EP2409085B1 - Turbomotorbrennkammer mit einer verbesserten primärluft-zufuhreinrichtung - Google Patents

Turbomotorbrennkammer mit einer verbesserten primärluft-zufuhreinrichtung Download PDF

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Publication number
EP2409085B1
EP2409085B1 EP10708769.4A EP10708769A EP2409085B1 EP 2409085 B1 EP2409085 B1 EP 2409085B1 EP 10708769 A EP10708769 A EP 10708769A EP 2409085 B1 EP2409085 B1 EP 2409085B1
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EP
European Patent Office
Prior art keywords
combustion chamber
air
annular
injection system
upstream
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EP10708769.4A
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English (en)
French (fr)
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EP2409085A1 (de
Inventor
Sébastien Alain Christophe BOURGOIS
Romain Nicolas Lunel
Thomas Olivier Marie Noel
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Safran Aircraft Engines SAS
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SNECMA SAS
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    • 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

Definitions

  • the present invention relates to an annular combustion chamber of a turbomachine, such as for example an airplane turbojet or turboprop.
  • Turbomachines generally comprise an annular combustion chamber mounted downstream of a compressor.
  • the combustion chamber is delimited upstream by an annular bottom equipped with injection systems regularly distributed around the axis of the turbomachine and for injecting a mixture of air and fuel into the combustion chamber.
  • the output of the compressor opens into an enclosure in which is housed the combustion chamber.
  • the compressor may be of axial type and have an output substantially aligned with the injection systems of the combustion chamber, or be of the centrifugal type, and comprise at the output an annular rectifier opening in a radially outer region of the enclosure of the combustion chamber.
  • Injection systems of the combustion chamber have peripheral bores through which air from the compressor can enter, and means for centering and guiding fuel injector heads.
  • the injection systems are designed to optimize the performance of the combustion chamber and thus reduce fuel consumption and pollutant emissions at the outlet of this combustion chamber.
  • the performance of the injection systems is, in general, even higher than the pressure drop is important inside these injection systems, and that the air supply of these systems is uniform. around their respective axes. To limit the overall pressure drop experienced by the air flow supplying the combustion chamber while allowing a high pressure drop inside the injection systems, it is therefore desirable to reduce the pressure drop as much as possible. upstream of these injection systems.
  • the document EP0153842 A1 shows a turbomachine combustion chamber having combustion air collectors associated with each injection system in an annular fairing.
  • the collectors have a shape of the circular holes formed in and by the fairing.
  • Said fairing intended to cover the annular chamber bottom of a turbomachine combustion chamber is described in the document FR2910597 .
  • Said fairing comprises openings to allow the passage of fuel injectors supported by the chamber bottom. Said openings extend to the free end of an outer fixing edge, so that the outer fixing edge is split between some of its attachment points.
  • the invention aims in particular to provide a simple, economical and effective solution to these problems, to avoid the aforementioned drawbacks.
  • it aims to reduce the pressure drop of the air flow coming from a compressor in a turbomachine, between the output of this compressor and the inlet of injection systems of a combustion chamber of the turbomachine , in particular to allow an increase in the pressure drop inside these injection systems without considerably increasing the overall pressure drop of the air flow supplying the combustion chamber.
  • the invention also aims to improve the uniformity of the air supply combustion chamber injection systems.
  • the invention proposes an annular combustion chamber intended to equip a turbomachine, comprising a chamber bottom arranged at the upstream end of the combustion chamber, as well as a plurality of air injection and air injection systems. fuel distributed circumferentially around an axis of the combustion chamber and mounted on the chamber bottom.
  • the annular combustion chamber further comprises, associated with each injection system, an air manifold comprising two walls mounted on the chamber bottom and projecting upstream to form an obstacle to a circumferential flow of air around the chamber. the axis of the combustion chamber, and an air inlet opening formed at the upstream end of the aforementioned air collector.
  • the air intake opening of each air collector is open radially outwards with respect to an axis of the corresponding injection system.
  • the air collectors according to the invention can optimally channel a flow of air from a radially outer region relative to the respective axes of the injection systems and feeding these injection systems, around each of these systems.
  • Air collectors thus make it possible to reduce the pressure drop experienced by this flow of air upstream of these injection systems, and to make the air supply of these systems more uniform.
  • the portion of said opening which is located radially outwardly with respect to the aforesaid tangential plane has an opening area greater than that of the part of said opening which is located radially inward with respect to this tangential plane.
  • This configuration further optimizes the intake of air from a radially outer region relative to the respective axes of the injection systems of the combustion chamber.
  • Each air manifold comprises two walls which are mounted on the chamber bottom, project upstream, and are arranged on either side of the corresponding injection system, these walls forming an obstacle to a circumferential flow of air around the axis of the combustion chamber.
  • each air collector has a concavity turned towards said air collector and are connected to one another by two opposite ends of each of these walls, so that each air manifold has a generally tubular shape and has an upstream end forming said air inlet opening.
  • each air manifold is shaped so that a radially inner portion of the upstream end is offset upstream relative to a radially outer portion of said upstream end of the air collector.
  • the combustion chamber comprises an annular fairing of chamber bottom arranged upstream of the chamber bottom and to which the walls of each air manifold are connected substantially sealingly on either side of an orifice corresponding formed in the shroud and forming said air intake opening of the air collector.
  • the aforementioned walls allow to delimit compartments forming air collectors between the chamber bottom and the fairing, around each injection system.
  • each air collector extends radially and each of these walls is part of two consecutive air collectors around the axis of the combustion chamber.
  • This configuration has the particular advantage of minimizing the total number of air collector walls.
  • each air manifold preferably has a flared shape radially outwardly.
  • the annular fairing may comprise a radially inner annular portion and a radially outer annular portion between which said air intake openings are formed, the radially inner annular portion being offset upstream relative to at the radially outer annular portion.
  • the shape of the fairing makes it possible to orient the air intake opening radially outwards.
  • each injection system comprising an injector head centering and guiding sleeve
  • each air collector preferably comprises at least one part extending upstream beyond an upstream end of said bushing of the corresponding injection system.
  • the air collectors and have optimal abilities to channel air admitted into the injection systems that equip the combustion chamber.
  • the invention also relates to a turbomachine comprising a combustion chamber of the type described above.
  • the Figures 1 to 2 represent a combustion chamber 10 of a turbomachine according to a demonstrative example as well as the immediate environment of this combustion chamber.
  • the combustion chamber 10 is housed in an enclosure 12 which is arranged downstream of a compressor of the turbomachine, of the centrifugal type, the output of which is connected to a radial diffuser 14, itself connected at the output to a flow rectifier 16 which opens into a radially outer region of the enclosure 12.
  • the combustion chamber 10 is delimited by two substantially cylindrical coaxial walls 18 and 20, respectively internal and external, and by an annular chamber bottom 22 which extends substantially radially at the upstream end of the chamber 10 and which is connected by its radial ends to both walls 18 and 20.
  • the inner 18 and outer 20 walls of the combustion chamber 10 are attached downstream by two inner and outer ferrules 24 and 26 respectively on a substantially cylindrical inner wall 28 connected to the diffuser 14, and on an outer casing 30, so as to delimit the enclosure 12.
  • Injection systems 32 which are regularly distributed around the axis 34 of the combustion chamber, are mounted in the chamber bottom 22.
  • Each injection system 32 comprises in particular a centering and guiding bushing 36.
  • a head 38 of a fuel injector 40, and air inlet ports 42 arranged around an axis 44 of the injection system.
  • each injection system 32 aligns the corresponding injector head 38 on the axis 44 of the injection system.
  • the injection systems 32 are configured to allow a certain radial and axial displacement of the injector heads 38, to take account of any differential expansions likely to cause relative displacements between the injectors 40 and the combustion chamber 10.
  • the air flow 46 which arrives in a radially outer region of the enclosure 12, separates into three parts in this chamber 12.
  • a first portion 48 of the air flow flows downstream along the outer wall 20 of the combustion chamber 10, and partially enters the combustion chamber 10 through orifices 50 formed in its outer wall 20.
  • a second portion 52 of the air flow flows downstream along the internal wall 18 of the combustion chamber 10, and partially enters the combustion chamber 10 through orifices 54 formed in its inner wall 18.
  • a third portion 56 of the air flow feeds the injection systems 32 of the combustion chamber 10.
  • the combustion chamber 10 is equipped with a plurality of air collectors 58 (one of which is visible on the Figures 1 to 2 ).
  • Each air manifold 58 comprises two similar walls 60 and 62 ( figure 1 ) which are curved around the injection system 32 corresponding by having a concavity facing the injection system 32, and which are mounted on the chamber bottom 22 at their respective downstream ends.
  • each air collector 58 each comprise two opposite end edges, respectively 60a, 60b and 62a, 62b, through which these two walls 60 and 62 are connected to each other. the other, so that each air manifold 58 has a generally tubular shape.
  • the air manifolds 58 each have an upstream end edge defining an air inlet opening 64, through which air 56 from the rectifier 16 can penetrate to reach the air inlet ports 42 of the injection systems 32.
  • each air collector 58 The two walls 60, 62 of each air collector 58 are truncated upstream along a plane inclined relative to the axis 44 of the corresponding injection system so that the air intake opening 64 of each collector air 58 is open towards the outlet of the rectifier 16, that is to say open radially outwardly relative to the axis 44 of the aforementioned injection system, to facilitate the entry of air from this rectifier 16 in the air collectors 58.
  • each air manifold 58 thus has a radially inner portion 66 which is offset upstream with respect to a radially outer portion 68 of the upstream edge.
  • each air manifold 58 extends upstream beyond the upstream end of the bushing 36 for centering and guiding the corresponding injector head 38.
  • This radially inner portion 66 thus forms a scoop which is particularly effective for guiding the flow of air 56 coming from the rectifier 16.
  • the inclination of the air intake opening 64 of each air manifold 58 with respect to the axis 44 of the corresponding injection system is notably defined so as not to hinder axial and radial displacements of the injector head 38 corresponding in operation and also during assembly and disassembly of the injector 40.
  • the air intake opening 64 forms with the axis 44 an angle ⁇ ( figure 2 ) which is typically between about 40 degrees and 80 degrees.
  • each air manifold 58 is fixed at their downstream end to an annular piece 70, sometimes called a cup stopper, which is integral with the chamber bottom 22, and which comprises an annular flange 72 extending radially about the axis 44 of the corresponding injection system 32, and an annular flange 74 which extends parallel to the 44 axis from the inner periphery of the annular flange 72 of the stop cup 70.
  • annular piece 70 sometimes called a cup stopper
  • Fixing the walls 60 and 62 on the stop cup 70 is for example made by welding and so that the walls 60 and 62 extend in the extension of the annular rim 74 of the stop cup 70.
  • the stop cup 70 makes it possible to axially block the injection system 32 by cooperation of the annular flange 72 of the stop cup with an annular flange 76 secured to the injection system 32 and mounted sliding radially in an annular groove formed between the chamber bottom 22 and the flange 72 of the stop cup 70.
  • the air collectors 58 make it possible to channel the air coming from the straightener 16 around each injection system 32, which makes it possible to reduce the pressure losses upstream of these injection systems improve the uniformity of the air supply of these injection systems.
  • the air collectors 58 have a remarkable property in that they each form an obstacle to the flow of air circumferentially between two neighboring injection systems, along the chamber bottom 22.
  • the figure 3 represents an embodiment of the invention in which the bottom 22 of the combustion chamber 10 is equipped with an annular protective fairing 78 arranged upstream of the chamber bottom 22.
  • the shroud 78 has a radially inner continuous annular portion 80 which has an edge 82 fastened together on an inner rim 84 of the chamber bottom 22 and on an upstream edge 86 of the inner wall 18 of the combustion chamber 10.
  • the fairing 78 further comprises air intake openings 88 which are arranged opposite each injection system 32 and which extend outwards as far as the radially outer end of the fairing 78 so that the latter has a radially outer edge 90 split at each of these openings 88.
  • This outer edge 90 of the shroud is fixed jointly on an outer rim 92 of the chamber bottom 22 and on an upstream edge 94 of the outer wall 20 of the combustion chamber 10.
  • the air intake openings 88 are thus open radially outwardly relative to the axis 44 of each injection system 32, which facilitates the flow of the air stream 56 from the rectifier 16 and feeding injection systems 32.
  • each air inlet opening 88 may have a shape centered on an axis 95 contained in a plane passing through the axis 44 of the corresponding injection system and by the axis 34 of the combustion chamber, and which is offset radially outwardly with respect to said axis 44 of the injection system or inclined with respect to this axis 44.
  • figure 4 illustrates an opening 88 of this type seen in projection in the aforementioned transverse plane P1.
  • each air intake opening 88 extends between a radially outer portion 102 of the fairing and the radially inner annular portion 80 of said fairing 78, which radially inner portion 80 is shifted towards the outside. upstream relative to the radially outer portion 102 above.
  • the bottom 22 of the combustion chamber 10 is equipped with pairs of collector walls 96 and 98 arranged on either side of each injection system 32 and on the other side. corresponding aperture 88, as shown in FIG. figure 3 .
  • These collector walls 96, 98 are flat and project upstream from the chamber bottom 22 extending in respective substantially radial planes with respect to the axis 34 of the combustion chamber.
  • Only one wall 96, 98 of the air collector 100 is provided between two adjacent injection systems 32, so that each wall 96, 98 of the air collector 100 participates in the formation of two collectors. 100 neighbors.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel-Injection Apparatus (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (6)

  1. Ringförmige Brennkammer (10), die dazu bestimmt ist, eine Turbomaschine auszurüsten, und die einen Kammerboden (22), der an dem stromaufwärtigen Ende der Brennkammer (10) angeordnet ist, eine ringförmige Kammerbodenverkleidung (78), die dem Kammerboden (22) vorgeordnet ist, sowie eine Vielzahl von Luft- und Treibstoffeinspritzsystemen (32) umfasst, die um eine Achse (34) der Brennkammer (10) umfangsmäßig verteilt und an dem Kammerboden (22) angebracht sind, wobei die Brennkammer (10) ferner, jedem Einspritzsystem (32) zugeordnet, einen Luftsammler (100) umfasst, der zwei Wände (96, 98) aufweist, die an dem Kammerboden (22) angebracht und sich auf beiden Seiten des Einspritzsystems (32) stromaufwärts erstrecken, um ein Hindernis für eine Luftumfangsströmung um die Achse (34) der Brennkammer (10) zu bilden, wobei die Wände (96, 98) an die ringförmige Kammerbodenverkleidung (78) auf beiden Seiten einer entsprechenden Öffnung, welche in der ringförmigen Kammerbodenverkleidung (78) ausgebildet ist und eine Luftzuführöffnung (88) an dem stromaufwärtigen Ende des Luftsammlers (100) bildet, im Wesentlichen dicht angeschlossen sind, wobei die Luftzuführöffnung (88) in Bezug auf eine Achse (44) des Einspritzsystems radial nach außen offen ist, wobei die Brennkammer (10) dadurch gekennzeichnet ist, dass die Wände (96, 98) sich radial erstrecken und dass eine jede dieser Wände (96, 98) zu zwei aufeinanderfolgenden Luftsammlern (100) gehört.
  2. Ringförmige Brennkammer nach Anspruch 1, dadurch gekennzeichnet, dass wenn die Luftzuführöffnung (88) eines jeden Luftsammlers (100) in Projektion in eine Querebene (P1) senkrecht zu einer durch die Achse (44) des entsprechenden Einspritzsystems (32) verlaufenden Tangentialebene (P2) betrachtet wird, der Teil der Öffnung (88), welcher in Bezug auf die Tangentialebene (P2) radial außerhalb gelegen ist, eine größere Öffnungsfläche als der Teil der Öffnung (88) aufweist, welcher in Bezug auf die Tangentialebene (P2) radial innerhalb gelegen ist.
  3. Ringförmige Brennkammer nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass die Luftzuführöffnung (88) eines jeden Luftsammlers (100) eine radial nach außen erweiterte Form aufweist.
  4. Ringförmige Brennkammer nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass die ringförmige Verkleidung (78) einen radial inneren Ringteil (80) und einen radial äußeren Ringteil (102) umfasst, zwischen denen die Luftzuführöffnungen (88) ausgebildet sind, wobei der radial innere Ringteil (80) gegenüber dem radial äußeren Ringteil (102) in stromaufwärtiger Richtung versetzt ist.
  5. Ringförmige Brennkammer nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass, da jedes Einspritzsystem (32) eine Hülse (36) zum Zentrieren und zum Führen eines Injektorkopfes umfasst, jeder Luftsammler (100) wenigstens ein Teil umfasst, das sich in stromaufwärtiger Richtung über ein stromaufwärtiges Ende der Hülse (36) des entsprechenden Einspritzsystems (32) hinaus erstreckt.
  6. Turbomaschine, dadurch gekennzeichnet, dass sie eine Brennkammer (10) nach einem der vorhergehenden Ansprüche umfasst.
EP10708769.4A 2009-03-17 2010-03-15 Turbomotorbrennkammer mit einer verbesserten primärluft-zufuhreinrichtung Active EP2409085B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0951673A FR2943403B1 (fr) 2009-03-17 2009-03-17 Chambre de combustion de turbomachine comprenant des moyens ameliores d'alimentation en air
PCT/EP2010/053249 WO2010105999A1 (fr) 2009-03-17 2010-03-15 Chambre de combustion de turbomachine comprenant des moyens ameliores d'alimentation en air

Publications (2)

Publication Number Publication Date
EP2409085A1 EP2409085A1 (de) 2012-01-25
EP2409085B1 true EP2409085B1 (de) 2015-02-25

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Country Status (8)

Country Link
US (1) US9127841B2 (de)
EP (1) EP2409085B1 (de)
CN (1) CN102362120B (de)
BR (1) BRPI1008982B1 (de)
CA (1) CA2754419C (de)
FR (1) FR2943403B1 (de)
RU (1) RU2527932C2 (de)
WO (1) WO2010105999A1 (de)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2964725B1 (fr) * 2010-09-14 2012-10-12 Snecma Carenage aerodynamique pour fond de chambre de combustion
FR3011317B1 (fr) * 2013-10-01 2018-02-23 Safran Aircraft Engines Chambre de combustion pour turbomachine a admission d'air homogene au travers de systemes d'injection
FR3017255B1 (fr) 2014-02-03 2017-10-13 Snecma Bougie d'allumage a semi-conducteur pour turbomachine d'aeronef, comprenant des ecopes d'evacuation d'eventuels reliquats de carburant
FR3035481B1 (fr) * 2015-04-23 2017-05-05 Snecma Chambre de combustion de turbomachine comportant un dispositif de guidage de flux d'air de forme specifique
EP3252378A1 (de) * 2016-05-31 2017-12-06 Siemens Aktiengesellschaft Ringbrennkammer-anordnung einer gasturbine
US10619856B2 (en) * 2017-03-13 2020-04-14 Rolls-Royce Corporation Notched gas turbine combustor cowl
US10907831B2 (en) * 2018-05-07 2021-02-02 Rolls-Royce Corporation Ram pressure recovery fuel nozzle with a scoop
US10982852B2 (en) 2018-11-05 2021-04-20 Rolls-Royce Corporation Cowl integration to combustor wall

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0153842B1 (de) * 1984-02-29 1988-07-27 LUCAS INDUSTRIES public limited company Brennkammer für Gasturbinen
US5142858A (en) * 1990-11-21 1992-09-01 General Electric Company Compact flameholder type combustor which is staged to reduce emissions
RU2062405C1 (ru) * 1992-10-23 1996-06-20 Владимир Алексеевич Маев Камера сгорания
US5623827A (en) * 1995-01-26 1997-04-29 General Electric Company Regenerative cooled dome assembly for a gas turbine engine combustor
US6148600A (en) 1999-02-26 2000-11-21 General Electric Company One-piece sheet metal cowl for combustor of a gas turbine engine and method of configuring same
US7222488B2 (en) * 2002-09-10 2007-05-29 General Electric Company Fabricated cowl for double annular combustor of a gas turbine engine
US6779268B1 (en) 2003-05-13 2004-08-24 General Electric Company Outer and inner cowl-wire wrap to one piece cowl conversion
FR2881813B1 (fr) * 2005-02-09 2011-04-08 Snecma Moteurs Carenage de chambre de combustion de turbomachine
FR2909163B1 (fr) * 2006-11-28 2011-02-25 Snecma Carenage de chambre de combustion de turbomachine.
FR2910597B1 (fr) * 2006-12-22 2009-03-20 Snecma Sa Carenage pour fond de chambre de combustion
FR2918444B1 (fr) 2007-07-05 2013-06-28 Snecma Deflecteur de fond de chambre, chambre de combustion le comportant et moteur a turbine a gaz en etant equipe
FR2941287B1 (fr) 2009-01-19 2011-03-25 Snecma Paroi de chambre de combustion de turbomachine a une seule rangee annulaire d'orifices d'entree d'air primaire et de dilution
FR2964725B1 (fr) 2010-09-14 2012-10-12 Snecma Carenage aerodynamique pour fond de chambre de combustion

Also Published As

Publication number Publication date
RU2527932C2 (ru) 2014-09-10
EP2409085A1 (de) 2012-01-25
BRPI1008982B1 (pt) 2021-01-26
CA2754419C (fr) 2017-04-04
FR2943403B1 (fr) 2014-11-14
BRPI1008982A2 (pt) 2016-03-22
RU2011141837A (ru) 2013-04-27
CN102362120A (zh) 2012-02-22
CN102362120B (zh) 2014-07-16
WO2010105999A1 (fr) 2010-09-23
US9127841B2 (en) 2015-09-08
US20120055164A1 (en) 2012-03-08
CA2754419A1 (fr) 2010-09-23
FR2943403A1 (fr) 2010-09-24

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