EP2405200A1 - Appareil de combustion et moteur de turbine à gaz - Google Patents

Appareil de combustion et moteur de turbine à gaz Download PDF

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Publication number
EP2405200A1
EP2405200A1 EP10168429A EP10168429A EP2405200A1 EP 2405200 A1 EP2405200 A1 EP 2405200A1 EP 10168429 A EP10168429 A EP 10168429A EP 10168429 A EP10168429 A EP 10168429A EP 2405200 A1 EP2405200 A1 EP 2405200A1
Authority
EP
European Patent Office
Prior art keywords
chamber
combustion
wall
coolant
cavity
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.)
Withdrawn
Application number
EP10168429A
Other languages
German (de)
English (en)
Inventor
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
Priority to EP10168429A priority Critical patent/EP2405200A1/fr
Priority to RU2013104536/06A priority patent/RU2013104536A/ru
Priority to EP11728817A priority patent/EP2553341A1/fr
Priority to CN201180033349XA priority patent/CN102959333A/zh
Priority to PCT/EP2011/060492 priority patent/WO2012004131A1/fr
Priority to US13/808,104 priority patent/US20140144143A1/en
Publication of EP2405200A1 publication Critical patent/EP2405200A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • 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
    • F23R3/005—Combined with pressure or heat exchangers

Definitions

  • the present invention relates to a combustion apparatus. More particularly the present invention relates to a cooling system of a combustion apparatus. Furthermore, the present invention relates to a gas turbine engine using a combustion apparatus.
  • the combustion chamber exhibits a first wall and a second wall spaced to each other building a cavity.
  • the first wall which is the outer skin of the combustion chamber exhibits holes so that a coolant can enter the cavity between the first and the second wall of the combustion chamber.
  • the second wall of the combustion chamber which is the inner layer, also exhibits openings, in particular perforations or a series of small holes, so that the coolant can enter from the cavity into the combustion chamber cooling the inner layer of the combustion chamber.
  • the perforations or small holes in the inner layer are smaller than those on the outer skin and provide for cooling and acoustic dampling.
  • An object of the present invention is to improve the cooling of a combustion apparatus.
  • a further object of the present invention is to reduce the NOx emissions of a combustion apparatus.
  • a combustion apparatus which comprises a combustion chamber in which combustion of a fuel/oxidant mix takes place, a pre-chamber which is located upstream of the combustion chamber, wherein the combustion chamber and the pre-chamber comprise a common first wall and a common second wall spaced to each other building a cavity, and wherein the first wall exhibits at least one first opening for introducing a coolant into the cavity.
  • the term upstream means the direction from the combustion chamber towards the pre-chamber.
  • the first wall is the outer wall, which faces the outer casing of the combustion apparatus.
  • a second wall is the inner wall, which faces the center of the combustion apparatus and which therefore faces the combustion flame.
  • the first opening can be realized by holes in the first wall.
  • the cavity is a continuous cavity which extends from the area of the pre-chamber to the area of the combustion chamber.
  • common can also have the meaning of one of the following terms: combined, joint or corporate.
  • the pre-chamber of the combustion apparatus Due to the common first wall and common second wall of the pre-chamber and the combustion chamber coolant introduced through the first opening into the cavity can also be supplied to the pre-chamber. Therefore, the pre-chamber of the combustion apparatus is also cooled.
  • the at least one first opening can be located in the area of the combustion chamber. Therefore, all coolant, in particular air, can come from the first opening.
  • the first wall can exhibit at least one second opening which is adapted for introducing the coolant into the cavity, as well, wherein the at least one second opening is located in the area of the pre-chamber.
  • the second opening in the first wall can be realized by a softwall or by at least one dilution hole or by a perforation of the first wall. Due to the provision of the at least one second opening in the first wall in the area of the pre-chamber an additional cooling of the pre-chamber can be provided.
  • the holes in the first wall have a larger diameter and are spaced at a greater distance than the holes in the second wall.
  • the second wall can exhibit at least one third opening adapted for outputting the coolant from the cavity to the combustion chamber and/or the pre-chamber.
  • an optimized cooling of the second wall can be realized by the realization of a cooling film next to the second wall. If more than one third opening is provided in the second wall then these openings can be located in the area of the pre-chamber and/or the area of the combustion chamber.
  • a first device can be provided for mixing a fuel with an oxidant, wherein the first device is located upstream of the pre-chamber.
  • the first device can be arranged in such a way that the coolant can be introduced from the cavity into the first device, wherein the first device is adapted for receiving the coolant from the cavity.
  • the coolant By introducing the coolant into the first device the coolant is supplied to the pre-chamber and to the combustion chamber by the first device. Therefore, an effective cooling of the pre-chamber and the combustion chamber can be achieved. More particularly, en effective cooling of the inner face of the second wall along the pre-chamber and the combustion chamber is achieved.
  • a second device can be provided between the first device and the cavity, wherein the second device is adapted for outputting the coolant to the first device and/or the pre-chamber.
  • the second device can also be located in the cavity, the second device being adapted for outputting the coolant to the first device and/or the pre-chamber.
  • the coolant through the second device By introducing the coolant through the second device into the first device an optimized provision of the coolant to the first device can be realized.
  • This coolant then is supplied to the pre-chamber and to the combustion chamber by the first device cooling the pre-chamber and the combustion chamber.
  • the second device outputs the coolant directly into the pre-chamber.
  • an optimized cooling of the pre-chamber can be realized. More particularly, en effective cooling of the inner face of the second wall along the pre-chamber and the combustion chamber is achieved.
  • the output of the coolant through the second device is so chosen that it matches the flow induced from the first device. This avoids any potential shear layers which may result in flash backs.
  • the second device can output the coolant radially or axially into the pre-chamber or can output the coolant axially into the first device.
  • the term radially means the direction towards a center axis of the combustion apparatus and the term axially means a direction parallel to the center axis of the combustion apparatus.
  • the second device therefore can be adapted to create a film that directs the flow along the pre-chamber wall. This coolant film is also realized by coolant outputted by third openings in the second wall.
  • the second device can comprise a swirler, in particular a radial swirler or an axial swirler.
  • the first device and the second device can be formed integrally, i.e. in one piece.
  • the combined device can be realized in a compact form. Moreover, the production of an integrally formed first and second device eases the production and the matching of the flows from the first device and the second device can be easily achieved.
  • the first device can comprise a swirler. If the coolant, in particular air, is been exiting into the main swirler then an axial type swirler can be used, if the coolant, in particular air, is been exiting into the prechamber a radial type swirler can be used.
  • the swirler creates a swirling mix of the fuel and the oxidant, which travels along the pre-chamber to the combustion chamber.
  • the swirler can be a radial swirler, i.e. the oxidant and/or the fuel/oxidant mix is outputted in a radial direction into the pre-chamber.
  • the present invention is not limited to a first device comprising a radial swirler.
  • the first device can also comprise an axial swirler outputting the oxidant and/or the fuel/oxidant mix in an axial direction into the pre-chamber.
  • the coolant can be an oxidant, in particular air.
  • the present invention discloses a gas turbine engine, which comprises at least one of the above described combustion apparatuses.
  • Figure 1 of the present invention shows a schematic cross-sectional side view of a combustion apparatus according to the prior art.
  • the combustion apparatus shown in Figure 1 comprises a combustion chamber 12, a pre-chamber 14 located upstream of the combustion chamber 12, a first device 10 for mixing a fuel with an oxidant, wherein the first device 10 is located upstream of the pre-chamber 14.
  • the combustion apparatus according to the prior art also comprises a back plate 50 and an outer casing.
  • the combustion chamber 12 exhibits a first wall 20 and a second wall 30, wherein the first wall 20 is spaced to the second wall 30. Therefore, the first wall 20 and the second wall 30 build a cavity 40.
  • the first wall 20 exhibits a first opening for introducing a coolant into the cavity 40.
  • the second wall 30 exhibits at least one opening 21 for outputting the coolant from the cavity 40 into the combustion chamber 12. Thereby, a cooling of the combustion chamber 12 is achieved.
  • An oxidant such as e.g. air
  • the flow direction of the oxidant is indicated by dotted arrows shown in the upper part of Figure 1 .
  • the first device 10 is adapted for mixing a fuel, which can be supplied by fuel galleries through the back plate 50, with the oxidant supplied by the not shown compressor.
  • the first device 10 outputs the oxidant or the fuel/oxidant mix into the pre-chamber 14.
  • the combustion apparatus exhibits a cylindrical geometry so that the first device 10 outputs the oxidant or the fuel/oxidant mix towards the center axis of the combustion apparatus and the first device 10 respectively.
  • a central recirculation is generated in the pre-chamber 14.
  • the flow structure having a central recirculation extends from the pre-chamber 14 into the combustion chamber 12.
  • the flow structure having the central recirculation is indicated by the dotted arrows extending from the pre-chamber 14 into the combustion chamber 12.
  • the recirculation is an aerodynamic feature of highly swirling flow.
  • the recirculating flow is generally hot combustion products and it is this which heats the prechamber and incoming fluids.
  • the not combusted oxidant and/or fuel/oxidant mix interacts with the wall of the pre-chamber 14 and therefore heats the pre-chamber 14.
  • FIG. 2 of the present invention shows a schematic cross-sectional side view of a combustion apparatus 100 according to the present invention.
  • the combustion apparatus 100 shown in Figure 2 comprises a combustion chamber 12 in which combustion of a fuel/oxidant mix takes place, and a pre-chamber 14 located upstream of the combustion chamber 12.
  • the combustion chamber 12 and the pre-chamber 14 comprise a common first wall 20 and a common second wall 30, wherein the first wall 20 and the second wall 30 are spaced to each other, so that they build a cavity 40.
  • the cavity 40 therefore extends from the combustion chamber 12 to the pre-chamber 14.
  • the first wall 20 of the combustion apparatus 100 exhibits at least one first opening 21 which is adapted for introducing a coolant into the cavity 40.
  • the common first wall 20 of the combustion chamber 12 and the pre-chamber 14 is the outer skin or the outer wall of the combustion chamber 12 and the pre-chamber 14.
  • the common second wall 30 of the combustion chamber 12 and the pre-chamber 14 is the inner skin of the combustion chamber 12 and the pre-chamber 14 facing the center of the combustion apparatus 100 and therefore facing the center of the combustion chamber 12 and the pre-chamber 14.
  • the at least one first opening 21 in the first wall 20 can e.g. be realized by a softwall, a dilution hole or simply by a perforation of the first wall.
  • the position of the first opening 21 in the first wall 20 is completely variable.
  • the first opening 21 in the first wall 20 can be located in the area of the combustion chamber 12, as shown in Figure 2 . Nevertheless, the present invention is not limited to this arrangement.
  • the first opening 21 of the first wall 20 can also be located in the area of the pre-chamber 14.
  • the at least one first opening 21 in the first wall 20 is located in the area of the combustion chamber 12. But this is not a limitation of the present invention.
  • the at least one first opening 21 can of course also be a plurality of first openings 21, which can be arranged in the first wall 20. This arrangement of the plurality of first openings 21 in the first wall 20 can be adapted by the person skilled in the art as required.
  • the first wall 20 additionally exhibits at least one second opening 22.
  • the at least one second opening 22 is also adapted for introducing the coolant into the cavity 40.
  • the at least one second opening 22 is located in the area of the pre-chamber 40. Nevertheless, the present invention is not limited to this arrangement.
  • the at least one second opening 22 in the first wall 20 can also be located in another area of the double skin arrangement of the combustion chamber 12 and the pre-chamber 14.
  • coolant introduced through the second opening 22 is directly coupled into the cavity 40 in the area of the pre-chamber 14. Therefore, a more effective cooling of the pre-chamber 14 is realized.
  • the at least one second opening 22 in the first wall 20 can be realized e.g. by a softwall or by at least one dilution hole or simply by a perforation of the common first wall 20 of the combustion chamber 12 and the pre-chamber 14.
  • the common second wall 30 of the combustion chamber 12 and the pre-chamber 14 exhibits at least one third opening 31.
  • This at least one third opening 31 is adapted for outputting the coolant from the cavity 40 to the combustion chamber 12 and/or the pre-chamber 14.
  • This at least one third opening 31 in the common second wall 30 of the combustion chamber 12 and the pre-chamber 14 can also be a plurality of third openings 31.
  • Figure 2 of the present invention it is shown that the at least one third opening 31 in the second wall 30 is positioned in the area of the combustion chamber 12. Nevertheless, the present invention is not limited to this arrangement.
  • the at least one third opening 31 can also be located in other areas of the second wall 30, which apply usefull for the person skilled in the art for an optimized cooling of the combustion chamber 12 and/or the pre-chamber 14.
  • Coolant which is outputted by the at least one third opening 31 into the combustion chamber 12 and/or the pre-chamber 14 can build a cooling film next to the common second wall 30 of the combustion chamber 12 and the pre-chamber 14. Therefore, an optimized cooling of the combustion chamber 12 and the pre-chamber 14 can be realized.
  • the at least one third opening 31 can be realized e.g. by a softwall or by at least one dilution hall or simply by a perforation of the second wall 30.
  • the combustion apparatus 100 comprises a first device 10, which is adapted for mixing a fuel with an oxidant.
  • the first device 10 is located upstream of the pre-chamber 14.
  • Oxidant which is supplied by a not shown compressor is supplied to the first device 10.
  • the flow direction of the oxidant is indicated by dotted arrows in the upper left part of Figure 2 .
  • the oxidant is outputted by the first device into a radial direction towards the center axis of the first device 10 and the combustion apparatus 100, respectively. It is possible that fuel is injected into the pre-chamber 14 by injection holes where the injected fuel is mixed with the oxidant supplied by the first device 10. Nevertheless, the present invention is not limited to this arrangement.
  • fuel is inserted into the first device 10 by e. g. fuel galleries or fuel injection holes so that mixing of the oxidant and the inserted fuel is already conducted in the first device 10. This fuel/oxidant mix is then outputted by the first device into the pre-chamber 14.
  • a second device 16 is located between the first device 10 and the cavity 40 the present invention is not limited to this arrangement. It is also possible that the second device 16 is omitted.
  • coolant introduced into the cavity 40 is directed towards the first device 10.
  • the first device 10 is adapted for receiving the coolant from the cavity 40. This coolant then is outputted to the pre-chamber 14 where it is spread also into the direction of the combustion chamber 12. Therefore, an optimized cooling of the pre-chamber 14 and the combustion chamber 12 and also of the combustion flame itself can be realized.
  • a second device 16 is located between the first device 10 and the cavity 40.
  • the second device 16 is adapted for outputting the coolant introduced into the cavity 40 to the first device 10 and/or the pre-chamber 14.
  • the second device 16 can output the coolant radially or axially. That is, the second device 16 can output the coolant parallel to the center axis of the combustion apparatus 100 or radially towards the center axis of the combustion apparatus 100.
  • the second device 16 can comprise a swirler.
  • This swirler may either be a radial swirler or an axial swirler.
  • the first device 10 can also comprise a swirler, which also may either be a radial swirler or an axial swirler.
  • the axial swirler 10 has to be introduced into the pre-chamber 14.
  • the first device 10 and the second device 16 are integrally formed.
  • a wall for a pre-chamber and a main combustion chamber, a wall is meant that continues along both chamber sections, the pre-chamber and the main combustion chamber.
  • the common wall may be a single sheet of metal pressed into the wanted form such that a pre-chamber and a main combustion chamber is built.
  • the first common wall and the second common wall may have separators between each other but otherwise should not be joined such that the cavity between the two walls would be blocked. Over the whole length of the walls, the cavity should have a width to let pass cooling fluid without major interruptions. Specifically no larger areas of the two walls should touch or should be bonded to each other to form a blockage for the cooling fluid.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Gas Burners (AREA)
EP10168429A 2010-07-05 2010-07-05 Appareil de combustion et moteur de turbine à gaz Withdrawn EP2405200A1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP10168429A EP2405200A1 (fr) 2010-07-05 2010-07-05 Appareil de combustion et moteur de turbine à gaz
RU2013104536/06A RU2013104536A (ru) 2010-07-05 2011-06-22 Сжигающее устройство и газотурбинный двигатель
EP11728817A EP2553341A1 (fr) 2010-07-05 2011-06-22 Appareil de combustion et moteur à turbine à gaz
CN201180033349XA CN102959333A (zh) 2010-07-05 2011-06-22 燃烧设备和燃气涡轮发动机
PCT/EP2011/060492 WO2012004131A1 (fr) 2010-07-05 2011-06-22 Appareil de combustion et moteur à turbine à gaz
US13/808,104 US20140144143A1 (en) 2010-07-05 2011-06-22 Combustion apparatus and gas turbine engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP10168429A EP2405200A1 (fr) 2010-07-05 2010-07-05 Appareil de combustion et moteur de turbine à gaz

Publications (1)

Publication Number Publication Date
EP2405200A1 true EP2405200A1 (fr) 2012-01-11

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Family Applications (2)

Application Number Title Priority Date Filing Date
EP10168429A Withdrawn EP2405200A1 (fr) 2010-07-05 2010-07-05 Appareil de combustion et moteur de turbine à gaz
EP11728817A Withdrawn EP2553341A1 (fr) 2010-07-05 2011-06-22 Appareil de combustion et moteur à turbine à gaz

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP11728817A Withdrawn EP2553341A1 (fr) 2010-07-05 2011-06-22 Appareil de combustion et moteur à turbine à gaz

Country Status (5)

Country Link
US (1) US20140144143A1 (fr)
EP (2) EP2405200A1 (fr)
CN (1) CN102959333A (fr)
RU (1) RU2013104536A (fr)
WO (1) WO2012004131A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3159609A1 (fr) * 2015-10-21 2017-04-26 Siemens Aktiengesellschaft Chambre de combustion pour turbine à gaz

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2504348A (en) * 2012-07-26 2014-01-29 Bharat Mohan Daswani A cover for a drinking glass
EP2837887B1 (fr) * 2013-08-15 2019-06-12 Ansaldo Energia Switzerland AG Chambre de combustion d'une turbine à gaz avec refroidissement de doublure optimisée de chute de pression
ES2870975T3 (es) * 2016-01-15 2021-10-28 Siemens Energy Global Gmbh & Co Kg Cámara de combustión para una turbina de gas
ITUA20163988A1 (it) * 2016-05-31 2017-12-01 Nuovo Pignone Tecnologie Srl Ugello carburante per una turbina a gas con swirler radiale e swirler assiale e turbina a gas / fuel nozzle for a gas turbine with radial swirler and axial swirler and gas turbine
CN107101224B (zh) * 2017-05-23 2023-01-10 新奥能源动力科技（上海）有限公司 一种单管燃烧室和燃气轮机

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EP0896193A2 (fr) * 1997-08-05 1999-02-10 European Gas Turbines Limited Chambre de combustion pour turbine à gaz
WO2001059369A1 (fr) * 2000-02-14 2001-08-16 Ulstein Turbine As Dispositif contenu dans un bruleur destine a des turbines a gaz
WO2008028621A1 (fr) * 2006-09-07 2008-03-13 Man Turbo Ag Chambre de combustion de turbine à gaz
US20090120094A1 (en) * 2007-11-13 2009-05-14 Eric Roy Norster Impingement cooled can combustor

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EP0725253A2 (fr) * 1995-02-01 1996-08-07 Mitsubishi Jukogyo Kabushiki Kaisha Chambre de combustion pour turbine à gaz
EP0896193A2 (fr) * 1997-08-05 1999-02-10 European Gas Turbines Limited Chambre de combustion pour turbine à gaz
WO2001059369A1 (fr) * 2000-02-14 2001-08-16 Ulstein Turbine As Dispositif contenu dans un bruleur destine a des turbines a gaz
WO2008028621A1 (fr) * 2006-09-07 2008-03-13 Man Turbo Ag Chambre de combustion de turbine à gaz
US20090120094A1 (en) * 2007-11-13 2009-05-14 Eric Roy Norster Impingement cooled can combustor

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3159609A1 (fr) * 2015-10-21 2017-04-26 Siemens Aktiengesellschaft Chambre de combustion pour turbine à gaz
WO2017067775A1 (fr) * 2015-10-21 2017-04-27 Siemens Aktiengesellschaft Chambre de combustion pour turbine à gaz

Also Published As

Publication number Publication date
RU2013104536A (ru) 2014-08-10
CN102959333A (zh) 2013-03-06
WO2012004131A1 (fr) 2012-01-12
US20140144143A1 (en) 2014-05-29
EP2553341A1 (fr) 2013-02-06

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