EP1952066B1 - Appareil de combustion - Google Patents

Appareil de combustion Download PDF

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Publication number
EP1952066B1
EP1952066B1 EP06819738.3A EP06819738A EP1952066B1 EP 1952066 B1 EP1952066 B1 EP 1952066B1 EP 06819738 A EP06819738 A EP 06819738A EP 1952066 B1 EP1952066 B1 EP 1952066B1
Authority
EP
European Patent Office
Prior art keywords
chamber
swirler
gas
annular
combustion
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 - Fee Related
Application number
EP06819738.3A
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German (de)
English (en)
Other versions
EP1952066A1 (fr
Inventor
Iain Jubb
Peter Martin
Victoria Sanderson
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
Original Assignee
Siemens 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 Siemens AG filed Critical Siemens AG
Publication of EP1952066A1 publication Critical patent/EP1952066A1/fr
Application granted granted Critical
Publication of EP1952066B1 publication Critical patent/EP1952066B1/fr
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F23R3/02—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
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes

Definitions

  • the present invention relates to a combustion apparatus.
  • the present invention relates to a combustion apparatus comprising: a device for mixing a fuel with an oxidant; a combustion chamber in which combustion of the fuel/oxidant mix takes place; a pre-chamber located between the device and the combustion chamber; and means for supplying a gas to the pre-chamber so as to form a film of gas on the interior surface of the pre-chamber so as to prevent a combustion flame from the combustion chamber attaching itself to this interior surface damaging the pre-chamber.
  • EP 0 924 469 A discloses a swirl cup for a gas turbine engine combustor including a tubular body having an inlet at one end for receiving a fuel injection nozzle, an outlet at an opposite end for discharging the fuel, and an annular septum therebetween.
  • a row of first swirl vanes is attached to the septum adjacent the body inlet, and a row of second swirl vanes is attached to the septum adjacent the first swirl vanes and spaced upstream from the body outlet. Air from the first and second swirl vanes is swirled directly around the injected fuel without a flow barrier or venturi therebetween.
  • EP 0 735 318 A discloses a combustion chamber head assembly consisting of an annular, domed combustor head separated on its downstream side from the combustion region by an annular bulkhead.
  • a number of fuel injector means are spaced apart around the head assembly and extend through to supply fuel-air mixture to the combustor region through apertures in the bulkhead.
  • Fuel is supplied by a nozzle at the upstream end of a mixing region. Air is admitted to this region through a variable geometry airflow arrangement comprising several airflow passage disposed concentrically around the nozzle, the passages may include swirl vanes.
  • a portion of the wall surrounding the mixing region is axially translatable to close-off one of the air inlet passages and direct air from the mixing region into the cavity enclosed by the combustor head and bulkhead from where it escapes into the combustion region through air-only apertures in the bulkhead wall.
  • US 5 816 050 A discloses a low-emission combustion chamber for gas turbine engines comprises an outer casing with an upstream end wall with a pilot fuel injector, a first flow swirler, an igniting members for initiating a stable diffusion frame in a pilot zone, at least one second coaxial swirler, main fuel injectors, secondary air inlets, and a main combustion zone.
  • the pilot zone is confined radially outwardly by a surrounding wall which constitutes the radially inner confinement of an axial outlet portion of a radial vaporization channel within the second swirler and a third radial flow swirler is adapted to supply the secondary air in a rotary motion opposite to that of the main flow of fuel and air.
  • a combustion apparatus comprising: a device for mixing a fuel with an oxidant; a combustion chamber in which combustion of the fuel/oxidant mix takes place; a pre-chamber located between the device and the combustion chamber; and means for supplying a gas to the pre-chamber so as to form a film of gas on the interior surface of the pre-chamber so as to prevent a combustion flame from the combustion chamber attaching itself to this interior surface damaging the pre-chamber, the supply of gas to the pre-chamber being such that where the gas first reaches the interior surface of the pre-chamber it forms a substantially continuous film of gas over this interior surface.
  • the means for supplying comprises a swirler for creating a swirling flow of the gas which travels over the interior surface of the pre-chamber to the combustion chamber.
  • the swirler comprises a plurality of slots for guiding the gas, the slots being arranged in a circle and extending generally radially inwardly.
  • the swirler comprises an annular base plate and a plurality of wedge pieces arranged circumferentially spaced around the annular base plate so as to form between adjacent wedge pieces the slots for guiding the gas, the wedge pieces being set back from the radially inner edge of the annular base plate thereby to define an annular ledge on the annular base plate immediately radially outward of the radially inner edge.
  • an apparatus further comprises an annular closing plate secured to the swirler such that one side of the annular closing plate forms a wall of the slots, the wedge pieces being set back from the radially inner edge of the annular closing plate thereby to define an annular ledge on the annular closing plate immediately radially outward of the radially inner edge of the annular closing plate.
  • the swirler is located between the device and the pre-chamber, and the swirler meets the pre-chamber by way of a smooth shoulder formed between the annular ledge on the annular base plate of the swirler and the interior surface of the pre-chamber.
  • the means for supplying is located between the device and the pre-chamber.
  • the device may comprise a swirler for creating a swirling mix of the fuel and oxidant which travels along the pre-chamber to the combustion chamber.
  • the oxidant may be air and the gas may be air.
  • the present invention also extends to a gas turbine engine including an apparatus according to any one of the preceding six paragraphs, wherein compressed gas from the compressor of the engine is shared between the device and the means for supplying, the majority of the gas being supplied to device.
  • the apparatus comprises a first swirler 1 for creating a swirling mix of a fuel and air, a combustion chamber 3 in which combustion of the fuel/air mix takes place, a second swirler 5 for creating a swirling flow of air, an annular closing plate 7 that separates swirlers 1 and 5, and a pre-chamber 9 located between second swirler 5 and combustion chamber 3.
  • First swirler 1 comprises an annular base plate 11, and a plurality of wedge pieces 13 arranged circumferentially spaced around annular base plate 11 so as to form, between adjacent wedge pieces 13, slots 15.
  • Plate 11 includes at the radially outer end of each slot 15 a port 17 by means of which fuel is supplied to first swirler 1.
  • Each wedge piece 13 includes at the radially outer end of one side 19 thereof a hole 21 by means of which fuel is also supplied to first swirler 1.
  • a plurality of fixing holes 23 extend through wedge pieces 13 and base plate 11. The radially inner thin ends 25 of wedge pieces 13 are set back from the radially inner edge 27 of annular base plate 11 thereby to define an annular ledge 29 immediately radially outward of edge 27.
  • Second swirler 5 is similar in form to first swirler 1 and comprises an annular base plate 31, and a plurality of wedge pieces 33 arranged circumferentially spaced around annular base plate 31 so as to form, between adjacent wedge pieces 33, slots 35.
  • the height of wedge pieces 33 above base plate 31 is much reduced as compared to the height of wedge pieces 13 above base plate 11 in first swirler 1.
  • a plurality of fixing holes 37 extend through wedge pieces 33 and base plate 31.
  • the radially inner thin ends 39 of wedge pieces 33 are set back from the radially inner edge 41 of annular base plate 31 thereby to define an annular ledge 43 immediately radially outward of edge 41.
  • Pre-chamber 9 is cylindrical in form and has an interior surface 47. Pre-chamber 9 is formed integrally with second swirler 5. In this regard, at the point where pre-chamber 9 meets second swirler 5, a smooth 90° shoulder 49 is formed between interior surface 47 of pre-chamber 9 and annular ledge 43 of second swirler 5.
  • Annular closing plate 7 includes a plurality of fixing holes 45.
  • First swirler 1, annular closing plate 7, and second swirler 5 (together with integrally formed pre-chamber 9) are secured together by means of nut and bolt fixings utilising fixing holes 23 in swirler 1, 45 in plate 7, and 37 in swirler 5.
  • one side of plate 7 forms a wall of each of slots 15 of first swirler 1
  • the other side of plate 7 forms a wall of each of slots 35 of second swirler 5.
  • the relationship of wedge pieces 13 of first swirler 1 to annular closing plate 7 can be seen in Fig 8 .
  • the radially inner thin ends 25 of wedge pieces 13 extend precisely as far as the radially inner edge 51 of annular closing plate 7.
  • the relationship of wedge pieces 33 of second swirler 5 to annular closing plate 7 can be seen in Fig 9 .
  • the radially inner thin ends 39 of wedge pieces 33 are set back from the radially inner edge 51 of annular closing plate 7 thereby to define an annular ledge 53 immediately radially outward of edge 51.
  • Air is supplied to the radially outer ends of slots 15 of first swirler 1 and travels generally radially inwardly along slots 15.
  • Fuel is supplied to ports 17 and holes 21 of first swirler 1 so as to enter slots 15 and mix with the air travelling along slots 15.
  • first swirler 1 creates a swirling mix of fuel and air in an annular region immediately radially inward of the radially inner ends of slots 15, see arrows 55 in Fig 8 .
  • This swirling mix travels axially along the apparatus to combustion chamber 3, passing through annular closing plate 7, second swirler 5, and pre-chamber 9, see arrows 57 in Fig 10 .
  • Ignition of the fuel/air mix is achieved by means of an ignition device (not shown) located in the circular opening of annular base plate 11 of first swirler 1.
  • the combustion apparatus includes a further part (not shown) disposed to the left of the apparatus as shown in Fig 1 , which part includes a face that occupies the circular opening of annular base plate 11.
  • the ignition device is disposed within this face. Following ignition by the ignition device, the combustion is self-sustaining.
  • Air is also supplied to the radially outer ends of slots 35 of second swirler 5 and travels generally radially inwardly along slots 35.
  • second swirler 5 creates a swirling flow of air in an annular region immediately radially inward of the radially inner ends of slots 35, see arrows 59 in Fig 4 .
  • This swirling flow swirls between annular ledge 53 of annular closing plate 7 and annular ledge 43 of second swirler 5, passes over 90° shoulder 49 between annular ledge 43 and interior surface 47 of pre-chamber 9, and travels axially along pre-chamber 9 to combustion chamber 3, see arrows 61 in Fig 10 .
  • second swirler 5 The purpose of the air flow provided by second swirler 5 is to provide a film of air on interior surface 47 of pre-chamber 9 thereby to prevent a combustion flame from combustion chamber 3 attaching itself to interior surface 47 damaging pre-chamber 9.
  • the supply of air by second swirler 5 is such that where the air first reaches interior surface 47, i.e. following 90° shoulder 49, it forms a continuous film of air over interior surface 47.
  • This continuous nature is due to (i) the presence of annular ledge 43, created by setting back wedge pieces 33 from edge 41 of second swirler 5, (ii) the presence of annular ledge 53, created by setting back wedge pieces 33 from edge 51 of annular closing plate 7, and (iii) the presence of 90° shoulder 49 between second swirler 5 and pre-chamber 9.
  • the design intent is that the velocity of the air flow from second swirler 5, see arrows 61 in Fig 10 , is as close as possible to the velocity of the fuel/air mix from first swirler 1, see arrows 57 in Fig 10 . In this way there is minimum disturbance of air flow 61 by mix flow 57, minimising corruption of protective air film 61.
  • a protective film of air is provided on the interior surface of pre-chamber 9. It is to be realised that this protective film need not be of air but could be of another gas, e.g. carbon dioxide. Similarly, the protective film could be a mix of a gaseous fuel and air, provided the particular mix used (concentration of the fuel in the air) does not ignite in the conditions present in pre-chamber 9 in the region of the interior surface of pre-chamber 9. Thus, a lean mix could be used wherein the concentration of the fuel is below that at which ignition can occur, or a rich mix could be used wherein the concentration of fuel is above that at which ignition can occur. Indeed, in the case of the rich mix, the concentration of the fuel could be 100 percent, i.e. no air present.
  • a swirler is used to provide a mix of fuel and air for combustion. It is to be realised that the fuel/air mix could be provided by an alternative device able to provide a sufficiently homogeneous mix of fuel and air.
  • a swirler is used to supply air for the protective film on the interior surface of pre-chamber 9. It is to be realised that an alternative means could be used for this purpose, provided the supply of air is such that where the air first reaches the interior surface it forms a substantially continuous film of air over this surface.
  • second swirler 5 is located immediately prior to pre-chamber 9. It is to be realised that swirler 5 could be located partway along the length of pre-chamber 9, such that the protective film of air is provided only in respect of the remaining portion of pre-chamber 9 between swirler 5 and combustion chamber 3. Further, the apparatus could include two second swirlers 5, one located immediately prior to pre-chamber 9, the other located partway along the length of pre-chamber 9. The swirler 5 located partway along the length of pre-chamber 9 would then provide protective air to supplement that provided by the swirler 5 located immediately prior to pre-chamber 9. This supplementary air would assist in the protection of pre-chamber 9 downstream of the swirler 5 located partway along the length of the pre-chamber.
  • the present invention finds particular application in gas turbine engines.
  • compressed air from the compressor of the engine would be shared between first swirler 1 and second swirler 5, the majority of the air being supplied to first swirler 1.
  • the present invention is particularly useful in the combustion of fuels of high flame speed. When using such fuels there is a greater tendency for a combustion flame from the combustion chamber to flashback to the pre-chamber and attach itself to the interior surface of the pre-chamber.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Cyclones (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
  • Gas Burners (AREA)

Claims (7)

  1. Appareil de combustion comprenant :
    un dispositif permettant de mélanger un combustible avec un comburant ;
    une chambre de combustion (3) dans laquelle la combustion du mélange combustible/comburant a lieu ;
    une préchambre (9) située entre le dispositif et la chambre de combustion (3), et
    des moyens pour amener un gaz jusqu'à la préchambre (9) de manière à former un film de gaz sur la surface intérieure (47) de la préchambre (9) afin d'empêcher une flamme de combustion provenant de la chambre de combustion (3) de s'accrocher à cette surface intérieure (47) et d'endommager la préchambre (9),
    l'amenée de gaz jusqu'à la préchambre (9) étant telle que, lorsque le gaz atteint d'abord la surface intérieure (47) de la préchambre (9), il forme un film sensiblement continu de gaz sur cette surface intérieure (47),
    les moyens d'amenée comprenant un générateur de turbulences (1, 5) en vue de créer un écoulement turbulent du gaz qui se déplace sur la surface intérieure (47) de la préchambre (9) jusqu'à la chambre de combustion (3),
    le générateur de turbulences (1, 5) comprenant une pluralité de fentes (15, 35) servant à guider le gaz,
    les fentes (15, 35) étant agencées en cercle et s'étendant globalement vers l'intérieur dans le sens radial,
    caractérisé en ce que :
    le générateur de turbulences (1, 5) comprend par ailleurs une plaque de base annulaire (11) et une pluralité de pièces en coin (13) agencées de manière circonférentielle et espacées sur le pourtour de la plaque de base annulaire (11) pour former entre des pièces en coin (13) adjacentes les fentes (15, 35) servant à guider le gaz ;
    en ce que les pièces en coin (13) sont en retrait par rapport au bord radialement interne (27) de la plaque de base annulaire (11), ce qui définit un rebord annulaire (53) sur la plaque de base annulaire (11) situé, dans le plan radial, immédiatement à l'extérieur du bord radialement interne (27).
  2. Appareil selon la revendication 1 comprenant par ailleurs une plaque de fermeture annulaire fixée au générateur de turbulences (1, 5) de telle sorte qu'un côté de la plaque de fermeture annulaire (7) forme une paroi des fentes (15, 35), les pièces en coin (13) étant en retrait par rapport au bord radialement interne de la plaque de fermeture annulaire (7), ce qui définit un rebord annulaire (53) sur la plaque de fermeture annulaire (7) situé, dans le sens radial, immédiatement à l'extérieur du bord radialement interne (27) de la plaque de fermeture annulaire (7).
  3. Appareil selon la revendication 1 ou la revendication 2 dans lequel le générateur de turbulences (1, 5) est situé entre le dispositif et la préchambre (9) et le générateur de turbulences (1, 5) rejoint la préchambre (9) au moyen d'un épaulement lisse formé entre le rebord annulaire (53) de la plaque de base annulaire (11) du générateur de turbulences (1, 5) et la surface intérieure (47) de la préchambre (9).
  4. Appareil selon la revendication 1 dans lequel le générateur de turbulences (1, 5) est situé entre le dispositif et la préchambre (9).
  5. Appareil selon l'une quelconque des revendications précédentes dans lequel le dispositif comprend un générateur de turbulences (1, 5) servant à créer un mélange turbulent de combustible et de comburant qui se déplace le long de la préchambre (9) jusqu'à la chambre de combustion (3).
  6. Appareil selon l'une quelconque des revendications précédentes dans lequel le comburant est de l'air et le gaz est de l'air.
  7. Moteur à turbine à gaz comprenant un appareil selon l'une quelconque des revendications précédentes, dans lequel du gaz comprimé provenant du compresseur du moteur est partagé entre le dispositif et le générateur de turbulences (1, 5), la majorité du gaz étant amenée jusqu'au dispositif.
EP06819738.3A 2005-11-26 2006-11-24 Appareil de combustion Expired - Fee Related EP1952066B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB0524097A GB2432655A (en) 2005-11-26 2005-11-26 Combustion apparatus
PCT/EP2006/068870 WO2007060216A1 (fr) 2005-11-26 2006-11-24 Appareil de combustion

Publications (2)

Publication Number Publication Date
EP1952066A1 EP1952066A1 (fr) 2008-08-06
EP1952066B1 true EP1952066B1 (fr) 2016-08-31

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Family Applications (1)

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EP06819738.3A Expired - Fee Related EP1952066B1 (fr) 2005-11-26 2006-11-24 Appareil de combustion

Country Status (7)

Country Link
US (1) US20090142716A1 (fr)
EP (1) EP1952066B1 (fr)
JP (1) JP4785932B2 (fr)
CN (1) CN101313178B (fr)
GB (1) GB2432655A (fr)
RU (1) RU2419031C2 (fr)
WO (1) WO2007060216A1 (fr)

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JP5172468B2 (ja) * 2008-05-23 2013-03-27 川崎重工業株式会社 燃焼装置および燃焼装置の制御方法
EP2169312A1 (fr) * 2008-09-25 2010-03-31 Siemens Aktiengesellschaft Agitateur à gradins pour contrôle dynamique
EP2192347B1 (fr) 2008-11-26 2014-01-01 Siemens Aktiengesellschaft Chambre tubulaire de tourbillonnement
FR2945854B1 (fr) * 2009-05-19 2015-08-07 Snecma Vrille melangeuse pour un injecteur de carburant dans une chambre de combustion d'une turbine a gaz et dispositif de combustion correspondant
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US9534790B2 (en) * 2013-01-07 2017-01-03 General Electric Company Fuel injector for supplying fuel to a combustor
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CN104329689B (zh) * 2014-03-26 2016-08-17 中国科学院工程热物理研究所 一种采用旋流叶片尾缘预膜雾化方式的燃烧室
CN104534514B (zh) * 2014-11-27 2017-09-15 北京华清燃气轮机与煤气化联合循环工程技术有限公司 一种燃气轮机燃烧室叶片引气旋流喷嘴
US10197269B2 (en) * 2015-07-31 2019-02-05 Nuvera Fuel Cells, LLC Burner assembly with low NOx emissions
EP3159609A1 (fr) * 2015-10-21 2017-04-26 Siemens Aktiengesellschaft Chambre de combustion pour turbine à gaz
US10859272B2 (en) 2016-01-15 2020-12-08 Siemens Aktiengesellschaft Combustor for a gas turbine
CN107014618B (zh) * 2017-03-29 2019-03-29 浙江大学 一种燃烧室和涡轮耦合作用机理实验研究装置
GB2561190A (en) * 2017-04-04 2018-10-10 Edwards Ltd Purge gas feeding means, abatement systems and methods of modifying abatement systems
US11280495B2 (en) * 2020-03-04 2022-03-22 General Electric Company Gas turbine combustor fuel injector flow device including vanes
CN112684099B (zh) * 2020-12-18 2022-09-09 郑州大学 一种组装式湍流火焰熄灭装置
US11761632B2 (en) * 2021-08-05 2023-09-19 General Electric Company Combustor swirler with vanes incorporating open area
CN114294676B (zh) * 2021-12-16 2023-05-12 北京动力机械研究所 一种宽点火边界的预燃室结构

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Also Published As

Publication number Publication date
US20090142716A1 (en) 2009-06-04
WO2007060216A1 (fr) 2007-05-31
GB2432655A (en) 2007-05-30
EP1952066A1 (fr) 2008-08-06
JP4785932B2 (ja) 2011-10-05
RU2008125896A (ru) 2010-01-10
CN101313178B (zh) 2011-08-31
RU2419031C2 (ru) 2011-05-20
GB0524097D0 (en) 2006-01-04
CN101313178A (zh) 2008-11-26
JP2009517621A (ja) 2009-04-30

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