass valve V comprises, besides cut-off valves for compressor air to the combustor BK, and cut-off valves for supply of combustion gases to the gas turbine GT, also a bypass conduit with a cut-off valve to provide a possibility of short-circuiting the compressor C and the gas turbine GT.
  • the invention relates to a method and a device for supplying the combustor BK with additional air by means of an addi ⁇ tional compressor AC.
  • Air to the additional compressor AC is sucked in via a second air intake 14 and is supplied to the combustor BK.
  • the supply of the additional air to the com ⁇ bustor BK can be arranged in several different ways.
  • the additional air can be passed via a conduit 16, as shown in Figures 1 and 2, to the intercept valve V in the same way as the air from the ordinary compressor C, whereupon the addi ⁇ tional air is passed to the combustor BK.
  • Figure la also shows a variant in which the additional air via a conduit 18 is injected into the ordinary compressor C at an injection hole 20 in the compressor C downstream of the air conduit 8, whereby the additional air is further compressed in the com- pressor C.
  • the additional compressor AC is driven by the gas turbine GT via the gear 12.
  • the additional compres ⁇ sor AC can be driven by the gas turbine GT via the generator shaft, whereby the additional compressor AC is mounted via a clutch or a gear 22 to the generator shaft according to Figure lb.
  • the additional compressor AC can be driven via a separate electric motor M connected to the additional compressor AC, as shown in Figure lc.
  • both the gas turbine GT and the compressor C are divided into several stages according to Figure 2.
  • the embodiment corresponds to the more general connection according to Figures la-lc.
  • the combustion gases from the combustor BK drive a high-pressure turbine HPT, which is mounted together with a high-pressure compressor HPC on a first shaft Al.
  • the gases expanded in the high- pressure turbine HPT are passed on to a low-pressure turbine LPT, from which the waste gases from the plant are removed via a waste gas conduit 10.
  • a second shaft A2 as the low-pressure turbine LPT is mounted on, also a low-pressure compressor LPC is arranged.
  • air is passed via the air conduit 8, whereafter the air, after compression in the low-pressure compressor LPC, is passed to the high-pressure compressor HPC, where the air is compressed further before it is supplied to the combustor BK via the intercept valve V.
  • the air may be cooled in an intermediate cooler IC before being supplied to the high-pressure compressor HPC.
  • the first shaft Al drives the generator G, via a gear 12, for generating electrical energy.
  • air is compressed in an addi- tional compressor AC and supplied to the combustor BK together with the air compressed in the high-pressure com ⁇ pressor HPC.
  • Air to the additional compressor AC is taken in via the air intake 14 and passed to the intercept valve V to the same inlet of the valve V through which the compressed air from the high-pressure compressor HPC is fed in.
  • the compressed air is passed from the additional compressor AC to the inlet of the high-pressure compressor HPC down ⁇ stream of the intermediate cooler IC via the conduit altl, or upstream of the intermediate cooler IC via the conduit alt2 in dependence on the type of high-pressure compressor and adaptation thereto and to optimize the performance.
  • the generator G in the preferred embodiment according to Figure 2 is driven according to any of the alternative modes of operation given above; for example, the additional compres ⁇ sor is arranged on an auxiliary shaft A3 connected to the gear 12, whereby the high-pressure turbine HPT drives the additional compressor AC via the gear 12.
  • Direct operation of the additional compressor AC by mounting the additional compressor AC on the same shaft as the shaft of the high- pressure turbine HPT, that is on the first shaft Al, consti ⁇ tutes another alternative for operation.
  • the size of the additional compressor is small relative to the high-pressure compressor HPC normally existing in a gas turbine plant of the kind discussed.
  • the air flow of the additional compressor AC is chosen to be 10% of the air flow of the high-pressure compressor HPC, a value which is in no way critical for the invention.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The invention relates to a method and a device for supplying additional air to a combustor in a gas turbine plant with the aid of an additional compressor for additional air, which entails compressing air in the additional compressor and supplying the air to the combustor by passing the compressed air wholly or partially past the ordinary compressor which delivers air to the combustor for pressurizing the combustor and for maintenance of a combustion in the combustor.

Description

Gas turbine plant with additional compressor
TECHNICAL FIELD
The present invention relates to a gas turbine plant comprising a compressor, a gas turbine and a pressurized combustor.
BACKGROUND ART
In a gas turbine plant in which pressurized combustion takes place in a combustor, combustion gases are generated which drive a gas turbine. This gas turbine, in turn, drives a compressor which compresses air for pressurizing the combus- tor. The compressed air is at the same time utilized as com¬ bustion air during the combustion. Usually the gas turbine is divided into a high-pressure and a low-pressure turbine. With such a division of the gas turbine, the low-pressure turbine can then, on a separate first shaft, drive a low- pressure compressor for compression of the air in a first stage. The high-pressure turbine then drives, via a second separate shaft, a high-pressure compressor in which air is compressed in a second stage before the air is supplied to the combustor. Between the low-pressure and high-pressure compressors a cooler may be provided for cooling the air after the first stage in the compression.
The fuel which is supplied to the combustor consists of gaseous, liquid or solid fuels, for example natural gas, oil or coal, in dependence on the nature of the plant. A PFBC power plant is an example of a plant comprising a gas tur¬ bine cycle according to the configuration described above in which a solid fuel, usually pulverized coal, is burnt in a fluidized bed in the combustor.
In a gas turbine plant, an electric generator for generating useful energy is usually connected to the high-pressure tur¬ bine by way of a gear. Upon start-up of the plant, it is possible to utilize the generator as electric motor to run up the compressor and hence pressurize the combustor.
When designing a gas turbine plant, the gas turbine and compressor sizes are chosen on the basis of power levels available on the market. This creates a number of different problems which the plant designer has to solve. Some of the problems arising will be described here.
An optimum choice of compressor size to achieve the intended air flow with respect to adaptation to other components in the plant is rendered difficult.
When designing the plant, a compressor size is usually chosen which provides optimal air flow at a low exterior air temperature known to the site of the plant. On the other • hand, when higher temperatures prevail at the site, the density of the air will be lower, whereby the air flow through the compressor is reduced.
A small incorrect dimensioning of the chosen capacity of the compressor cannot be compensated for afterwards by simple means.
As the ordinary compressor ages, the capacity thereof is reduced, which means that the originally calculated flows no longer correspond to the reality, which cannot be compensated for.
SUMMARY OF THE INVENTION
The invention relates to a method and a device for supplying additional air to a combustor in a gas turbine plant with the aid of an additional compressor for additional air, which means that air is compressed in the additional com¬ pressor and supplied to the combustor by passing the com¬ pressed air wholly or partially past the ordinary compressor which delivers air to the compressor for pressurizing the combustor and for maintenance of a combustion in the com¬ bustor.
The additional compressor is driven by the gas turbine. If the latter is divided into a high-pressure and a low- pressure turbine, the additional compressor is suitably driven by the high-pressure turbine. The operation of the additional compressor can be performed via a gear or by mounting it on the same shaft as the turbine. Another alternative mode of operation is to mount the additional compressor on the same shaft as the generator via a clutch. A still further variant for operation of the additional compressor is to provide it with its own electric motor.
By distributing additional air to the combustor, the possi¬ bility of adaptation to other components in the plant and to the necessary air flow, caused by these components, to the combustion process in the combustor is improved. A possi¬ bility is also provided of compensating for the power reduc- tion in the plant caused by the reduced air flow to the combustor at higher exterior air temperatures. Further advantages are that possibilities are created for readjust¬ ment of the air flow capacity for the compressors, which is the case, for example, when the ordinary compressor is incorrectly dimensioned or when a reduction of the air flow occurs because of changes in the ordinary compressor caused by, for example, the ageing of the compressor.
BRIEF DESCRIPTION OF THE DRAWINGS
Figures la-lc schematically illustrates a number of general variants of a gas turbine plant wherein additional air is supplied to a combustor from an additional compressor.
Figure 2 shows the supply of additional air from an addi¬ tional compressor to a combustor in a gas turbine plant, in which the gas turbine and the compressor are divided into high-pressure and low-pressure units. DESCRIPTION OF THE PREFERRED EMBODIMENTS
With reference to the accompanying drawings, a number of embodiments of the present invention will be described.
In the figures, which schematically illustrate different variants of a gas turbine plane, BK designates a combustor in which a fuel is fired under high pressure. The high pressure is accomplished by means of a compressor C, which compresses air which is supplied to the combustor BK via an intercept and bypass valve V. Air to the compressor is admitted via the air conduit 8. The combustion gases which are generated in the combustor BK are passed via the inter¬ cept and bypass valve V to a gas turbine GT to utilize the energy in the combustion gases, whereupon the consumed waste gases are removed via a waste gas conduit 10. The gas tur¬ bine GT is mounted on the same shaft A as the compressor C and thus drives the compressor. On the same shaft A on which the compressor C and the gas turbine GT are mounted, also a gear 12 is arranged. Via this gear 12 the gas turbine GT also drives a generator G for conversion of energy utilized in the gas turbine plant to electrical energy. The intercept and bypass valve V comprises, besides cut-off valves for compressor air to the combustor BK, and cut-off valves for supply of combustion gases to the gas turbine GT, also a bypass conduit with a cut-off valve to provide a possibility of short-circuiting the compressor C and the gas turbine GT.
The invention relates to a method and a device for supplying the combustor BK with additional air by means of an addi¬ tional compressor AC. Air to the additional compressor AC is sucked in via a second air intake 14 and is supplied to the combustor BK. The supply of the additional air to the com¬ bustor BK can be arranged in several different ways. The additional air can be passed via a conduit 16, as shown in Figures 1 and 2, to the intercept valve V in the same way as the air from the ordinary compressor C, whereupon the addi¬ tional air is passed to the combustor BK. Figure la also shows a variant in which the additional air via a conduit 18 is injected into the ordinary compressor C at an injection hole 20 in the compressor C downstream of the air conduit 8, whereby the additional air is further compressed in the com- pressor C.
The additional compressor AC is driven by the gas turbine GT via the gear 12. As an alternative, the additional compres¬ sor AC can be driven by the gas turbine GT via the generator shaft, whereby the additional compressor AC is mounted via a clutch or a gear 22 to the generator shaft according to Figure lb. In a still further alternative mode of operation, the additional compressor AC can be driven via a separate electric motor M connected to the additional compressor AC, as shown in Figure lc.
In a preferred embodiment, both the gas turbine GT and the compressor C are divided into several stages according to Figure 2. In other respects, the embodiment corresponds to the more general connection according to Figures la-lc. In the embodiment according to Figure 2, the combustion gases from the combustor BK drive a high-pressure turbine HPT, which is mounted together with a high-pressure compressor HPC on a first shaft Al. The gases expanded in the high- pressure turbine HPT are passed on to a low-pressure turbine LPT, from which the waste gases from the plant are removed via a waste gas conduit 10. On the same shaft, a second shaft A2, as the low-pressure turbine LPT is mounted on, also a low-pressure compressor LPC is arranged. To this low- pressure compressor, air is passed via the air conduit 8, whereafter the air, after compression in the low-pressure compressor LPC, is passed to the high-pressure compressor HPC, where the air is compressed further before it is supplied to the combustor BK via the intercept valve V. After compression of the air in the low-pressure compressor LPC, the air may be cooled in an intermediate cooler IC before being supplied to the high-pressure compressor HPC. The first shaft Al drives the generator G, via a gear 12, for generating electrical energy.
According to the invention, air is compressed in an addi- tional compressor AC and supplied to the combustor BK together with the air compressed in the high-pressure com¬ pressor HPC. Air to the additional compressor AC is taken in via the air intake 14 and passed to the intercept valve V to the same inlet of the valve V through which the compressed air from the high-pressure compressor HPC is fed in. In alternative embodiments of the plant according to Figure 2, the compressed air is passed from the additional compressor AC to the inlet of the high-pressure compressor HPC down¬ stream of the intermediate cooler IC via the conduit altl, or upstream of the intermediate cooler IC via the conduit alt2 in dependence on the type of high-pressure compressor and adaptation thereto and to optimize the performance. The generator G in the preferred embodiment according to Figure 2 is driven according to any of the alternative modes of operation given above; for example, the additional compres¬ sor is arranged on an auxiliary shaft A3 connected to the gear 12, whereby the high-pressure turbine HPT drives the additional compressor AC via the gear 12. Direct operation of the additional compressor AC by mounting the additional compressor AC on the same shaft as the shaft of the high- pressure turbine HPT, that is on the first shaft Al, consti¬ tutes another alternative for operation.
The size of the additional compressor is small relative to the high-pressure compressor HPC normally existing in a gas turbine plant of the kind discussed. As a suggestion, the air flow of the additional compressor AC is chosen to be 10% of the air flow of the high-pressure compressor HPC, a value which is in no way critical for the invention.

Claims

1. A method of supplying additional air to a pressurized combustor (BK) in a gas turbine plant which, for pressuriza- tion of the combustor (BK) , comprises a compressor (C) driven by a gas turbine (GT) , which in turn is driven by gases generated during combustion of a fuel in the combustor (BK) , characterized in that air is compressed in an addi¬ tional compressor (AC) and supplied to the combustor by wholly or partially bypassing the compressor (C) .
2. A method according to claim 1 in a gas turbine plant, wherein the compressor (C) is divided into a high-pressure compressor (HPC) and a low-pressure compressor (LPC) and the gas turbine (GT) divided into a high-pressure turbine (HPT) and a low-pressure turbine (LPT) , characterized in that the air which is compressed in the additional compressor (AC) is supplied to the combustor downstream of or upstream of the high-pressure compressor (HPC) .
3. A method according to claim 2, characterized in that the air which is compressed in the additional compressor (AC) , when being supplied to the combustor upstream of the high-pressure compressor (HPC) , is connected downstream or upstream of an intermediate cooler (IC) arranged between the high-pressure compressor (HPC) and the low-pressure compressor (LPC) .
4. A method according to claim 1, characterized in that the additional compressor (AC) is driven by the gas turbine
(GT) by connecting the additional compressor (AC) to the gas turbine shaft (A, Al) directly or via a gear (12), or via the same shaft to which a generator (G) is connected via the gear (12) to the gas turbine shaft (A, Al), or driven by a separate electric motor (M) .
5. A device for carrying out the method of supplying additional air to a pressurized combustor (BK) in a gas turbine plant which, for pressurization of the combustor (BK) , comprises a compressor (C) driven by a gas turbine (GT) , which in turn is driven by gases generated during combustion of a fuel in the combustor (BK) , characterized in that an additional compressor (AC) is adapted to supply additional air to the combustor (BK) as a complement to the compressed air which is supplied to the combustor (BK) from the compressor (C) .
6. A device according to claim 5, characterized in that the additional compressor (AC) is adapted to be driven by the gas turbine (GT) or the high-pressure turbine (HPT) or by a separate electric motor (M) .
7. A device according to claim 5, characterized in that the compressed additional air is supplied to the combustor (BK) by feeding in the additional air downstream of the compressor (C) or downstream of the high-pressure compressor (HPC) , or is supplied to the combustor (BK) by injection into the compressor (C) or upstream of the high-pressure compressor (HPC) .
8. A device according to claim 7, characterized in that when a connection for additional air is arranged to the high-pressure compressor (HPC) upstream thereof, additional air is injected downstream or upstream of an intermediate cooler (IC) arranged between the low-pressure compressor and the high-pressure compressor.
EP93919753A 1992-08-28 1993-08-17 Gas turbine plant with additional compressor Withdrawn EP0769098A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
SE9202467 1992-08-28
SE9202467A SE500150C2 (en) 1992-08-28 1992-08-28 Methods and apparatus for supplying additional air to a combustion chamber at a gas turbine plant
PCT/SE1993/000679 WO1994005904A1 (en) 1992-08-28 1993-08-17 Gas turbine plant with additional compressor

Publications (1)

Publication Number Publication Date
EP0769098A1 true EP0769098A1 (en) 1997-04-23

Family

ID=20387027

Family Applications (1)

Application Number Title Priority Date Filing Date
EP93919753A Withdrawn EP0769098A1 (en) 1992-08-28 1993-08-17 Gas turbine plant with additional compressor

Country Status (4)

Country Link
EP (1) EP0769098A1 (en)
JP (1) JPH08500655A (en)
SE (1) SE500150C2 (en)
WO (1) WO1994005904A1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104937239A (en) * 2012-11-02 2015-09-23 通用电气公司 System and method for oxidant compression in a stoichiometric exhaust gas recirculation gas turbine system

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH06241065A (en) * 1993-02-17 1994-08-30 Mitsubishi Heavy Ind Ltd Gas turbine facility
US5896738A (en) * 1997-04-07 1999-04-27 Siemens Westinghouse Power Corporation Thermal chemical recuperation method and system for use with gas turbine systems
US6038849A (en) * 1998-07-07 2000-03-21 Michael Nakhamkin Method of operating a combustion turbine power plant using supplemental compressed air
EP1536118A1 (en) * 2003-11-25 2005-06-01 Alstom Technology Ltd Power station
FR3033836B1 (en) * 2015-03-19 2018-08-03 Valeo Systemes De Controle Moteur SYSTEM FOR PRODUCING ENERGY OR TORQUE
WO2017116613A2 (en) * 2015-12-04 2017-07-06 Jetoptera Inc. Micro-turbine gas generator and propulsive system

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SE446560B (en) * 1983-02-15 1986-09-22 Asea Atom Ab KIT IN COMBUSTION OF THE WATER AND / OR WHEAT FUEL AND RECOVERY OF ENERGY FROM THE COMBUSTION OF CERTAIN GAS GASES, CLEANING THESE AND DEVICE FOR IMPLEMENTATION OF THE KIT
US4628687A (en) * 1984-05-15 1986-12-16 A/S Kongsberg Vapenfabrikk Gas turbine combustor with pneumatically controlled flow distribution
DE3644030A1 (en) * 1986-12-22 1988-08-04 Siemens Ag CHARGED, COAL-FIRED STEAM GENERATOR

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO9405904A1 *

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104937239A (en) * 2012-11-02 2015-09-23 通用电气公司 System and method for oxidant compression in a stoichiometric exhaust gas recirculation gas turbine system
US9599070B2 (en) 2012-11-02 2017-03-21 General Electric Company System and method for oxidant compression in a stoichiometric exhaust gas recirculation gas turbine system
US10683801B2 (en) 2012-11-02 2020-06-16 General Electric Company System and method for oxidant compression in a stoichiometric exhaust gas recirculation gas turbine system

Also Published As

Publication number Publication date
SE500150C2 (en) 1994-04-25
JPH08500655A (en) 1996-01-23
WO1994005904A1 (en) 1994-03-17
SE9202467L (en) 1994-03-01
SE9202467D0 (en) 1992-08-28

Similar Documents

Publication Publication Date Title
US5680752A (en) Gas turbine plant with additional compressor
US5459994A (en) Gas turbine-air separation plant combination
US6901759B2 (en) Method for operating a partially closed, turbocharged gas turbine cycle, and gas turbine system for carrying out the method
US10145303B2 (en) Gas turbine efficiency and regulation speed improvements using supplementary air system continuous and storage systems and methods of using the same
US6269624B1 (en) Method of operating a power plant with recycled CO2
US5934063A (en) Method of operating a combustion turbine power plant having compressed air storage
JP2853681B2 (en) Method for operating an integrated gas turbine / air separation unit at partial load
US7383684B2 (en) Hybrid engine
US10107199B2 (en) Aero boost—gas turbine energy supplementing systems and efficient inlet cooling and heating, and methods of making and using the same
US20100024433A1 (en) System and method of operating a gas turbine engine with an alternative working fluid
US20040088987A1 (en) Integrated gas compressor
JPS60256522A (en) Gas turbine engine apparatus and its operation
WO1994025746A1 (en) High efficiency multi-shaft reheat turbine with intercooling and recuperation
US20150240719A1 (en) Gas turbine efficiency and regulation speed improvements using supplementary air system continuous and storage systems and methods of using the same
WO2010039318A1 (en) System and method of operating a power generation system with an alternative working fluid
CA2543379C (en) Turbo set with starting device
US20060232071A1 (en) Turbo set with starting device
WO1994005904A1 (en) Gas turbine plant with additional compressor
US5353597A (en) Inlet air cooling system
WO1997020135A1 (en) A method and a device for supplying air to a combustor
JPH08326554A (en) Power generating equipment with coal gasifying gas turbine and nitrogen feeding method therefor
Taher et al. Design Options for GHG Reduction of Gas Turbine Driven LNG Plants
US5873709A (en) Device for producing compressed air for various uses
Garner The Small Bleed-Off Gas-Turbine Engine
MXPA98006343A (en) Separation plant of a

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 19950303

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): DE DK ES FR GB IT

17Q First examination report despatched

Effective date: 19980427

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION HAS BEEN WITHDRAWN

18W Application withdrawn

Withdrawal date: 20000309