EP0882932A2 - Chambre de combustion - Google Patents

Chambre de combustion Download PDF

Info

Publication number
EP0882932A2
EP0882932A2 EP98810304A EP98810304A EP0882932A2 EP 0882932 A2 EP0882932 A2 EP 0882932A2 EP 98810304 A EP98810304 A EP 98810304A EP 98810304 A EP98810304 A EP 98810304A EP 0882932 A2 EP0882932 A2 EP 0882932A2
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
plenum
opening
downstream
bypass
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
EP98810304A
Other languages
German (de)
English (en)
Other versions
EP0882932A3 (fr
EP0882932B1 (fr
Inventor
Leif Andersson
Peter Dr. Jansohn
Jonathan Lloyd
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 Research Ltd Switzerland
ABB Alstom Power Switzerland Ltd
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 Research Ltd Switzerland, ABB Alstom Power Switzerland Ltd filed Critical ABB Research Ltd Switzerland
Publication of EP0882932A2 publication Critical patent/EP0882932A2/fr
Publication of EP0882932A3 publication Critical patent/EP0882932A3/fr
Application granted granted Critical
Publication of EP0882932B1 publication Critical patent/EP0882932B1/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
    • F23D14/46—Details
    • F23D14/62—Mixing devices; Mixing tubes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C7/00—Combustion apparatus characterised by arrangements for air supply
    • F23C7/02—Disposition of air supply not passing through burner
    • F23C7/06—Disposition of air supply not passing through burner for heating the incoming air

Definitions

  • the invention relates to a combustion chamber according to the preamble of claim 1.
  • the combustion chambers of gas turbine plants are made up of a number of burners with liquid and / or gaseous fuel and with atomizing air provided.
  • the burners are often arranged in a burner hood, which the Space around the burner, the so-called plenum, closes off from the outside.
  • the Plenum is located upstream of the combustion chamber and with the combustion chamber wall connected.
  • the air required for combustion is supplied by the compressor Gas turbine system delivered.
  • the main air flow is initially used for cooling the combustion chamber wall and used in cooling channels on the outside Passed along the combustion chamber wall.
  • the cooling channels open into the plenum. From from there, the air preheated in the cooling channels arrives as combustion air over the burner into the combustion chamber and is finally together with the used fuel burned.
  • the combustion air entering the burner hood a defined flow structure can be impressed.
  • Cooling air and combustion air quantities partly clearly different from each other. Because very large amounts of air are required for combustion, in addition to Cooling air flows a corresponding amount of air from the compressor air flow directly into the Burner hood directed. So that this so-called bypass air also enters the plenum suitable openings are formed in the burner hood, as shown for example in DE 195 16 798 A1.
  • the temperature design of the gas turbine and the one used Fuel can be used for combustion in the combustion chamber and for cooling the air requirement required in the combustion chamber can be very different. Therefore it is necessary that the amount of bypass air can be varied. Despite one changed mass flow of the bypass air, however, the flow conditions not be disturbed in the burner hood. Otherwise, i.e. with unfavorable Inflow conditions of the bypass air result in eddies, backflow zones and other such phenomena, which negatively affect the main air flow and whose stability can affect.
  • the invention tries to avoid all these disadvantages. You have the task based on creating a combustion chamber with an improved air supply, which also with different mass flows of cooling and combustion air an optimal burner flow guaranteed.
  • the at least one cooling channel into that Plenum lengthened and formed there as a diffuser with an opening into the plenum is.
  • the at least one opening of the burner hood is in the area of the Diffuser or immediately downstream of its confluence. Downstream everyone The opening of the burner hood closes a separate bypass duct with a junction to the plenary.
  • the confluence of each bypass channel is opposite that Opening of the diffuser staggered towards the outside and at least aligned approximately parallel to its confluence.
  • Any bypass channel is equipped with a pressure regulator for the bypass air.
  • bypass air is not only parallel to the main air flow but also directly as a so-called wall jet introduced into the plenum on the inner wall of the burner hood. Consequently flow separations can be countered effectively.
  • the in the bypass channels attached pressure regulating devices advantageously lead to a Adjustment of the pressure conditions of the secondary air flow (bypass air) to the in of the main air flow prevailing pressure conditions.
  • the diffuser also ensures a reduction the flow rate and for maximum pressure recovery the main air flow. If no bypass air is required, they work Junctions of the bypass channels as steps and form a so-called step diffuser, at the end of which a defined separation point is created. So that will the risk of an undefined, i.e. Avoid localized detachment in the diffuser.
  • At least one further opening in is particularly advantageous downstream of each opening the burner hood.
  • Each of these bypass channels also has a pressure regulating device on.
  • the channel height of each individual bypass channel is thus successful to adapt to an optimal diffuser operation.
  • the confluence of the Bypass channels arranged one behind the other in the direction of the main air flow Openings are staggered and at least approximately parallel to each other arranged. This double stage leads to the required alignment of the bypass air. Because the release areas in the step wake of smaller steps accordingly are smaller, several small steps result in less pressure loss as one big step.
  • the pressure regulating devices act as honeycombs are formed and arranged in the slots on the air inlet side. With help of the honeycomb body, the bypass air is aligned and even so that a defined inflow to the plenum can be achieved.
  • the secondary air flow can be adjusted accordingly the general operating conditions of the combustion chamber Speed and pressure ratios of the main air flow can be adjusted.
  • the honeycomb can be replaced during inspection and downtimes. so that these pressure regulators also respond to changing operating conditions are customizable.
  • At least on the most downstream Honeycomb is attached to a bracket for a honeycomb cover. By the assembly of the honeycomb cover, which also takes place when the machine is at a standstill the honeycomb can be closed and thus advantageously also on a larger one Cooling air needs to be responded to.
  • the pressure regulating device consists of a Opening-closing blocking plate with at least one, penetrating the latter Impact hole and arranged in the interior of the bypass channel Impact surface.
  • the baffle holes When operating the combustion chamber, they bounce through the baffle holes rays of the secondary air flow penetrating into the plenum initially on the Impact surfaces, whereby the desired pressure loss is achieved.
  • At least one of the impact holes is designed to be closable and provided with a bracket for a hole cover.
  • the assembly or disassembly of the perforated cover also takes place when the machine is at a standstill.
  • the inflowing Mass of bypass air adapted to the cooling requirements of the combustion chamber will.
  • it is useful if the most downstream arranged baffle hole of each locking plate can be closed, so that the best possible diffuser effect for the main air flow is guaranteed.
  • At least two openings are formed in the burner hood and in an at least approximately transverse to the compressor air flow level evenly distributed.
  • the gas turbine system for example, does not show the compressor and the gas turbine and the fuel feeds located outside the burner hood.
  • the direction of flow of the work equipment is indicated by arrows.
  • the gas turbine plant mainly consists of a compressor, a combustion chamber 1 designed as an annular combustion chamber with a Combustion chamber 2 and a combustion chamber wall 3, a gas turbine and one this connected generator.
  • a combustion chamber 1 designed as an annular combustion chamber with a Combustion chamber 2 and a combustion chamber wall 3, a gas turbine and one this connected generator.
  • the combustion chamber 2 of the annular combustion chamber 1 are numerous, fixed in a burner hood 4, serving the fuel supply and connected as a cone burner 5 connected. Every cone burner 5 on the upstream side consists of a swirl generator 6 and a seamlessly connecting in the combustion chamber 2 opening mixing section 7.
  • the EP 07 04 657 A2 known and accordingly trained cone burner 5 also referred to as a tube burner due to its tubular mixing section 7. she are each via a burner lance 8 shown only schematically from outside the burner hood 4 is supplied with fuel 9.
  • others can too Burners are used.
  • Cooling channels 10 are arranged outside the combustion chamber 2 and encasing them, in which to burn the fuel 9 in the annular combustion chamber 1 required combustion air is brought in by the compressor.
  • the first to Cooling the combustion chamber wall 3 used combustion air forms a uniform Main air flow 11, which via openings 12 of the cooling channels 10th in a space 13 formed within the burner hood 4, the so-called Plenum of the cone burner 5, is initiated.
  • the cooling channels 10 to in the plenum 13 is extended and formed as a diffuser 14 within the plenum 13, so that the mouths 12 of the cooling channels 10 with those of the diffusers 14 coincide.
  • each of the Slots 15, 15 ' Downstream of each of the Slots 15, 15 'enclose a bypass duct 16, 16' with an opening 17, 17 'in plenary 13.
  • the orifices 17, 17 'of the bypass channels 16, 16' are approximate aligned parallel to the mouths 12 of the diffusers 14.
  • the openings 17, 17 'of the bypass channels 16, 16' to each other and to the The mouths 12 of the diffusers 14 are staggered outwards.
  • the bypass channels are on the air inlet side 16, 16 'pressure regulating devices 18 designed as honeycombs, 18 'arranged.
  • the honeycombs 18, 18 ' are on both sides of the burner hood 4 a bracket 19 for a honeycomb cover 26 shown in dashed lines and thus formed closable (Fig. 2).
  • the honeycomb covers 26 can also be welded on.
  • the pressure regulating devices are 18, 18 'each as a combination of two rows in one die Slits 15, 15 'closing blocking plate 21, 21' arranged baffle holes 22, 22 ', with one slot 15, 15' each, arranged inside the bypass channel 16, 16 ' Impact surface 23, 23 'is formed.
  • the baffle holes 22, 22 ' are over the distributed over the entire circumference of the locking plate 21, 21 '.
  • the one on one side of the burner hood 4, upstream slot 15 has a first impact surface 23 and that formed on the same side of the burner hood 4, downstream Slot 15 'a second impact surface 23'. Both impact surfaces 23, 23 'and the burner hood 4 arranged downstream are in the direction of the main air flow 11 graduated.
  • the impingement holes 22, 22 ' are on both sides of the burner hood 4 designed to be closable and with a holder 24 for a dashed line hole cover 27 shown provided.
  • one or several rows of baffles are closed, with those arranged downstream Bump hole rows is started.
  • the other adjustment of the secondary air flow 20 to the main air flow 11 takes place analogously to the first embodiment.
  • the outer slot 15 'of the so-called Double stage are blocked (Fig. 2, only partially shown in Fig. 3).
  • the inner slot 15 keeps the secondary air flow 20 to the required extent upright, while the outer slot 15 'acts as a stepped diffuser. If no Bypass air 20 is required, both slots 15, 15 'can also be closed, creating a two-stage diffuser (not shown). With one Diffuser can achieve a greater pressure gain than with a single, big stage. A corresponding separation distance between the two slots 15, 15 'ensures that no backflow occurs in the diffuser 14.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Gas Burners (AREA)
  • Air Supply (AREA)
EP98810304A 1997-05-17 1998-04-09 Chambre de combustion Expired - Lifetime EP0882932B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19720786A DE19720786A1 (de) 1997-05-17 1997-05-17 Brennkammer
DE19720786 1997-05-17

Publications (3)

Publication Number Publication Date
EP0882932A2 true EP0882932A2 (fr) 1998-12-09
EP0882932A3 EP0882932A3 (fr) 2000-03-22
EP0882932B1 EP0882932B1 (fr) 2003-03-12

Family

ID=7829802

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98810304A Expired - Lifetime EP0882932B1 (fr) 1997-05-17 1998-04-09 Chambre de combustion

Country Status (5)

Country Link
US (1) US6106278A (fr)
EP (1) EP0882932B1 (fr)
JP (1) JP4036962B2 (fr)
CN (1) CN1114787C (fr)
DE (2) DE19720786A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2339013A (en) * 1998-07-01 2000-01-12 Asea Brown Boveri Gas Turbine

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19900025A1 (de) * 1999-01-02 2000-07-06 Abb Research Ltd Brennerhaube
DE10064259B4 (de) * 2000-12-22 2012-02-02 Alstom Technology Ltd. Brenner mit hoher Flammenstabilität
US6889523B2 (en) * 2003-03-07 2005-05-10 Elkcorp LNG production in cryogenic natural gas processing plants
US20050076644A1 (en) * 2003-10-08 2005-04-14 Hardwicke Canan Uslu Quiet combustor for a gas turbine engine
US7270539B1 (en) * 2003-10-28 2007-09-18 Soil-Therm Equipment, Inc. Method and apparatus for destruction of vapors and waste streams using flash oxidation
US7273366B1 (en) * 2003-10-28 2007-09-25 Soil-Therm Equipment, Inc. Method and apparatus for destruction of vapors and waste streams
WO2016061067A1 (fr) * 2014-10-13 2016-04-21 Eclipse, Inc. Brûleur à jet tourbillonnant
KR101596715B1 (ko) * 2014-11-25 2016-02-23 주식회사 경동나비엔 연소실 냉각 구조를 갖는 연소장치

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19516798A1 (de) 1995-05-08 1996-11-14 Abb Management Ag Vormischbrenner mit axialer oder radialer Luftzuströmung
DE19523094A1 (de) 1995-06-26 1997-01-02 Abb Management Ag Brennkammer

Family Cites Families (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2458497A (en) * 1945-05-05 1949-01-11 Babcock & Wilcox Co Combustion chamber
FR1430185A (fr) * 1964-12-23 1966-03-04 Foyer de combustion à fentes tourbillonnaires
US3333414A (en) * 1965-10-13 1967-08-01 United Aircraft Canada Aerodynamic-flow reverser and smoother
GB1180929A (en) * 1966-04-28 1970-02-11 English Electric Co Ltd Combustion Apparatus, for example for Gas Turbines.
US3899876A (en) * 1968-11-15 1975-08-19 Secr Defence Brit Flame tube for a gas turbine combustion equipment
GB1315856A (en) * 1970-03-20 1973-05-02 Secr Defence Flow restrictors
US3669628A (en) * 1970-07-31 1972-06-13 Continental Carbon Co Burner and feedstock injection assembly for carbon black reactor
GB1550368A (en) * 1975-07-16 1979-08-15 Rolls Royce Laminated materials
FR2340453A1 (fr) * 1976-02-06 1977-09-02 Snecma Corps de chambre de combustion, notamment pour turboreacteurs
GB1571213A (en) * 1977-01-28 1980-07-09 Kainov G Combustion chamber for gas turbine engine
DE2728399C2 (de) * 1977-06-24 1982-04-22 Brown, Boveri & Cie Ag, 6800 Mannheim Brennkammer für eine Gasturbine
US4297842A (en) * 1980-01-21 1981-11-03 General Electric Company NOx suppressant stationary gas turbine combustor
US4389848A (en) * 1981-01-12 1983-06-28 United Technologies Corporation Burner construction for gas turbines
JPS5872822A (ja) * 1981-10-26 1983-04-30 Hitachi Ltd ガスタ−ビン燃焼器の冷却構造
US4584834A (en) * 1982-07-06 1986-04-29 General Electric Company Gas turbine engine carburetor
US4651534A (en) * 1984-11-13 1987-03-24 Kongsberg Vapenfabrikk Gas turbine engine combustor
CA1263243A (fr) * 1985-05-14 1989-11-28 Lewis Berkley Davis, Jr. Couloir de transition refroidi par projection
GB2205934A (en) * 1987-06-16 1988-12-21 Stirling Power Systems Corp Burner for a hot-gas engine
US4949545A (en) * 1988-12-12 1990-08-21 Sundstrand Corporation Turbine wheel and nozzle cooling
DE4232442A1 (de) * 1992-09-28 1994-03-31 Asea Brown Boveri Gasturbinenbrennkammer
DE4239856A1 (de) * 1992-11-27 1994-06-01 Asea Brown Boveri Gasturbinenbrennkammer
DE4435266A1 (de) * 1994-10-01 1996-04-04 Abb Management Ag Brenner

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19516798A1 (de) 1995-05-08 1996-11-14 Abb Management Ag Vormischbrenner mit axialer oder radialer Luftzuströmung
DE19523094A1 (de) 1995-06-26 1997-01-02 Abb Management Ag Brennkammer

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2339013A (en) * 1998-07-01 2000-01-12 Asea Brown Boveri Gas Turbine

Also Published As

Publication number Publication date
JPH10325542A (ja) 1998-12-08
CN1114787C (zh) 2003-07-16
CN1199837A (zh) 1998-11-25
JP4036962B2 (ja) 2008-01-23
DE19720786A1 (de) 1998-11-19
EP0882932A3 (fr) 2000-03-22
DE59807433D1 (de) 2003-04-17
EP0882932B1 (fr) 2003-03-12
US6106278A (en) 2000-08-22

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