EP0718558A2 - Brûleur - Google Patents

Brûleur Download PDF

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Publication number
EP0718558A2
EP0718558A2 EP95810761A EP95810761A EP0718558A2 EP 0718558 A2 EP0718558 A2 EP 0718558A2 EP 95810761 A EP95810761 A EP 95810761A EP 95810761 A EP95810761 A EP 95810761A EP 0718558 A2 EP0718558 A2 EP 0718558A2
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
fuel
vortex
inflow channel
side surfaces
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
EP95810761A
Other languages
German (de)
English (en)
Other versions
EP0718558B1 (fr
EP0718558A3 (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
ABB Asea Brown Boveri Ltd
Original Assignee
ABB Management AG
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 Management AG filed Critical ABB Management AG
Publication of EP0718558A2 publication Critical patent/EP0718558A2/fr
Publication of EP0718558A3 publication Critical patent/EP0718558A3/fr
Application granted granted Critical
Publication of EP0718558B1 publication Critical patent/EP0718558B1/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
    • F23D23/00—Assemblies of two or more burners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M9/00—Baffles or deflectors for air or combustion products; Flame shields
    • F23M9/02—Baffles or deflectors for air or combustion products; Flame shields in air inlets
    • 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • 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
    • F23R2900/03341—Sequential combustion chambers or burners

Definitions

  • the present invention relates to a combustion chamber according to the preamble of claim 1. It also relates to a method for operating such a combustion chamber.
  • the blades of the turbine are acted upon integrally with gases of the same temperature, whereby it should be noted that in the case of an annular combustion chamber operated according to an auto-ignition method, the blades of the turbine are exposed to an even greater caloric load, since they take place upstream of the turbine reliable auto-ignition temperatures are sought, which have a certain safety margin against extinguishing the flame, whereby the blades themselves are exposed to a higher temperature than is the case with conventional combustion chambers.
  • the invention seeks to remedy this.
  • the invention as characterized in the claims, is based on the task of accomplishing a temperature gradation within the hot gas flow in a combustion chamber of the type mentioned at the outset.
  • a temperature gradation within the hot gas flow can preferably be achieved in an annular combustion chamber into which the fuel is injected via a number of fuel lances acting in the circumferential direction of the annular combustion chamber.
  • Each of these fuel lances has several, differently directed nozzles, through which the fuel is introduced into the flow cross-section of the annular combustion chamber, with which initially a sectoral enrichment of the fuel mixture is achieved.
  • Such a configuration is ideally suited, a different enrichment of the fuel mixture in different sectors to accomplish, wherein the injected fuel is mainly distributed within the sector assigned to it, which makes it possible to influence the temperature distribution via the fuel mixture. This achieves a temperature gradation in the radial direction, which represents the profile flow for the blades to be loaded.
  • vortex generators which are placed upstream of the fuel lances.
  • a major advantage of this provision is that the vortex generators are arranged sectorally, according to the fuel injection, and can also produce an individual effect there.
  • the temperature gradation can be specifically adjusted in the radial direction.
  • the introduction of the fuel is preferably handled in such a way that the blade roots are relieved of the hot gases at a given average temperature.
  • the temperature of the hot gases in the area of the blade roots is lower than the average temperature, this loss can easily be compensated for by producing a slightly higher temperature of the hot gases along the much larger area of the remaining blade profile. If the caloric load generally drops in the area of the weak points, the cooling of the blading can be reduced accordingly, which ultimately results in an improvement in efficiency.
  • a further advantage of the invention is that a better transient behavior of the rotor can be achieved by a targeted temperature grading, in particular in the transient load ranges, which leads to smaller clearances between the stator and the rotating parts.
  • a different enrichment also leads to the fact that the richer area has a flame-stabilizing effect, so that this area can easily function as a pilot stage, which means that a combination of pilot burners and main burners can be dispensed with.
  • a further surprising advantage of the invention has resulted from tests: a temperature gradation achieved in this way has the effect of sound insulation.
  • annular combustion chamber 1 which essentially takes the form of a coherent annular or quasi-annular cylinder.
  • a combustion chamber can also consist of only a single cylinder.
  • a combustion chamber which consists of a number of individual cylinders running axially, quasi-axially or helically, which are arranged in the circumferential direction with respect to the downstream turbine.
  • Fig. 1 shows only the significant part of the annular combustion chamber 1, namely the vortex formation, the fuel lance leading to a temperature gradation and the turbine located downstream and to be acted upon.
  • the main flow 4 is always a combustion air flow, the temperature and composition of which can be very different.
  • the main flow 4 consists of compressed air which forms the combustion air; however, if the present ring combustion chamber 1 is connected to an upstream first combustion chamber and a first turbine, this main flow consists of still relatively hot exhaust gases, the temperature of which leads to self-ignition of the fuel injected there.
  • the combustion air 4 thus flows into an inflow zone 5, which already on the inside and in the circumferential direction of the channel wall 6 with a number of vortex-generating elements 200 as vortex generators were named, which will be discussed in more detail below.
  • the combustion air 4 is swirled by the vortex generators 200 such that no recirculation areas occur in the subsequent premixing and combustion zone 5a after the vortex generators 200 mentioned.
  • a plurality of fuel lances 3 are arranged in the circumferential direction of this premixing and combustion zone 5a, which take over the supply of fuel 11 and supporting air 12.
  • the supply of these media 11, 12 to the individual fuel lances 3 can be accomplished, for example, by a ring line, not shown.
  • the swirl flow triggered individually by the vortex generators 200 is operatively connected to the sectorally injected fuel 7a, 7b, such that, by appropriately regulating the amount of fuel across the individual sectors, the individual vortex generators 200 have different levels of enrichment due to the effect of the vortex generators 200 Partial flows of the combustion air 4 result, which triggers a different temperature profile in the subsequent combustion.
  • a temperature gradation 8 over the flow cross-section is shown graphically and qualitatively in the figure.
  • this temperature-graded hot gas front acts on the rotor blades of a turbine 2 via corresponding guide vanes 9.
  • the blade roots are calorically less stressed, but the remaining blade surface is subjected to a slightly higher temperature, so that for the Efficiency and the performance-determining mean hot gas temperature is maintained.
  • FIG. 2 shows, for each fuel lance 3 in the area of the vortex generators 200, a chamber typical of an annular annular combustion chamber 1 is formed, with which side vortex generators 200 can also be attached. If the combustion chamber consists of individual tubes, such a subdivision is not necessary because the tube then also forms the chamber. Seen this way the fuel lance 3 is encased by vortex generators 200 in terms of flow.
  • the sectoral fuel injection 7a, 7b is dependent on the position of the vortex generators 200 placed upstream, wherein this injection should preferably be directed between the individual flank surfaces of the vortex generators 200 to ensure a temperature gradation, so that the swirling that occurs there mixes well with the appropriate amount of fuel.
  • the fuel injection 7a, 7b can also be accomplished via a larger number of nozzles, depending on the desired temperature grading and depending on the position of the individual vortex generators 200 within the flow cross-section of the annular combustion chamber 1.
  • This annular combustion chamber can have a radial expansion consist of several superordinate rows of chambers, one row of chambers being designed as a pilot stage to the remaining concentrically arranged rows of chambers.
  • a vortex generator 200, 201, 202 essentially consists of three freely flowing triangular surfaces. These are a roof surface 210 and two side surfaces 211 and 213. In their longitudinal extent, these surfaces run at certain angles in the direction of flow.
  • the side walls of the vortex generators 200, 201, 202, which preferably consist of right-angled triangles, are fixed with their long sides on the channel wall 6 already mentioned, preferably gas-tight. They are oriented so that they form a joint on their narrow sides, including an arrow angle ⁇ .
  • the push is designed as a sharp connecting edge 216 and is perpendicular to each channel wall 6 with which the side surfaces are flush.
  • the two side surfaces 211, 213 including the arrow angle ⁇ are symmetrical in shape, size and orientation in FIG. 3, they are arranged on both sides of an axis of symmetry 217 which is oriented in the same direction as the channel axis.
  • the roof surface 210 lies against the same channel wall 6 as the side surfaces 211, 213 with a very narrow edge 215 running transversely to the flow channel. Its longitudinal edges 212, 214 are flush with the longitudinal edges of the side surfaces 211 protruding into the flow channel , 213.
  • the roof surface 210 extends at an angle of inclination ⁇ to the channel wall 6, the longitudinal edges 212, 214 of which, together with the connecting edge 216, form a point 218.
  • the vortex generator 200, 201, 202 can also be provided with a bottom surface with which it is attached to the channel wall 6 in a suitable manner. Such a floor area is, however, unrelated to the mode of operation of the element.
  • the mode of operation of the vortex generator 200, 201, 202 is as follows: When flowing around the edges 212 and 214, the main flow is converted into a pair of opposing vortices, as is schematically outlined in the figures.
  • the vortex axes lie in the axis of the main flow.
  • the number of swirls and the location of the vortex breakdown (vortex breakdown), if the latter is aimed for, are determined by appropriate selection of the angle of attack ⁇ and the arrow angle ⁇ .
  • the vortex strength or the number of swirls is increased, and the location of the vortex bursting shifts upstream into the region of the vortex generator 200, 201, 202 itself.
  • these two angles ⁇ and ⁇ are due to structural conditions and determined by the process itself.
  • These vortex generators only have to be adjusted in terms of length and height, as will be explained in more detail below under FIG. 6.
  • the connecting edge 216 of the two side surfaces 211, 213 forms the downstream edge of the vortex generator 200.
  • the edge 215 of the roof surface 210 running transversely to the flow through the channel is thus the edge which is first acted upon by the channel flow.
  • FIG. 4 shows a so-called half "vortex generator” based on a vortex generator according to FIG. 6.
  • the vortex generator 201 shown here only one of the two side surfaces is provided with the arrow angle ⁇ / 2.
  • the other side surface is straight and oriented in the direction of flow.
  • only one vortex is generated on the arrowed side, as is shown in the figure. Accordingly, there is no vortex-neutral field downstream of this vortex generator, but a swirl is forced on the flow.
  • FIG. 5 differs from FIG. 3 in that the sharp connecting edge 216 of the vortex generator 202 is the point which is first acted upon by the channel flow. The element is therefore rotated by 180 °. As can be seen from the illustration, the two opposite vortices have changed their sense of rotation.
  • FIG. 6 shows the basic geometry of a vortex generator 200 installed in a channel 5.
  • the height h of the connecting edge 216 will be coordinated with the channel height H, or the height of the channel part which is assigned to the vortex generator that the vortex generated immediately downstream of the vortex generator 200 already reaches such a size that the full channel height H is filled. This leads to a uniform speed distribution in the cross-section applied.
  • a Another criterion that can influence the ratio of the two heights h / H to be selected is the pressure drop that occurs when the vortex generator 200 flows around. It goes without saying that the pressure loss coefficient also increases with a larger ratio h / H.
  • the vortex generators 200, 201, 202 are mainly used when it comes to mixing two flows.
  • the main flow 4 for example as hot gases, attacks the transverse edge 215 or the connecting edge 216 in the direction of the arrow.
  • the secondary flow in the form of a gaseous and / or liquid fuel, which is possibly enriched with a portion of supporting air (see FIG. 1) a significantly smaller mass flow than the main flow. In the present case, this secondary flow is introduced into the main flow downstream of the vortex generator, as can be seen particularly well from FIG. 1.
  • the vortex generators 200 are distributed at a distance over the circumference of a chamber of the channel 5.
  • the vortex generators can also be strung together in the circumferential direction so that no gaps are left on the channel wall 6.
  • the vortices to be generated are ultimately decisive for the choice of the number and the arrangement of the vortex generators.
  • FIGS. 7-13 show further possible forms of introducing the fuel into the main flow 4. These variants can be combined in a variety of ways with one another and with a central fuel injection, as can be seen, for example, from FIG. 1.
  • the fuel is also injected via wall bores 221 which are located directly next to the side surfaces 211, 213 and in their longitudinal extent in the same channel wall 6 on which the vortex generators are arranged.
  • the introduction of the fuel through the wall bores 221 gives the generated vortices an additional impulse, which extends the lifespan of the vortex generator.
  • the fuel is injected via a slot 222 or via wall bores 223, both precautions being located directly in front of the edge 215 of the roof surface 210 running transversely to the flow channel and in its longitudinal extent in the same channel wall 6 on which the Vortex generators are arranged.
  • the geometry of the wall bores 223 or of the slot 222 is selected such that the fuel is introduced into the main flow 4 at a specific injection angle and largely shields the post-placed vortex generator as a protective film against the hot main flow 4 by flow around it.
  • the secondary flow (cf. above) is first introduced into the hollow interior of the vortex generators via guides (not shown) through the channel wall 6. This creates an internal cooling facility for the vortex generators without providing any additional equipment.
  • the fuel is injected via wall bores 224, which are located inside the roof surface 210 directly behind and along the edge 215 running transversely to the flow channel.
  • the vortex generator is cooled here more externally than internally.
  • the emerging secondary flow forms when flowing around the roof surface 210 a protective layer shielding it against the hot main flow 4.
  • the fuel is injected via wall bores 225, which are staggered within the roof surface 210 along the line of symmetry 217.
  • the channel walls 6 are particularly well protected from the hot main flow 4, since the fuel is first introduced on the outer circumference of the vortex.
  • the fuel is injected via wall bores 226, which are located in the longitudinal edges 212, 214 of the roof surface 210.
  • This solution ensures good cooling of the vortex generators, since the fuel escapes from its extremities and thus completely flushes the inner walls of the element.
  • the secondary flow is fed directly into the resulting vortex, which leads to defined flow conditions.
  • the injection takes place via wall bores 227, which are located in the side surfaces 211 and 213, on the one hand in the region of the longitudinal edges 212 and 214 and on the other hand in the region of the connecting edge 216.
  • This variant is similar in effect to that from FIG. 7 (bores 221 ) and from Fig. 12 (bores 226).

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
  • Combustion Of Fluid Fuel (AREA)
EP95810761A 1994-12-24 1995-12-05 Brûleur Expired - Lifetime EP0718558B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4446611 1994-12-24
DE4446611A DE4446611A1 (de) 1994-12-24 1994-12-24 Brennkammer

Publications (3)

Publication Number Publication Date
EP0718558A2 true EP0718558A2 (fr) 1996-06-26
EP0718558A3 EP0718558A3 (fr) 1997-04-23
EP0718558B1 EP0718558B1 (fr) 2001-04-18

Family

ID=6537131

Family Applications (1)

Application Number Title Priority Date Filing Date
EP95810761A Expired - Lifetime EP0718558B1 (fr) 1994-12-24 1995-12-05 Brûleur

Country Status (5)

Country Link
US (1) US5609030A (fr)
EP (1) EP0718558B1 (fr)
JP (1) JP3977454B2 (fr)
CN (1) CN1076786C (fr)
DE (2) DE4446611A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1400752A1 (fr) * 2002-09-20 2004-03-24 Siemens Aktiengesellschaft Brûleur à prémélange avec un écoulement d'air profilé
EP2112433A1 (fr) * 2008-04-23 2009-10-28 Siemens Aktiengesellschaft Chambre de mélange
WO2013139914A1 (fr) * 2012-03-23 2013-09-26 Alstom Technology Ltd Dispositif de combustion
US10072532B2 (en) 2013-03-06 2018-09-11 General Electric Technology Gmbh Method for starting-up and operating a combined-cycle power plant

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EP0807213B1 (fr) * 1995-02-03 2002-07-31 Rolls-Royce Deutschland Ltd & Co KG Corps de guidage de l'ecoulement pour chambres de combustion de turbines a gaz
JP2003035417A (ja) * 2001-07-24 2003-02-07 Mitsubishi Heavy Ind Ltd ガスタービン燃焼器のパイロットノズル
DE10219354A1 (de) * 2002-04-30 2003-11-13 Rolls Royce Deutschland Gasturbinenbrennkammer mit gezielter Kraftstoffeinbringung zur Verbesserung der Homogenität des Kraftstoff-Luft-Gemisches
US7810336B2 (en) * 2005-06-03 2010-10-12 Siemens Energy, Inc. System for introducing fuel to a fluid flow upstream of a combustion area
DE102007043626A1 (de) * 2007-09-13 2009-03-19 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenmagerbrenner mit Kraftstoffdüse mit kontrollierter Kraftstoffinhomogenität
JP5453322B2 (ja) 2008-03-07 2014-03-26 アルストム テクノロジー リミテッド バーナ装置並びにバーナ装置の使用
EP2257736B1 (fr) 2008-03-07 2015-11-25 Alstom Technology Ltd Procédé de production de gaz chaud
ES2400247T3 (es) * 2008-12-19 2013-04-08 Alstom Technology Ltd Quemador de una turbina de gas que tiene una configuración de lanza especial
EP2230455B1 (fr) 2009-03-16 2012-04-18 Alstom Technology Ltd Brûleur pour une turbine à gaz et procédé de refroidissement local d'un flux de gaz chauds passant par un brûleur
EP2253888B1 (fr) * 2009-05-14 2013-10-16 Alstom Technology Ltd Brûleur d'une turbine à gaz ayant un générateur de vortex avec une lance à combustible
AU334043S (en) 2010-07-15 2010-12-07 Sharp Kk Electronic calculator
EP2644997A1 (fr) 2012-03-26 2013-10-02 Alstom Technology Ltd Agencement de mélange pour mélanger un combustible avec un flux de gaz contenant de l'oxygène
DE102012213852A1 (de) * 2012-08-06 2014-02-06 Siemens Aktiengesellschaft Lokale Verbesserung der Mischung von Luft und Brennstoff in Brennern mit Drallerzeugern
EP2789915A1 (fr) * 2013-04-10 2014-10-15 Alstom Technology Ltd Procédé de fonctionnement d'une chambre de combustion et chambre de combustion
EP2894405B1 (fr) * 2014-01-10 2016-11-23 General Electric Technology GmbH Dispositif à combustion séquentielle avec un gaz de dilution
CN107076416B (zh) 2014-08-26 2020-05-19 西门子能源公司 用于燃气涡轮发动机中的声共振器的薄膜冷却孔装置
EP3081862B1 (fr) * 2015-04-13 2020-08-19 Ansaldo Energia Switzerland AG Agencement de génération de vortex pour un brûleur à pré-mélange d'une turbine à gaz et turbine à gaz avec un tel agencement de génération de vortex
KR102787680B1 (ko) 2020-03-31 2025-03-28 지멘스 에너지 글로벌 게엠베하 운트 코. 카게 버너의 버너 구성요소 및 이러한 유형의 버너 구성요소를 갖는 가스 터빈의 버너
US11384937B1 (en) * 2021-05-12 2022-07-12 General Electric Company Swirler with integrated damper
US11454396B1 (en) * 2021-06-07 2022-09-27 General Electric Company Fuel injector and pre-mixer system for a burner array
KR102667812B1 (ko) * 2022-02-07 2024-05-20 두산에너빌리티 주식회사 연소기용 노즐 및 이를 포함하는 가스 터빈

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Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1400752A1 (fr) * 2002-09-20 2004-03-24 Siemens Aktiengesellschaft Brûleur à prémélange avec un écoulement d'air profilé
EP2112433A1 (fr) * 2008-04-23 2009-10-28 Siemens Aktiengesellschaft Chambre de mélange
US8424310B2 (en) 2008-04-23 2013-04-23 Siemens Aktiengesellschaft Mixing chamber
WO2013139914A1 (fr) * 2012-03-23 2013-09-26 Alstom Technology Ltd Dispositif de combustion
US9568198B2 (en) 2012-03-23 2017-02-14 General Electric Technology Gmbh Combustion device having a distribution plenum
US10072532B2 (en) 2013-03-06 2018-09-11 General Electric Technology Gmbh Method for starting-up and operating a combined-cycle power plant

Also Published As

Publication number Publication date
JP3977454B2 (ja) 2007-09-19
US5609030A (en) 1997-03-11
CN1130718A (zh) 1996-09-11
DE4446611A1 (de) 1996-06-27
EP0718558B1 (fr) 2001-04-18
EP0718558A3 (fr) 1997-04-23
DE59509206D1 (de) 2001-05-23
CN1076786C (zh) 2001-12-26
JPH08226647A (ja) 1996-09-03

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