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GB2395753A - Fuel compressor system for a gas turbine - Google Patents

Fuel compressor system for a gas turbine Download PDF

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Publication number
GB2395753A
GB2395753A GB0226135A GB0226135A GB2395753A GB 2395753 A GB2395753 A GB 2395753A GB 0226135 A GB0226135 A GB 0226135A GB 0226135 A GB0226135 A GB 0226135A GB 2395753 A GB2395753 A GB 2395753A
Authority
GB
United Kingdom
Prior art keywords
compressor
fuel
turbine
fuel compressor
gas turbine
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Withdrawn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
GB0226135A
Other versions
GB0226135D0 (en
Inventor
David Flaxington
David Ainsworth
Alexander Kenworthy Molyneaux
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.)
Bowman Power Systems Ltd
Original Assignee
Bowman Power Systems Ltd
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 Bowman Power Systems Ltd filed Critical Bowman Power Systems Ltd
Priority to GB0226135A priority Critical patent/GB2395753A/en
Publication of GB0226135D0 publication Critical patent/GB0226135D0/en
Publication of GB2395753A publication Critical patent/GB2395753A/en
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
    • F01D15/08—Adaptations for driving, or combinations with, pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01K—STEAM ENGINE PLANTS; STEAM ACCUMULATORS; ENGINE PLANTS NOT OTHERWISE PROVIDED FOR; ENGINES USING SPECIAL WORKING FLUIDS OR CYCLES
    • F01K23/00—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids
    • F01K23/02—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engine cycles being thermally coupled
    • F01K23/06—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engine cycles being thermally coupled combustion heat from one cycle heating the fluid in another cycle
    • F01K23/10—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engine cycles being thermally coupled combustion heat from one cycle heating the fluid in another cycle with exhaust fluid of one cycle heating the fluid in another cycle
    • 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
    • F02C3/20—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products
    • F02C3/22—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being gaseous at standard temperature and pressure
    • 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
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/18—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use using the waste heat of gas-turbine plants outside the plants themselves, e.g. gas-turbine power heat plants
    • 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
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/08—Heating air supply before combustion, e.g. by exhaust gases
    • 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
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/22—Fuel supply systems
    • 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
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/32—Arrangement, mounting, or driving, of auxiliaries
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/70—Application in combination with
    • F05D2220/72—Application in combination with a steam turbine
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E20/00—Combustion technologies with mitigation potential
    • Y02E20/14—Combined heat and power generation [CHP]

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)

Abstract

A micro turbine generator system (10) includes a gas fuel compressor (54) which is driven by a steam powered turbine (44). The turbine (44) is driven by steam produced in a heat recovery steam generator (36), which is heated by the exhaust from the gas turbine engine.

Description

FUEL COMPRESSOR SYSTEM FOR A GAS TURBINE ENGINE
The present invention relates to a fuel compressor system for a gas turbine engine, and to a gas turbine engine incorporating such a system. The 5 invention also relates to methods of operating gas turbine engines. The present invention relates particularly, but not exclusively, to micro turbine generators, of the type including a gas turbine engine and an electrical generator, usually being relatively small, such as usually developing no more than about l00kW to 250kW or 300 kW of electrical power.
10 A known fuel compressor system for a micro turbine generator comprises a compressor driven by an electric motor. The electric motor drive has implications on micro turbine generator net thermal efficiency. In some applications, such as when a 3kw to 4 kW high speed electric drive might be required, the electric drive would be relatively complex and expensive.
15 it is also desirable in gas turbines that any leakage between fuel in a compressor and air or other gases nearby should not lead to an air/fuel ratio which could cause an undesirable combustion and possibly an explosion.
The present invention aims to alleviate at least to a certain extent the problems of the prior art and to provide a fuel compressor with lower and
20 preferably as near to no impact as possible on the micro turbine generator efficiency. According to a first aspect of the present invention there is provided a fuel compressor system as set out in claim 1. The use of a steam powered fuel compressor enables a potentially cheaper installation with lower effects on 25 efficiency. According to a second aspect of the present invention there is provided a fuel compressor system as set out in claim 3.
Various optional features are set out in dependent claims 2 and 4 to 12.
According to further aspects of the invention there is provided a gas turbine engine system as set out in claim 13. Various optional features are set out in claims 14 to 15. A further aspect of the invention comprises a method of operating a gas turbine engine as set out in claim 17. The various optional 5 features are set out in claims 18 to 20. Preferably, the compressor is for compressing gaseous fuel.
Further aspects of the invention are set out in claims 22, 34 and 35.
Various optional features are set out in claims 23 to 33.
In preferred embodiments of the present invention, a gas boost 10 compressor may be driven by heat recovered from the exhaust of a micro turbine generator. The gas boost compressor (or fuel compressor) may be of the centrifugal type, so as to be light and cheap, at least compared to known screw compressors. In preferred embodiments of the invention, exhaust heat may be used to generate high pressure steam and the steam may be used in a 15 turbine to drive the gas compressor. This may use no power from the micro turbine generator which would not otherwise be wasted and so may have no real effect on micro turbine generator electrical efficiency. A small amount of heat only may be taken from the exhaust. This may have a very small affect on the total efficiency in combined heat and power applications, which are 20 envisaged in the present invention. Total efficiency may be particularly good.
An additional advantage is that steam, where employed, can be generated at high pressure. This may allow sealing between the fuel compressor and any turbine used to drive it to be arranged so that there would only be a flow from the steam side into gas, rather than vice versa, for safety 25 reasons. Furthermore, no air will be likely to enter the gas and no gas will be likely to leak to atmosphere, thus ensuring safety.
In embodiments where a steam circuit is not present, steam could be vented to atmosphere or dueled to a water cooling circuit (such as for an
alternator of the gas turbine engine) or may be ducted to an air inlet of the micro turbine generator.
At start-up, when no steam is present, and electric boiler may be employed to produce steam. This may be switched off once sufficient steam is 5 being generated.
The gas fuel compressor may be designed to have an excess flow capacity. Excess flow may be recycled to the inlet, after cooling. This may allow the gas boost compressor/fuel compressor to operate at a constant speed and may allow part load conditions to be achieved by varying the recycled flow 10 rate. The present invention may be carried out in various ways and two examples of preferred embodiments of fuel compressor systems in accordance with the invention will now be described by way of example with reference to the accompanying drawing, in which: 15 Figure 1 is a schematic view of a fuel compressor system and gas turbine engine/generator system.
Figure 2 is a schematic view of a further fuel compressor system and gas turbine engine/generator system; and Figure 3 is a schematic side view of the fuel compressor of Figure 2.
20 As shown in Figure 1, a micro turbine generator system 10 includes a main air compressor 12, a main turbine 14, a combustor 16, a recuperator 18, and an alternator 20. Rotors 20, 22, 24 of the compressor, turbine and alternator respectively, are located on a common shaft 28. During start-up, the alternator 20 acts as a motor to spin up the shaft 28. The alternator 20 may 25 then be switched to become a generator to power an electrical load 30. The main air compressor 12 draws air from an air inlet 32 and supplies compressed air through the recuperator 18 to the combustor 16, the combustor being provided with fuel from a fuel compressor system 34. Combusted gasses from the combustor 16 pass through the main turbine 14 (which drives the
compressor 12 and alternator 20) and the exhausted products then pass through the recuperator 18 and a heat recovery steam generator 36 of the fuel compressor system 34 and then to an exhaust stack 38 or other appliance.
The fuel compressor system includes a steam circuit 40 in which steam 5 is circulated by a pump 42 through the heat recovery steam generator 36, a turbine drive 44 and a condenser 46. An electric boiler 48 is provided in the circuit to produce steam at start-up, when the heat recovery steam generator 36 has not yet been heated up by exhaust gasses on the way to the exhaust stack 38. 10 The drive turbine 44 is connected by a drive shaft 50 to a centrifugal compressor rotor 52 of a gas fuel compressor 54. The turbine 44 thus causes the compressor 54 to compress fuel for delivery to the combustor 16. The compressor 54 is part of a fuel circuit 56 which includes a variable pressure return valve 58 and a plenum/reservoir 60, the circuit 56 being provided with 15 gaseous fuel from a mains fuel supply 62.
A controller 64 is connected by signal paths 66, 68, 70, 72 to the pump 66, valve 58, speed sensor 74 and pressure sensor 76, so that the fuel delivery pressure and speed of the shaft 50 may be obtained within desirable parameters. For example, the gas boost compressor may be operated at 20 constant speed with part load conditions being achieved by varying the recycle flow rate, using the valve 58.
In other embodiments, the steam may be vented to atmosphere, or dueled to a water cooling circuit for the system (such as a circuit for cooling the alternator 20 and associated electronics, or the steam may be ducted to the 25 air inlet 32.
Figure 2 shows a further embodiment of a micro turbine generator 100 having a main air compressor 102, main turbine 104, alternator 106, recuperator 108 and combustor 110.
An air bleed line 112 from the air compressor 102 leads via a variable valve 114 to the inlet 116 of a turbine 118. The turbine 118 has a rotor 120 of the radial inflow/axial outflow type, connected by a shaft 122 to a compressor rotor 124 of the axial inflow/radial outflow type of a fuel compressor 126 for 5 compressing, gas fuel such as natural gas.
Fuel from fuel inlet 128 is driven by the compressor rotor 124 via the compressor inlet 130, along channels 132 adjacent compressor blades 134 shrouded by shroud 136 to the compressor outlet 138, the fuel then passing along conduit 140 to combustorlburner 110 of the micro turbine generator 100.
10 The spinning fuel compressor rotor 124 is driven by shaft 122, shaft being supported on bearings (not shown), by spinning turbine rotor 120.
The speed of rotation of the shaft 122 is controlled by variable valve 114, admitting high pressure air from the air compressor 102 to the turbine inlet 116 of the turbine rotor 120 of the fuel compressor 150. This air passes from 15 turbine inlet 116 along channels 140 between rotor blades 142 which are shrouded by shroud 144 to the turbine outlet 146, the air then passing to exhaust point 148.
The shaft 122 has a seal 152 for preventing gases from passing between the compressor 126 of the fuel compressor system 150 and the turbine 118 of 20 the fuel compressor system 150, and vice versa. However, due to the nature of means for sealing rotating shafts, the seal 152 may not always be perfect meaning that a small passage for flow may exist between the compressor and turbine sides of the fuel compressor system.
However, the turbine rotor 120 has a low pressure side 160 thereof at the 25 turbine outlet 146 facing the low pressure side 162 of the compressor 124 near the compressor inlet 130. The fuel compressor system 150 is arranged and the micro turbine generator system operated in such a way that the exit pressure at the low pressure side 160 of the turbine will be somewhat higher than the inlet pressure at the turbine inlet point 162. Therefore, any small leakage past the
seal 152 will be a small leakage of air from the turbine 118 of the fuel compressor system 150 to the compressor 126 side, rather than the other way around. Accordingly, any leak will be a small leak of air into fuel, not reaching a sufficient air/fuel ratio for an undesirable and potentially explosive 5 combustion in or near the fuel compressor system 150.
It will be noted that the configuration of the fuel compressor system 150 is quite unlike the configuration of known turbochargers and micro turbine generator main compressor/turbine wheel sets in which the compressor outlet and turbine inlet are adjacent one another with the compressor inlet and turbine 10 outlet facing away from one another in opposite directions. The opposite construction used in the present embodiment is advantageous therefore because, when the fuel pressure at the fuel compressor outlet 138 is higher than the pressure at the turbine inlet 116, this does not result in the possibility of the leakage of a small amount of fuel from the compressor side into the turbine 15 side of the fuel compressor system which could provide an air/fuel ratio capable of an undesirable, and potentially explosive, combustion in or near to the fuel compressor system 150. Accordingly, in this embodiment there are similar safety advantages to those in the embodiment of Figure 1 in which the steam pressure at the turbine may be maintained sufficiently high to ensure that 20 any small leakage is towards the compressor rather than towards the turbine of the fuel compressor system.
In the preferred embodiments, the fuel compressor 52,126 may be designed for an excess capacity. In this case a fuel recirculation path to the low pressure side of the compressor may be provided for the excess fuel. A 25 significant loss may be due to fuel leakage over the blade tips from one channel to the next. This leakage is proportioned to the proportion of the blade height, measured across the passage at right angles to the flow direction, that is taken up by the clearance space. If excess fuel is compressed, the blade height will increase and the proportion of the height taken by the clearance will reduce.
Instead of providing radial-type compressor and turbine wheels, other types of compressor and turbine such as axial flow type may be used.
Various modifications may be made to the embodiment described without departing from the scope of the invention as defined by the 5 accompanying claims as interpreted under patent law.

Claims (1)

  1. g CLAIMS
    1. A fuel compressor system for a gas turbine engine, the system having a steam powered fuel compressor.
    2. A fuel compressor system as claimed in claim 1 in which steam for powering the fuel compressor is produced by a heat recovery device for recovering heat from combustion exhaust of a gas turbine engine.
    10 3. A fuel compressor system for a gas turbine engine, the system having a fuel compressor, and a heat recovery device for recovering heat from combustion exhaust of a gas turbine engine in order to power the fuel compressor. 15 4. A fuel compressor system as claimed in claim 3 in which the fuel compressor is steam powered.
    5. A fuel compressor system as claimed in claim 2 or claim 3, or claim 4 when dependent upon claim 2 or claim 3, in which the heat recovery device 20 comprises a heat recovery steam generator.
    6. A fuel compressor system as claimed in any preceding claim in which the compressor is driven from a steam powered turbine.
    25 7. A fuel compressor system as claimed in claim 6 in which the steam powered turbine is adapted to operate at higher inlet pressure than the outlet pressure of the fuel compressor.
    8. A fuel compressor system as claimed in any one of the preceding claims, which includes a steam circuit.
    9. A fuel compressor system as claimed in claim 8 in which the steam 5 circuit includes a condenser, a pump and an evaporator.
    10. A fuel compressor system as claimed in claim 9 when dependent upon claim 5 in which the evaporator is located in the heat recovery steam generator.
    10 11. A fuel compressor system as claimed in any one of claim 7 or claim 8 when dependent upon claim 9 or claim 10, which includes a boiler for producing steam for powering the fuel compressor during start-up.
    12. A fuel compressor system substantially as described herein with 15 reference to the accompanying drawing.
    13. A gas turbine system which includes a fuel compressor system as claimed in any one of the preceding claims.
    20 14. A gas turbine system as claimed in claim 13 in which a fuel exit from the fuel compressor is connected by a conduit to a combustor of a gas turbine engine of the system.
    15. A gas turbine system as claimed in claim 14 when dependent upon claim 25 5 in which the gas turbine engine includes a recuperator the recuperator being located between a main turbine of the gas turbine engine and the heat recovery steam generator in an exhaust gaseous path from the gas turbine engine.
    16. A gas turbine system substantially as described herein with reference to the accompanying drawing.
    17. A method of operating a gas turbine comprising providing fuel to the gas 5 turbine with a steam powered fuel compressor.
    18. A method as claimed in claim 17 in which the compressor is driven from a steam powered turbine.
    10 19. A method as claimed in claim 18 which includes maintaining steam inlet pressure to the turbine higher than the fuel outlet pressure from the fuel compressor. 20. A method as claimed in any one of claims 17 to 19 in which the fuel is 1 5 gaseous.
    21. A method of operating a gas turbine engine substantially as described herein with reference to the accompanying drawing.
    20 22. A fuel compressor apparatus for a gas turbine, the apparatus comprising: a compressor for compressing fuel; a turbine for driving the compressor; the turbine rotor having one side thereof facing an adjacent side of the compressor; the apparatus being adapted to run with pressure at said one side of the turbine higher than pressure at the adjacent side of the compressor.
    23. A fuel compressor apparatus as claimed in claim 22 in which the compressor has a radial flow rotor.
    24. A fuel compressor apparatus as claimed in claim 22 or claim 23 in which the turbine has a radial flow rotor.
    25. A fuel compressor apparatus as claimed in claim 22, claim 23 or claim 5 24 in which the compressor has a rotor located on the same shaft as and driven by a rotor of the turbine.
    26. A fuel compressor apparatus as claimed in claim 25 which includes a shaft seal between the compressor rotor and turbine rotor.
    27. A fuel compressor apparatus as claimed in any one of claims 22 to 26 in which the turbine has a steam driven rotor.
    28. A fuel compressor apparatus as claimed in claim 27 which is adapted to 15 operate with steam inlet pressure to the turbine higher than fuel exit pressure from the compressor.
    29. A fuel compressor apparatus as claimed in any one of claims 22 to 28 which is adapted to operate with turbine exhaust pressure higher than 20 compressor inlet pressure.
    30. A fuel compressor apparatus as claimed in any one of claims 22 to 29 which is arranged with a compressor inlet located on a side of the compressor which faces the turbine.
    31. A fuel compressor apparatus as claimed in any one of claims 22 to 30 which is arranged with a turbine outlet from the turbine located on a side of the turbine which faces the compressor.
    32. A fuel compressor apparatus as claimed in any one of claims 22 to 31 in which the turbine has a radial flow rotor having a diameter which increases in an axial direction thereof away from the compressor.
    5 33. A fuel compressor apparatus as claimed in any one of claims 22 to 32 in which the compressor has a radial flow rotor having a diameter which increases in an axial direction thereof away from the turbine.
    34. A gas turbine including a fuel compressor apparatus as claimed in any l O one of claims 22 to 31.
    35. A method of providing fuel to a gas turbine comprising providing a fuel compressor apparatus as claimed in any one of claims 22 to 31 and operating the fuel compressor while maintaining pressure at one side of the turbine higher 15 than the pressure at an adjacent side of the compressor.
    36. A system as claimed in any one of claims 1 to 16 in which the fuel compressor is adapted for operation at flow capacity in excess of that required by the system.
    37. A method as claimed in claim 35 which includes operating the compressor at a fuel capacity in excess of that required by the gas turbine.
GB0226135A 2002-11-08 2002-11-08 Fuel compressor system for a gas turbine Withdrawn GB2395753A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB0226135A GB2395753A (en) 2002-11-08 2002-11-08 Fuel compressor system for a gas turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB0226135A GB2395753A (en) 2002-11-08 2002-11-08 Fuel compressor system for a gas turbine

Publications (2)

Publication Number Publication Date
GB0226135D0 GB0226135D0 (en) 2002-12-18
GB2395753A true GB2395753A (en) 2004-06-02

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Family Applications (1)

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GB0226135A Withdrawn GB2395753A (en) 2002-11-08 2002-11-08 Fuel compressor system for a gas turbine

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GB (1) GB2395753A (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2446810A (en) * 2007-02-22 2008-08-27 Bowman Power Group Ltd An Auxillary Power Generation Apparatus
JP2009052489A (en) * 2007-08-28 2009-03-12 Miura Co Ltd Steam system
EP2500546A1 (en) * 2011-03-18 2012-09-19 General Electric Company System and method for controlling a fuel supply associated with a turbomachine
CN103104350A (en) * 2011-11-15 2013-05-15 株式会社日立制作所 Twin-shaft gas turbine
US8522523B2 (en) 2008-03-06 2013-09-03 Miura Co., Ltd. Steam system

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH0388903A (en) * 1989-08-31 1991-04-15 Mitsubishi Heavy Ind Ltd Compound engine
JPH0968006A (en) * 1995-08-29 1997-03-11 Kawasaki Heavy Ind Ltd Gas turbine equipment
JPH11153041A (en) * 1997-11-19 1999-06-08 Toshiba Eng & Constr Co Ltd Gas turbine system

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH0388903A (en) * 1989-08-31 1991-04-15 Mitsubishi Heavy Ind Ltd Compound engine
JPH0968006A (en) * 1995-08-29 1997-03-11 Kawasaki Heavy Ind Ltd Gas turbine equipment
JPH11153041A (en) * 1997-11-19 1999-06-08 Toshiba Eng & Constr Co Ltd Gas turbine system

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2446810A (en) * 2007-02-22 2008-08-27 Bowman Power Group Ltd An Auxillary Power Generation Apparatus
GB2446810B (en) * 2007-02-22 2011-09-14 Bowman Power Group Ltd An auxiliary power generation apparatus
JP2009052489A (en) * 2007-08-28 2009-03-12 Miura Co Ltd Steam system
US8522523B2 (en) 2008-03-06 2013-09-03 Miura Co., Ltd. Steam system
EP2500546A1 (en) * 2011-03-18 2012-09-19 General Electric Company System and method for controlling a fuel supply associated with a turbomachine
CN103104350A (en) * 2011-11-15 2013-05-15 株式会社日立制作所 Twin-shaft gas turbine
CN103104350B (en) * 2011-11-15 2015-09-16 三菱日立电力系统株式会社 Twin-shaft turbine

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