EP3462090A1 - Buse à extension axiale pour une chambre de combustion d'un moteur - Google Patents

Buse à extension axiale pour une chambre de combustion d'un moteur Download PDF

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Publication number
EP3462090A1
EP3462090A1 EP18196580.7A EP18196580A EP3462090A1 EP 3462090 A1 EP3462090 A1 EP 3462090A1 EP 18196580 A EP18196580 A EP 18196580A EP 3462090 A1 EP3462090 A1 EP 3462090A1
Authority
EP
European Patent Office
Prior art keywords
nozzle
extension
air
combustion chamber
axial direction
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Withdrawn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
EP18196580.7A
Other languages
German (de)
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
Publication of EP3462090A1 publication Critical patent/EP3462090A1/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Withdrawn legal-status Critical Current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
    • F23R3/02—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 outlet opening of the nozzle.
  • a nozzle usually also serves to distort the supplied air, which is then, mixed with the supplied fuel, conveyed to the nozzle outlet opening of the nozzle in the combustion chamber.
  • a plurality of nozzles are combined in a nozzle assembly that includes a plurality of nozzles arranged side by side, usually along a circular line, for introducing fuel into the combustion chamber.
  • the US 9,423,137 B2 known nozzles with a plurality of air ducts and at least one Kraftstoffleitkanal provide that a first air duct along a nozzle longitudinal axis of the nozzle main body extends and a Kraftstoffleitkanal relative to the first air duct, based on the nozzle longitudinal axis, radially further out. At least one further air duct is then additionally in relation to the fuel duct, with respect to the nozzle longitudinal axis, radially provided further out.
  • From the prior art is also known and, for example, in the US 9,423,137 B2 provided to provide such a nozzle with a third air duct, which optionally radially outwardly offset end in the axial direction follows the end of the second air duct.
  • the nozzle is positioned via a burner seal which seals the nozzle to the combustion chamber of the combustion chamber.
  • the burner seal is in this case usually floatingly mounted on a top plate of the combustion chamber to compensate for radial and axial movements between the nozzle and the combustion chamber at different operating conditions and to ensure a reliable sealing effect.
  • the burner seal For guiding the fuel-air mixture provided by the nozzle, the burner seal frequently has a flow-guiding element on the combustion chamber side.
  • the aerodynamic conditions vary depending on the operating state of the engine.
  • a design-dictated radial distance between the nozzle and the burner seal complicates a precisely predetermined guidance of the fuel-air mixture via the flow guide of the burner seal. Both of these aspects influence the formation of undesirable soot emissions.
  • an extension extending in the axial direction relative to the nozzle longitudinal axis is now provided for the guidance of the fuel-air mixture.
  • the axial direction, along which the extension extends has in the intended arrangement of a nozzle assembly comprising the combustion chamber assembly to a combustion chamber to a combustion chamber of the combustion chamber.
  • the axial extension is thus at the intended arrangement of the nozzle to the combustion chamber within the combustion chamber and extends in the flow direction of the fuel-air mixture to be provided.
  • the nozzle main body in the case of a nozzle according to the invention, provision is thus made for the nozzle main body to be formed in the region of the air guide element of the at least one further air duct (in the case of several air ducts of the radially outermost) with an extension for guiding the fuel-air mixture provided at the nozzle outlet opening.
  • the axial extension is thus set up and provided for guiding the generated mixture of fuel from the fuel guide channel and the air from the first, inner air guide channel and the at least one further air guide channel.
  • the spoiler element of the at least one further air duct for guiding the air from the at least one further air duct is provided and provided, in particular to deflect the flowing and usually twisted air with a radially inwardly pointing directional component, the axial extension for the leadership of created and provided fuel-air mixture produced.
  • a mixture guide is integrated into the nozzle, whereby any combustion chamber-side flow elements on a burner seal over which the nozzle is positioned on the combustion chamber, can be omitted.
  • the Burner seal can thereby be limited to their sealing function and executed without flow-influencing aerodynamic elements.
  • the extension is tubular.
  • the extension is then formed, for example, in the manner of a pipe section at the combustion chamber end of the nozzle main body.
  • the extension can be formed on the nozzle main body so tubular end piece or integrally formed thereon.
  • the extension extends in the axial direction with a length which is smaller than 3.5 times a height of the at least one further air duct and / or which is less than 3.5 times a height a provided in the at least one further air duct Verdrallelements.
  • a height H of the at least one further air duct or the Verdrallelements for a length l 5 , extending with the extension in the axial direction: l 5 ⁇ 3.5 H.
  • a corresponding geometric relationship between the length of the axial Extension and the height of the at least one further air duct and / or one provided in this air duct Verdrallelements has proved to be advantageous for the flow control.
  • a radially outer circumferential surface of the extension connects to a radially outer circumferential surface of the air guide element.
  • the air guide element and the extension have substantially or exactly the same outer diameter. The extension thus does not increase a maximum outer diameter of the nozzle at its end which reaches into the combustion chamber in the intended state.
  • an inner lateral surface of the extension connects in the axial direction to an inner circumferential surface of the air guiding element of the at least one further air duct.
  • An inner circumferential surface of the air guide element thus passes, for example paragraph-free respectively without forward or return in the inner circumferential surface of the extension.
  • the lateral surfaces of the extension and of the air-guiding element thus continuously merge into one another at a transition.
  • the extension has at least two successive sections in the axial direction with different inner diameters. This includes, for example, that a first portion of the extension with an axially constant inside diameter (along the nozzle longitudinal axis) upstream of a second portion is provided, which has a different and optionally up to the end of the extension increasing inner diameter. In this case, a continuous expansion of the flow-through opening may be provided in the second section.
  • a length measured in the axial direction of a second (end-side) section which has a larger and / or inner diameter that increases in the axial direction, is significantly smaller than a corresponding (axial) length of the first section.
  • the length of the second downstream shorter section is only a fraction of the length of the first section.
  • At least a portion of the extension an inner diameter (the nozzle outlet opening) in the axial direction continuously or at least once stepped increase.
  • This variant therefore includes in particular the variant explained above that two sections with different inner diameters are provided. But this also includes variants in which not only a portion of the extension, but the extension itself has a continuously increasing diffuser-like inner diameter.
  • the at least one section of the extension or the extension itself has an inner circumferential surface which extends radially outward with respect to the longitudinal axis of the nozzle and / or is curved in a concave manner.
  • the inner circumferential surface of the extension defines, for example, a frusto-conical widening (nozzle exit) opening for the fuel-air mixture.
  • nozzle exit a widening opening for the fuel-air mixture.
  • an optionally additionally provided widening of the opening (nozzle outlet) defined by the extension can be provided, in particular at an end of the extension lying in the axial direction.
  • the extension has an inner diameter which is constant in the axial direction.
  • a combustor assembly having a combustor seal having a bearing portion extending along the nozzle longitudinal axis with a through-opening and a nozzle positioned in the passage opening of the bearing portion.
  • the nozzle then also has here an extending in the axial direction extension for the guidance of the fuel-air mixture.
  • the extension of the nozzle in the axial direction projects beyond the bearing section.
  • the leadership of the fuel-air mixture, which is provided at the nozzle outlet opening, in the direction of the combustion chamber takes place here exclusively through the nozzle and its axial extension.
  • the burner seal is designed without (on the combustion chamber side) flow guide elements.
  • the burner seal is thus limited to the function of the seal and is not designed for aerodynamic function.
  • the function of the flow guidance of the fuel-air mixture then takes over alone or at least primarily the nozzle with its axial extension.
  • an engine with at least one nozzle according to the invention or a combustion chamber assembly according to the invention is provided.
  • the Figure 8A illustrates schematically and in section a (turbofan) engine T, in which the individual engine components along a Rotation axis or center axis M are arranged one behind the other and the engine T is designed as a turbofan engine.
  • a fan F This arranged in a fan housing FC fan F is driven by a rotor shaft S, which is rotated by a turbine TT of the engine T in rotation.
  • the turbine TT adjoins a compressor V, which has, for example, a low-pressure compressor 11 and a high-pressure compressor 12, and possibly also a medium-pressure compressor.
  • the fan F leads on the one hand in a primary air flow F1 to the compressor V air and on the other hand, to generate the thrust in a secondary air flow F2 a secondary flow channel or bypass channel B.
  • the bypass channel B extends around a compressor V and the turbine TT comprehensive core engine, the a primary flow channel for the supplied through the fan F to the core engine air.
  • the air conveyed into the primary flow passage via the compressor V enters a combustion chamber section BKA of the core engine in which 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 thereby drives the rotor shaft S and thus the fan F via the energy released during combustion in order to generate the required thrust via the air conveyed into the bypass duct B.
  • Both the air from the bypass passage B and the exhaust gases from the primary flow passage of the core engine flow through an outlet A at the end of the engine T.
  • the outlet A in this case usually has a discharge nozzle with a centrally arranged outlet cone C.
  • FIG. 8B shows a longitudinal section through the combustion chamber section BKA of the engine T. It can be seen in particular in a (ring) combustion chamber 3 of the engine T.
  • a nozzle assembly is provided for injecting fuel or an air-fuel mixture into a combustion chamber 30 of the combustion chamber 3.
  • This comprises a combustion chamber ring R, on which along a circular line around the central axis M a plurality of (fuel / injection) nozzles 2 are arranged.
  • the nozzle outlet openings of the respective nozzles 2 are provided on the combustion chamber ring R, which lie within the combustion chamber 3.
  • Each nozzle 2 in this case comprises a flange, via which a nozzle 2 is screwed to an outer housing G of the combustion chamber 3.
  • FIG. 8C shows now in cross-sectional view of the basic structure of a nozzle 2 and the surrounding components of the engine T in the installed state of Nozzle 2.
  • the nozzle 2 hereby forms part of a combustion chamber system of the engine T.
  • the nozzle 2 is located downstream of a diffuser DF and, during assembly, passes through an access hole L through a combustion chamber head 31, through a heat shield 300 and a top plate 310 of the combustion chamber 3 pushed to the combustion chamber 30 of the combustion chamber 3, so that a formed on a nozzle main body 20 nozzle outlet opening extends into the combustion chamber 30.
  • the nozzle 2 further comprises a nozzle stem 21 extending substantially radially with respect to the center axis M and housing a fuel supply line 210 which delivers fuel to the nozzle main body 20.
  • On the nozzle main body 20 there are further formed a fuel chamber 22, fuel passages 220, heat shields 23, and air chambers for isolation 23a and 23b.
  • the nozzle main body 20 forms a (first) inner air duct 26 extending centrally along a nozzle longitudinal axis DM and radially outer (second and third) outer air ducts 27a and 27b for this purpose.
  • These air guide channels 26, 27 a and 27 b extend in the direction of the nozzle outlet opening of the nozzle 2.
  • At least one fuel guide channel 26 is formed on the nozzle main body 20.
  • This Kraftstoffleitkanal 25 is located between the first inner air duct 26 and the second outer air duct 27 a.
  • Verdralletti 270a, 270b for twisting the air supplied thereto. Furthermore, the nozzle main body 20 at the end of the third outer air duct 27b still an outer, radially inwardly facing air guide element 271b.
  • the nozzle 2 which is, for example, a pressure-assisted injection nozzle, follow according to the FIG. 8C with respect to the nozzle longitudinal axis DM and in the direction of the nozzle exit opening, onto the end of the fuel guide channel 25, from which fuel is supplied from the first inner, centrally extending air duct 26 during operation of the engine T, the ends of the second and third radially outward lying Vietnameseleitkanäle 27a and 27b.
  • a sealing element 28 is still provided peripherally on the nozzle main body 20.
  • This seal member 28 is floatingly mounted between the heat shield 300 and the top plate 310 to compensate for radial and axial movement between the nozzle 2 and the combustion chamber 3 at various operating conditions and to ensure a reliable seal.
  • the burner seal 4 usually has a flow guide element 40 to the combustion chamber 30.
  • This flow guide 40 in conjunction with the third outer air duct 27b on the nozzle 2 for a desired flow guidance of the fuel-air mixture from the nozzle 2, more precisely the twisted air from the air ducts 26, 27a and 27b, and the Kraftstoffleitkanal 25th , arises.
  • an extension 5 extending in the axial direction to be provided on the air guide element 271b of the outermost, third air guide channel 27b in order to guide the generated fuel-air mixture in the direction of the combustion chamber 30.
  • This extension 5 which is for example integrally formed on or molded onto the nozzle skin body 20, projects in each case beyond a bearing section 41 of the burner seal 4 on the burner chamber side.
  • the through hole is provided, via which the nozzle 2 to the burner seal 4th is positioned.
  • the nozzle 2 of the FIG. 1 which adjoins the air guide element 271b extension 5 of the illustrated embodiments an outer diameter D2, which corresponds substantially to the outer diameter of the air guide element 271b and thus the nozzle 2 in the region of the burner seal 4.
  • the extension 5 of the respective nozzle 2 is further configured tubular and has an axial length l 5 , which is smaller than 3.5 times a height H of the provided in the third air duct 27b Verdrallelements 270b.
  • the axial extent of the extension 5 is further each dimensioned so that a further proved advantageous geometric relationship is met.
  • the air guide element 271b of the third air guide channel 27b for the guidance of air flowing out of the air guide channel 27b radially inwardly defines a region with a minimum inner diameter D1 and thus a minimum cross-sectional area of the nozzle exit opening.
  • a distance I of a reference point E1 at the location of this minimum inner diameter D1 to an axially further, further reference point E2, which marks the end of the extension 5, is now dimensioned such that: H ⁇ l ⁇ 3.5 H.
  • the extension 5 in the FIG. 1 illustrated nozzle 2 has two successive sections 50 and 51 with different inner diameter.
  • extension 5 in the transition from the air guide element 271b of the radially outermost, third air guide channel 27b forms a shoulder and thus return, on which the inner diameter increases comparatively abruptly sees the embodiment of the FIG. 2 an extension 5 with a softer transition between an inner circumferential surface of the air guide element 271b and an inner circumferential surface of the extension 5 before.
  • extension 5 continuously diffuser-like, so that an inner diameter of the extension 5 increases continuously in the axial direction and the inner circumferential surface of the extension 5 extends radially outward with respect to the nozzle longitudinal axis DM.
  • the extension 5 for a smoother transition between the air guide element 271b and the extension 5 a slight concave inside curvature.
  • the lateral surfaces of the air guide element 271b and the extension 5 merge into one another without offset.
  • a flow is thus guided along the air guide element 271b and the extension 5 at their inner surface which merges into one another without edges.
  • a slight convex inner curvature is provided at the downstream end of the extension 5.
  • the extension 5 is also designed such that the lateral surfaces of the air guide element 271b and the extension 5 merge into each other at a transition 52 paragraph-free and thus the extension 5 connects directly to the air guide 271b of the radially outermost third air duct 27b.
  • the extension 5 is designed such that the extension 5 continuously widens in the axial direction along the nozzle longitudinal axis DM up to a tapered trailing edge.
  • the inner circumferential surface of the extension 5 is here slightly curved concave.
  • the nozzle 2 is axially extended downstream of an air guide element 271b, in each case at a radially outermost third air guide channel 27b.
  • the axial extension 5 provided for this purpose is in each case tubular and has the same outer diameter D 2 as the nozzle 2 in the region
  • the inner contour of the extension 5 is in each case selected such that, at least in one section, a widening of the extension 5 along the nozzle longitudinal axis DM results in the direction of the combustion chamber 30.
  • the burner seal 4 Due to the formation of the extension 5 at the nozzle 2, at which the fuel-air mixture generated is guided in the direction of the combustion chamber 30, an authorized axial displaceability of the burner seal 4 and the nozzle 2 relative to each other does not affect the leadership of the fuel-air mixture. This is particularly advantageous with regard to the avoidance of interfering soot emissions. Furthermore, the burner seal 4 here only needs to be set up and designed to ensure the sealing effect. The integration of a flow guide 40 on the burner direction 4 can be omitted.

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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)
EP18196580.7A 2017-09-28 2018-09-25 Buse à extension axiale pour une chambre de combustion d'un moteur Withdrawn EP3462090A1 (fr)

Applications Claiming Priority (1)

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

Publications (1)

Publication Number Publication Date
EP3462090A1 true EP3462090A1 (fr) 2019-04-03

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EP18196580.7A Withdrawn EP3462090A1 (fr) 2017-09-28 2018-09-25 Buse à extension axiale pour une chambre de combustion d'un moteur

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US (1) US20190093896A1 (fr)
EP (1) EP3462090A1 (fr)
DE (1) DE102017217328A1 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102018106051A1 (de) * 2018-03-15 2019-09-19 Rolls-Royce Deutschland Ltd & Co Kg Brennkammerbaugruppe mit Brennerdichtung und Düse sowie einer Leitströmungserzeugungseinrichtung
US11156360B2 (en) * 2019-02-18 2021-10-26 General Electric Company Fuel nozzle assembly
US11378275B2 (en) * 2019-12-06 2022-07-05 Raytheon Technologies Corporation High shear swirler with recessed fuel filmer for a gas turbine engine

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19729246A1 (de) * 1997-07-09 1999-01-14 Deutsch Zentr Luft & Raumfahrt Zerstäuberdüse für die Kraftstoffzerstäubung in Brennern
US20050103020A1 (en) * 2002-02-01 2005-05-19 Mancini Alfred A. 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
US20120304650A1 (en) * 2010-02-26 2012-12-06 Snecma Injection system for a turbomachine combustion chamber, including air injection means improving the air-fuel mixture
US20160363321A1 (en) * 2015-06-10 2016-12-15 General Electric Company Prefilming air blast (pab) pilot for low emissions combustors

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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
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
JP2007162998A (ja) * 2005-12-13 2007-06-28 Kawasaki Heavy Ind Ltd ガスタービンエンジンの燃料噴霧装置
DE102008014744A1 (de) * 2008-03-18 2009-09-24 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrenner für eine Gasturbine mit Spülmechanismus für eine Brennstoffdüse
US9423137B2 (en) 2011-12-29 2016-08-23 Rolls-Royce Corporation Fuel injector with first and second converging fuel-air passages
GB2543803B (en) * 2015-10-29 2019-10-30 Rolls Royce Plc A combustion chamber assembly

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19729246A1 (de) * 1997-07-09 1999-01-14 Deutsch Zentr Luft & Raumfahrt Zerstäuberdüse für die Kraftstoffzerstäubung in Brennern
US20050103020A1 (en) * 2002-02-01 2005-05-19 Mancini Alfred A. 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
US20120304650A1 (en) * 2010-02-26 2012-12-06 Snecma Injection system for a turbomachine combustion chamber, including air injection means improving the air-fuel mixture
US20160363321A1 (en) * 2015-06-10 2016-12-15 General Electric Company Prefilming air blast (pab) pilot for low emissions combustors

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DE102017217328A1 (de) 2019-03-28
US20190093896A1 (en) 2019-03-28

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