EP3910238A1 - Cône pilote - Google Patents

Cône pilote Download PDF

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Publication number
EP3910238A1
EP3910238A1 EP20174892.8A EP20174892A EP3910238A1 EP 3910238 A1 EP3910238 A1 EP 3910238A1 EP 20174892 A EP20174892 A EP 20174892A EP 3910238 A1 EP3910238 A1 EP 3910238A1
Authority
EP
European Patent Office
Prior art keywords
cooling air
pilot
burner
pilot cone
air passages
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Withdrawn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
EP20174892.8A
Other languages
German (de)
English (en)
Inventor
Christian Beck
Jürgen MEISL
Stefan Reich
Sabrina Isolde Siebelist
Christopher Grandt
Benjamin WITZEL
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 EP20174892.8A priority Critical patent/EP3910238A1/fr
Priority to EP21711744.9A priority patent/EP4121696A1/fr
Priority to US17/923,588 priority patent/US11971171B2/en
Priority to CN202180035346.3A priority patent/CN115605712A/zh
Priority to PCT/EP2021/054508 priority patent/WO2021228447A1/fr
Publication of EP3910238A1 publication Critical patent/EP3910238A1/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Withdrawn legal-status Critical Current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
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion

Definitions

  • the invention relates to a pilot cone for use in a burner arrangement, as well as a burner arrangement.
  • the invention also relates to a method for cooling a pilot cone of a burner arrangement.
  • Providing a central pilot burner with a cone for flame design is a widely used measure.
  • a pilot cone is cooled.
  • cooling air is guided on the rear side of the pilot cone or in cooling channels within the pilot cone. It is common here for the cooling air to be directed into the combustion chamber downstream of the pilot cone. This is to be regarded as unfavorable in terms of reducing NO x emissions.
  • closed cooling with reuse of the cooling air in the pilot burner is necessary.
  • the pilot cone With closed cooling, the pilot cone is usually cooled by an integrated design with air, which is used as combustion air after the cooling task has been completed. For this purpose, it is known to provide the pilot cone with large-volume cooling channels which finally lead the cooling air as combustion air to the pilot burner.
  • the object of the invention is to provide a pilot cone in which cooling air and scavenging air consumption are as small as possible and which is at the same time as simple and inexpensive to manufacture as possible.
  • Another object of the invention is to provide a burner arrangement with a pilot cone.
  • the generic pilot cone is intended for use in a burner arrangement.
  • the pilot cone has a conically shaped jacket which widens downstream along a burner axis. It is provided that a plurality of cooling air passages are arranged in the jacket, by means of which cooling of the jacket is made possible.
  • the pilot cone also has an inner wall which extends upstream from the upstream end of the shell. It is provided that an annular gap is arranged along the inner jacket on the radially outer side, through which a cooling air can be supplied. On the jacket adjacent to the annular gap, a plurality of cooling air openings are required, which establish a connection from the annular gap to the cooling air passages. In this way, during operation of the burner arrangement, cooling air can be guided outside the inner wall through the annular gap and through the cooling air openings and through the cooling air passages, thus cooling the jacket.
  • the invention provides that an outer wall is arranged spaced from the inner wall on the radially outer side. This limits the annular gap on the radially outer side and also extends upstream from the jacket. This opens up targeted cooling air guidance to the cooling air openings.
  • annular gap is formed on the pilot cone by two preferably coaxial, radially inner and radially outer walls arranged on the jacket and extending upstream in the circumferential direction, over which the air supplied to the pilot cone for cooling is distributed according to its use.
  • cooling air is supplied through the annular gap than the jacket needs.
  • the compensation and thus the optimal setting of the cooling air flow in the cooling air passages is made possible by providing the inner wall with a plurality of openings. This leads to a division of the air flow supplied through the annular gap, on the one hand, to a flow through the openings and, on the other hand, to a cooling air flow through the cooling air openings into the cooling air passages of the jacket.
  • pilot cone By utilizing the design options that additive manufacturing allows, it is possible to manufacture a pilot cone with integrated cooling.
  • the pilot cone is therefore a compact component that can be easily integrated into an existing burner and that enables a long service life.
  • the complexity of the cooling air routing is completely hidden inside the pilot cone and can advantageously be produced using additive manufacturing methods.
  • the cooling air throughput is limited to the air throughput required for cooling, so that more air is available for premixing with the fuel.
  • the sum of the cross-sectional areas of all openings is greater than the sum of the cross-sectional areas of all cooling air openings on the jacket of the pilot cone.
  • cooling air flow supplied to the jacket can be adjusted by appropriately dimensioning the cooling air openings. It is necessary that the sum of the cross-sections of the cooling air openings is smaller than the sum of the cross-sections of the cooling air passages, which flow parallel to each other.
  • opening cross sections of the respective cooling air openings are smaller than the cross sections of the respective cooling air passages.
  • the openings which, as it were, represent the inlet openings into the cooling air duct in the pilot cone, are the smallest passages in the system and can intercept particles that could block subsequent cooling channels. They are viewed as an integrated filter device.
  • the number of cooling air openings exceeds the number of cooling air passages running in parallel in terms of flow. This enables the cross section of the individual cooling air openings to be selected to be small in relation to the cross section of the cooling air passages, thus preventing the cooling air passage from being clogged by particles.
  • annular distributor is arranged in the jacket of the pilot cone, into which the cooling air openings arranged in the circumferential direction open in order to distribute the cooling air evenly over the circumference of the pilot cone. This ensures that even if individual cooling air openings are blocked, a more or less uniform distribution of the cooling air flow over the cooling air passages can be guaranteed. It is provided that cooling air passages branch off from the distributor.
  • the arrangement of the pilot cone in the burner arrangement is advantageously made possible if the pilot cone has a centering collar for receiving a pilot burner. It is provided that the centering collar is upstream of the jacket is arranged radially inward of the inner wall. In a particularly advantageous manner, the centering collar forms a cylindrical fitting surface.
  • annular groove is arranged between the centering collar and the jacket. This is obviously designed to be open towards the burner axis.
  • sealing air outlets in the annular groove.
  • the sealing air outlets here form the end of the cooling air passages, so that the cooling air fed through the cooling air openings flows out through the sealing air outlets.
  • these are advantageously distributed equidistantly over the circumference, so that there is a uniform supply of sealing air in the area of the interface between the pilot cone and the pilot burner.
  • the blocking air outlets are aligned at an incline.
  • a swirling pilot burner flow can be taken into account and, on the other hand, the flow can be applied downstream of the annular groove along the surface of the jacket, or a detachment of the flow is avoided.
  • An advantageous cooling air duct in the jacket is achieved if downstream first cooling air passages and circumferentially offset upstream second cooling air passages are used, the first cooling air passages being connected to the second cooling air passages via the first transverse passages at the downstream end of the jacket. It is provided that the cooling air is supplied from the cooling air openings to the first cooling air passages, the cooling air flowing back to the upstream end of the jacket after being deflected at the first transverse passages through the second cooling air passages.
  • the transverse passages extend in the circumferential direction.
  • the first cooling air passages begin at the distributor.
  • a first transverse passage connects at least two first cooling air passages and at least two second cooling air passages with one another. If at least two first cooling air passages open into a first transverse passage and at least two second cooling air passages branch off from the first transverse passage, there are two advantages. On the one hand, the temperature can be distributed more evenly over the circumference of the pilot cone. On the other hand, if a cooling air passage is blocked, an entire path does not immediately fail, but rather only the flow in one direction along an individual cooling air passage is disturbed or interrupted, while cooling air can continue to flow in the neighboring area.
  • two second cooling air passages are advantageously arranged adjacent to one another between two first cooling air passages.
  • first cooling air passages which are not connected to one another via a first transverse passage, are connected to one another via second transverse passages.
  • first cooling air passages are adjacent in the connection via the first transverse passage are arranged to each other between two second cooling air passages.
  • the second transverse passage is arranged in the direction of the combustion chamber axis, offset upstream from the first transverse passage. A flow in the second transverse passages is therefore only relevant in cases when there is a restriction in the flow through the connected cooling air passages.
  • the first and second cooling air passages are round in cross section. With rectangular cooling air passages, larger duct cross-sections can be realized, but round cooling air passages are more advantageous with regard to material stresses and service life.
  • the inner surface of the jacket of the pilot cone i.e. the surface on the combustion chamber side
  • a thermal insulation layer as is generally the case.
  • the additive manufacturing method enables the simple addition of additional features. It can therefore be expedient if at least three protruding prongs are arranged on the outside of the pilot cone as a safety catch. This safety catch keeps the pilot cone in the main burner in the unlikely event of an unintentional loosening of the pilot cone.
  • the inner wall surrounds the pilot burner in sections as intended.
  • the inner wall is designed in such a way that it expands upstream from the jacket. This creates a larger installation space for the pilot burner.
  • the annular gap also inevitably widens upstream, starting from the jacket of the pilot cone.
  • this has a shape that widens accordingly upstream.
  • a novel pilot cone enables the implementation of a new burner arrangement according to the invention.
  • This generic first of all comprises a centrally arranged pilot burner extending along a burner axis.
  • a pilot cone is arranged at the downstream end of the pilot burner.
  • the burner arrangement comprises a main burner which comprises a central opening. Inside there is a pilot burner with the pilot cone.
  • the pilot cone here has a shape as described above.
  • a contact point between the pilot burner and the pilot cone is advantageously designed as a sliding seat.
  • a sliding fit is understood here to mean a fit that can be easily joined and furthermore allows different thermal expansions in the direction of the burner axis.
  • the design of the contact point allows leakage with a slight flow of cooling air. This prevents a fixed connection between the pilot cone and the pilot burner at the contact point due to excessive thermal loads and / or deposits, which prevents relative displacement, in particular due to different thermal expansions, and can lead to thermal stresses.
  • the existing sealing air outlets in the pilot cone are directed towards an end section of the pilot burner immediately downstream of the contact point. This enables optimal protection of the contact point.
  • the cooling air of the pilot cone is thus used again after the pilot cone has been cooled for flushing at the contact point between the pilot burner and the pilot cone. Otherwise air would have to be fed separately to this area.
  • annular groove in the pilot cone is partially covered by an end section of the pilot burner. This enables the contact point, in particular the sliding seat, to be in a protected position between the pilot cone and the pilot burner. On the other hand, this creates an annular cavity that promotes further cooling air flow. The supplied cooling air then emerges from a sealing air gap between the upstream end of the jacket of the pilot cone and the end section of the pilot burner.
  • pilot cone is fastened to a pilot cone carrier.
  • connection is particularly preferably made to the upstream end of the inner wall.
  • the inner wall can, for example, merge seamlessly into the pilot cone carrier.
  • pilot cone carrier also enables the cooling air to be guided.
  • a cooling air supply runs radially outside of the pilot cone carrier and merges into the annular gap.
  • the pilot cone carrier is formed in a simple and advantageous manner in the form of a cylinder.
  • a main burner carrier is advantageously arranged radially outside the pilot cone carrier. If there is a cooling air supply radially outside of the pilot cone carrier limits the cooling air supply on the radially outer side of the main burner carrier.
  • the outer wall is mounted on the main burner support at its upstream end. It can be provided that a fixed connection / assembly takes place or a sliding seat is provided which allows different thermal expansion.
  • annular chamber is advantageously arranged on the side of the inner wall facing the burner axis, which is fluidically connected to a pilot burner inlet.
  • the amount of air supplied for cooling the pilot cone can thus be divided into a part necessary for cooling the pilot cone with a flow through the cooling air openings and an excess part with a flow through the openings, which is fed to the pilot burner for combustion.
  • the object directed to a method is achieved by a method for cooling a pilot cone of a burner arrangement with a pilot burner, wherein the pilot cone comprises a jacket that widens downstream and is arranged immediately downstream of the pilot burner and is fluidically connected to it, in which cooling air is guided inside the jacket and the cooling air leaving the jacket flushes an interface between the pilot burner and the pilot cone.
  • Cooling air is advantageously supplied in the jacket of the pilot cone via a first cooling air passage and is returned via a second cooling air passage adjacent to the first cooling air passage.
  • First and second cooling air passages are connected to one another in the vicinity of the downstream end of the pilot burner via comparatively short first transverse passages.
  • the cooling air is guided on the shortest path from the annular distributor at the upstream end to the vicinity of the downstream end of the pilot cone and from returned there by the shortest route. This results in an efficient and as uniform as possible cooling or temperature distribution in the pilot cone.
  • cooling air is returned via a second cooling air passage adjacent to the blocked second cooling air passage.
  • the main advantages of the invention are, in particular, a compact pilot cone without expansion hindrance with a uniform component temperature and the resulting long component service life.
  • closed air cooling of the pilot cone can be implemented with flushing of the interface between the pilot cone and the pilot burner, in which the cooling air already used to cool the jacket of the pilot cone is used again. It is also particularly advantageous here that the cooling air exiting at the contact point between the pilot cone and the pilot burner can also be used as combustion air.
  • Another advantage is the improved insensitivity to a blockage of cooling air openings or individual cooling air passages and an undiminished guarantee of an advantageous cooling of the jacket of the pilot cone.
  • the complex internal channel structure is favorably favored by the use of additive manufacturing.
  • the component can therefore be constructed very efficiently in terms of cooling performance and cooling air balance.
  • Another advantage of additive manufacturing is the very short production times.
  • a pilot cone 01 according to the invention is shown in a perspective view in longitudinal section.
  • the pilot cone 01 has a jacket 04 widening downstream in a main flow direction of fuel and air.
  • the information upstream always refers to the side opposite to a combustion chamber following the pilot cone, while downstream always refers to the side facing the combustion chamber.
  • An inner surface 16 of the jacket 04 of the pilot cone 01 is provided with a thermal insulation layer 17.
  • a cooling air duct 05 runs inside the jacket 04 (not visible in this view).
  • an inner wall 07 extends upstream, which 07 also expands in the process.
  • the outer wall 08 is located on the radially outer side.
  • an annular gap 06 is formed between the inner wall 07 and the outer wall 08, which is used to guide the cooling air.
  • a section of a burner arrangement with the pilot cone 01 and a pilot burner 03 arranged therein is sketched.
  • the inner wall 07 has a plurality of perforations 09 distributed around the circumference, which establish a connection between the annular gap 06 and the annular chamber 26 09.
  • the cooling air duct from the annular gap 06 into the jacket 04 of the pilot cone 01 is off Fig. 6 can be seen and is explained in more detail below.
  • a centering collar 17 can also be seen at the upstream end of the jacket 04, in which 17 the pilot burner 03 is mounted in a contact point 23 with a sliding seat.
  • the contact point 23 allows a relative displacement of the pilot burner 03 relative to the pilot cone 01 and thus prevents thermal stresses.
  • the contact point 23 between the pilot burner 03 and the pilot cone 01 as sliding seats allows the cooling air to leak from the Annular chamber 26 and thus counteracts the two components 01, 03 from sticking to one another in the contact point 23.
  • An annular groove 30 is located between the contact point 23 and the jacket 04 of the pilot cone. This is covered in sections on the radially inner side by an end section of the pilot burner 03. This forms a circumferential cavity 29.
  • a sealing air gap 28 is located between the end section of the pilot burner 03 and the upstream end of the jacket 04 of the pilot cone 01.
  • the Fig. 3 shows schematically and by way of example a section of a burner arrangement 02 with a central burner axis 21, comprising a main burner 19 and a pilot burner 03 arranged in the main burner 19.
  • the pilot cone 01 is arranged directly downstream of the pilot burner 03.
  • the main burner 19 is supported on the radially inner side via a main burner support 22.
  • a main burner support 22 it is provided in this exemplary embodiment that the outer wall 08 of the pilot cone 01 is supported at its 08 upstream end in the main burner support 22 and thus centering takes place.
  • a pilot cone carrier 25 is located in relation to the main burner carrier 22 on the side facing the burner axis 21.
  • the inner wall 07 of the pilot cone 01 adjoins the end of the pilot cone carrier 25.
  • a plurality of protruding prongs 18 are distributed around the circumference in this exemplary embodiment and are arranged on the outside. These prevent a displacement out of the main burner 19 when the pilot cone 01 is released.
  • the main burner support 22 and the pilot cone support 25 are designed to be cylindrical in this exemplary embodiment and are arranged coaxially to one another and effect a fluidic separation. This is between the main burner support 22 and the pilot cone carrier 25 a cooling air supply 24 is formed. The cooling air flowing through the cooling air supply 24 also causes the main burner support 22 to be cooled.
  • the cooling air supply 24 is optimized in order to generate the flow velocity necessary for the heat transfer with a low pressure loss at the same time.
  • the high pressure gradient between the cooling air inlet and outlet of the pilot cone 1 enables efficient cooling with a comparatively low air mass flow.
  • the outer cooling air supply 24 opens into the annular gap 06 of the pilot cone 01, which 06 is formed by the two upstream inclined coaxial, radially inner and radially outer walls 07, 08 arranged on the jacket 04 and extending in the circumferential direction.
  • the radially inner wall 07 is connected to the pilot cone carrier 25 and the radially outer wall 08 is connected to the main burner carrier 22, so that a closed cooling air duct to the pilot cone 01 is formed between the main burner 19 and the pilot burner 03.
  • the cooling air flows proportionally through the openings 09 in the inner wall 07 into the annular chamber 26 and then to the main flow path of the combustion air supplied to the pilot burner to a pilot burner inlet 27.
  • the cooling air duct 05 in the jacket 04 of the pilot cone 01 is based on the Figures 4 to 9 explained in more detail - see in particular Fig. 7 .
  • the cooling air duct 05 has a pattern that is repeated in its circumference, so that the Figures 4 to 6 , 8 and 9 obviously the structure in the jacket 04 of the pilot cone 01 opens up.
  • a plurality of cooling air openings 10 are distributed around the circumference near the upstream end of the jacket 04 - see Fig. 5 and 6th , which establish a connection from the annular gap 06 to the cooling air passages 12, 14 in the jacket 04.
  • An annular distributor 11 is located in the jacket 04 of the pilot cone 01 arranged, in the 11, the circumferential cooling air openings 10 open. When the burner arrangement 02 is in operation, the air for cooling the pilot cone 01 thus initially flows through a multiplicity of cooling air openings 10, which are arranged distributed in the circumferential direction, into the aforementioned annular distributor 11.
  • First cooling air passages 12 branch off from the distributor 11 and extend essentially downstream within the jacket 04 - see FIG Fig. 5 and Fig. 8 .
  • the first cooling air passages 12 each open into first transverse passages 13 which extend in the circumferential direction - see FIG Fig. 9 . From the first transverse passages 13, in turn, upstream second cooling air passages 14 branch off - see FIG Fig. 4 . In this embodiment it is provided that two adjacent first cooling air passages 12 open into a first transverse passage 13 and two second cooling air passages 14 branch off from the first transverse passage 13.
  • the first and second cooling air passages 12, 14 are round in cross section as an advantageous and simplest embodiment.
  • the air thus flows through the first cooling air passages 12 to the front edge of the pilot cone 01 and there flows via first transverse passages 13 to respectively adjacent second cooling air passages 14, which are provided for returning the air to the interface with the pilot burner 03.
  • the first and second cooling air passages 12, 14, that is, the supply and return channels, are arranged alternately and adjacent second cooling air passages 14 are connected by second transverse passages 15 in order to allow, in the unlikely event of a blocked cooling passage, an albeit reduced cooling air flow through unblocked sections .
  • This emergency cooling property is intended to counteract further damage to the pilot cone 01 after damage with blocked cooling passages 12, 14, so that more or less uniform cooling can be ensured even if an individual cooling air passage 12, 14 is blocked.
  • the cross-sections of the cooling air openings 10 are selected to be smaller than the cross-sections of the first and second cooling air passages 12, 14 or the first and second transverse passages 13, 15, so that a filter function results at the entrance to the cooling air duct 05.
  • the second cooling air passages 14 open into the annular groove 30 or into the circumferential cavity 29 at the contact point 23 of the pilot cone 01 with the pilot burner 03 - see Fig. 4 (even Fig. 2 ). That is to say, after flowing through the pilot cone 01, the cooling air enters a circumferential cavity 29 which blocks the interface between the pilot cone 01 and the pilot burner 03 against the penetration of hot gas. The cooling air then mixes with the pilot burner flow.
  • the passages of the second cooling air passages 14 near the exit are arranged equidistantly over the circumference in the annular groove 30 and are oriented in such a way that, when the burner arrangement 02 is in operation, they are inclined in the direction of a swirling pilot burner flow, so that the flow is present downstream of the annular groove 30 to effect the jacket 04, or to avoid detachment. As a side effect of the overlap, the sealing air outlets 32 are protected.
  • the cooling is viewed as closed or cooling air-neutral. Due to the high pressure gradient between the cooling air inlet and outlet, a high cooling effect is achieved with a low cooling air mass flow.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
EP20174892.8A 2020-05-15 2020-05-15 Cône pilote Withdrawn EP3910238A1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP20174892.8A EP3910238A1 (fr) 2020-05-15 2020-05-15 Cône pilote
EP21711744.9A EP4121696A1 (fr) 2020-05-15 2021-02-24 Refroidissement de cône de veilleuse
US17/923,588 US11971171B2 (en) 2020-05-15 2021-02-24 Pilot cone cooling
CN202180035346.3A CN115605712A (zh) 2020-05-15 2021-02-24 先导锥冷却
PCT/EP2021/054508 WO2021228447A1 (fr) 2020-05-15 2021-02-24 Refroidissement de cône de veilleuse

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP20174892.8A EP3910238A1 (fr) 2020-05-15 2020-05-15 Cône pilote

Publications (1)

Publication Number Publication Date
EP3910238A1 true EP3910238A1 (fr) 2021-11-17

Family

ID=70738334

Family Applications (2)

Application Number Title Priority Date Filing Date
EP20174892.8A Withdrawn EP3910238A1 (fr) 2020-05-15 2020-05-15 Cône pilote
EP21711744.9A Pending EP4121696A1 (fr) 2020-05-15 2021-02-24 Refroidissement de cône de veilleuse

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP21711744.9A Pending EP4121696A1 (fr) 2020-05-15 2021-02-24 Refroidissement de cône de veilleuse

Country Status (4)

Country Link
US (1) US11971171B2 (fr)
EP (2) EP3910238A1 (fr)
CN (1) CN115605712A (fr)
WO (1) WO2021228447A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114233514A (zh) * 2021-12-01 2022-03-25 中国航发沈阳发动机研究所 一种强制对流气冷中心锥

Citations (5)

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Publication number Priority date Publication date Assignee Title
US5941076A (en) * 1996-07-25 1999-08-24 Snecma-Societe Nationale D'etude Et De Construction De Moteurs D'aviation Deflecting feeder bowl assembly for a turbojet engine combustion chamber
US20040146399A1 (en) * 2001-07-13 2004-07-29 Hans-Thomas Bolms Coolable segment for a turbomachinery and combustion turbine
US20080236165A1 (en) * 2007-01-23 2008-10-02 Snecma Dual-injector fuel injector system
US20100180601A1 (en) * 2007-09-25 2010-07-22 Mitsubishi Heavy Industries, Ltd. Cooling structure of gas turbine combustor
US20190086088A1 (en) * 2017-09-21 2019-03-21 General Electric Company Combustor mixer purge cooling structure

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Publication number Priority date Publication date Assignee Title
CA2288557C (fr) * 1998-11-12 2007-02-06 Mitsubishi Heavy Industries, Ltd. Montage de refroidissement de chambre de combustion a turbine a gaz
DE10051221A1 (de) 2000-10-16 2002-07-11 Alstom Switzerland Ltd Brenner mit gestufter Brennstoff-Eindüsung
JP4709433B2 (ja) * 2001-06-29 2011-06-22 三菱重工業株式会社 ガスタービン燃焼器
JP2004085120A (ja) 2002-08-28 2004-03-18 Mitsubishi Heavy Ind Ltd 燃焼器
JP6012407B2 (ja) 2012-10-31 2016-10-25 三菱日立パワーシステムズ株式会社 ガスタービン燃焼器及びガスタービン
US10451282B2 (en) * 2013-12-23 2019-10-22 General Electric Company Fuel nozzle structure for air assist injection
EP3002415A1 (fr) * 2014-09-30 2016-04-06 Siemens Aktiengesellschaft Composant de turbomachine, en particulier d'un composant de moteur à turbine à gaz, avec une paroi refroidie et procédé de fabrication
US9982892B2 (en) 2015-04-16 2018-05-29 General Electric Company Fuel nozzle assembly including a pilot nozzle
EP3450851B1 (fr) 2017-09-01 2021-11-10 Ansaldo Energia Switzerland AG Conduit de transition pour une chambre de combustion tubulaire de turbine à gaz et turbine à gaz comportant un tel conduit de transition
US11112117B2 (en) * 2018-07-17 2021-09-07 General Electric Company Fuel nozzle cooling structure
EP3805642A1 (fr) * 2019-10-11 2021-04-14 Siemens Aktiengesellschaft Refroidissement du cône pilote

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5941076A (en) * 1996-07-25 1999-08-24 Snecma-Societe Nationale D'etude Et De Construction De Moteurs D'aviation Deflecting feeder bowl assembly for a turbojet engine combustion chamber
US20040146399A1 (en) * 2001-07-13 2004-07-29 Hans-Thomas Bolms Coolable segment for a turbomachinery and combustion turbine
US20080236165A1 (en) * 2007-01-23 2008-10-02 Snecma Dual-injector fuel injector system
US20100180601A1 (en) * 2007-09-25 2010-07-22 Mitsubishi Heavy Industries, Ltd. Cooling structure of gas turbine combustor
US20190086088A1 (en) * 2017-09-21 2019-03-21 General Electric Company Combustor mixer purge cooling structure

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Publication number Publication date
US11971171B2 (en) 2024-04-30
US20230184437A1 (en) 2023-06-15
WO2021228447A1 (fr) 2021-11-18
CN115605712A (zh) 2023-01-13
EP4121696A1 (fr) 2023-01-25

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