EP2017535A1 - Turbine à gaz à combustible liquide - Google Patents

Turbine à gaz à combustible liquide Download PDF

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Publication number
EP2017535A1
EP2017535A1 EP07014223A EP07014223A EP2017535A1 EP 2017535 A1 EP2017535 A1 EP 2017535A1 EP 07014223 A EP07014223 A EP 07014223A EP 07014223 A EP07014223 A EP 07014223A EP 2017535 A1 EP2017535 A1 EP 2017535A1
Authority
EP
European Patent Office
Prior art keywords
liquid fuel
gas turbine
combustion chamber
fuel
gas
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Withdrawn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
EP07014223A
Other languages
German (de)
English (en)
Inventor
Vladimir Vlahovic
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.)
Siemens AG
Original Assignee
Siemens AG
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 Siemens AG filed Critical Siemens AG
Priority to EP07014223A priority Critical patent/EP2017535A1/fr
Priority to PCT/EP2008/059284 priority patent/WO2009010525A1/fr
Publication of EP2017535A1 publication Critical patent/EP2017535A1/fr
Withdrawn legal-status Critical Current

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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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23K—FEEDING FUEL TO COMBUSTION APPARATUS
    • F23K5/00—Feeding or distributing other fuel to combustion apparatus
    • F23K5/02—Liquid fuel
    • F23K5/14—Details thereof
    • F23K5/22—Vaporising devices

Definitions

  • the invention relates to a gas turbine operated with liquid fuel and a combustion chamber of such a gas turbine.
  • Gas turbines are nowadays used in many different ways and, in particular, are generally operated with liquid fuel as so-called oil-fired gas turbines.
  • liquid fuel for such gas turbines either specially prepared fuel types are available or operated with liquid fuel gas turbines must be operated with liquid fuels of rather poor quality. This is the case, for example, with gas turbines, which are used to drive pumps on oil pipelines.
  • gas turbines which are used to drive pumps on oil pipelines.
  • oil is partially diverted from the respective pipeline itself.
  • the quality of the intended for the operation of the gas turbine liquid fuel can vary accordingly strong.
  • the invention has for its object to provide a run on liquid fuel gas turbine and a combustion chamber for such a gas turbine, in which the above problems are overcome.
  • a coking of a waste heat boiler on a combined cycle turbine should be prevented as much as possible, without having to accept loss of efficiency.
  • a liquid fuel powered gas turbine having a combustion chamber and a supply means for supplying the liquid fuel to the combustion chamber, wherein an evaporator unit is provided by means of which the liquid fuel is converted to vapor state before being fed into the combustion chamber can.
  • a combustor of a gas turbine operated with a liquid fuel in which a supply means for supplying the liquid fuel to the combustion chamber and an evaporator means are provided, by means of which the liquid fuel can be converted to a vapor state before being fed into the combustion chamber.
  • the liquid fuel is vaporized at the combustion chamber of a gas turbine prior to injection and injected in gas form into the combustion zone.
  • the combustion process is thereby accelerated according to the invention.
  • Chemical chains of the liquid fuel are shortened by evaporation, resulting in a general improvement in the combustion situation of oil-fired gas turbines. Since the evaporation takes place outside the combustion zone, there will be more time in the combustion zone to react the vaporous fuel with the oxygen. The resulting longer combustion time reduces unburned hydrocarbons and possibly produced soot particles and improves combustion efficiency.
  • a blowing device for introducing the fuel transferred into the vapor state into the combustion chamber is correspondingly provided in the case of the liquid-fueled gas turbine.
  • an energy recovery device is advantageously provided, by means of which the energy required for vaporizing the liquid fuel is at least partially recovered from the exhaust gas produced when the fuel burns.
  • the efficiency of the gas turbine according to the invention is further improved by such energy recovery.
  • the energy recovery device is advantageously designed in the form of a heat transfer, are passed through the on the one hand fuel and the other incurred exhaust gas.
  • the energy recovery device is designed as a so-called direct energy recovery, in which hot exhaust gas from the combustion process of the gas turbine (direct) is introduced into the liquid fuel. If the heat of the hot exhaust gas is not sufficient for the complete evaporation of the fuel, the Evaporation can be assisted with controlled "cold" flame. As a result, in particular the ignition is supported by active radicals. Furthermore, a low NOx emission is achieved. Any incombustible particles present in the fuel according to the invention do not reach the combustion zone.
  • FIG shows a highly schematic partial representation of an embodiment of a gas turbine according to the invention.
  • a gas turbine 10 shown in FIG. 1 comprises a combustion chamber 12, which can be supplied with fuel, on the one hand, through a line 14 and, on the other hand, through a line 16.
  • a combustion chamber 12 which can be supplied with fuel, on the one hand, through a line 14 and, on the other hand, through a line 16.
  • exhaust gas from the combustion chamber 12 flows out of the combustion chamber 12 through a line 18.
  • the thus-derived exhaust gas passes into a heat exchanger or heat exchanger 20, in which heat energy is transferred from the exhaust gas to likewise introduced into the heat exchanger 20 in a direct or indirect countercurrent process.
  • the exhaust gas subsequently flows out of the heat exchanger 20 through a line 22, while fuel flows through a line 24 into the heat exchanger 20.
  • the fuel flowing into the heat exchanger 20 is liquid and is vaporized within the heat exchanger 20, so that it passes in the vapor state through the conduit 14 into the combustion chamber 12 and is burned there.
  • the energy required for vaporizing the liquid fuel is at least partially recovered from the exhaust gas produced when the fuel is combusted.

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  • 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)
EP07014223A 2007-07-19 2007-07-19 Turbine à gaz à combustible liquide Withdrawn EP2017535A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP07014223A EP2017535A1 (fr) 2007-07-19 2007-07-19 Turbine à gaz à combustible liquide
PCT/EP2008/059284 WO2009010525A1 (fr) 2007-07-19 2008-07-16 Turbine à gaz fonctionnant avec un combustible liquide

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP07014223A EP2017535A1 (fr) 2007-07-19 2007-07-19 Turbine à gaz à combustible liquide

Publications (1)

Publication Number Publication Date
EP2017535A1 true EP2017535A1 (fr) 2009-01-21

Family

ID=39877726

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07014223A Withdrawn EP2017535A1 (fr) 2007-07-19 2007-07-19 Turbine à gaz à combustible liquide

Country Status (2)

Country Link
EP (1) EP2017535A1 (fr)
WO (1) WO2009010525A1 (fr)

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4838029A (en) * 1986-09-10 1989-06-13 The United States Of America As Represented By The Secretary Of The Air Force Externally vaporizing system for turbine combustor
EP0877156A2 (fr) * 1997-05-09 1998-11-11 Abb Research Ltd. Méthode et dispositif de vaporisation de carburant liquide pour son utilisation dans la chambre de combustion d'une turbine à gaz
EP1074699A2 (fr) * 1999-08-02 2001-02-07 Isuzu Ceramics Research Institute Co., Ltd. Combinaison turbine - génératrice
WO2004033886A2 (fr) * 2002-10-10 2004-04-22 Combustion Science & Engineering, Inc. Systeme de vaporisation de combustibles liquides pour la combustion et procede d'utilisation

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4838029A (en) * 1986-09-10 1989-06-13 The United States Of America As Represented By The Secretary Of The Air Force Externally vaporizing system for turbine combustor
EP0877156A2 (fr) * 1997-05-09 1998-11-11 Abb Research Ltd. Méthode et dispositif de vaporisation de carburant liquide pour son utilisation dans la chambre de combustion d'une turbine à gaz
EP1074699A2 (fr) * 1999-08-02 2001-02-07 Isuzu Ceramics Research Institute Co., Ltd. Combinaison turbine - génératrice
WO2004033886A2 (fr) * 2002-10-10 2004-04-22 Combustion Science & Engineering, Inc. Systeme de vaporisation de combustibles liquides pour la combustion et procede d'utilisation

Also Published As

Publication number Publication date
WO2009010525A1 (fr) 2009-01-22

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