WO2010101498A1 - Dispositif de turbine à vapeur et à gaz - Google Patents

Dispositif de turbine à vapeur et à gaz Download PDF

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Publication number
WO2010101498A1
WO2010101498A1 PCT/SE2009/050234 SE2009050234W WO2010101498A1 WO 2010101498 A1 WO2010101498 A1 WO 2010101498A1 SE 2009050234 W SE2009050234 W SE 2009050234W WO 2010101498 A1 WO2010101498 A1 WO 2010101498A1
Authority
WO
WIPO (PCT)
Prior art keywords
rotor
turbine device
rotor hub
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.)
Ceased
Application number
PCT/SE2009/050234
Other languages
English (en)
Inventor
Torbjörn Eriksson
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.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Priority to CN200980157881.5A priority Critical patent/CN103429848B/zh
Priority to PCT/SE2009/050234 priority patent/WO2010101498A1/fr
Publication of WO2010101498A1 publication Critical patent/WO2010101498A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

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
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/02—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines
    • F01D1/023—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines the working-fluid being divided into several separate flows ; several separate fluid flows being united in a single flow; the machine or engine having provision for two or more different possible fluid flow paths
    • 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
    • F01K23/12—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engines being mechanically coupled
    • F01K23/16—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engines being mechanically coupled all the engines being turbines
    • 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
    • F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
    • F02C3/073—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages the compressor and turbine stages being concentric
    • 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
    • F05D2220/30—Application in turbines
    • F05D2220/31—Application in turbines in steam turbines
    • 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
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • 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
    • 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
    • F05D2220/74—Application in combination with a gas turbine

Definitions

  • the present invention relates to a turbine device for converting a flow of gas and a flow of steam into a rotational movement in a shaft.
  • Gas turbines are frequently used in different applications for conversion of chemical energy into mechanical energy. This conversion of energy is achieved by generating a flow of gas that is used for rotating a rotor in the gas turbine.
  • the flow of gas is generated by combustion gases from the combustion of for example natural gas or an oil based product.
  • the combustion takes place in a combustion chamber placed upstream of the rotor. Air is continuously supplied to the chamber and in order to improve the efficiency of the turbine, air is preferably supplied to the combustion chamber under pressure generated by a compressor.
  • the heat generated in the gas turbine during the combustion is used for generating a flow of steam that, in combination with the flow of combustion gases, could be used to rotate the rotor.
  • the efficiency the ratio between the amount of supplied energy and the amount of delivered mechanical energy from the gas turbine is thereby improved further.
  • a gas turbine device designed for using a flow of combustion gases and a flow of steam is disclosed in WO 2008/111905.
  • the disclosed gas turbine device comprises a stator surrounding a rotor placed in the centre of the space within the stator.
  • the stator is provided with stator discs placed along the inside of the stator and extending from the inside of the stator towards the rotor hub.
  • rotor wings extending from the rotor hub are placed.
  • two passages are arranged concentrically and separated from each other. The two passages are separated by sealing elements placed between each stator disc and rotor wing.
  • the gas turbine rotor is rotating at high speed which makes it very difficult to provide the desired sealing between the stator discs and the rotor wings which is essential to keep the two passages separated from each other.
  • the sealings are furthermore exposed to high temperature that makes it even more complicated, and expensive, to provide sealing that provides the required long time performance.
  • the disclosed gas turbine device is complex which makes it expensive to manufacture.
  • the present invention provides gas turbine device that solves the problems defined above.
  • the present invention provides a gas turbine device for converting a flow of gas and a flow of steam into a rotational movement in a shaft that reduces the problems described above.
  • the claimed turbine device for converting a flow of gas and a flow of steam into a rotational movement in a shaft comprises: a gas turbine portion, a steam turbine portion arranged concentrically with the gas turbine portion, and an outer stator surrounding the gas turbine portion and the steam turbine portion, a rotor comprising a rotor hub placed in the centre of the stator.
  • the turbine device is characterised in that the gas turbine portion or the steam turbine portion is extending inside the rotor hub.
  • the claimed turbine device solves the problems related to previously known turbine devices by letting the gas turbine portion or the steam turbine portion extend within the rotor hub.
  • the rotor hub separates the gas portion and the steam portion whereby the need for complicated and expensive sealings between the rotor wheels and the stator discs is eliminated.
  • a further advantage with the claimed turbine device is that the hot gas turbine portion and the considerably less hot steam turbine portion are separated by the rotor hub instead of, as in the turbine device disclosed in WO 2008/111905 Al, the sealings placed between the rotor blades and the stator discs. This difference improves the reliability of the turbine device since each of the rotor blades and the sealings in the turbine device disclosed in WO 2008/111905 Al will be exposed to big temperature differences that cause thermal expansion, and tensions, within the blades and the sealings that could damages the sealings and blades, while each blade in the turbine device according to the invention only is exposed to either the flow of gas or flow of steam.
  • the turbine device according to the present invention is structurally considerably less complicated which makes it less expensive to manufacture, and reduces the risk for turbine device failure.
  • the outer stator comprises stator discs extending from the inside surface of the stator towards the rotor hub substantially transversal to the rotational axis of the rotor.
  • the stator discs are used for directing the flow of gas or steam within the turbine portion in the desired direction and thereby improve the efficiency of the gas turbine device.
  • the rotor comprises rotor wheels extending in substantially radial direction from the rotor hub towards the inside of the outer stator.
  • Each rotor wheel comprises a number of inclined rotor blades. When the flow of gas or steam reaches the inclined rotor blades the rotor is turned around its rotational axis.
  • One embodiment of the turbine device further comprises an inner stator placed in the centre of the rotor hub.
  • the inner stator have an outer diameter smaller than the inside diameter of the rotor hub in order to generate a space for the turbine portion extending inside the rotor hub between the inner stator and the inside surface of the rotor hub.
  • This embodiment provides a turbine device, and a turbine portion extending within the rotor hub, that is effective and reliably.
  • the rotor comprises inner rotor wheels extending in substantially radial direction from the inside surface of the rotor hub towards the inner stator.
  • Each rotor wheel comprises a number of inclined rotor blades. When the flow of gas or steam reaches the inclined rotor blades the rotor is turned around its rotational axis.
  • the inner stator comprises inner stator discs extending from the inner stator towards the inside surface of the rotor hub between adjacent inner rotor wheels. The inner stator discs are positioned in the space between two adjacent discs in order to direct the flow in a desired direction to improve the efficiency of the turbine device further.
  • the flow of gas or steam is lead into the turbine portion within the rotor hub via a passage in the inner stator.
  • the flow of gas or steam exits the turbine portion within the rotor hub via at least one opening in the downstream end of the rotor hub.
  • the inner rotor wheels comprises a number of inner rotor blades
  • the rotor wheels comprises a number of rotor blades
  • a passageway is arranged within the rotor blades, the rotor hub and the inner rotor blades so that a fluid flowing in the passageway transfer heat from the gas turbine portion to the steam turbine portion.
  • the steam turbine portion is extending within the rotor hub.
  • the steam turbine portion is preferably arranged within the rotor hub since the flow of steam, generated by the heat from the gas generator, is smaller than the flow of combustion gas and the cross sectional area of the turbine portion within the rotor hub is smaller than the cross sectional area of the turbine portion on the opposite side of the rotor hub.
  • the inside diameter of the outer stator is increasing downstream the turbine device. This outer stator design improves the efficiency of the gas turbine device.
  • the rotor hub has a substantially constant outer diameter.
  • the outside diameter of the inner stator is decreasing downstream the turbine device. This inner stator design improves the efficiency of the gas turbine device.
  • Figure 1 illustrates a schematic cross sectional view through the gas turbine device
  • Figure 2 illustrates the turbine device in figure 1 with some additional features.
  • the gas turbine device 10 according the present invention could be used in combination with several different arrangements used for generating the desired flow of combustion gas, as well as several different arrangements for generating and deliver the desired flow of steam to the gas turbine device 10.
  • the arrangement for generating a flow of combustion gas could involve one or more compressors in order to increase the pressure within the combustion chamber before the fuel, such as natural gas or an oil based fuel, is combusted within the combustion chamber and the desired increase of pressure within the combustion chamber is achieved.
  • the generated flow of combustion gas is lead to the turbine device 10 from the combustion chamber.
  • This heat is preferably used for vaporisation of a fluid to steam that could be used in the turbine device 10 to increase the efficiency of the turbine device 10.
  • the turbine device 10 illustrated in the figures, comprises an outer stator 11 having a tubular shape. In the centre of the space within the outer stator 11 a rotor 12 is arranged thereby creating a gas flow portion 20 extending within the turbine device 10 between the outer stator 11 and a rotor hub 13 placed in the centre of the rotor 12.
  • the gas flow portion 20 has an inlet 27 for the gas from the gas generator in the upstream end of the turbine device 10 and a gas outlet 16 in the downstream end of the turbine device 10.
  • the inlet 27 and the outlet 16 are arranged around the inside periphery of the outer stator 11.
  • the inlet 27 is connected to the gas flow generator described above.
  • the gas flow generator could be placed in the axial upstream direction of the turbine device 10.
  • the rotor 12 is able to rotate around a rotational axis coaxial with the longitudinal axis of the outer stator 10.
  • the rotor 12 comprises the substantially cylindrical rotor hub 13 placed in the centre of the rotor 12 and a number of rotor wheels 14 arranged along the cylindrical rotor hub 13 to rotate together with the rotor hub 13.
  • Each rotor wheel 14 comprises a number of inclined rotor blades, that, when exposed to the flow of gas, will turn the rotor 12.
  • the number of blades and the exact shape of each blade could differ depending on the desired turbine features and the specific application for the turbine device 10.
  • the rotor wheels 14 are positioned at a constant axial distance from each other along the cylindrical rotor hub 13. The number of rotor wheels 14 is selected depending on the size of the turbine device 10, and the specific application for the turbine device 10.
  • stator disc 15 is positioned in each of the spaces between adjacent rotor wheels 14.
  • the stator discs 15 are rigidly attached to the outer stator 11 and extend from the inside surface of the outer stator 11 in substantially radial direction towards the rotor hub 13 to fill the space between the adjacent rotor wheels 14.
  • Each stator disc 15 comprises a number of stator wings, not illustrated, that are influencing the flow of gas through the gas turbine portion 20 in order to increase the efficiency of the turbine device 10.
  • the stator wings are preferably as long as possible to fill the space between the adjacent rotor wheels 14, but should preferably not be in contact with the rotor hub 13 to avoid additional friction within the turbine device 10.
  • the outer stator 11 inner diameter is changing along the axial direction of the turbine device 10.
  • the inner diameter of the outer stator 11 is decreasing downstream to reach its minimum in the area close to the first stator disc 15. The diameter is then increasing downstream the turbine device 10.
  • the radial length of the rotor wheels 14 and the stator discs 15 increase accordingly since the distance between the inside surface of the outer stator 11 and the cylindrical rotor hub 13 is increasing downstream the turbine device 10.
  • the flow of combustion gas into the turbine device inlet 27 is illustrated by arrows A.
  • the flow of gas is passing through the gas turbine portion 20 and exits the turbine device 10 via the exit opening 16 downstream the turbine device 10.
  • the flow of gas out from the turbine device 10 is illustrated by arrows B.
  • the rotor 12 is turnably supported in relation to a support structure 17 placed in the centre of the turbine device 10 by bearings 18 placed in the upstream and downstream ends of the rotor 12.
  • the support structure 17 In the upstream end of the turbine device 10, and upstream of the rotor hub 13, the support structure 17 has a diameter substantially equal to the outside diameter of the cylindrical rotor hub 13. Close to the upstream end of the rotor hub 13, the diameter of the support structure 17 is reduced considerably and the support structure 17 extends downstream inside the rotor hub 13.
  • the support structure within the rotor hub 13 constitutes an inner stator 19 extending inside the cylindrical rotor hub 13 to the downstream end of the rotor hub 13 to support also the downstream end of the rotor 12 via bearings 18.
  • the bearings could be of different types but should ensure that the rotor is able to rotate as easy as possible in relation to the support structure 17 to avoid additional friction losses.
  • the outer diameter of the inner stator 19 is smaller than the inside diameter of the cylindrical rotor hub 13 thereby generating a steam turbine portion 30 that extends within the rotor hub 13 concentrically with the gas turbine portion 20 outside the rotor hub 13.
  • the support structure 17 is mechanically connected to the outer stator 11 and thereby prevented from turning together with the rotor 12.
  • each inner rotor wheel 22 comprises a number of inclined rotor blades, that when exposed to the flow of steam will assist rotating the rotor 12.
  • the inner rotor wheels 22 are positioned at a substantially constant axial distance from each other along the inside of the cylindrical rotor hub 13. In each of the spaces between the adjacent inner rotor wheels 22 an inner stator disc 23 is placed in a similar way as within the gas turbine portion 20.
  • the inner stator discs 23 are rigidly attached to the inner stator 19 and extend from the surface of the inner stator 19 in substantially radial directions towards the inside surface of the rotor hub 13 to fill the space between adjacent inner rotor wheels 22.
  • Each inner stator disc 23 comprises a number of inner stator wings, not illustrated, that are influencing the flow of steam through the steam turbine portion 30 in order to increase the efficiency of the turbine device 10.
  • the diameter of the inner stator 19 is decreasing towards the downstream end of the turbine device 10.
  • the length of the inner rotor wheels 22 and the inner stator discs 23 increase accordingly since the distance between the inside surface of the rotor hub 13 and the inner stator 19 is increasing downstream the turbine device 10.
  • the flow of steam from the steam generating arrangement enters the steam turbine portion 30 via passages 24 arranged in the supporting structure 17.
  • the passages 24 end close to the inner surface of the cylindrical rotor hub 13 upstream of the inner rotor wheels 22 and the inner stator discs 23.
  • the flow of steam into the steam turbine portion 30 is illustrated by arrows C.
  • the flow of steam is passing through the steam turbine portion 30 and exits the turbine device 10 via openings 25 in the downstream end of the rotor hub 13.
  • the flow of steam out from the turbine device 10 is illustrated by arrow D.
  • a passageway is arranged within the rotor blades, the rotor hub and the inner rotor blades so that a fluid flowing in the passageway transfer heat from the gas turbine portion 20 to the steam turbine portion 30.
  • This embodiment of the turbine device 10 increases the efficiency of the turbine device further since the hot combustion gases will heat the rotor blades in the gas turbine portion, and consequently also the fluid flowing in the passageway so that the fluid is vaporised and the heat transferred by the fluid to the steam turbine portion 30 where it will assist in increasing the efficiency of the gas turbine portion further.
  • the fluid flowing in the passageways in the rotor blades will also cool the blades in the gas turbine portion which is a further advantage.
  • the vaporised fluid could also be introduced in the main flow of steam in the steam turbine portion 30.
  • the stator blades and the inner stator blades are preferably arranged at the same axial position along the rotor hub 13 in order to facilitate the manufacturing of the passageway within the blades and the rotor hub 13.
  • a directing structure 27 Downstream the rotor 12 a directing structure 27 is arranged downstream the rotor 12 a directing structure 27 is arranged.
  • the directing structure 27 is substantially cylindrical and has a diameter substantially equal to the rotor hub 13.
  • the directing structure 27 is used for directing the exit gas and exit steam in the desired direction and in other embodiments of the invention the structure could have a completely different shape to direct the hot exit gas and exit steam in a desired direction.
  • the directing structure is rigidly attached to the outer stator 11.
  • the diameter of the rotor hub 13 is reduced to constitute an outgoing shaft 26 for transferring the rotational movement generated by the turbine device 10.
  • the shaft 26 is for example connected to a generator for transforming the rotational movement into electrical energy, or a propeller etc in order to power an aircraft, vehicle, ship or yacht.
  • the shaft 26 is either connected directly to the arrangement where the rotational movement is used or first lead to a gear in order to makes it possible to adapt the rotational speed and power for a specific application.
  • the shaft 28 is structurally rigid connected to the outgoing shaft 26 and extends in the opposite direction from the outgoing shaft 24 upstream the turbine device.
  • the shaft 28, extending upstream the turbine device 10 could be used to drive one or more compressors used in combination with the gas generator that generates the combustion gas flow to the turbine device.
  • the shaft 28 preferably extends all the way to the gas generator that the compressor is directly driven by the shaft 28.
  • the number of rotor wheels, inner rotor wheels, outer and inner stator discs could be changed.
  • the number and positions of the bearings could be changed as well as the type of bearing could be changed.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

La présente invention porte sur un dispositif de turbine (10) destiné à convertir un écoulement de gaz et un écoulement de vapeur en un mouvement de rotation dans un arbre (26), ledit dispositif comprenant : une partie turbine à gaz (20), une partie turbine à vapeur (30) disposée de manière concentrique avec la partie turbine à gaz (20) et un stator extérieur (11) entourant la partie turbine à gaz (20) et la partie turbine à vapeur (30), et un rotor (12) comprenant un moyeu de rotor (13) disposé au centre du stator extérieur (11). Le dispositif de turbine selon l'invention est caractérisé en ce que la partie turbine à gaz (20) ou la partie turbine à vapeur (30) s'étend à l'intérieur du moyeu de rotor (13).
PCT/SE2009/050234 2009-03-06 2009-03-06 Dispositif de turbine à vapeur et à gaz Ceased WO2010101498A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
CN200980157881.5A CN103429848B (zh) 2009-03-06 2009-03-06 气体和蒸汽涡轮装置
PCT/SE2009/050234 WO2010101498A1 (fr) 2009-03-06 2009-03-06 Dispositif de turbine à vapeur et à gaz

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/SE2009/050234 WO2010101498A1 (fr) 2009-03-06 2009-03-06 Dispositif de turbine à vapeur et à gaz

Publications (1)

Publication Number Publication Date
WO2010101498A1 true WO2010101498A1 (fr) 2010-09-10

Family

ID=41346021

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/SE2009/050234 Ceased WO2010101498A1 (fr) 2009-03-06 2009-03-06 Dispositif de turbine à vapeur et à gaz

Country Status (2)

Country Link
CN (1) CN103429848B (fr)
WO (1) WO2010101498A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20160237895A1 (en) * 2015-02-13 2016-08-18 United Technologies Corporation Turbine engine with a turbo-compressor

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4333309A (en) * 1980-01-30 1982-06-08 Coronel Paul D Steam assisted gas turbine engine
WO2008111905A1 (fr) * 2007-03-09 2008-09-18 Eriksson Development And Innovation Ab Dispositif turbine

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH308991A (de) * 1952-03-08 1955-08-15 Schmalfeldt Hans Verfahren zum Kühlen von Turbinenschaufeln.
US3132842A (en) * 1962-04-13 1964-05-12 Gen Electric Turbine bucket supporting structure
FR2309712A1 (fr) * 1975-04-28 1976-11-26 Garrett Corp Turbomachine a courants fluidiques multiples
US5340274A (en) * 1991-11-19 1994-08-23 General Electric Company Integrated steam/air cooling system for gas turbines
WO1999040305A1 (fr) * 1996-08-27 1999-08-12 Mitsubishi Heavy Industries, Ltd. Turbine a gaz pour centrale a cycle mixte

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4333309A (en) * 1980-01-30 1982-06-08 Coronel Paul D Steam assisted gas turbine engine
WO2008111905A1 (fr) * 2007-03-09 2008-09-18 Eriksson Development And Innovation Ab Dispositif turbine

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20160237895A1 (en) * 2015-02-13 2016-08-18 United Technologies Corporation Turbine engine with a turbo-compressor

Also Published As

Publication number Publication date
CN103429848A (zh) 2013-12-04
CN103429848B (zh) 2015-05-06

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