WO2009010525A1 - Turbine à gaz fonctionnant avec un combustible liquide - Google Patents

Turbine à gaz fonctionnant avec un combustible liquide Download PDF

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Publication number
WO2009010525A1
WO2009010525A1 PCT/EP2008/059284 EP2008059284W WO2009010525A1 WO 2009010525 A1 WO2009010525 A1 WO 2009010525A1 EP 2008059284 W EP2008059284 W EP 2008059284W WO 2009010525 A1 WO2009010525 A1 WO 2009010525A1
Authority
WO
WIPO (PCT)
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.)
Ceased
Application number
PCT/EP2008/059284
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
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Publication of WO2009010525A1 publication Critical patent/WO2009010525A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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
    • F23R3/28—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 a variety of ways and, in particular, usually with liquid fuel
  • Fuel operated as so-called oil-fired gas turbines As a 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. For such gas turbines, 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 object of the invention is to provide a gas turbine operated with liquid fuel and a combustion chamber for such a gas turbine, in which coking is largely avoided and consequently undesirable deposits are minimized. Also, 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.
  • the object is inventively with a liquid
  • a liquid fuel gas turbine having a combustion chamber and a supply means for supplying the liquid fuel to the combustion chamber in which an evaporator unit is provided by means of which the liquid fuel is in a vaporous state before being fed into the combustion chamber can be transferred.
  • a combustion chamber of a gas turbine operated with liquid fuel in which a supply device for supplying the liquid fuel to the combustion chamber and an evaporator device are provided, by means of which the liquid fuel is supplied before being introduced into the combustion chamber the combustion chamber can be converted into a vaporous state.
  • the liquid fuel is vaporized at the combustion chamber of a gas turbine prior to injection and injected into the combustion zone in gaseous form.
  • the combustion process is thereby accelerated according to the invention.
  • the vaporized fuel is further heated prior to injection into the combustion chamber, so that chemical chains of the liquid fuel are shortened by evaporation, resulting in a general improvement of the combustion situation of oil-fired gas turbines.
  • shortening chemical chains is generally meant the cracking of the carbon chains. Since cracking occurs in the vaporizer device, the deposits resulting from cracking, such as e.g. Tar in the evaporator device. The deposits settle on corresponding, provided for internals, and are thus retained by the evaporator and do not get into the combustion chamber of the gas turbine.
  • Combustion zone for the reaction of the vaporous fuel with the oxygen.
  • the resulting longer combustion time reduces unburned hydrocarbons and possibly produced soot particles and improves the efficiency of combustion.
  • 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, through which, on the one hand, fuel and, on the other hand, exhaust gas produced are passed.
  • the energy recovery device is also 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 insufficient to completely evaporate the fuel, the evaporation can be assisted with a controlled "cold" flame, which in particular promotes the ignition by active radicals and low NOx emissions According to the invention, incombustible particles present in the fuel 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 exhaust gas thus derived passes into a heat exchanger or heat exchanger 20 in which heat energy is transferred from the exhaust gas to fuel 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.

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

L'invention prévoit pour une turbine à gaz (10) fonctionnant avec un combustible liquide et présentant une chambre de combustion (12) et un dispositif d'alimentation (24) pour amener le combustible liquide dans la chambre à combustion (12), un dispositif de vaporisation (20) permettant de transférer le combustible liquide dans un état de vapeur avant de l'amener dans la chambre de combustion (12).
PCT/EP2008/059284 2007-07-19 2008-07-16 Turbine à gaz fonctionnant avec un combustible liquide Ceased WO2009010525A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP07014223A EP2017535A1 (fr) 2007-07-19 2007-07-19 Turbine à gaz à combustible liquide
EP07014223.7 2007-07-19

Publications (1)

Publication Number Publication Date
WO2009010525A1 true WO2009010525A1 (fr) 2009-01-22

Family

ID=39877726

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2008/059284 Ceased WO2009010525A1 (fr) 2007-07-19 2008-07-16 Turbine à gaz fonctionnant avec un 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
EP2017535A1 (fr) 2009-01-21

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