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EP1062461B1 - Chambre de combustion et mode de fonctionnement d'une chambre de combustion - Google Patents

Chambre de combustion et mode de fonctionnement d'une chambre de combustion Download PDF

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Publication number
EP1062461B1
EP1062461B1 EP99913091A EP99913091A EP1062461B1 EP 1062461 B1 EP1062461 B1 EP 1062461B1 EP 99913091 A EP99913091 A EP 99913091A EP 99913091 A EP99913091 A EP 99913091A EP 1062461 B1 EP1062461 B1 EP 1062461B1
Authority
EP
European Patent Office
Prior art keywords
combustion
combustion chamber
burner
heat
shield element
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
EP99913091A
Other languages
German (de)
English (en)
Other versions
EP1062461A1 (fr
Inventor
Gerwig Poeschl
Heinrich Pütz
Stefan Hoffmann
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 EP1062461A1 publication Critical patent/EP1062461A1/fr
Application granted granted Critical
Publication of EP1062461B1 publication Critical patent/EP1062461B1/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
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/12—Radiant burners
    • F23D14/16—Radiant burners using permeable blocks
    • 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
    • F23R3/002—Wall structures
    • 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
    • F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
    • 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
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • 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
    • F23R3/34—Feeding into different combustion zones
    • F23R3/346—Feeding into different combustion zones for staged combustion

Definitions

  • the invention relates to a combustion chamber with a combustion chamber wall and with one of a variety of heat shield elements formed inner lining and a method for Operation of a combustion chamber.
  • EP 0 576 697 B1 describes a combustion chamber of a gas turbine described in which, in addition to classic burner types catalytic burners are also used. As classic burner types, premix burners are used, with which the main combustion is carried out. Through the Combining these types of burners results in a simpler one Regulation with changing load conditions of the gas turbine.
  • Such a two-stage combustion is also from the US 4,910,957 known in which the multi-stage combustion for Reduction of NOx emissions is used.
  • a combustion gas turbine is known from DE-C-253 189 with an annular combustion chamber on its side walls each has a porous clay plate, which as so-called surface burner works.
  • the Combustion chamber rear side through the porous clay plate led a fuel gas mixture.
  • the fuel gas mixture is on the surface of the clay plate facing the combustion chamber ignited and burned to the surface. Through the radiated heat from the clay plate becomes a propellant for heated the drive of the combustion gas turbine.
  • the object of the invention is to provide a combustion chamber which in a particularly simple design, a supply of fuel and of combustion air.
  • Another object of the invention is the specification of a method for operating a combustion chamber, through which a stepped in a particularly simple manner Combustion is enabled.
  • a combustion chamber Object achieved by a combustion chamber with a combustion chamber wall and with one of a variety of heat shield elements formed inner lining, at least one a heat shield element acting as a burner is a burner heat shield element is a fuel supply for supply of fuel and a combustion air supply for Combustion air supply are connected upstream.
  • the burner heat shield element with numerous Cavities material, the fuel and the combustion air can be supplied so that combustion can be generated within this material.
  • combustion is under construction enables in a particularly simple manner that a heat shield element, soft part of the fireproof inner lining the combustion chamber is used as a burner. a such burner heat shield element becomes fuel and combustion air for combustion in the heat shield element fed.
  • Such a burner heat shield element represents a so-called Pore burner. Fuel and combustion air So burned in the cavities or pores, which is Material heats up. On the one hand, this leads to good stabilization the combustion. On the other hand, the pore structure works strongly dampening on combustion vibrations. This Both properties of a pore burner lead to the fact that there is almost no combustion in a pore burner Forms combustion vibration. The material continues to shine, which, as mentioned, strongly changes during combustion heats up a significant amount of heat. This leads to, that the flame temperature of the combustion within the material is comparatively low. This in turn has Consequence that less nitrogen oxides are formed. The advantage the lower flame temperature can also be used for this become more fuel and the burner heat shield element to supply less fuel to the burner in a first stage. This reduces the formation of such combustion vibrations, which is caused by the burner of the first stage can be.
  • a pre-mixing space is preferred for the burner heat shield element upstream, into which the fuel and the combustion air can be initiated.
  • Fuel and combustion air are first fed to the premixing room, where a fuel-air mixture is formed. This fuel-air mixture is then fed to the burner heat shield element. In order to the result is a homogeneous one which is favorable for the combustion Fuel-air mixture.
  • the combustion chamber wall has an outside, along which preferably extends from a fuel line Fuel can be admitted into the premixing chamber.
  • Fuel line could e.g. for an annular combustion chamber one in the circumferential direction of the annular combustion chamber around the combustion chamber wall circular ring line, from which e.g. also in simple Way for a variety of burner heat shield elements, which are arranged along this circumferential direction, fuel can be supplied.
  • At least one burner is intended for a first stage of combustion, and being through the burner heat shield element downstream of the first stage a second stage of combustion can be generated.
  • the burner heat shield element is simple realized a second stage of a two-stage combustion. Of course, further stages of combustion can also be provided his.
  • the two-stage or multi-stage of Combustion becomes a reaction zone of combustion on one distributed larger volume. This results in the combustion chamber a lower tendency to form combustion vibrations. Such combustion vibrations can possibly substantial Cause damage in the combustion chamber.
  • a two-stage or a multi-stage combustion a particularly good controllability for adaptation to different power outputs, i.e. Load conditions, e.g. for a gas turbine operated under different loads. Becomes a gas turbine through the exhaust gas from the combustion chamber is driven for combustion depending on the load the gas turbine-oriented fuel-air ratio required.
  • At least two Burners have a wide range of parameters for control the combustion.
  • e.g. - if necessary - The fuel supply to the burner heat shield element are omitted so that through the burner heat shield element only air flows into the combustion chamber.
  • the air mass flow through the burner is the first Level can be reduced. This has in particular to Consequence that the burner can be made smaller. In order to e.g. the advantage that the burner in simpler Be removed from a surrounding housing can.
  • the burner heat shield element extends along the Direction of expansion from a first end to a second End, the pre-mixing space preferably between the Combustion chamber wall and the burner heat shield element lies and an outlet opening being provided in the region of the second end that connects the premixing chamber with the combustion chamber.
  • Cooling air can preferably be supplied to the burner heat shield element, the cooling air being used as combustion air is usable.
  • the heat shield elements are often thereby cooled that cooling air from the outside of the combustion chamber wall e.g. through holes in the back of the heat shield elements to be led.
  • this cooling air supply as a combustion air supply there is a special one simple supply of combustion air to the burner heat shield element.
  • the material of the burner heat shield element is preferably the pore burner, a foamed ceramic, especially zirconium oxide or silicon carbide.
  • a foamed ceramic especially zirconium oxide or silicon carbide.
  • Such materials are z. B. producible in that in a foam-forming Carrier material the ceramic is introduced and after a foaming and curing of the carrier material is etched away, so that a porous ceramic remains.
  • the combustion chamber is preferably an annular space forming annular combustion chamber, being along a circumferential direction of the annulus a plurality of heat shield elements is designed as a burner heat shield elements. Preferably is most of the along a circumferential direction arranged heat shield elements as burner heat shield elements educated. This results in a uniform Distribution of the second stage of combustion over the Circumference of the ring combustion chamber.
  • the combustion chamber is preferred in a gas turbine, in particular used in a stationary gas turbine.
  • the gas turbine has an output greater than 60 MW.
  • According to the invention is directed to a method Problem solved by a method for operating a Combustion chamber with a combustion chamber wall and with one out of one A large number of inner lining elements formed, wherein at least one of the heat shield elements is fuel and supplied combustion air for combustion and the fuel and the combustion air within a porous structure of the heat shield element be burned.
  • a first stage of combustion preferably runs first from, then a via the heat shield element second stage of combustion takes place.
  • the method in a combustion chamber is further preferred, especially in an annular combustion chamber, a gas turbine carried out.
  • FIG. 1 shows a longitudinal section through an annular combustion chamber 1 for a gas turbine.
  • the ring combustion chamber 1 is rotationally symmetrical around an axis 2. For the sake of clarity only half of the longitudinal section is shown.
  • the ring combustion chamber 1 has a combustion chamber wall 3.
  • the combustion chamber wall 3 encloses an annular space 4.
  • the inner wall of the combustion chamber wall 3 is lined with an inner lining 5.
  • the inner lining 5 is made by a variety of heat shield elements 6 formed.
  • Such heat shield elements 6 are e.g. made of fireproof ceramic.
  • Burner system 7 This is formed by a diffusion burner 8 and a premix burner 9, which is the diffusion burner 8 surrounds in the form of an annular channel.
  • the burner system 7 is at a burner end 11 of the annular combustion chamber 1 arranged. At an opposite end 11 of the burner turbine-side end 13 closes one schematically shown gas turbine 15.
  • the gas turbine system When using such an annular combustion chamber 1 in one here
  • the gas turbine system is the pilot burner 8 Fuel 17A supplied.
  • the pilot burner 8 is also Combustion air 18A supplied.
  • the fuel 17A and the Combustion air 18A are diffused through the Pilot burner 8 burned in the annular space 4 of the annular combustion chamber 1.
  • On the flame stabilized on the pilot burner 8 Combustion ignites a mixture of fuel 17B and Combustion air 18B, which is fed to the premix burner 9 becomes.
  • the exhaust gas 20 generated by the combustion emerges the turbine-side end 13 of the annular combustion chamber 1 and drives the gas turbine 15.
  • FIG 2 shows a section of a corresponding to Figure 1 Longitudinal section through an annular combustion chamber 1.
  • One of the Heat shield elements 6 is as a burner heat shield element 22 executed. Like each of the heat shield elements 6 is also the burner heat shield element 22 with a screw 24 the combustion chamber wall 3 screwed. In the combustion chamber wall 3 22 holes are behind the burner heat shield element 26 provided. On the outside 28 of the combustion chamber wall 3 a fuel line 30 is also provided. Of the Fuel line 30 leads through hole 32 of the combustion chamber wall 3 to a pre-mixing space 34, which by the at the Combustion chamber wall 3 adjacent burner heat shield element 22 is formed. The through holes also open into the premixing chamber 34 26.
  • the burner heat shield element 22 extends from a first end 23 to a second end 25.
  • the burner heat shield element 22 is now in the following manner for a second stage of combustion in the annular combustion chamber 1 used:
  • Fuel 36 is preferred via fuel line 30 Natural gas, the premixing chamber 34 is supplied via the bore 32. Combustion air 38 is also passed through the perforations 26 fed to the premixing chamber 34. In the premixing room 34 the natural gas 36 mixes with the combustion air 38. Am second end 25, an outlet opening 40 is provided which Natural gas-air mixture 42 discharges into the annular combustion chamber 1. The Natural gas-air mixture 42 ignites in the hot annular combustion chamber 1. This creates a second stage of combustion out. With this second stage, the reaction zone the combustion occurring in the annular combustion chamber 1 is increased. This leads to a reduced tendency to training of combustion vibrations. The significant combustion air flow 38 continues to result in high cooling performance for the burner heat shield element 22 and also for the downstream side located in front of the burner heat shield element 22 further heat shield elements 6.
  • Figure 3 shows again in an enlarged and schematic Representation of a arranged on the burner chamber wall 3 Burner heat shield element 22.
  • a burner heat shield element is shown schematically in a longitudinal section in FIG 22 shown, which on a combustion chamber wall 3 is arranged.
  • the burner heat shield element 22 is formed from a porous material 44. It is with brackets 46 attached to the combustion chamber wall 3.
  • brackets 46 attached to the combustion chamber wall 3.
  • a fuel line 30 is integrated into the wall 48. Openings 50 are also provided in the wall 48.
  • the premixing chamber 34 is fluidically connected to the Burner heat shield element 22 through holes 26 in the Combustion chamber wall 3 connected.
  • Combustion air 38 enters the premixing chamber via the openings 50 34.
  • Fuel comes from the fuel line 30, preferably natural gas, also in the premixing chamber 34.
  • the fuel-air mixture passes through the through holes 26 42 from the premixing chamber 34 into the burner heat shield element 22.
  • the fuel-air mixture 42 penetrates into the porous Material 44 a. Due to the heat in one, no further
  • the combustion chamber shown ignites the fuel-air mixture 42 and burns within the pores of the porous material 44.
  • the porous material 44 heats up. This leads to a particularly stable combustion.
  • a combustion vibration due to the pore structure of the porous material 44 suppressed.
  • the porous continues to shine Material 44 heat. This leads to the flame temperature the combustion within the porous material 44 by comparison is low. This in turn has the consequence that less nitrogen oxides are formed.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)

Claims (12)

  1. Chambre de combustion (1) comprenant une paroi (3) de chambre de combustion entourant un espace (4) de combustion et un revêtement (5) intérieur formé d'une pluralité d'éléments (6) de bouclier thermique, caractérisée en ce qu'au moins un élément (5) de bouclier thermique servant de brûleur est un élément (22) de bouclier thermique de brûleur en amont duquel sont montés un conduit (30) d'apport de combustible (36) et un conduit (26) d'apport d'air (38) de combustion et l'élément (22) de bouclier thermique de brûleur présente une matière (44) qui est pourvue d'innombrables cavités (45) et qui est constituée de manière à ce qu'une combustion puisse se produire au sein de cette matière (44).
  2. Chambre de combustion (1) suivant la revendication 1,
       caractérisée en ce qu'il est monté en amont de l'élément (22) de bouclier thermique de brûleur un espace (34) de prémélange, dans lequel le combustible (36) et l'air (38) de combustion peuvent être introduits.
  3. Chambre de combustion (1) suivant la revendication (2), caractérisée en ce que la paroi (3) de la chambre de combustion a une face (28) extérieure le long de laquelle s'étend le conduit (30) d'apport de combustible.
  4. Chambre de combustion (1) suivant l'une des revendications précédentes, dans laquelle un courant (20) de gaz de combustion peut passer le long d'une direction dans laquelle elle s'étend d'un côté (11) d'entrée jusqu'à un côté (13) de sortie, au moins un brûleur (8) pour un premier étage d'une combustion étant prévu, caractérisée en ce que, par l'élément (22) de bouclier thermique de brûleur, il peut être produit en aval du premier étage un deuxième étage de la combustion.
  5. Chambre de combustion (1) suivant les revendications 2 et 4, caractérisée en ce que l'espace (34) de prémélange est disposé entre la paroi (3) de la chambre de combustion et l'élément (22) de bouclier thermique de brûleur, l'élément (22) de bouclier thermique de brûleur s'étendant le long de la direction suivant laquelle la chambre de combustion s'étend d'une première extrémité (23) à une deuxième extrémité (25) et dans la partie de la deuxième extrémité (25) une ouverture (40) de sortie met l'espace (34) de prémélange en communication avec l'espace (4) de combustion.
  6. Chambre de combustion (1) suivant l'une des revendications précédentes, caractérisée en ce que la matière (44) de l'élément (22) de bouclier thermique de brûleur est du métal dans lequel sont ménagées mécaniquement, notamment par perçage, les cavités (45).
  7. Chambre de combustion (1) suivant l'une des revendications 1 à 5, caractérisée en ce que la matière (44) de l'élément (22) de bouclier thermique de brûleur est une céramique poreuse, notamment de l'oxyde de zirconium ou du carbure de silicium.
  8. Chambre de combustion (1 ), notamment chambre de combustion annulaire, suivant l'une des revendications précédentes, dans laquelle l'espace (4) de combustion est de forme annulaire,
       caractérisée en ce que le long d'une direction périphérique de l'espace (4) annulaire sont constitués une multitude d'éléments (6) de bouclier thermique servant d'éléments (22) de bouclier thermique de brûleur.
  9. Utilisation d'une chambre de combustion (1) suivant l'une des revendications précédentes pour une turbine à gaz, notamment pour une turbine à gaz fixe d'une puissance supérieure à 60 MW.
  10. Procédé pour faire fonctionner une chambre de combustion (1) ayant une paroi (3) de chambre de combustion et un revêtement (5) intérieur formé d'une pluralité d'éléments (6, 22) de bouclier thermique, caractérisé en ce que l'on envoie du combustible (36) et de l'air (38) de combustion pour une combustion à au moins l'un des éléments (6, 22) de bouclier thermique et en ce que l'on brûle le combustible (36) et l'air (38) de combustion au sein d'une matière (44) poreuse de l'élément (22) de bouclier thermique.
  11. Procédé suivant la revendication 10, caractérisé en ce que l'on fait d'abord se dérouler un premier stade d'une combustion et ensuite sur l'élément (22) de bouclier thermique un deuxième stade de la combustion.
  12. Mise en oeuvre du procédé suivant l'une des revendications 10 ou 11 dans une chambre de combustion (1 ), notamment dans une chambre de combustion annulaire d'une turbine à gaz.
EP99913091A 1998-03-10 1999-02-25 Chambre de combustion et mode de fonctionnement d'une chambre de combustion Expired - Lifetime EP1062461B1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE19810276 1998-03-10
DE19810276 1998-03-10
PCT/DE1999/000513 WO1999046540A1 (fr) 1998-03-10 1999-02-25 Chambre de combustion et mode de fonctionnement d'une chambre de combustion

Publications (2)

Publication Number Publication Date
EP1062461A1 EP1062461A1 (fr) 2000-12-27
EP1062461B1 true EP1062461B1 (fr) 2003-12-03

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP99913091A Expired - Lifetime EP1062461B1 (fr) 1998-03-10 1999-02-25 Chambre de combustion et mode de fonctionnement d'une chambre de combustion

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Country Link
EP (1) EP1062461B1 (fr)
JP (1) JP4365027B2 (fr)
DE (1) DE59907940D1 (fr)
WO (1) WO1999046540A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7029272B2 (en) 2001-08-09 2006-04-18 Siemens Aktiengesellschaft Premix burner and method for operation thereof
DE102017207487A1 (de) * 2017-05-04 2018-11-08 Siemens Aktiengesellschaft Brennkammer

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP4524902B2 (ja) * 2000-10-25 2010-08-18 株式会社Ihi 予混合燃料噴射弁を備えた低ＮＯｘ燃焼器
EP1460339A1 (fr) * 2003-03-21 2004-09-22 Siemens Aktiengesellschaft Turbine à gaz
ATE483138T1 (de) * 2004-01-21 2010-10-15 Siemens Ag Brenner mit gekühltem bauteil, gasturbine sowie verfahren zur kühlung des bauteils
EP1847696A1 (fr) 2006-04-21 2007-10-24 Siemens Aktiengesellschaft Composant pour un système de post-combustion dans une turbine à gaz et turbine à gaz associée.
EP1847684A1 (fr) 2006-04-21 2007-10-24 Siemens Aktiengesellschaft Aube de turbine
US8800293B2 (en) * 2007-07-10 2014-08-12 United Technologies Corporation Floatwell panel assemblies and related systems
EP2161500A1 (fr) 2008-09-04 2010-03-10 Siemens Aktiengesellschaft Système de chambre de combustion et procédé de réduction de l'instabilité de combustion et/ou émissions d'un système de chambre de combustion
US11248795B2 (en) 2018-03-09 2022-02-15 Siemens Energy Global Gmbh & Co Kg Finely distributed combustion system for a gas turbine engine
US11174792B2 (en) 2019-05-21 2021-11-16 General Electric Company System and method for high frequency acoustic dampers with baffles
US11156164B2 (en) 2019-05-21 2021-10-26 General Electric Company System and method for high frequency accoustic dampers with caps

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US3981675A (en) * 1974-12-19 1976-09-21 United Technologies Corporation Ceramic burner construction
US4112676A (en) * 1977-04-05 1978-09-12 Westinghouse Electric Corp. Hybrid combustor with staged injection of pre-mixed fuel
US4910957A (en) * 1988-07-13 1990-03-27 Prutech Ii Staged lean premix low nox hot wall gas turbine combustor with improved turndown capability
FR2647534B1 (fr) * 1989-05-29 1991-09-13 Europ Propulsion Chambre de reacteur et procede pour sa fabrication
EP0576697B1 (fr) 1992-06-29 1997-08-27 Abb Research Ltd. Chambre de combustion pour turbine à gaz
DE59208713D1 (de) 1992-11-09 1997-08-21 Asea Brown Boveri Gasturbinen-Brennkammer
JP3404981B2 (ja) * 1995-04-21 2003-05-12 日本鋼管株式会社 気体加熱装置

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7029272B2 (en) 2001-08-09 2006-04-18 Siemens Aktiengesellschaft Premix burner and method for operation thereof
DE102017207487A1 (de) * 2017-05-04 2018-11-08 Siemens Aktiengesellschaft Brennkammer
WO2018202407A1 (fr) 2017-05-04 2018-11-08 Siemens Aktiengesellschaft Chambre de combustion

Also Published As

Publication number Publication date
EP1062461A1 (fr) 2000-12-27
WO1999046540A1 (fr) 1999-09-16
JP4365027B2 (ja) 2009-11-18
JP2002506193A (ja) 2002-02-26
DE59907940D1 (de) 2004-01-15

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