EP3320269B1 - Gebogene brennkammer eines turbinenmotors - Google Patents

Gebogene brennkammer eines turbinenmotors Download PDF

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Publication number
EP3320269B1
EP3320269B1 EP16748329.6A EP16748329A EP3320269B1 EP 3320269 B1 EP3320269 B1 EP 3320269B1 EP 16748329 A EP16748329 A EP 16748329A EP 3320269 B1 EP3320269 B1 EP 3320269B1
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EP
European Patent Office
Prior art keywords
flame tube
combustion chamber
injection system
axis
injector
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.)
Active
Application number
EP16748329.6A
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English (en)
French (fr)
Other versions
EP3320269A1 (de
Inventor
Guillaume Aurélien GODEL
Alain René CAYRE
Romain Nicolas Lunel
Haris MUSAEFENDIC
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.)
Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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Publication date
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Application filed by Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Priority to PL16748329T priority Critical patent/PL3320269T3/pl
Publication of EP3320269A1 publication Critical patent/EP3320269A1/de
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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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/425—Combustion chambers comprising a tangential or helicoidal arrangement of the flame tubes
    • 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
    • F23R2900/03342—Arrangement of silo-type combustion chambers

Definitions

  • the invention relates to the field of combustion chambers for turbomachines and more particularly the structure and the fixing of a flame tube in a combustion chamber of a turbomachine.
  • a turbomachine downstream of a high-pressure compressor (not shown), a turbomachine comprises a combustion chamber delimited by inner revolution casings 1b and external la which are concentric.
  • the combustion chamber comprises a flame tube 2 disposed in the space defined by the inner casings 1b and external 1a.
  • the flame tube 2 is delimited by internal walls 2b and external 2a called internal and external ferrules and a bottom plate of chamber 3 which serves as a support for injectors 4.
  • the combustion chamber also comprises a shroud 5 arranged in front of the chamber floor to partially cover the injectors 4 in order to protect them from possible shocks (that can occur when ingestion of a bird or an ice block in engines) and reduce aerodynamic energy losses to improve engine consumption.
  • the combustion chamber comprises an air diffuser 6 opening on the injector 4 which allows to cool the injectors 4.
  • the bottom plate 3, the inner walls 2b and outer 2a of the flame tube 2 and the fairing 5 are assembled by bolts (not shown).
  • the combustion chamber of the figure 1 is said to be annular axial direct in that it extends in the preferred direction of the motor axis without reversal cylindrical shells flame tube.
  • This architecture is the reference for modern turbomachines, especially on high power. In the field of small powers, it coexists with the return chamber architecture which is very compact axially. However, it has the main disadvantage a large area-to-volume ratio which makes it difficult to cool the walls of the flame tube and handicaps their lifetimes.
  • the invention proposes to overcome at least one of these disadvantages.
  • the invention proposes, according to a first aspect, a combustion chamber of a turbomachine according to claim 1.
  • the invention is advantageously completed by the following characteristics, taken alone or in any of their technically possible combination.
  • the mouth comprises a straight portion extending tangentially to the circular portion and a diverging portion extending from the circular portion.
  • the circular portion has a constant radius around the injector axis.
  • the circular portion has a growing radius around the injector axis.
  • the mouth has a general shape: circular, rectangular, profiled.
  • the flame tube is connected to the outer casing via said injection system in connection with the chamber bottom.
  • the invention also relates to a turbomachine comprising a combustion chamber according to the invention.
  • the invention makes it possible to bring air from the diffuser more efficiently.
  • the invention makes it possible to lower the pressure drop between the diffuser and the inlet of the collector.
  • the outlet flow of the compressor partially feeds the injector (between 10% and 30% of the total flow compressor output).
  • the remaining percentage is both reintroduced along the flame tube via the various holes (primary holes, dilution holes and multi-perforation) and is also used to cool a set of parts of the turbine unit.
  • the diffuser compressor outlet
  • the invention solves this problem by placing between the diffuser outlet and the inlet of the injection system a manifold whose role is to capture a portion of the air flow and achieve aerodynamic continuity.
  • This device makes it possible to optimize the compressor / injection system connection, to channel the flow towards the injection system and to reduce the passage of orifices or the circumvention of parts by the flow.
  • the particular shape of the manifold allows to direct the flow of air before admission into the injection system to improve the supply of the injection system.
  • the injection system is composed of several tendrils whose role is to generate a rotating flow output of the injection system. These tendrils have a wedging angle (between 10 ° and 80 ° with respect to the injector axis).
  • the feed of the tendrils is not optimal in the case of a conventional injection system whose main axis is inclined relative to the mean direction of the flow at the outlet of the diffuser.
  • the flow can be made to make significant changes of direction to feed a spin which has a singular transition, detrimental to the performance of the combustion chamber module.
  • the invention that solves this problem is to use one of the two side walls of the manifold to guide the flow before admission into the injection system without applying to the flow other significant change of direction other than expected by its rotation.
  • This technical solution makes it possible to generate an overall rotation movement around the axis around which the tendrils are arranged, which is beneficial for feeding the tendrils.
  • the figures 2 and 3 illustrate views of a combustion chamber according to one embodiment.
  • the combustion chamber comprises an outer casing 10a to which is connected a flame tube 20.
  • the flame tube 20 comprises an inner annular wall 20b and an outer annular wall 20a.
  • the inner and outer annular walls define on the one hand a first radial portion 201 around a radial axis Y of the combustion chamber and which extends radially with respect to a longitudinal axis XX of rotation of the turbomachine.
  • the inner and outer annular walls define a second axial portion 202 about a longitudinal axis X perpendicular to the radial axis Y and parallel to the longitudinal axis XX of rotation of the turbomachine.
  • the first portion 201 extends to the second portion 202 forming a bend between the inlet and the outlet of the flame tube.
  • Such a bend allows an effective aerodynamic connection with a high pressure stage downstream of the gas flow (dashed arrow on the figure 2 ).
  • this bent shape makes it possible to reduce the axial size of the flame tube 20.
  • the combustion chamber also comprises a chamber bottom 30 which has the shape of a plate located at the inlet of the flame tube 20.
  • combustion chamber may optionally include a heat shield 50 in the form of a plate attached to the chamber bottom 30 located in the flame tube 20.
  • This heat shield 50 is located at the entrance of the flame tube 20 and protects the injection system 40 from high temperatures above 2200 K that can prevail in the flame tube 20.
  • Primary holes 202a, 202b are drilled in the inner and outer annular walls at the first portion 201 at the inlet of the flame tube.
  • dilution holes 203a, 203b are drilled in the inner and outer annular walls at the bent portion of the flame tube 20 (see FIG. figure 3 ).
  • the number of holes, their respective diameters and positions may vary depending on the intended application.
  • a diffuser 60 can bring air to the injection system 40 to cool it.
  • the injection system 40 comprises an injector body 40a surrounding an injection pipe 40b through which the fuel is introduced as such into the flame tube 20.
  • the injector body 40a is fixed to the outer casing 10a by means of bolts 70 and fixing plates 80 (see FIG. figure 3 ).
  • the inner and outer annular walls are fixed to the outer casing 10a via the injector body 40a thus making it possible to simplify the bowl-chamber connection and thus to avoid the use of a play-catching system.
  • a connecting disk 40c surmounted by a cylinder 40d in which is inserted the body 40a of the injector is connected to the chamber bottom 30 in which a recess 30a to the size of the connecting disk has been formed.
  • the body 40a of the injector is connected to the injection pipe 40b and the body 40a of the injection system 40 is inserted into the cylinder 40d surmounting the connecting disk 40c so that the injector body 40a ( and therefore the injection pipe 40b) is movable relative to the cylinder 40d. This allows a compensation of the movements to which the flame tube 20 is subjected. There is therefore no need for complex compensation systems.
  • the injector body 40a comprises an air inlet 40e through which air from the diffuser 60 is introduced. This air makes it possible to supply air to the injection system 40.
  • the air inlet 40e has, in a nonlimiting manner, the shape of an oval recess formed in the injector body 40a. It will therefore be understood that other forms can be envisaged.
  • the combustion chamber according to a second embodiment differs from the first embodiment by the structure of an injection system 40 'of a second type.
  • the flame tube 20 involved in this second embodiment is identical to that previously described.
  • the injection system 40 ' is attached to the chamber bottom 30, the flame tube 20 being connected to the outer casing 10a of the turbomachine via the injection system 40'.
  • the injection system 40 'in this second embodiment comprises an injector body 40'a surmounting a circular connecting structure 40'c comprising at least one connecting disc.
  • the connecting structure 40'c is inserted into the chamber bottom 30 in which a recess of the size of the circular connecting structure has been formed.
  • the collector 40'd is integral with the injector body 40'a.
  • the inner and outer annular walls are fixed to the outer casing 10a via the injector body 40'a thus making it possible to simplify the connection between the bowl and the chamber bottom and thus to avoid the use of a system of catching up games.
  • the injector body 40 ' surrounds an injection pipe 40' (along the injector axis AA ') through which the fuel is fed as such into the flame tube 20.
  • the injector axis AA' is coincides with the radial axis Y, so as to be parallel to the first radial portion 201 of the flame tube 20.
  • an air collector 40'd overcomes the injection pipe 40'b.
  • the tendrils are formed by vanes arranged around a parallel implantation axis with the injector axis AA '.
  • This collector is arranged near the diffuser 60 without being connected to the latter (in which case the vibrations could damage the structure). In addition, the collector is physically separated from the diffuser because of the expansion rates that are different.
  • the air collector 40'd may be in the axis AA 'of the injection system and comprises a circular portion 41 surrounding the injection pipe 40'b according to a constant radius.
  • This circular portion 41 has identical dimensions to the injector body 40'a. From this circular portion 41 extends a mouth 42 through which air from the diffuser 60 is introduced.
  • the mouth 42 has a straight portion 43 tangent to the circular portion 41 and a diverging portion 44 from the circular portion 41 (or converging from the air inlet).
  • the collector can of course take other forms.
  • the circular shape of this circular part 41 makes it possible to facilitate the rotation of the air flow around the axis of implantation of the tendrils which coincides with the injector axis AA 'on the exemplary embodiment illustrated in FIGS. Figures 6 and 7 .
  • the air collector 40'd can be offset relative to the axis AA 'of the injector. In these figures, it is deported to the left but can of course be deported to the right of the axis AA 'of the injector.
  • the collector comprises a circular portion 41 'having a radius increasing around the injection pipe (non-constant radius around the injection pipe).
  • the circular portion 41 ' first extends in a constant radius on a first portion, and a radius increasing beyond (volute type). And from this circular portion 41 'extends the mouth 42 having a straight portion 43 tangential to the circular portion and a diverging portion 44 from the circular portion.
  • the mouth 42 can take several forms: rectangular, circular or profiled.
  • the latter can prevent water entering the engine in the case of ingestion of water or hail from entering the collector and then injected into the flame tube, especially in the primary combustion zone.
  • the outer radius of the mouth 42 may be judiciously adapted to not capture the water (liquid or vapor) which is preferably on the outer radii of the centrifugal wheel and the axial diffuser.

Landscapes

  • 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)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)

Claims (7)

  1. Brennkammer eines Turbinenmotors, umfassend:
    - ein äußeres ringförmiges Gehäuse (10a);
    - ein an das äußere Gehäuse (10a) angeschlossenes Flammrohr, wobei das Flammrohr (20) eine innere ringförmige Wand (20b) und eine äußere ringförmige Wand (20a) umfasst, die zum einen einen radialen ersten Abschnitt (201) am Eingang des Flammrohrs und zum anderen einen axialen zweiten Abschnitt (202) am Ausgang des Flammrohrs bilden, wobei sich der erste Abschnitt (201) des Flammrohrs (20) zum zweiten Abschnitt (202) erstreckt und dabei eine Krümmung zwischen dem Eingang und dem Ausgang des Flammrohrs (20) bildet, wobei das Flammrohr ferner einen Kammerboden (30) umfasst, der sich am Eingang des Flammrohrs (20) befindet;
    - ein Brennstoff-Einspritzsystem (40'), das konfiguriert ist, um Brennstoff in das Flammrohr über den Eingang des Flammrohrs einzuspritzen, wobei das Einspritzsystem eine Einspritzachse (AA') umfasst und eine zu einer Längsachse Y, gemäß der sich der erste Abschnitt (201) erstreckt, koaxiale Hauptrichtung aufweist, wobei das Einspritzsystem (40') einen Luftsammler umfasst, umfassend einen kreisförmigen Teil (41) um die Einspritzachse, wobei der kreisförmige Teil, ab dem sich eine Mündung (42) erstreckt, einen Lufteinlass des Sammlers bildet, wobei die Mündung (42) konfiguriert ist, um die eintretende Luftströmung um die Montageachse in Rotation zu versetzen, damit sie die Schrauben versorgt, wobei die Brennkammer dadurch gekennzeichnet ist, dass die Einspritzachse (AA') des Einspritzsystems parallel zum ersten Abschnitt (201) ist, dass das Einspritzsystem (40') Schrauben (40'e) umfasst, die um eine Montageachse angeordnet sind, die zur Einspritzachse (AA') parallel ist, und dass der Luftsammler (40'd) ferner konfiguriert ist, um Luft zu den Schrauben (40'e) des Einspritzsystems (40') zu führen.
  2. Brennkammer nach Anspruch 1, wobei die Mündung (42) einen geraden Teil (43) umfasst, der sich tangential zum kreisförmigen Teil (41) erstreckt, und einen divergierenden Teil (44), der sich ab dem kreisförmigen Teil (41) erstreckt.
  3. Brennkammer nach einem der Ansprüche 1 bis 2, wobei der kreisförmige Teil (41) einen konstanten Radius um die Einspritzachse (AA') aufweist.
  4. Brennkammer nach einem der Ansprüche 1 bis 2, wobei der kreisförmige Teil (41) einen um die Einspritzachse (AA') zunehmenden Radius aufweist.
  5. Brennkammer nach einem der Ansprüche 1 bis 4, wobei die Mündung (42) eine kreisförmige, rechteckige oder Profilform aufweist.
  6. Brennkammer nach einem der Ansprüche 1 bis 5, wobei das Flammrohr an das externe Gehäuse (10a) über das Einspritzsystem (40) in Verbindung mit dem Kammerboden (30) angeschlossen ist.
  7. Turbinenmotor, umfassend eine Brennkammer nach einem der vorangehenden Ansprüche.
EP16748329.6A 2015-07-08 2016-07-07 Gebogene brennkammer eines turbinenmotors Active EP3320269B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL16748329T PL3320269T3 (pl) 2015-07-08 2016-07-07 Zagięta komora spalania maszyny wirowej

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1556482A FR3038699B1 (fr) 2015-07-08 2015-07-08 Chambre de combustion coudee d'une turbomachine
PCT/FR2016/051735 WO2017006063A1 (fr) 2015-07-08 2016-07-07 Chambre de combustion coudée d'une turbomachine

Publications (2)

Publication Number Publication Date
EP3320269A1 EP3320269A1 (de) 2018-05-16
EP3320269B1 true EP3320269B1 (de) 2019-03-13

Family

ID=54199854

Family Applications (1)

Application Number Title Priority Date Filing Date
EP16748329.6A Active EP3320269B1 (de) 2015-07-08 2016-07-07 Gebogene brennkammer eines turbinenmotors

Country Status (6)

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US (1) US11125435B2 (de)
EP (1) EP3320269B1 (de)
CN (1) CN107735619B (de)
FR (1) FR3038699B1 (de)
PL (1) PL3320269T3 (de)
WO (1) WO2017006063A1 (de)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3090747B1 (fr) * 2018-12-21 2021-01-22 Turbotech Chambre de combustion d'une turbomachine
US20220252268A1 (en) * 2019-06-07 2022-08-11 Safran Helicopter Engines Method for manufacturing a flame tube for a turbomachine
FR3107564B1 (fr) * 2020-02-24 2022-12-02 Safran Helicopter Engines Ensemble de combustion pour turbomachine

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US3605405A (en) * 1970-04-09 1971-09-20 Gen Electric Carbon elimination and cooling improvement to scroll type combustors
US3648457A (en) * 1970-04-30 1972-03-14 Gen Electric Combustion apparatus
JPS548890B1 (de) * 1971-04-01 1979-04-19
US4081957A (en) * 1976-05-03 1978-04-04 United Technologies Corporation Premixed combustor
US4458481A (en) * 1982-03-15 1984-07-10 Brown Boveri Turbomachinery, Inc. Combustor for regenerative open cycle gas turbine system
FR2827367B1 (fr) * 2001-07-16 2003-10-17 Snecma Moteurs Systeme d'injection aeromecanique a vrille primaire anti-retour
US6834505B2 (en) * 2002-10-07 2004-12-28 General Electric Company Hybrid swirler
US7310952B2 (en) * 2003-10-17 2007-12-25 General Electric Company Methods and apparatus for attaching swirlers to gas turbine engine combustors
US7437876B2 (en) * 2005-03-25 2008-10-21 General Electric Company Augmenter swirler pilot
FR2886714B1 (fr) * 2005-06-07 2007-09-07 Snecma Moteurs Sa Systeme d'injection anti-rotatif pour turbo-reacteur
CA2621958C (en) * 2005-09-13 2015-08-11 Thomas Scarinci Gas turbine engine combustion systems
US7716931B2 (en) * 2006-03-01 2010-05-18 General Electric Company Method and apparatus for assembling gas turbine engine
EP1994260B1 (de) * 2006-03-15 2017-09-20 Siemens Aktiengesellschaft Brennkammer für eine gasturbine umfassend eine verstellvorrichtung
CN201991616U (zh) * 2011-01-25 2011-09-28 苏艾今 超燃双工质汽轮机
RU2604260C2 (ru) * 2011-05-17 2016-12-10 Снекма Кольцевая камера сгорания для турбомашины
FR3035707B1 (fr) 2015-04-29 2019-11-01 Safran Aircraft Engines Chambre de combustion coudee d'une turbomachine

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Also Published As

Publication number Publication date
WO2017006063A1 (fr) 2017-01-12
FR3038699A1 (fr) 2017-01-13
US20180209649A1 (en) 2018-07-26
PL3320269T3 (pl) 2019-07-31
EP3320269A1 (de) 2018-05-16
CN107735619B (zh) 2019-07-05
US11125435B2 (en) 2021-09-21
FR3038699B1 (fr) 2022-06-24
CN107735619A (zh) 2018-02-23

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