EP0870157A1 - Procede d'exploitation d'un groupe generateur a turbines a gaz avec du combustible de faible pouvoir calorifique - Google Patents

Procede d'exploitation d'un groupe generateur a turbines a gaz avec du combustible de faible pouvoir calorifique

Info

Publication number
EP0870157A1
EP0870157A1 EP96940973A EP96940973A EP0870157A1 EP 0870157 A1 EP0870157 A1 EP 0870157A1 EP 96940973 A EP96940973 A EP 96940973A EP 96940973 A EP96940973 A EP 96940973A EP 0870157 A1 EP0870157 A1 EP 0870157A1
Authority
EP
European Patent Office
Prior art keywords
fuel
low
calorific
gas
combustion air
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.)
Granted
Application number
EP96940973A
Other languages
German (de)
English (en)
Other versions
EP0870157B1 (fr
Inventor
Rolf Dr. Althaus
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.)
General Electric Switzerland GmbH
Original Assignee
ABB Asea Brown Boveri Ltd
Alstom SA
Asea Brown Boveri AB
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 ABB Asea Brown Boveri Ltd, Alstom SA, Asea Brown Boveri AB filed Critical ABB Asea Brown Boveri Ltd
Publication of EP0870157A1 publication Critical patent/EP0870157A1/fr
Application granted granted Critical
Publication of EP0870157B1 publication Critical patent/EP0870157B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • 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
    • F23R3/36—Supply of different 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00002—Gas turbine combustors adapted for fuels having low heating value [LHV]

Definitions

  • the invention relates to a method for operating a gas turbine group with low-calorific fuel, the gas turbine group essentially consisting of a compressor, a combustion chamber, a turbine and a generator, and the low-calorific fuel being compressed by means of a fuel compressor
  • the invention is based on the object of stabilizing the combustion of fuels with low calorific values in a method for operating a gas turbine group with low-calorific fuel of the type mentioned at the outset
  • the essence of the invention is therefore that when starting the gas turbine group in a part of the combustion air, low-calorific fuel is admixed in an over-stoichiometric manner, so that a stable flame is produced that the quantity of low-calorific fuel at the latest after reaching the nominal speed and synchronization is lowered to such an extent that a superstoichiometric ratio is just reached and that the remaining low-calorific fuel is mixed into the remaining combustion air flow in order to achieve the desired load.
  • the advantages of the invention can be seen, inter alia, in the fact that the gas turbo group can essentially be operated solely with low-calorific fuel. This increases the economy of gas turbines which are operated with low calorific substances with the lowest calorific values.
  • Figure 1 is a schematic representation of a gas turbine group.
  • FIG. 3 shows a schematic illustration of the operating method of the gas turbo group
  • FIG. 5 shows a partial cross section through the burner from FIG. 4;
  • FIG. 6 shows a partial development of the burner from FIG. 4;
  • Fig. 7 top view of the burner outlet from the cavity.
  • FIG. 1 schematically shows a gas turbine group, essentially consisting of a compressor 40, a gas turbine 41 and a generator 46, which are connected by a shaft 42, and a combustion chamber 43.
  • a fuel compressor 48 is arranged to compress low-calorific, gaseous fuel.
  • the fuel compression can also be carried out in any other way.
  • the compressor 40 air is sucked in via an air supply 44, compressed and the compressed air is conducted into the combustion chamber 43.
  • the combustion air is supplied with fuel in the form of additional fuel 45 (pilot gas or liquid fuel) or compressed, low-calorific fuel 11 and the fuel-air mixture is burned.
  • the resulting flue gases are introduced into the gas turbine 41, where they are expanded and part of the energy of the flue gases is converted into rotational energy. This rotational energy is used via the shaft 42 to drive the generator 46 and the compressor 40.
  • the still hot exhaust gases are discharged via a line 47.
  • a burner 1 of the combustion chamber 43 consists essentially of a central fuel lance 2, an inner tube 3 and an outer tube 4, which are arranged concentrically to an axis of symmetry 8.
  • a fuel nozzle (not shown in more detail) for the injection of liquid fuel.
  • the liquid fuel is directed to the fuel nozzle via the fuel lance.
  • An annular channel 5 is formed by the fuel lance 2 and the inner tube 3, via which low-calorific gas, to which high-calorific gas can be added depending on the calorific value, is introduced as a pilot gas 10 into the combustion chamber 43.
  • An inner channel 3 is formed by the inner tube 3 and the outer tube 4 and is divided into an inner partial channel 21 and an outer partial channel 22 via a partition.
  • the ratio of the partial cross sections of the partial channels 21, 22 can be set by the radial position of the partition 20, whereby the low-calorific fuel can also be divided accordingly.
  • the combustion air is also divided into two partial air flows 9a and 9b by the partition wall 20. Flows through the inner sub-channel 21 Partial fuel stream 11a of the low calorific fuel, through the outer subchannel 22 a partial fuel stream 11b of the low calorific fuel flows.
  • the partial flows 11a, 11b are regulated by various valves, not shown.
  • swirl bodies 7 are arranged which support the mixing of fuel 10, 11 and combustion air 9a, 9b.
  • the fuel quantity M is plotted in percent on the ordinate.
  • the speed is plotted on the abscissa from point A to point B and the load from point B to point C. At point A, the speed is zero and rises to point B, where the nominal speed is reached, for example 3600 revolutions per minute for 60 hearts
  • the transient start-up process is carried out with low-calorific gas 11 a, which is supplied through the inner partial duct 21. Because the low caloric gas required for starting with a smaller amount of air, i.e. with the partial air flow 9a, due to the smaller cross section of the sub-channel 21, a richer mixture is created and thus a stable combustion
  • the gas turbine group After reaching the nominal speed in point B, the gas turbine group is synchronized with the network into which the electrical energy generated in generator 46 is to be fed
  • the second partial fuel flow 11b of the low-calorie fuel is switched on via the outer partial channel 22 before or after the synchronization.
  • the fuel quantity of the first partial fuel stream 11a is to be reduced so far that a stable flame is maintained.
  • the second partial fuel flow 11b is thus also provided with the largest possible amount of fuel, which leads to stable operation even when the external burner subchannel 22 is switched on.
  • the total amount of low calorific fuel 11a and 11b is set essentially linear to the load.
  • fuel 12 can additionally be injected into the center of the flame. This is done by means of liquid fuel via the fuel lance 2 or by means of pilot gas 10 via the channel 5 of the burner.
  • the amount of fuel 12 is small and is usually below five percent of the amount of fuel supplied.
  • the burner 1 is arranged in a combustion chamber 43.
  • Combustion air 9 is fed into a dome 24 and from there it is led to the downstream end of the burner 1 via air channels 25 running in the flow direction.
  • the air duct is not divided into an outer and an inner area.
  • the burner 1 is here also divided by means of partition walls 28 in the flow direction alternately into radially expanding air ducts 25 and fuel ducts 21 ', 22', the fuel ducts in turn being subdivided into a ring by the partition wall 20.
  • the low calorific gas 11a and 11b is guided around the burner via annular channels 26 and 27, which surround the burner 1, and is fed into the inner fuel channel 21 'and the outer fuel channel 22' via openings 29, 30.
  • the low-calorific fuel is fed in when starting and operating the burner as described above. Even though here the combustion air is not subdivided into a ring, the low-calorific gas 11a supplied through the inner subchannel 21 essentially mixes only with the combustion air in the center of the burner, corresponding to FIG ⁇ mixed air 9, a rich mixture is formed at least in the center of the burner and thus a stable combustion. A flame thus arises in the interior of the combustion chamber which, if no fuel 11b is supplied via the outer fuel channel 22 ', is enveloped with combustion air 9.
  • No swirl bodies 7 are arranged in the burner from FIG.
  • the mixing of combustion air 9 and fuel 11a, 11b takes place through a curvature of the partition wall 28 at the downstream end of the burner 1. This creates a swirl when exiting the burner, which mixes fuel and combustion air.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Feeding And Controlling Fuel (AREA)
  • Combustion Of Fluid Fuel (AREA)

Abstract

Selon ce procédé d'exploitation d'un groupe générateur à turbines à gaz avec du combustible de faible pouvoir calorifique, le groupe générateur à turbines à gaz comprend un compresseur, une chambre de combustion, une turbine et un générateur. Le combustible de faible pouvoir calorifique est comprimé par un compresseur. Lorsque l'on fait démarrer le groupe générateur à turbines à gaz, on ajoute une quantité surstoechiométrique de combustible de faible pouvoir calorifique (11a) à une partie de l'air de combustion (9, 9a) afin de générer une flamme stable. Au plus tard lorsque la vitesse nominale de rotation (B) est atteinte et que les turbines sont synchronisées, on réduit la quantité de combustible de faible pouvoir calorifique (11a) jusqu'à ce qu'un rapport surstoechiométrique subsiste tout juste encore. On ajoute le reste du combustible de faible pouvoir calorifique (11b) au courant résiduel d'air de combustion (9, 9b) afin d'atteindre la charge voulue.
EP96940973A 1995-12-29 1996-12-16 Procede d'exploitation d'un groupe generateur a turbines a gaz avec du combustible de faible pouvoir calorifique Expired - Lifetime EP0870157B1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE19549140 1995-12-29
DE19549140A DE19549140A1 (de) 1995-12-29 1995-12-29 Verfahren zum Betrieb einer Gasturbogruppe mit niederkalorischem Brennstoff
PCT/CH1996/000441 WO1997024561A1 (fr) 1995-12-29 1996-12-16 Procede d'exploitation d'un groupe generateur a turbines a gaz avec du combustible de faible pouvoir calorifique

Publications (2)

Publication Number Publication Date
EP0870157A1 true EP0870157A1 (fr) 1998-10-14
EP0870157B1 EP0870157B1 (fr) 2002-11-06

Family

ID=7781642

Family Applications (1)

Application Number Title Priority Date Filing Date
EP96940973A Expired - Lifetime EP0870157B1 (fr) 1995-12-29 1996-12-16 Procede d'exploitation d'un groupe generateur a turbines a gaz avec du combustible de faible pouvoir calorifique

Country Status (7)

Country Link
US (1) US6148603A (fr)
EP (1) EP0870157B1 (fr)
JP (1) JP4103965B2 (fr)
CN (1) CN1119569C (fr)
AU (1) AU1028697A (fr)
DE (2) DE19549140A1 (fr)
WO (1) WO1997024561A1 (fr)

Families Citing this family (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6935117B2 (en) 2003-10-23 2005-08-30 United Technologies Corporation Turbine engine fuel injector
JP4068546B2 (ja) * 2003-10-30 2008-03-26 株式会社日立製作所 ガスタービン発電設備及びその運用方法
EP1614967B1 (fr) * 2004-07-09 2016-03-16 Siemens Aktiengesellschaft Procédé et système de combustion à prémélange
EP1645807A1 (fr) * 2004-10-11 2006-04-12 Siemens Aktiengesellschaft Brûleur pour gas à faible capacité calorifique et méthode d'utilisation d'un tel brûleur
EP1659339A1 (fr) * 2004-11-18 2006-05-24 Siemens Aktiengesellschaft Procédé de démarrage d'un brûleur
WO2007036964A1 (fr) * 2005-09-30 2007-04-05 Ansaldo Energia S.P.A. Procédé d’activation d’une turbine à gaz équipée d’un brûleur à gaz, et dispositif de tourbillonnement axial pour ledit brûleur
JP5115372B2 (ja) * 2008-07-11 2013-01-09 トヨタ自動車株式会社 ガスタービンの運転制御装置
EP2312215A1 (fr) * 2008-10-01 2011-04-20 Siemens Aktiengesellschaft Brûleur et procédé de fonctionnement d'un brûleur
US8490406B2 (en) * 2009-01-07 2013-07-23 General Electric Company Method and apparatus for controlling a heating value of a low energy fuel
DE102009038848A1 (de) * 2009-08-26 2011-03-03 Siemens Aktiengesellschaft Brenner, insbesondere für Gasturbinen
DE102009038845A1 (de) * 2009-08-26 2011-03-03 Siemens Aktiengesellschaft Drallschaufel, Brenner und Gasturbine
US8355819B2 (en) 2010-10-05 2013-01-15 General Electric Company Method, apparatus and system for igniting wide range of turbine fuels
EP2551470A1 (fr) * 2011-07-26 2013-01-30 Siemens Aktiengesellschaft Procédé de démarrage d'une turbine à gaz stationnaire
US9182124B2 (en) * 2011-12-15 2015-11-10 Solar Turbines Incorporated Gas turbine and fuel injector for the same
US20170191428A1 (en) * 2016-01-05 2017-07-06 Solar Turbines Incorporated Two stream liquid fuel lean direct injection
US10234142B2 (en) * 2016-04-15 2019-03-19 Solar Turbines Incorporated Fuel delivery methods in combustion engine using wide range of gaseous fuels
US10731570B2 (en) * 2017-05-31 2020-08-04 Pratt & Whitney Canada Corp. Reducing an acoustic signature of a gas turbine engine
US20210010675A1 (en) * 2019-07-08 2021-01-14 Opra Technologies Bv Nozzle and fuel system for operation on gas with varying heating value

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DE1137266B (de) * 1960-06-02 1962-09-27 Siemens Ag Verfahren und Einrichtung zur Verbrennung von schwachmethanhaltigen Gasgemischen, insbesondere Grubenwettern
GB1317727A (en) * 1969-07-02 1973-05-23 Struthers Scient International Gas turbine engine
DD101457A1 (fr) * 1972-12-20 1973-11-05
US4202169A (en) * 1977-04-28 1980-05-13 Gulf Research & Development Company System for combustion of gases of low heating value
US4253301A (en) * 1978-10-13 1981-03-03 General Electric Company Fuel injection staged sectoral combustor for burning low-BTU fuel gas
US4653278A (en) * 1985-08-23 1987-03-31 General Electric Company Gas turbine engine carburetor
JPS63194111A (ja) * 1987-02-06 1988-08-11 Hitachi Ltd ガス燃料の燃焼方法及び装置
GB8911806D0 (en) * 1989-05-23 1989-07-12 Rolls Royce Plc Gas turbine engine fuel control system with enhanced relight capability
DE59204270D1 (de) * 1991-04-25 1995-12-14 Siemens Ag Brenneranordnung, insbesondere für gasturbinen, zur schadstoffarmen verbrennung von kohlegas und anderen brennstoffen.
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Non-Patent Citations (1)

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Also Published As

Publication number Publication date
JP2000502771A (ja) 2000-03-07
WO1997024561A1 (fr) 1997-07-10
EP0870157B1 (fr) 2002-11-06
CN1206455A (zh) 1999-01-27
AU1028697A (en) 1997-07-28
US6148603A (en) 2000-11-21
DE19549140A1 (de) 1997-07-03
CN1119569C (zh) 2003-08-27
JP4103965B2 (ja) 2008-06-18
DE59609859D1 (de) 2002-12-12

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