EP2530383B1 - Chambre de combustion de turbine à gaz - Google Patents

Chambre de combustion de turbine à gaz Download PDF

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Publication number
EP2530383B1
EP2530383B1 EP10844548.7A EP10844548A EP2530383B1 EP 2530383 B1 EP2530383 B1 EP 2530383B1 EP 10844548 A EP10844548 A EP 10844548A EP 2530383 B1 EP2530383 B1 EP 2530383B1
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EP
European Patent Office
Prior art keywords
fuel
gas turbine
cylindrical portion
air
compressed air
Prior art date
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Active
Application number
EP10844548.7A
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German (de)
English (en)
Other versions
EP2530383A4 (fr
EP2530383A1 (fr
Inventor
Atsushi c/o Kawasaki Jukogyo K.K. HORIKAWA
Hideki c/o Kawasaki Jukogyo K.K. OGATA
Kenta c/o Kawasaki Jukogyo K.K. YAMAGUCHI
Ryusuke c/o Kawasaki Jukogyo K.K. MATSUYAMA
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.)
Kawasaki Heavy Industries Ltd
Kawasaki Motors Ltd
Original Assignee
Kawasaki Heavy Industries Ltd
Kawasaki Jukogyo KK
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Priority claimed from JP2010016521A external-priority patent/JP4838888B2/ja
Application filed by Kawasaki Heavy Industries Ltd, Kawasaki Jukogyo KK filed Critical Kawasaki Heavy Industries Ltd
Publication of EP2530383A1 publication Critical patent/EP2530383A1/fr
Publication of EP2530383A4 publication Critical patent/EP2530383A4/fr
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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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
    • 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

Definitions

  • the present invention relates to a combustor (hereinafter referred to as a gas turbine combustor) in a gas turbine or a jet engine for an aircraft.
  • a gas turbine combustor hereinafter referred to as a gas turbine combustor
  • annular type combustor shown in Fig. 7 is widely used (see Non-Patent Literature 1).
  • the annular type combustor includes an annular combustion tube 8 defined by an annular outer liner 9, an annular inner liner 10, and a cowling 20 located upstream of the annular outer liner 9 and the annular inner liner 10.
  • the interior of the combustion tube 8 serves as a combustion chamber 11.
  • a support member 21 constituting a portion of the cowling 20 supports a swirler 14 via a heat shield 23.
  • the heat shield 23 protects the support member 21 from heat generated by combustion in the interior of the combustion chamber 11.
  • the swirler 14 is a device which swirls compressed air CA for combustion and supplies it to the combustion chamber 11, to enable stable combustion.
  • a fuel injector 13 for injecting a fuel penetrates the cowling 20 through an opening 20a of the cowling 20 and is internally fitted to the swirler 14.
  • EP 0 521 687 A1 which forms the basis for the preamble of claim 1, discloses a combustor dome assembly which includes an annular support plate fixedly joined to a combustion liner which confines combustion gases.
  • the support plate includes a plurality of circumferentially spaced support openings for supporting respective carburetors, and respective splashplates fixedly joined coaxially to each of the support openings.
  • Each of the splashplates includes an intermediate flared portion spaced axially downstream from an intermediate portion of the support plate to define a plenum, and a distal end spaced radially away from the liner to define a circumferential extending outlet gap in flow communication with the plenum.
  • US 4,584,834 A discloses a carburetion assembly including flow control means which is provided for controlling a discharge spray angle of a fuel and air mixture thereof.
  • the flow control means can comprise a plurality of circumferentially spaced apertures in a shroud member which are effective for providing a control portion of compressor airflow in a downstream, axial direction from a swirler stage of the swirler assembly.
  • the apertures provide a predetermined amount of airflow circumferentially about the fuel and air mixture for constraining the mixture and controlling the discharge spray angle thereof.
  • Non-Patent Literature 1 " Technologies for High Performance Turbofan Engine” written by Satoshi Yashima, Defense Technology Journal, 92.8, Vol. 12, No. 8 (ISSN 0285-0893), P31-40 Figure 8
  • annular space 39 defined by a rear end wall 25 of the swirler 14, a cylindrical portion 23b of the heat shield 23, and a guide member 34.
  • the annular space 39 opens in the combustion chamber 11 at a downstream side. Therefore, in the annular space 39, an air-fuel mixture M containing a fuel becomes stagnant and soot 60 tends to be deposited. If the deposited soot 60 is heated by combustion gas, a portion of the guide member 34 of the swirler 14 or a portion of the cylindrical portion 23b of the heat shield 23 may be damaged.
  • the present invention is directed to solving the above mentioned problem, and an object of the present invention is to provide a gas turbine combustor in which soot is less likely to be deposited therein.
  • the invention provides a gas turbine combustor according to claim 1.
  • the air-fuel mixture having flowed through the guide member and the air introduced through the purge hole flow along the flare. This results in a back-flow zone having a proper speed component in a center axis portion. Thus, good flame stabilizing performance can be ensured.
  • the air introduced through the purge hole suppresses the air-fuel mixture which has flowed through the guide member from diffusing radially outward in the combustor. This can prevent the fuel in the air-fuel mixture from adhering onto the heat shield and liquid droplets of the fuel from increasing in size. As a result, degradation of combustion performance can be suppressed.
  • the air introduced through the purge hole is the compressed air generated in the compressor.
  • the purge hole preferably includes 10 to 30 purge holes formed on a circumference of the cylindrical portion. If the purge holes are less than ten in number, it is difficult to introduce the compressed air into the space between the guide member and the cylindrical portion of the heat shield uniformly in the circumferential direction. Therefore, the flow of the compressed air cannot effectively push out the fuel, the air-fuel mixture, and flame, which are going to enter the space, into the combustion chamber. If the purge holes are greater than thirty in number, deposition of the soot cannot be prevented substantially effectively, but process work will increase and cost will increase.
  • the flare is inclined 40 to 60 degrees with respect to a center axis of the guide member. If the inclination angle is less than 40 degrees, the swirl flow of the compressed air from the swirler cannot be expanded radially sufficiently when it is supplied to the interior of the combustion chamber, which makes it difficult to form a back-flow zone having a sufficient area. On the other hand, if the inclination angle is greater than 60 degrees, the swirl flow of the compressed air from the swirler is separated from the inner surface of the flare, which makes it impossible to form a back-flow zone having a desired area.
  • the swirl flow of the compressed air from the swirler can be flowed into the combustion chamber while expanding it up to a suitable angle, and thus, a good back-flow zone can be formed.
  • the air introduced through the purge hole pushes out the fuel, the air-fuel mixture and the flame which are going to enter the space between the guide member and the cylindrical portion of the heat shield, and thus, deposition of soot on the guide member can be prevented effectively.
  • Fig. 1 is a schematic longitudinal sectional view in a direction perpendicular to a canter axis of a gas turbine combustor 1 according to an embodiment of the present invention.
  • the combustor 1 is configured to mix compressed air supplied from a compressor (not shown) and a fuel to generate an air-fuel mixture and combust the air-fuel mixture in the interior thereof.
  • High-temperature and high-pressure combustion gas generated by combustion in the combustor 1 is sent to a turbine and actuates the turbine.
  • the combustor 1 is an annular type combustor. As shown in Fig. 1 , the combustor 1 is configured in such a manner that an annular housing 2 is defined by an outer casing 3 and an inner casing 4, and an annular combustion tube 8 is defined by an outer liner 9 and an inner liner 10 in the interior of the annular housing 2. An annular inner space is formed in the interior of the combustion tube 8. This inner space serves as a combustion chamber 11.
  • a plurality of (e.g., 14 to 20) fuel injection devices 12 for injecting a fuel to the interior of the combustion chamber 11 are arranged at equal intervals in a circumferential direction thereof.
  • Each fuel injection device 12 includes a fuel injector 13 for injecting the fuel and a main swirler 14 of a radial flow type.
  • the main swirler 14 is configured to swirl compressed air and introduce it into the combustion chamber 11.
  • the main swirler 14 encloses the outer periphery of the fuel injector 13.
  • Two ignition plugs 18 are mounted to the lower portion of the combustor 1.
  • a cowling 20 includes an annular cowling outer 20A and an annular cowling inner 20B.
  • the outer liner 9 is fastened to the cowling outer 20A, while the inner liner 10 is fastened to the cowling inner 20B.
  • the cowling outer 20A has a retaining tube member 29 integrally formed therewith.
  • a fastening pin 30 is inserted into the retaining tube member 29 from outside of the outer casing 3.
  • the combustion tube 8 is fastened to the outer casing 3 by means of the fastening pin 30.
  • the downstream end portion of the cowling outer 20A and the downstream end portion of the cowling inner 20B are coupled to each other by means of an annular support member (hereinafter referred to as a dome) 21.
  • the dome 21 is attached with a heat shield 23 for protecting the dome 21 from heat generated by combustion in the interior of the combustion chamber 11.
  • the fuel injection device 12 includes a stem 15 containing a fuel pipe therein.
  • the fuel injector 13 is attached to the tip end of the stem 15.
  • the main swirler 14 is a radial-flow type swirler which introduces the compressed air CA from radially outward to radially inward.
  • the main swirler 14 is mounted to the hear shield 23 via a retaining plate 24. This mounting structure will be described later.
  • the stem 15 of the fuel injection device 12 is fastened to the outer casing 3 via a mounting plate 28.
  • the fuel injector 13 penetrates the top portion of the cowling 20 through an opening 20a formed between the cowling outer 20A and the cowling inner 20B, and is internally fitted to the main swirler 14.
  • An annular gap is formed between the peripheral edge of the opening 20a of the cowling 20 and the fuel injector 13. Through the annular gap, the compressed air CA is introduced into the combustion tube 8.
  • a first-stage nozzle TN of the turbine is coupled to the downstream end portion of the combustion tube 8.
  • the fuel injector 13 of the fuel injection device 12 includes an axial (axial-flow) inner swirler 31 at a center portion thereof and an axial outer swirler 32 at an outer peripheral side.
  • the swirlers 31 and 32 are laid out around a center axis C2 of the fuel injection device 12.
  • an annular fuel passage 33 is provided to introduce a fuel F supplied from the fuel pipe inside the stem 15 to the interior of the combustion chamber 11.
  • a plurality of fuel injection holes 33a are arranged annularly around the center axis C2.
  • the fuel F is injected through the injection holes 33a and supplied in a film form from the tip end of the fuel passage 33 to the interior of the combustion chamber 11.
  • the fuel F injected through the injection holes 33a is atomized into small particles by the swirl flow of the compressed air CA from the inner and outer swirlers 31 and 32, and is transformed into the air-fuel mixture M, which is supplied to the interior of the combustion chamber 11.
  • the fuel injection device 12 is of an air blast type.
  • the heat shield 23 is positioned downstream of the main swirler 14.
  • the heat shield 23 includes a shield body 23a of a trapezoidal shape when viewed from a direction of the center axis C2 ( Fig. 3 ) of the fuel injection device 12, and a cylindrical portion 23b protruding toward the upstream side of the fuel injection device 12 such that the shield body 23a and the cylindrical portion 23b have a unitary structure.
  • the inner space of the cylindrical portion 23b is a central through-hole 27.
  • the heat shield 23 is placed annularly to have a predetermined gap (e.g., 1mm).
  • the hole edge portion of the retaining hole 21a is welded to the dome 21 and a large-diameter stepped portion 23c formed on the outer peripheral surface of the cylindrical portion 23b of the heat shield 23. This allows the heat shield 23 to be fastened to the dome 21.
  • the inner peripheral edge portion of the ring-shaped retaining plate 24 is welded to a small-diameter portion 23d formed on the opening edge portion of the cylindrical portion 23b of the heat shield 23. This allows the retaining plate 24 to be fastened to the heat shield 23.
  • a tubular guide member 34 is provided integrally with a rear end wall 25 positioned downstream of the main swirler 14.
  • the guide member 34 serves to introduce the swirl flow of the compressed air CA from the main swirler 14 into the combustion chamber 11.
  • the guide member 34 is placed concentrically with the cylindrical portion 23b of the heat shield 23 on the inner peripheral side of the cylindrical portion 23b.
  • a flare 38 is coupled to the downstream end of the guide member 34 and is inclined from radially outward relative to the fuel injector 13 toward a downstream side. In other words, the flare 38 is configured to have a diameter which increases toward the downstream side.
  • the guide member 34 and the flare 38 may be formed integrally with each other.
  • a combustion zone S ( Fig. 2 ) can be set by adjusting this swirl flow.
  • the rear end wall 25 of the main swirler 14 includes mounting plates 26 protruding radially outward.
  • the mounting plates 26 are provided in two locations such that the mounting plates 26 face each other.
  • the mounting plates 26 have pin holes 26a, respectively.
  • the retaining plate 24 has a pair of recesses 24a which open in an outer peripheral portion thereof.
  • Mounting pins 41 are inserted into the recesses 24a, respectively.
  • the mounting pins 41 are fitted into and secured to the pin holes 26a, respectively.
  • the recess 24a of the retaining plate 24 has a circumferential width greater than the outer diameter of the mounting pin 41. Therefore, the main swirler 14 is supported on the retaining plate 24 such that the main swirler 14 is displaceable in the circumferential direction and in the radial direction. This makes it possible to absorb a displacement between the main swirler 14 and the heat shield 23 which occurs due to a difference in thermal expansion rate between the components which is caused by high-temperature combustion gas, or an assembling process.
  • An annular space 39 is defined by the rear end wall 25 located downstream of the main swirler 14, the cylindrical portion 23b of the heat shield 23, and the guide member 34 located radially inward relative to the cylindrical portion 23b of the heat shield 23.
  • the annular space 39 is coaxial with the fuel injection device 12 and opens toward the downstream side.
  • Purge holes 40 are formed in a portion of the cylindrical portion 23b which is upstream of a location at which the dome 21 is fastened to the cylindrical portion 23b.
  • the plurality of purge holes 40 are formed at circumferentially equal intervals on the circumference of the cylindrical portion 23b, and through the purge holes 40, the compressed air CA is introduced from radially outward into the annular space 39.
  • the purge holes 40 penetrate the cylindrical portion 23b radially.
  • the compressed air CA introduced into the annular space 39 through the purge holes 40 flows into the combustion chamber 11 through an outlet 39a at the downstream end of the annular space 39.
  • the flow of the compressed air CA can push back the fuel F, the air-fuel mixture M, and a flame which are going to enter the annular space 39, into the combustion chamber 11.
  • Ten to thirty purge holes 40 are formed at circumferentially equal intervals on the circumference of the cylindrical portion 23b. If the purge holes 40 are less than ten in number, it becomes difficult to introduce the compressed air CA into the annular space 39 between the guide member 34 and the heat shield 23, uniformly in the circumferential direction. Therefore, the flow of the compressed air CA cannot effectively push back the fuel F, the air-fuel mixture M, and the flame, which are going to enter the annular space 39, into the combustion chamber 11. If the purge holes 40 are greater than thirty in number, deposition of the soot cannot be prevented effectively, but process work will increase and cost will increase. Preferably, the purge hole 40 has a diameter of about 1 ⁇ 0.3mm.
  • the flow rate of the compressed air CA introduced through the purge holes 40 is about 10 ⁇ 5 % of the flow rate of the compressed air CA from the main swirler 14.
  • the flow rate of the compressed air CA from the main swirler 14 is preferably reduced by that flow rate.
  • a total flow rate of the compressed air CA introduced into the combustion chamber 11 is equal to the flow rate in a case where no purge holes 40 are provided. Therefore, preset combustion performance can be maintained.
  • the compressed air CA is introduced through the purge holes 40, into a space in which the soot tends to be deposited in a conventional combustor, specifically, the annular space 39, and can push back the fuel F, the air-fuel mixture M, and flame which are going to enter the annular space 39, into the combustion chamber 11.
  • the flare 38 mainly has two functions.
  • the first function is to serve as a guide section which guides the flow of the compressed air CA introduced through the purge holes 40, in a radially outward direction (changes the direction of the flow). That is, as shown in Fig. 3 , the flare 38 forms a flow passage extending in an obliquely outward direction toward the downstream side, between the outer peripheral surface thereof and the heat shield 23.
  • the flare 38 causes the compressed air CAto flow along this flow passage such that the compressed air CA is guided in the obliquely outward direction toward the downstream side. It is desired that a portion of the heat shield 23 which faces the flare 38 be inclined in a radially outward direction toward the downstream side. In this configuration, resistance in the flow passage can be reduced, and a more stable flow can be supplied to the interior of the combustion chamber 11.
  • the second function is to adjust the flow of the compressed air CA which has passed through the guide member 34.
  • the swirl flow of the compressed air CA which has passed through the guide member 34 flows along the inner peripheral surface of the flare 38. Therefore, by adjusting the inclination angle or the like of the flare 38, the swirl flow of the compressed air CA can be adjusted. As described above, it is very important to adjust the swirl flow of the compressed air CA, in setting the combustion zone S.
  • the compressed air CA supplied from the swirler 14 flows radially outward relative to the fuel injection device 12 in the interior of the combustion chamber 11 along the inner surface 23e of the heat shield 23.
  • a pressure decreases over a wide range in the vicinity of the center axis, thereby causing the released compressed air CA to flow at a high speed, toward the wide range in the vicinity of the center axis. That is, as a whole, the compressed air CA forms a circulation flow P1 which flows while expanding radially outward, and then strongly flows back toward the center axis portion of the combustion chamber 11.
  • the air-fuel mixture M disperses as shown in Fig. 5D .
  • the air-fuel mixture M supplied from the fuel injector 13 is pushed back by the circulation flow PI, and a large amount of air-fuel mixture M is present in the vicinity of the fuel injector 13 in the interior of the combustion chamber 11. Therefore, in some cases, it is less likely that the air-fuel mixture M reaches the combustion zone S with an adequate amount.
  • the air-fuel mixture M is guided by the compressed air CA to flow along the inner surface 23e of the heat shield 23, and the fuel in the air-fuel mixture M adheres onto the inner surface 23e of the heat shield 23 and forms liquid droplets. If the fuel adhering onto the inner surface 23e of the heat shield 23 is supplied in a state of great liquid droplets to the combustion zone of the combustion chamber 11, the fuel is atomized insufficiently, and thus, high ignition performance and stable combustion performance cannot be achieved.
  • the compressed air CA which has flowed into the annular space 39 flows along the outer peripheral surface of the flare 38 in the obliquely outward direction toward the downstream side in the interior of the combustion chamber 11 such that the flow of the compressed air CA expands to a suitable degree.
  • the compressed air CA flowing in the obliquely outward direction toward the downstream side wraps the compressed air CA from the main swirler 14 and the air-fuel mixture M, from radially outward, and prevents the compressed air CA from the main swirler 14 and the air-fuel mixture M, from expanding excessively.
  • the inclination angle of the flare 38 with respect to the center axis of the guide member 34 is preferably set to a range of 40 degrees to 60 degrees. If the inclination angle is less than 40 degrees, the swirl flow of the compressed air CA from the main swirler 14 cannot be expanded radially sufficiently when it is supplied to the interior of the combustion chamber 11, which makes it difficult to form a back-flow zone having a sufficient area. On the other hand, if the inclination angle is greater than 60 degrees, the swirl flow of the compressed air CA from the main swirler 14 is separated from the inner surface of the flare 38, which makes it impossible to form a back-flow zone having a desired area.
  • the inclination angle of the flare 38 is set to 45 degrees, it is possible to form the swirl flow of the compressed air CA which can achieve highest combustion efficiency.
  • the inclination angle of the inner peripheral surface of the flare 38 is equal to the inclination angle of the outer peripheral surface of the flare 38, they may be made different.
  • the flare 38 is configured to have a thickness increasing toward the downstream side, the inclination angle of the inner peripheral surface is smaller than the inclination angle of the outer peripheral surface.
  • the gas turbine combustor 1 by introducing the compressed air CA into the annular space 39 through the purge holes 40, it is possible to prevent deposition of the soot and damage by combustion. In addition, the size of the liquid droplets of the fuel F is reduced and combustion performance is improved. Furthermore, by using the flare 38 provided at the downstream end of the guide member 34, the flow of the compressed air CA which has flowed through the main swirler 14 and the dispersion distribution of the fuel F injected from the fuel injector 13 can be controlled in an optimized manner. As a result, higher ignition performance and stable combustion performance can be achieved with a considerably improved level. This could be confirmed based on actual measurement result of Fig. 6 .
  • a horizontal axis indicates an air flow rate of the combustor 1
  • a vertical axis indicates an air-fuel ratio of the overall combustor 1.
  • White-circle symbols indicate flameout
  • black-circle symbols indicate fire (ignition).
  • Characteristic curve lines A and B represented by solid lines indicate actual measurement results of the gas turbine combustor 1 of the present invention.
  • X symbols indicate misfire (ignition failure) of the gas turbine combustor 1 of the present invention, while ⁇ symbols indicate misfire (ignition failure) of the conventional gas turbine combustor.
  • the air-fuel ratio with which the flame blows out is much higher in the gas turbine combustor 1 of the present invention, than in the conventional gas turbine combustor.
  • the air-fuel ratio with which the air-fuel mixture M can be ignited is much higher in the gas turbine combustor 1 of the present invention, than in the conventional gas turbine combustor.
  • the air-fuel ratio with which misfire occurs is much higher, in the gas turbine combustor 1 of the present invention, than in the conventional gas turbine combustor.
  • the gas turbine combustor 1 of the present invention can ignite the air-fuel mixture M surely with a higher air-fuel ratio, i.e., with a lesser fuel F.
  • the flameout and misfire are less likely to occur even when the air-fuel ratio is high.
  • the gas turbine combustor 1 of the present invention can perform combustion stably with a high air-fuel ratio, and improve a combustion efficiency. Therefore, the amount of generation of CO 2 can be reduced.
  • the gas turbine combustor 1 of the present invention is equivalent to the conventional combustor of Fig. 7 , regarding a pressure loss in the interior of the combustor 1, a temperature distribution at an outlet of the combustion tube 8, a combustion efficiency, the amount of smoke, and the amount of emission of NO x .
  • the gas turbine combustor 1 of the present invention can be implemented merely by providing the purge holes 40 and the flare 38 at the downstream end of the guide member 34, in the conventional combustor.
  • the present invention is also applicable to a combustor of a back flow can type.
  • the present invention is not limited to the above embodiment, but can be added, changed or deleted in various ways within a scope of the present invention. Such addition, change and deletion can be included in the scope of the present invention as defined by the appended claims.

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  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
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  • General Engineering & Computer Science (AREA)

Claims (4)

  1. Chambre de combustion de turbine à gaz comprenant :
    un dôme (21) ayant un trou de retenue (21a) ;
    un injecteur de carburant (13) pour injecter un carburant vers une chambre de combustion (11) ;
    une coupelle de turbulence (14) qui aspire l'air comprimé généré dans un compresseur et fait tourbillonner l'air comprimé, à proximité de l'injecteur de carburant (13) ;
    un élément de guidage (34) tubulaire pour guider l'air comprimé aspiré depuis la coupelle de turbulence (14) et un mélange air-carburant d'un carburant injecté depuis l'injecteur de carburant (13), vers la chambre de combustion (11) ; et
    un écran thermique (23) ayant un corps d'écran (23a) et une partie cylindrique (23b) située vers l'extérieur par rapport à l'élément de guidage (34), la partie cylindrique (23b) faisant saillie vers un côté amont d'un dispositif d'injection de carburant (12) de sorte que le corps d'écran (23a) et la partie cylindrique (23b) aient une structure unitaire ;
    la partie cylindrique (23b) ayant un trou de purge (40) ; et
    de l'air étant introduit par le trou de purge (40) et étant amené dans un espace formé entre l'élément de guidage (34) et la partie cylindrique (23b), la chambre de combustion de turbine à gaz comprenant en outre :
    une section de guidage (38) de l'élément de guidage (34) tubulaire pour guider l'air introduit à travers le trou de purge (40), vers une région dans une direction obliquement vers l'extérieur vers un côté aval,
    la section de guidage (38) étant un évasement disposé au niveau d'une extrémité aval de l'élément de guidage (34) et ayant un diamètre augmentant vers le côté aval, et
    une partie de l'écran thermique (23), la partie faisant face à la section de guidage (38), étant inclinée radialement vers l'extérieur,
    caractérisée en ce que la chambre de combustion de turbine à gaz comprend en outre une plaque de retenue annulaire (24) ayant une paire d'évidements (24a) qui s'ouvrent dans une position périphérique extérieure de celle-ci ;
    le corps d'écran (23a) a une forme trapézoïdale lorsqu'il est vu depuis une direction d'un axe central (C2) du dispositif d'injection de carburant (12) ;
    une surface périphérique extérieure de la partie cylindrique (23b) ayant une partie étagée de grand diamètre (23c) est soudée au trou de retenue (21a) du dôme (21) ;
    une partie de petit diamètre (23d) formée sur une partie de bord d'ouverture de la partie cylindrique (23b) est soudée à une partie de bord périphérique interne de la plaque de retenue annulaire (24) ;
    l'élément de guidage (34) tubulaire est placé concentriquement autour de la partie cylindrique (23b) de l'écran thermique (23) et est muni intégralement d'une paroi d'extrémité arrière (25) positionnée en aval de la coupelle de turbulence (14) ;
    la paroi d'extrémité arrière (25) comprend des plaques de montage (26) faisant saillie radialement et disposées au niveau de deux emplacements se faisant face ;
    les plaques de montage (26) ont des trous de goupille (26a) et des goupilles de montage (41) sont insérées dans les évidements (24a), respectivement ;
    la coupelle de turbulence (14) est supportée sur la plaque de retenue (24) en montant les goupilles (41) insérées dans les trous de goupille (26a) et fixées à ceux-ci, respectivement, de sorte que la coupelle de turbulence (14) puisse être déplacée dans une direction circonférentielle et dans une direction radiale.
  2. Chambre de combustion de turbine à gaz selon la revendication 1,
    l'air introduit à travers le trou de purge (40) étant l'air comprimé généré dans le compresseur.
  3. Chambre de combustion de turbine à gaz selon la revendication 1 ou 2,
    le trou de purge (40) comprenant de 10 à 30 trous de purge formés sur une circonférence de la partie cylindrique (23b).
  4. Chambre de combustion de turbine à gaz selon l'une quelconque des revendications 1 à 3,
    l'évasement étant incliné de 40 à 60 degrés par rapport à un axe central de l'élément de guidage (34).
EP10844548.7A 2010-01-28 2010-11-29 Chambre de combustion de turbine à gaz Active EP2530383B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2010016521A JP4838888B2 (ja) 2009-05-27 2010-01-28 ガスタービン燃焼器
PCT/JP2010/006931 WO2011092779A1 (fr) 2010-01-28 2010-11-29 Chambre de combustion de turbine à gaz

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EP2530383A1 EP2530383A1 (fr) 2012-12-05
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EP2530383B1 true EP2530383B1 (fr) 2019-09-18

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JP5924618B2 (ja) * 2012-06-07 2016-05-25 川崎重工業株式会社 燃料噴射装置
JP6410133B2 (ja) * 2014-08-18 2018-10-24 川崎重工業株式会社 燃料噴射装置
US10041679B2 (en) * 2015-06-24 2018-08-07 Delavan Inc Combustion systems
US10578021B2 (en) 2015-06-26 2020-03-03 Delavan Inc Combustion systems
GB201515883D0 (en) 2015-09-08 2015-10-21 Rolls Royce Plc Cooling apparatus for a fuel injector

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CA2070518C (fr) * 1991-07-01 2001-10-02 Adrian Mark Ablett Ensemble dome pour chambre de combustion
DE19508111A1 (de) * 1995-03-08 1996-09-12 Bmw Rolls Royce Gmbh Hitzeschild-Anordnung für eine Gasturbinen-Brennkammer
US6442940B1 (en) * 2001-04-27 2002-09-03 General Electric Company Gas-turbine air-swirler attached to dome and combustor in single brazing operation
US6834505B2 (en) * 2002-10-07 2004-12-28 General Electric Company Hybrid swirler
FR2893390B1 (fr) * 2005-11-15 2011-04-01 Snecma Fond de chambre de combustion avec ventilation
JP4421620B2 (ja) * 2007-02-15 2010-02-24 川崎重工業株式会社 ガスタービンエンジンの燃焼器

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US5941076A (en) * 1996-07-25 1999-08-24 Snecma-Societe Nationale D'etude Et De Construction De Moteurs D'aviation Deflecting feeder bowl assembly for a turbojet engine combustion chamber

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EP2530383A1 (fr) 2012-12-05
WO2011092779A1 (fr) 2011-08-04

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