EP0870157B1 - 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 Download PDF

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Publication number
EP0870157B1
EP0870157B1 EP96940973A EP96940973A EP0870157B1 EP 0870157 B1 EP0870157 B1 EP 0870157B1 EP 96940973 A EP96940973 A EP 96940973A EP 96940973 A EP96940973 A EP 96940973A EP 0870157 B1 EP0870157 B1 EP 0870157B1
Authority
EP
European Patent Office
Prior art keywords
fuel
calorific
low
gas
value fuel
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.)
Expired - Lifetime
Application number
EP96940973A
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German (de)
English (en)
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EP0870157A1 (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
Alstom SA
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Filing date
Publication date
Application filed by Alstom SA filed Critical Alstom SA
Publication of EP0870157A1 publication Critical patent/EP0870157A1/fr
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Publication of EP0870157B1 publication Critical patent/EP0870157B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • 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 consisting essentially of one Compressor, a combustion chamber, a turbine and a generator exists and wherein the low calorific fuel is compressed by means of a fuel compressor becomes.
  • US 5,451,160 describes a burner for the combustion of gases various heating values.
  • the burner includes an inner part that acts as Pilot burner acts and an outer, concentrically surrounding the pilot burner Main burner.
  • Pilot burner acts and an outer, concentrically surrounding the pilot burner Main burner.
  • the invention has for its object in a method for operating a Gas turbine group with low-calorie fuel of the type mentioned Stabilize combustion of fuels with low calorific values.
  • the essence of the invention is therefore that when the gas turbine group is started up in one Part of the combustion air is mixed with low-calorific fuel in a stoichiometric manner is so that a stable flame arises that at the latest after reaching the nominal speed and the synchronization the amount of low calorie Fuel is lowered so far that it is just over-stoichiometric Ratio is reached and that in the remaining combustion air flow the remaining low-calorie fuel to achieve the desired load is added.
  • a gas turbine group is shown schematically, consisting essentially from a compressor 40, a gas turbine 41 and a generator 46, the are connected via a shaft 42 and a combustion chamber 43.
  • a fuel compressor 48 for Compression of low calorific, gaseous fuel arranged.
  • the compressor 40 air is sucked in via an air supply 44, compressed and the compressed air is passed into the combustion chamber 43.
  • the Combustion air fuel in the form of additional fuel 45 (pilot gas or liquid fuel) or from compressed low-calorific fuel 11 and the fuel-air mixture burned.
  • the smoke gases produced are introduced into the gas turbine 41, where they are expanded and part of the Energy of the flue gases is converted into turning energy. This turning energy is driven via shaft 42 to drive generator 46 and compressor 40 used.
  • the still hot exhaust gases are discharged via a line 47.
  • a burner 1 of the combustion chamber 43 consists essentially of one central fuel lance 2, an inner tube 3 and an outer tube 4, which are arranged concentrically to an axis of symmetry 8.
  • On the downstream The end of the fuel lance 2 is a fuel nozzle, not shown arranged 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, via the low calorific gas, to which high calorific gas is added depending on the calorific value can be introduced as pilot gas 10 into the combustion chamber 43.
  • an annular channel formed by a partition into an inner sub-channel 21 and an outer Subchannel 22 is divided.
  • the ratio of the partial cross sections of the partial channels 21, 22 can be set, whereby the low-calorie fuel is also divided accordingly can.
  • the combustion air is also in two Partial air flows 9a and 9b divided.
  • Flows through the inner sub-channel 21 Partial fuel flow 11a of the low calorific fuel, through the outer Subchannel 22 flows a partial fuel stream 11b of the low calorific fuel.
  • the sub-streams 11a, 11b are different, not shown Valves regulated.
  • Swirl bodies 7 are arranged at the downstream end of the channel 6, which is the mixing of fuel 10, 11 and combustion air 9a, 9b support.
  • the fuel quantity M is plotted in percent on the ordinate.
  • On the abscissa is the speed from point A to point B, and from point B to Point C plotted the load.
  • the speed is zero and increases 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 subchannel 21.
  • the system compressor 40 and turbine 41 begins to convert the amount of heat supplied into the combustion chamber 43 into power in the upper third of the nominal speed B.
  • the drive power from the generator 46 and thus also the temperature in the combustion chamber 43 can be reduced, which results in a reduction in the amount of low-calorie fuel 11a at point D.
  • the system compressor 40 and turbine 41 is in thermal equilibrium.
  • the connection of the second partial fuel stream 11 b of the low calorific Fuel via the outer subchannel 22 takes place before or after the synchronization.
  • the fuel quantity of the first partial fuel stream 11a is so lower far enough to maintain a stable flame. This will make the difference between the required fuel for the selected load point and the Maximum amount of fuel in the first partial fuel stream 11 a.
  • the second Partial fuel flow 11b is thus also the largest possible amount of fuel available, which leads to stable operation even when the exterior is switched on Burner subchannel 22 leads.
  • Fuel 12 in the center can additionally fuel 12 in the center to be injected into the flame. This is done using 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 widening 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.
  • the combustion air is not subdivided into a ring
  • the low-calorific gas 11 a supplied through the inner subchannel 21 essentially only mixes with the combustion air in the center of the burner, corresponding to FIG Combustion air 9 mixed, creates a rich mixture 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. 4.
  • the mixing of combustion air 9 and fuel 11 a, 11 b takes place through a curvature of the partition wall 28 at the downstream end of the burner 1. This creates a swirl when it emerges from 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.

Claims (4)

  1. Procédé en vue du fonctionnement d'un groupe de turbine à gaz à combustible faiblement calorifique, le groupe à turbine à gaz se composant pour l'essentiel d'un compresseur (40), d'une chambre de combustion (43), d'une turbine (41) et d'un générateur (46) et le combustible faiblement calorifique étant comprimé à l'aide d'un compresseur de combustible (48), caractérisé en ce que, lors de la mise en marche du groupe à turbine à gaz, on achemine, dans une partie de l'air de combustion (9, 9a), d'une manière surstoechiométrique, un combustible faiblement calorifique (11a) de manière à produire une flamme stable, en ce que, au plus tard une fois parvenu au nombre de tours nominal (B) et à la synchronisation, la quantité du combustible faiblement calorifique (11a) est abaissée de façon à parvenir tout juste encore à un rapport surstoechiométrique et en ce que, dans le courant d'air de combustion restant (9, 9b) le combustible faiblement calorifique restant (11b) est ajouté par mélange en vue de l'obtention de la charge souhaitée.
  2. Procédé selon la revendication 1, caractérisé en ce que l'on injecte le combustible (12) dans le centre de l'air de combustion (9, 9a).
  3. Procédé selon la revendication 1, caractérisé en ce que l'air de combustion est subdivisé avant l'admission dans la chambre de combustion en au moins deux courants d'air partiels (9a, 9b).
  4. Procédé selon la revendication 1, caractérisé en ce que le premier courant d'air partiel (9a) est entouré du deuxième courant d'air partiel (9b).
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
DE19549140A DE19549140A1 (de) 1995-12-29 1995-12-29 Verfahren zum Betrieb einer Gasturbogruppe mit niederkalorischem Brennstoff
DE19549140 1995-12-29
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 EP0870157A1 (fr) 1998-10-14
EP0870157B1 true 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)

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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
DE102009038845A1 (de) * 2009-08-26 2011-03-03 Siemens Aktiengesellschaft Drallschaufel, Brenner und Gasturbine
DE102009038848A1 (de) * 2009-08-26 2011-03-03 Siemens Aktiengesellschaft Brenner, insbesondere für Gasturbinen
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
GB202219380D0 (en) 2022-12-21 2023-02-01 Rolls Royce Plc Gas turbine operating conditions
GB202219384D0 (en) 2022-12-21 2023-02-01 Rolls Royce Plc Aircraft fuelling

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GB1317727A (en) * 1969-07-02 1973-05-23 Struthers Scient International Gas turbine engine
DD101457A1 (fr) * 1972-12-20 1973-11-05
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US4253301A (en) * 1978-10-13 1981-03-03 General Electric Company Fuel injection staged sectoral combustor for burning low-BTU fuel gas
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GB8911806D0 (en) * 1989-05-23 1989-07-12 Rolls Royce Plc Gas turbine engine fuel control system with enhanced relight capability
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Also Published As

Publication number Publication date
CN1206455A (zh) 1999-01-27
DE59609859D1 (de) 2002-12-12
EP0870157A1 (fr) 1998-10-14
US6148603A (en) 2000-11-21
JP4103965B2 (ja) 2008-06-18
AU1028697A (en) 1997-07-28
WO1997024561A1 (fr) 1997-07-10
JP2000502771A (ja) 2000-03-07
CN1119569C (zh) 2003-08-27
DE19549140A1 (de) 1997-07-03

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