WO2003010426A1 - Multifuel gas turbine engines - Google Patents

Multifuel gas turbine engines Download PDF

Info

Publication number
WO2003010426A1
WO2003010426A1 PCT/AU2002/000991 AU0200991W WO03010426A1 WO 2003010426 A1 WO2003010426 A1 WO 2003010426A1 AU 0200991 W AU0200991 W AU 0200991W WO 03010426 A1 WO03010426 A1 WO 03010426A1
Authority
WO
WIPO (PCT)
Prior art keywords
air inlet
stage
gas turbine
turbine engine
combustion
Prior art date
Application number
PCT/AU2002/000991
Other languages
French (fr)
Inventor
Stuart Daevys
Original Assignee
Micro Gas Turbine Pty 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 Micro Gas Turbine Pty Ltd filed Critical Micro Gas Turbine Pty Ltd
Publication of WO2003010426A1 publication Critical patent/WO2003010426A1/en

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube
    • 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
    • F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
    • 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
    • F02C9/20—Control of working fluid flow by throttling; by adjusting vanes
    • 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
    • F02C9/26—Control of fuel supply
    • F02C9/40—Control of fuel supply specially adapted to the use of a special fuel or a plurality of fuels
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/26—Controlling the air flow
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/14—Two-dimensional elliptical
    • F05D2250/141—Two-dimensional elliptical circular
    • 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
    • F05D2250/00—Geometry
    • F05D2250/40—Movement of components
    • F05D2250/41—Movement of components with one degree of freedom
    • F05D2250/411—Movement of components with one degree of freedom in rotation

Definitions

  • the present invention relates to gas turbine engines and more particularly such engines which are capable of operating on a range of fuels.
  • a typical conventional gas turbine engine has an air inlet leading on a compressor stage which supplies compressed air to a combustion stage where fuel is injected and burning takes place.
  • a downstream turbine stage is drawn and applies rotational power to the turbine shaft whereby the compression stage turbines are driven.
  • the present invention provides, in one aspect, a gas turbine engine comprising a compressor stage, a combustion stage and a turbine stage, the turbine stage being coupled to a shaft which drives the compressor stage and the engine being characterised by a variable air inlet to the combustion stage with means for adjusting the air inlet whereby adjustment of the turbine can be made to suit different types or grades of fuel.
  • the invention may be defined as consisting in an air inlet adaptor kit for a gas turbine engine for adjusting air inlet characteristics to the combustion stage whereby adaptation is made to suit the particular grade or type of fuel to be used.
  • the air inlet to the combustion stage is of the nature of an annular configuration extending around the axis of the combustion stage and having a multiplicity of spaced inlet ports with an adjustment element moveable to vary the cross-sectional area of the air inlet ports.
  • this adjustment is through a mechanical linkage which permits adjustment at any time.
  • a preferred embodiment has the air inlet ports in the form of teardrop shaped apertures which align with other apertures and the adjustment is formed by circumferentially displacing one of the elements relative to the other whereby the cross-sectional area is varied.
  • a practical form of an advantageous embodiment is one in which an annular cavity is defined around the combustion chamber and between a casing of the combustion chamber and a turbine casing whereby compressed air from the compressor stage is fed to the annular chamber and the adjustable cross-sectional air inlet ports to the combustion chamber control the air supply.
  • the turbine includes an exhaust heat system for recovery of exhaust heat for energy generation purposes . It is believed that embodiments of the invention can be especially beneficial when applied to the market of micro-turbines where it is believed there is a particular potential demand for a compact but highly efficient unit which can operate on a multiplicity of different fuels.
  • micro-turbine is used to refer to turbines having the following parameters:
  • Figure 1 shows a perspective schematic view of a turbine stage of a turbine engine according to a preferred embodiment of the invention
  • Figure 2 shows a perspective schematic and in part sectional view of the turbine stage
  • Figure 3 shows a schematic perspective view of parts of the turbine stage.
  • the turbine engine comprises a compressor stage (not shown) and a turbine stage 10.
  • Compressor stage and turbine stage are positioned on a common shaft (also not shown) .
  • the turbine stage 10 is arranged for coupling to the compressor stage on face 12.
  • the turbine stage comprises an annular combustion chamber 14 and an outer casing 16.
  • the outer casing 16 has a multiplicity of spaced air inlet ports 18, 20 and 22 through which in use air provided by the combustion stage enters the outer casing 16.
  • the annular combustion chamber 14 also has a multiplicity of spaced air inlet ports 24 and 26 through which air enters from the annular chamber.
  • fuel lines 28 direct fuel into the combustion chamber and air intakes 30 are arranged such that, in use, an air/fuel swirl is generated in the combustion chamber.
  • the air inlet ports 20 have an adjustable cross- sectional area. By adjusting the cross-sectional area it is possible to select the volume of air that is fed into the combustion chamber. As the air/fuel ratio required for optimum combustion conditions is dependent on the type or grade of fuel used, it is possible to adjust the turbine stage for use of different fuels.
  • the adjustment is effected by an adjustment element that comprises a sleave 32 that is rotatable on the outer casing 16 and that has a plurality of teardrop shaped apertures 34 which align with the air inlet ports 20 of the annular chamber and the adjustment is effected by circumferentially displacing the sleave 32 whereby the cross- sectional area is varied.
  • the sleave 32 is adjustable through a rack and pinion arrangement 36. This rack and pinion arrangement 36 is externally controlled through mechanical linkages (not shown) .
  • a turbine engine of conventional design may be combined with a suitable adaptor kit for adjusting air inlet characteristics.
  • a kit may comprise an outer casing having air intake ports with adjustable cross-sectional areas.
  • Any form of the inventive turbine engine may also comprise an exhaust heat system for recovery of exhaust heat for energy generation purposes .

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

A gas turbine engine adapted for use with a range of fuels has a compressor stage, a combustion stage (14) and a turbine stage (10) with an air inlet arrangement from the compressor stage arranged in an annular form and having a variable cross section air inlet (18, 20, 22) into the combustion stage (14) with means for adjusting the cross-sectional area, whereby adaptation of the turbine for optimum performance on different fuels is provided.

Description

MULTIFUEL GAS TURBINE ENGINES
Field of the Invention
The present invention relates to gas turbine engines and more particularly such engines which are capable of operating on a range of fuels.
Background of the Invention
Generally gas turbine engines are designed and constructed to work on a particular grade of fuel with appropriate air inlet devices to produce efficient fuel burning and power generation. A typical conventional gas turbine engine has an air inlet leading on a compressor stage which supplies compressed air to a combustion stage where fuel is injected and burning takes place. A downstream turbine stage is drawn and applies rotational power to the turbine shaft whereby the compression stage turbines are driven.
Summary of the Invention
Broadly the present invention provides, in one aspect, a gas turbine engine comprising a compressor stage, a combustion stage and a turbine stage, the turbine stage being coupled to a shaft which drives the compressor stage and the engine being characterised by a variable air inlet to the combustion stage with means for adjusting the air inlet whereby adjustment of the turbine can be made to suit different types or grades of fuel.
In another aspect the invention may be defined as consisting in an air inlet adaptor kit for a gas turbine engine for adjusting air inlet characteristics to the combustion stage whereby adaptation is made to suit the particular grade or type of fuel to be used.
The novel concept of the present invention may be implemented in various forms. One important form of the invention is where the air inlet to the combustion stage is of the nature of an annular configuration extending around the axis of the combustion stage and having a multiplicity of spaced inlet ports with an adjustment element moveable to vary the cross-sectional area of the air inlet ports.
Preferably this adjustment is through a mechanical linkage which permits adjustment at any time. A preferred embodiment has the air inlet ports in the form of teardrop shaped apertures which align with other apertures and the adjustment is formed by circumferentially displacing one of the elements relative to the other whereby the cross-sectional area is varied. A practical form of an advantageous embodiment is one in which an annular cavity is defined around the combustion chamber and between a casing of the combustion chamber and a turbine casing whereby compressed air from the compressor stage is fed to the annular chamber and the adjustable cross-sectional air inlet ports to the combustion chamber control the air supply.
Preferably the turbine includes an exhaust heat system for recovery of exhaust heat for energy generation purposes . It is believed that embodiments of the invention can be especially beneficial when applied to the market of micro-turbines where it is believed there is a particular potential demand for a compact but highly efficient unit which can operate on a multiplicity of different fuels. In this specification, the term "micro-turbine" is used to refer to turbines having the following parameters:
Brief Description of Drawings
For illustrative purposes an embodiment will now be described with references to the accompanying drawings of which: Figure 1 shows a perspective schematic view of a turbine stage of a turbine engine according to a preferred embodiment of the invention;
Figure 2 shows a perspective schematic and in part sectional view of the turbine stage; and
Figure 3 shows a schematic perspective view of parts of the turbine stage.
Detailed Description of the Drawings
Referring to Figures 1 to 3 , a turbine engine according to the preferred embodiment is now described. In general, the turbine engine comprises a compressor stage (not shown) and a turbine stage 10. Compressor stage and turbine stage are positioned on a common shaft (also not shown) . The turbine stage 10 is arranged for coupling to the compressor stage on face 12. In this embodiment the turbine stage comprises an annular combustion chamber 14 and an outer casing 16. The outer casing 16 has a multiplicity of spaced air inlet ports 18, 20 and 22 through which in use air provided by the combustion stage enters the outer casing 16. The annular combustion chamber 14 also has a multiplicity of spaced air inlet ports 24 and 26 through which air enters from the annular chamber.
In this embodiment fuel lines 28 direct fuel into the combustion chamber and air intakes 30 are arranged such that, in use, an air/fuel swirl is generated in the combustion chamber. The air inlet ports 20 have an adjustable cross- sectional area. By adjusting the cross-sectional area it is possible to select the volume of air that is fed into the combustion chamber. As the air/fuel ratio required for optimum combustion conditions is dependent on the type or grade of fuel used, it is possible to adjust the turbine stage for use of different fuels. In the preferred form the adjustment is effected by an adjustment element that comprises a sleave 32 that is rotatable on the outer casing 16 and that has a plurality of teardrop shaped apertures 34 which align with the air inlet ports 20 of the annular chamber and the adjustment is effected by circumferentially displacing the sleave 32 whereby the cross- sectional area is varied. In this embodiment, the sleave 32 is adjustable through a rack and pinion arrangement 36. This rack and pinion arrangement 36 is externally controlled through mechanical linkages (not shown) .
It will be appreciated that the invention may take different forms. For example, a turbine engine of conventional design may be combined with a suitable adaptor kit for adjusting air inlet characteristics. Such a kit may comprise an outer casing having air intake ports with adjustable cross-sectional areas. Any form of the inventive turbine engine may also comprise an exhaust heat system for recovery of exhaust heat for energy generation purposes .

Claims

CLAIMS :
1. A gas turbine engine comprising a compressor stage, a combustion stage and a turbine stage, the turbine stage being coupled to a shaft which drives the compressor stage and the engine being characterised by a variable air inlet to the combustion stage with means for adjusting the air inlet whereby adjustment of the turbine can be made to suit different types or grades of fuel.
2. A gas turbine engine as claimed in claim 1, wherein air inlet to the combustion stage is of an annular configuration extending around the axis of the combustion stage and having a multiplicity of spaced inlet ports with an adjustment element moveable to vary the cross-sectional area of the air inlet ports.
3. A gas turbine engine as claimed in claim 2, wherein the adjustment element includes a mechanical linkage operable during turbine operations.
4. A gas turbine engine as claimed in any one of claims 1-3, wherein the variable air inlet has air inlet ports in the form of teardrop shaped apertures in a first element which are moveable relative to secondary apertures in a second element to a selected degree of registry by an adjustment comprising circumferentially displacement of one of the elements relative to the other whereby the cross-sectional area of the air inlet is varied.
5. A gas turbine engine as claimed in claim 4, wherein an annular cavity is defined around the combustion chamber and between a casing of the combustion chamber and a turbine casing whereby compressed air from the compressor stage is fed to the annular chamber and the adjustable cross-sectional air inlet ports to the combustion chamber control the air supply.
6. A gas turbine engine as claimed in any one of the preceding claims, and further comprising an exhaust heat system for recovery of exhaust heat for energy generation purposes .
7. An air inlet adaptor kit for a gas turbine engine for adjusting air inlet characteristics to the combustion stage the adaptor kit including a variable air inlet part for controlling air supply and means for adjusting the inlet port to control the air supply whereby adaptation is made to suit the particular grade or type of fuel to be used.
8. An adaptor kit as claimed in claim 7, wherein the air inlet to the combustion stage is of an annular configuration extending around the axis of the combustion stage and having a multiplicity of spaced inlet ports with an adjustment element moveable to vary the cross-sectional area of the air inlet ports.
9. A micro turbine in the form of a gas turbine engine as claimed in any one of the preceding claims .
PCT/AU2002/000991 2001-07-25 2002-07-25 Multifuel gas turbine engines WO2003010426A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
AUPR6579A AUPR657901A0 (en) 2001-07-25 2001-07-25 A miniature multifuel gas turbine engine
AUPR6579 2001-07-25

Publications (1)

Publication Number Publication Date
WO2003010426A1 true WO2003010426A1 (en) 2003-02-06

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ID=3830536

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/AU2002/000991 WO2003010426A1 (en) 2001-07-25 2002-07-25 Multifuel gas turbine engines

Country Status (2)

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AU (1) AUPR657901A0 (en)
WO (1) WO2003010426A1 (en)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10308384A1 (en) * 2003-02-27 2004-09-09 Alstom Technology Ltd Operating procedure for a gas turbine
JP2005265380A (en) * 2004-03-22 2005-09-29 Japan Aerospace Exploration Agency Air flow rate adjustment valve for gas turbine combustor
CN105378248A (en) * 2013-05-13 2016-03-02 索拉透平公司 Tapered gas turbine engine liquid gallery
CN109099460A (en) * 2017-06-20 2018-12-28 中国航发商用航空发动机有限责任公司 A kind of air inlet area regulating device and combustion chamber
WO2021076671A1 (en) 2019-10-14 2021-04-22 William Marsh Rice University Porous polymeric carbon sorbents for gas storage and methods of making and using same
WO2022220828A1 (en) 2021-04-14 2022-10-20 William Marsh Rice University Porous polymeric carbon sorbents and methods of making and using same
FR3141755A1 (en) * 2022-11-08 2024-05-10 Safran Aircraft Engines Combustion chamber of a turbomachine

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US3765171A (en) * 1970-04-27 1973-10-16 Mtu Muenchen Gmbh Combustion chamber for gas turbine engines
US3869246A (en) * 1973-12-26 1975-03-04 Gen Motors Corp Variable configuration combustion apparatus
US3930368A (en) * 1974-12-12 1976-01-06 General Motors Corporation Combustion liner air valve
US4050240A (en) * 1976-08-26 1977-09-27 General Motors Corporation Variable air admission device for a combustor assembly
US5317863A (en) * 1992-05-06 1994-06-07 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Gas turbine combustion chamber with adjustable primary oxidizer intake passageways
JPH08135969A (en) * 1994-11-08 1996-05-31 Hitachi Ltd Air flow rate regulator for gas turbine combustor
JPH10122568A (en) * 1996-10-14 1998-05-15 Nissan Motor Co Ltd Structure of combustion device in gas turbine
JPH1130423A (en) * 1997-07-09 1999-02-02 Ishikawajima Harima Heavy Ind Co Ltd Low nox combustor for gas turbine
US5996333A (en) * 1996-10-16 1999-12-07 Societe National D'etude Et De Construction De Moteurs D'aviation Oxidizer control device for a gas turbine engine

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3765171A (en) * 1970-04-27 1973-10-16 Mtu Muenchen Gmbh Combustion chamber for gas turbine engines
US3869246A (en) * 1973-12-26 1975-03-04 Gen Motors Corp Variable configuration combustion apparatus
US3930368A (en) * 1974-12-12 1976-01-06 General Motors Corporation Combustion liner air valve
US4050240A (en) * 1976-08-26 1977-09-27 General Motors Corporation Variable air admission device for a combustor assembly
US5317863A (en) * 1992-05-06 1994-06-07 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Gas turbine combustion chamber with adjustable primary oxidizer intake passageways
JPH08135969A (en) * 1994-11-08 1996-05-31 Hitachi Ltd Air flow rate regulator for gas turbine combustor
JPH10122568A (en) * 1996-10-14 1998-05-15 Nissan Motor Co Ltd Structure of combustion device in gas turbine
US5996333A (en) * 1996-10-16 1999-12-07 Societe National D'etude Et De Construction De Moteurs D'aviation Oxidizer control device for a gas turbine engine
JPH1130423A (en) * 1997-07-09 1999-02-02 Ishikawajima Harima Heavy Ind Co Ltd Low nox combustor for gas turbine

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DATABASE WPI Derwent World Patents Index; Class Q52, AN 1996-311980/32 *
DATABASE WPI Derwent World Patents Index; Class Q52, AN 1998-336602/30 *
DATABASE WPI Derwent World Patents Index; Class Q73, AN 1999-176389/15 *

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10308384A1 (en) * 2003-02-27 2004-09-09 Alstom Technology Ltd Operating procedure for a gas turbine
US7516608B2 (en) 2003-02-27 2009-04-14 Alstom Technology Ltd. Method for operating a gas turbine
JP2005265380A (en) * 2004-03-22 2005-09-29 Japan Aerospace Exploration Agency Air flow rate adjustment valve for gas turbine combustor
CN105378248A (en) * 2013-05-13 2016-03-02 索拉透平公司 Tapered gas turbine engine liquid gallery
CN109099460A (en) * 2017-06-20 2018-12-28 中国航发商用航空发动机有限责任公司 A kind of air inlet area regulating device and combustion chamber
WO2021076671A1 (en) 2019-10-14 2021-04-22 William Marsh Rice University Porous polymeric carbon sorbents for gas storage and methods of making and using same
WO2021076670A1 (en) 2019-10-14 2021-04-22 William Marsh Rice University Porous polymeric carbon sorbents for co2 capture and methods of making and using same
WO2021076672A1 (en) 2019-10-14 2021-04-22 William Marsh Rice University Porous polymeric carbon sorbents for direct air capture of co2 and methods of making and using same
WO2022220828A1 (en) 2021-04-14 2022-10-20 William Marsh Rice University Porous polymeric carbon sorbents and methods of making and using same
FR3141755A1 (en) * 2022-11-08 2024-05-10 Safran Aircraft Engines Combustion chamber of a turbomachine

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