US20190093896A1 - Nozzle comprising axial extension for a combustion chamber of an engine - Google Patents

Nozzle comprising axial extension for a combustion chamber of an engine Download PDF

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Publication number
US20190093896A1
US20190093896A1 US16/117,062 US201816117062A US2019093896A1 US 20190093896 A1 US20190093896 A1 US 20190093896A1 US 201816117062 A US201816117062 A US 201816117062A US 2019093896 A1 US2019093896 A1 US 2019093896A1
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US
United States
Prior art keywords
nozzle
extension
air
air channel
fuel
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.)
Abandoned
Application number
US16/117,062
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English (en)
Inventor
Carsten Clemen
Benno Wurm
Ruud EGGELS
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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 Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Assigned to ROLLS-ROYCE DEUTSCHLAND LTD & CO KG reassignment ROLLS-ROYCE DEUTSCHLAND LTD & CO KG ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: Eggels, Ruud, CLEMEN, CARSTEN, WURM, BENNO
Publication of US20190093896A1 publication Critical patent/US20190093896A1/en
Abandoned 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
    • F23R3/02—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
    • 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
    • F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details, e.g. burner cooling means, noise reduction means
    • F23D11/38—Nozzles; Cleaning devices therefor
    • 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
    • F23R2900/00012—Details of sealing 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
    • F23R3/28—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

Definitions

  • the invention relates to a nozzle for a combustion chamber of an engine for providing a fuel-air mixture at a nozzle exit opening of the nozzle.
  • An (injection) nozzle for a combustion chamber of an engine in particular for an annular chamber of a gas turbine engine, comprises a nozzle main body that has a nozzle exit opening and that, in addition to a fuel guiding channel for conveying fuel to the nozzle exit opening, has multiple (at least two) air guiding channels for conveying air intermixed with fuel to the nozzle exit opening.
  • a nozzle usually also serves for swirling the supplied air, which, intermixed which the supplied fuel, is subsequently conveyed into the combustion chamber at the nozzle exit opening of the nozzle.
  • multiple nozzles may be grouped together in a nozzle assembly group that comprises multiple nozzles arranged next to each other, usually along a circular line, for introducing fuel into the combustion chamber.
  • nozzles with multiple air guiding channels and at least one fuel guiding channel as they are known from the state of the art, for example from U.S. Pat. No. 9,423,137 B2, it is provided that a first air channel extends along a nozzle longitudinal axis of the nozzle main body and a fuel guiding channel is positioned radially further outwards than the first air channel with respect to the nozzle longitudinal axis. In that case, it is additionally provided that at least one further air channel is positioned radially further outwards than the fuel guiding channel with respect to the nozzle longitudinal axis.
  • one end of the fuel guiding channel at which the fuel form the fuel guiding channel flows out in the direction of the air from the first air guiding channel is typically located—with respect to the nozzle longitudinal axis and in the direction of the nozzle exit opening—in front of the end of the second air channel from which the air then flows out in the direction of a mixture of air from the first air channel and fuel from the fuel guiding channel.
  • What is further provided in the state of the art and for example also provided in U.S. Pat. No. 9,423,137 B2 is to provide such a nozzle with a third air channel, with its end, which may also be displaced radially outwards, following the end of the second air channel in the axial direction.
  • the nozzle is positioned at the combustion chamber via a burner seal that seals the nozzle towards the combustion space of the combustion chamber.
  • the burner seal is usually floatingly mounted at a head plate of the combustion chamber to compensate for radial and axial movements between the nozzle and the combustion chamber and to ensure a reliable sealing effect in different operating states.
  • the burner seal For guiding the fuel-air mixture provided by the nozzle, the burner seal often has a flow guiding element at the combustion space side.
  • the aerodynamic conditions vary depending on the operational state of the engine.
  • a radial distance between the nozzle and the burner seal which has to be provided due to the construction, renders it more difficult to achieve an exactly predefined guidance of the fuel-air mixture via the flow guiding element of the burner seal.
  • This objective is achieved through a nozzle of claim 1 .
  • a nozzle for a combustion chamber of an engine for providing a fuel-air mixture at a nozzle exit opening of the nozzle wherein the nozzle comprises the nozzle main body that comprises the nozzle exit opening and that extends along a nozzle longitudinal axis.
  • the nozzle main body further comprises at least the following:
  • an extension for guiding the fuel-air mixture extending in the axial direction with respect to the nozzle longitudinal axis is provided at the air guide element of the at least one further air channel.
  • the axial direction along which the extension extends is oriented towards a combustion space of the combustion chamber when the combustion chamber assembly group comprising the nozzle is arranged at a combustion chamber according to the intended use.
  • the axial extension is located inside the combustion space and extends in the flow direction of the fuel-air mixture to be provided if the nozzle is arranged at the combustion chamber according to the intended use.
  • the nozzle main body is formed with an extension for guiding the fuel-air mixture that is provided at the nozzle exit opening in the area of the air guide element of the at least one further (in the case of multiple air guiding channels of the radially outermost) air channel.
  • the axial extension is configured and provided for guiding the created mixture of the fuel from the fuel guiding channel and the air from the first, inner air channel as well as the at least one further air channel.
  • the air guide element of the at least one further air channel is configured and provided for guiding air from the at least one further air channel, in particular for deflecting the flowing and usually swirled air with a radially inwardly oriented directional component
  • the axial extension is configured and provided for guiding the created fuel-air mixture.
  • a mixture guidance is integrated in the nozzle, whereby any flow elements at the combustion-space side can be omitted at a burner seal via which the nozzle is positioned at the combustion chamber.
  • the burner seal can be limited to its sealing function, and can be embodied without aerodynamic elements that influence the flow.
  • the extension is formed in a tubular manner.
  • the extension may for example be embodied in the kind of a tube piece at the combustion-space side end of the nozzle main body.
  • the extension can be formed or molded at the nozzle main body as a tubular end piece.
  • the extension extends in the axial direction with a length that is less than 3.5 times a height of the at least one further air channel and/or that is less than 3.5. times a height of a swirling element provided in the at least one further air channel.
  • a height H of the at least one further air channel or of the swirling element the following thus applies to a length l 5 with which the extension extends in the axial direction: l 5 ⁇ 3.5 H.
  • a corresponding geometric correlation between the length of the axial extension and the height of the at least one further air channel and/or of a swirling element provided in this air channel has proven to be advantageous for influencing the flow.
  • the air guide element of the at least one further air channel has a section (which is hollow and is passed by air from the air channel during operation of the engine) at which an inner diameter defined by the air guide element and thus the cross-sectional surface of the nozzle exit opening which is passable by a flow is minimal, and the extension—measured from a first reference point at this section and at the location of the minimal inner diameter—extends in the axial direction up to a second reference point that is located at a certain distance from the first reference point.
  • the distance between the first reference point and the second reference point that is measured along the nozzle longitudinal axis
  • a radially outwardly located lateral surface of the extension connects to a radially outwardly located lateral surface of the air guide element.
  • the air guide element and the extension have substantially or exactly the same outer diameter.
  • an inner lateral surface of the extension connects to an inner lateral surface of the air guide element of the at least one further air channel in the axial direction.
  • An inner lateral surface of the air guide element thus transitions into the inner lateral surface of the extension without any steps or without any projection or recess, for example. In this way, the lateral surfaces of the extension and of the air guide element continuously transition into each other in such an embodiment variant.
  • the extension has at least two sections succeeding each other in the axial direction and having different inner diameters.
  • This for example includes that a first section of the extension with an inner diameter which remains constant in the axial direction (along the nozzle longitudinal axis) is provided upstream of a second section, with the latter having a different inner diameter that be increasing up to the end of the extension, if necessary.
  • a continuous widening of the opening that is passed by the flow can be provided in the second section.
  • a length of a second (end-side) section measured in the axial direction and having a larger and/or increasing inner diameter in the axial direction is considerably smaller than a corresponding (axial) length of the first section.
  • the length of the second downstream, shorter section represents only a fraction of the length of the first section.
  • an inner diameter (of the nozzle exit opening) can increase continuously or at least with one step in the axial direction at least at one section of the extension.
  • this variant in particular includes the previously described variant in which two sections with different inner diameters are provided. But this also includes variants in which not only a section of the extension, but the extension itself has an inner diameter that increases continuously in a diffuser-like manner.
  • the at least one section of the extension or the extension itself has an inner lateral surface that extends in a manner pointing radially outwards with respect to the nozzle longitudinal axis and/or that is concavely curved.
  • the inner lateral surface of the extension defines a (nozzle exit) opening for the fuel-air mixture widening in the shape of a truncated cone.
  • a (nozzle exit) opening for the fuel-air mixture widening in the shape of a truncated cone.
  • an additionally provided widening of the (nozzle exit) opening defined by the extension can be provided, in particular at an end of the extension that is located in the axial direction.
  • the extension has a constant inner diameter in the axial direction.
  • a further aspect of the suggested solution relates to the provision of a combustion chamber assembly group, with a burner seal that comprises a bearing section having a passage opening and extending along the nozzle longitudinal axis, and with a nozzle that is positioned inside the passage opening of the bearing section.
  • the nozzle also here has an extension for guiding the fuel-air mixture extending in the axial direction.
  • the extension of the nozzle projects in the axial direction (which is oriented to a combustion space of the combustion chamber if the combustion chamber assembly group is arranged at a combustion chamber according to the intended use) beyond the bearing section.
  • the guidance of the fuel-air mixture that is provided at the nozzle exit opening in the direction of the combustion space is realized exclusively by means of the nozzle and its axial extension.
  • the burner seal is formed without flow guiding elements (at the combustion-space side).
  • the burner seal is thus limited to its sealing function and is not designed for an aerodynamic function. In that case, the function of the flow guidance of the fuel-air mixture is taken over exclusively or at least predominantly by the nozzle with its axial extension.
  • an engine with at least one nozzle according to the invention or a combustion chamber assembly group according to the invention is also provided within the scope of the solution according to the invention.
  • FIGS. 1 to 7 show, respectively in sections and in cross-sectional view, different embodiment variants of a nozzle according to the invention with an axial extension in the area of a nozzle exit opening;
  • FIG. 8A shows an engine in which a combustion chamber with a nozzle according to one of the embodiment variants of FIGS. 1 to 7 is used;
  • FIG. 8B shows, in sections and an enlarged scale, the combustion chamber of the engine of FIG. 8A ;
  • FIG. 8C shows, in a cross-sectional view, the basic structure of a nozzle according to the state of the art and the surrounding components of the engine in the installed state of the nozzle;
  • FIG. 8D shows a back view of a nozzle exit opening, also illustrating swirling elements that are provided in radially outwardly located air guiding channels of the nozzle.
  • FIG. 8A schematically illustrates, in a sectional view, a (turbofan) engine T in which the individual engine components are arranged in succession along a rotational axis or central axis M and the engine T is embodied as a turbofan engine.
  • a fan F By means of a fan F, air is suctioned in along an entry direction at an inlet or an intake E of the engine T.
  • This fan F which is arranged inside a fan housing FC, is driven via a rotor shaft S that is set into rotation by a turbine TT of the engine T.
  • the turbine TT connects to a compressor V, which for example has a low-pressure compressor 11 and a high-pressure compressor 12 , and where necessary also a medium-pressure compressor.
  • the fan F supplies air to the compressor V in a primary air flow F 1 , on the one hand, and, on the other, to a secondary flow channel or bypass channel B in a secondary air flow F 2 for creating a thrust.
  • the bypass channel B extends about a core engine that comprises the compressor V and the turbine TT, and also comprises a primary flow channel for the air that is supplied to the core engine by the fan F.
  • the air that is conveyed via the compressor V into the primary flow channel is transported into the combustion chamber section BKA of the core engine where the driving power for driving the turbine TT is generated.
  • the turbine TT has a high-pressure turbine 13 , a medium-pressure turbine 14 , and a low-pressure turbine 15 .
  • the turbine TT drives the rotor shaft S and thus the fan F by means of the energy that is released during combustion in order to generate the necessary thrust by means of the air that is conveyed into the bypass channel B.
  • the air from the bypass channel B as well as the exhaust gases from the primary flow channel of the core engine are discharged via an outlet A at the end of the engine T.
  • the outlet A usually has a thrust nozzle with a centrally arranged outlet cone C.
  • FIG. 8B shows a longitudinal section through the combustion chamber section BKA of the engine T.
  • a nozzle assembly group is provided for injecting fuel or an air-fuel-mixture into a combustion space 30 of the combustion chamber 3 .
  • It comprises a combustion chamber ring R along which multiple (fuel/injection) nozzles 2 are arranged along a circular line about the central axis M.
  • the nozzle exit openings of the respective nozzles 2 that are positioned inside the combustion chamber 3 are provided at the combustion chamber ring R.
  • each nozzle 2 comprises a flange by means of which a nozzle 2 is screwed to an outer housing G of the combustion chamber 3 .
  • FIG. 8C now shows a cross-sectional view of the basic structure of a nozzle 2 as well as the surrounding components of the engine T in the installed state of the nozzle 2 .
  • the nozzle 2 is part of a combustion chamber system of the engine T.
  • the nozzle 2 is located downstream of a diffuser DF and during mounting is inserted through an access hole L through a combustion chamber head 31 , through a heat shield 300 and a head plate 310 of the combustion chamber 3 up to the combustion space 30 of the combustion chamber 3 , so that a nozzle exit opening formed at a nozzle main body 20 reaches all the way to the combustion space 30 .
  • the nozzle 2 further comprises a nozzle neck 21 which substantially extends radially with respect to the central axis M and inside of which a fuel supply 210 conveying fuel to the nozzle main body 20 is accommodated. Further formed at the nozzle main body 20 are a fuel chamber 22 , fuel passages 220 , heat shields 23 as well as air chambers for insulation 23 a and 23 b.
  • the nozzle main body 20 forms a (first) inner air channel 26 extending centrally along a nozzle longitudinal axis DM and, positioned radially further outside with respect to the same, a (second and third) outer air guiding channel 27 a and 27 b .
  • These air guiding channels 26 , 27 a and 27 b extend in the direction of the nozzle exit opening of the nozzle 2 .
  • At least one fuel guiding channel 26 is formed at the nozzle main body 20 .
  • This fuel guiding channel 25 is located between the first inner air channel 26 and the second outer air channel 27 a .
  • the end of the fuel guiding channel 25 via which fuel flows out in the direction of the air from the first inner air channel 26 during operation of the nozzle 2 , is located—with respect to the nozzle longitudinal axis DM and in the direction of the nozzle exit opening—in front of the end of the second air channel 27 a from which air from the second, outer air channel 27 a flows out in the direction of a mixture of air from the first, inner air channel 26 and fuel from the fuel guiding channel 25 .
  • Swirling elements 270 a , 270 b for swirling the air supplied through the air guiding channels 27 a and 27 b are provided in the outer air guiding channels 27 a and 27 b .
  • the nozzle main body 20 also comprises an outer, radially inwardly oriented air guide element 271 b at the end of the third outer air channel 27 b .
  • the nozzle 2 which may e.g.
  • a sealing element 28 is also provided at the nozzle main body 20 at its circumference for sealing the nozzle 2 towards the combustion space 30 .
  • This sealing element 28 forms a counter-piece to a burner seal 4 .
  • This burner seal 4 is floatingly mounted between the heat shield 300 and the head plate 310 to compensate for radial and axial movements between the nozzle 2 and the combustion chamber 3 and to ensure reliable sealing in different operational states.
  • the burner seal 4 usually has a flow guiding element 40 towards the combustion space 30 .
  • this flow guiding element 40 ensures a desired flow guidance of the fuel-air mixture that results from the nozzle 2 , more precisely the swirled air from the air guiding channels 26 , 27 a and 27 b , as well as the fuel guiding channel 25 .
  • an extension 5 is provided at the air guide element 271 b of the outermost, third air channel 27 b , extending in the axial direction in order to guide the resulting fuel-air mixture in the direction of the combustion space 30 .
  • This extension 5 which may for example be formed or molded integrally at the nozzle main body 20 , respectively projects beyond a bearing section 41 of the burner seal 4 at the combustion chamber side.
  • the passage opening through which the nozzle 2 is positioned at the burner seal 4 is provided in this bearing section 41 .
  • the extension 5 of the shown embodiment variants that connects to the air guide element 271 b has an outer diameter D 2 that substantially corresponds to the outer diameter of the air guide element 271 b and thus the nozzle 2 in the area of the burner seal 4 .
  • the extension 5 of the respective nozzle 2 is further designed in a tubular manner, and has an axial length l 5 that is less than 3.5. times a height H of the swirling element 270 b provided in the third air channel 27 b.
  • extension 5 is respectively dimensioned in such a manner that other geometric conditions having proven to be advantageous are met.
  • the air guide element 271 b of the third air channel 27 b defines an area with a minimal inner diameter D 1 and thus a minimal cross-sectional surface of the nozzle exit opening through which the flow passes.
  • a distance I of a reference point E 1 at the location of this minimal inner diameter D 1 to a further reference point E 2 located in the axial direction and marking the end of the extension 5 is now dimensioned such that the following applies: H ⁇ I ⁇ 3.5 ⁇ H.
  • extension 5 of the nozzle 2 shown in FIG. 1 has two successive sections 50 and 51 with different inner diameters.
  • a first section 50 with an inner diameter which remains constant along the nozzle longitudinal axis DM connects to the air guide element 271 b .
  • second section 51 is followed in the direction of the combustion space 30 by a considerably shorter, second section 51 , where the inner diameter increases and accordingly the extension 5 widens.
  • the embodiment variant of FIG. 2 provides an extension 5 with a smoother transition between an inner lateral surface of the air guide element 271 b and an inner lateral surface of the extension 5 .
  • the extension 5 is further continuously enlarged in a diffuser-like manner, so that an inner diameter of the extension 5 is continuously enlarged in the axial direction, and the inner lateral surface of the extension 5 extends radially outwards with respect to the nozzle longitudinal axis DM.
  • the transition between the air guide element 271 b and the extension 5 is realized through a ledge.
  • the downstream (end-side) section 51 is embodied so as to taper off towards the trailing edge.
  • the extension 5 has a slightly concave inner curvature for a smoother transition between the air guide element 271 b and the extension 5 .
  • the lateral surfaces of the air guide element 271 b and the extension 5 transition into each other without steps.
  • a flow is guided along the air guide element 271 b and the extension 5 along their inner lateral surface, which transitions without any edges.
  • a slightly convex inner curvature is provided at the downstream distal end of the extension 5 .
  • the extension 5 is also designed in such a manner that the lateral surfaces of the air guide element 271 b and the extension 5 transition into each other without any steps at a transition 52 , and the extension 5 thus directly connects to the air guide element 271 b of the radially outermost, third air channel 27 b .
  • the extension 5 is embodied in such a manner that the extension 5 widens continuously in the axial direction along the nozzle longitudinal axis DM all the way to a tapering trailing edge.
  • the inner lateral surface of the extension 5 is slightly concavely curved.
  • the embodiment variant of FIG. 7 provides a continuous, diffuser-like widening of the extension 5 directly connecting to the air guide element 271 b through an inner lateral surface that extends in a linear manner and is oriented radially outwards at a constant angle to the nozzle longitudinal axis DM.
  • the nozzle 2 is respectively axially extended at a radially outermost third air channel 27 b downstream of an air guide element 271 b .
  • the axial extension 5 provided for this purpose is respectively formed in a tubular manner and has the same outer diameter D 2 as the nozzle 2 in the area of the burner seal 4 .
  • the inner contour of the extension 5 is respectively chosen in such a manner that a widening of the extension 5 occurs along the nozzle longitudinal axis DM in the direction of the combustion space 30 at least in one section.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Spray-Type Burners (AREA)
  • Processes For Solid Components From Exhaust (AREA)
US16/117,062 2017-09-28 2018-08-30 Nozzle comprising axial extension for a combustion chamber of an engine Abandoned US20190093896A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102017217328.9A DE102017217328A1 (de) 2017-09-28 2017-09-28 Düse mit axialer Verlängerung für eine Brennkammer eines Triebwerks
DE102017217328.9 2017-09-28

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EP (1) EP3462090A1 (de)
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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111578311A (zh) * 2019-02-18 2020-08-25 通用电气公司 燃料喷嘴组件
US10808623B2 (en) * 2018-03-15 2020-10-20 Rolls-Royce Deutschland Ltd & Co Kg Combustion chamber assembly with burner seal and nozzle as well as guiding flow generating equipment
US20210172604A1 (en) * 2019-12-06 2021-06-10 United Technologies Corporation High shear swirler with recessed fuel filmer

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6546732B1 (en) * 2001-04-27 2003-04-15 General Electric Company Methods and apparatus for cooling gas turbine engine combustors
US7673460B2 (en) * 2005-06-07 2010-03-09 Snecma System of attaching an injection system to a turbojet combustion chamber base
US7921650B2 (en) * 2005-12-13 2011-04-12 Kawasaki Jukogyo Kabushiki Kaisha Fuel spraying apparatus of gas turbine engine
US8443609B2 (en) * 2008-03-18 2013-05-21 Rolls-Royce Deutschland Ltd & Co Kg Gas-turbine burner for a gas turbine with purging mechanism for a fuel nozzle
US20170122565A1 (en) * 2015-10-29 2017-05-04 Rolls-Royce Plc Combustion chamber assembly

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19729246C2 (de) * 1997-07-09 2001-06-28 Deutsch Zentr Luft & Raumfahrt Zerstäuberdüse für die Kraftstoffzerstäubung in Brennern
US6550251B1 (en) * 1997-12-18 2003-04-22 General Electric Company Venturiless swirl cup
US6354072B1 (en) * 1999-12-10 2002-03-12 General Electric Company Methods and apparatus for decreasing combustor emissions
US6865889B2 (en) * 2002-02-01 2005-03-15 General Electric Company Method and apparatus to decrease combustor emissions
DE102007050276A1 (de) * 2007-10-18 2009-04-23 Rolls-Royce Deutschland Ltd & Co Kg Magervormischbrenner für ein Gasturbinentriebwerk
FR2956897B1 (fr) * 2010-02-26 2012-07-20 Snecma Systeme d'injection pour chambre de combustion de turbomachine, comprenant des moyens d'injection d'air ameliorant le melange air-carburant
US9423137B2 (en) 2011-12-29 2016-08-23 Rolls-Royce Corporation Fuel injector with first and second converging fuel-air passages
US9927126B2 (en) * 2015-06-10 2018-03-27 General Electric Company Prefilming air blast (PAB) pilot for low emissions combustors

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6546732B1 (en) * 2001-04-27 2003-04-15 General Electric Company Methods and apparatus for cooling gas turbine engine combustors
US7673460B2 (en) * 2005-06-07 2010-03-09 Snecma System of attaching an injection system to a turbojet combustion chamber base
US7921650B2 (en) * 2005-12-13 2011-04-12 Kawasaki Jukogyo Kabushiki Kaisha Fuel spraying apparatus of gas turbine engine
US8443609B2 (en) * 2008-03-18 2013-05-21 Rolls-Royce Deutschland Ltd & Co Kg Gas-turbine burner for a gas turbine with purging mechanism for a fuel nozzle
US20170122565A1 (en) * 2015-10-29 2017-05-04 Rolls-Royce Plc Combustion chamber assembly

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10808623B2 (en) * 2018-03-15 2020-10-20 Rolls-Royce Deutschland Ltd & Co Kg Combustion chamber assembly with burner seal and nozzle as well as guiding flow generating equipment
CN111578311A (zh) * 2019-02-18 2020-08-25 通用电气公司 燃料喷嘴组件
US20210172604A1 (en) * 2019-12-06 2021-06-10 United Technologies Corporation High shear swirler with recessed fuel filmer
US11378275B2 (en) * 2019-12-06 2022-07-05 Raytheon Technologies Corporation High shear swirler with recessed fuel filmer for a gas turbine engine

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EP3462090A1 (de) 2019-04-03

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