EP3483503B1 - Joint d'étanchéité du brûleur d'une turbine à gaz et son procédé de fabrication - Google Patents

Joint d'étanchéité du brûleur d'une turbine à gaz et son procédé de fabrication Download PDF

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Publication number
EP3483503B1
EP3483503B1 EP17201073.8A EP17201073A EP3483503B1 EP 3483503 B1 EP3483503 B1 EP 3483503B1 EP 17201073 A EP17201073 A EP 17201073A EP 3483503 B1 EP3483503 B1 EP 3483503B1
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EP
European Patent Office
Prior art keywords
funnel
burner seal
cooling
combustion chamber
burner
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
EP17201073.8A
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German (de)
English (en)
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EP3483503A1 (fr
Inventor
Carsten Clemen
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
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Rolls Royce Deutschland Ltd and Co KG
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Publication date
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Priority to EP17201073.8A priority Critical patent/EP3483503B1/fr
Publication of EP3483503A1 publication Critical patent/EP3483503A1/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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2206/00—Burners for specific applications
    • F23D2206/10—Turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/14—Special features of gas burners
    • F23D2900/14001—Sealing or support of burner plate borders
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00018—Manufacturing combustion chamber liners or subparts
    • 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
    • F23R2900/03042—Film cooled combustion chamber walls or domes

Definitions

  • the invention relates to a burner seal of a gas turbine and to a method for its production.
  • the invention relates to a burner seal with an essentially tubular base body, which has an annular inlet lip on an inflow side and a funnel on its outflow side, an inside diameter of the inflow side being larger than an inside diameter of a sealing surface arranged axially in front of the funnel, wherein cooling channels are formed distributed around the circumference in the base body.
  • a burner seal of the above type is used to seal fuel nozzles of a combustion chamber of a gas turbine against a head plate and / or a heat shield of the combustion chamber.
  • the funnel of the burner seal protrudes into the combustion chamber and is exposed to the high temperatures prevailing there. As a result, it is necessary to cool the burner seal and in particular the funnel sufficiently. If the cooling is insufficient, there is a risk that the funnel with the funnel-shaped lip formed on it will burn off.
  • FIG. 2 a simplified axial sectional view of a gas turbine combustor with a burner seal.
  • Fig. 3 is a schematic sectional view, analog Fig. 2 , the burner seal shown.
  • the combustion chamber shown comprises a combustion chamber wall 1 with a top plate 2, which is protected from the combustion chamber by means of a heat shield 3.
  • a heat shield 3 On the inside of the combustion chamber wall 1, shingles 7 are arranged, which by means of bolts 10 and nuts 11 are screwed to the combustion chamber wall 1 and shield it from the combustion chamber.
  • FIG. 2 The construction shown is an annular combustion chamber. It goes without saying that this has an outer and an inner combustion chamber wall in relation to a radial direction based on an engine center axis. For the sake of simplicity, this is shown in Fig. 2 not explained in detail.
  • admixing holes 8 are provided, which also reach through the shingles 7 and serve to supply mixed air.
  • the combustion chamber wall is provided with impingement cooling holes 12, the shingles 7 have effusion cooling holes 13. All of this is known from the prior art, so that a detailed further description can be dispensed with.
  • the Fig. 2 further shows that the heat shield 3 is provided with cooling holes 14, through which cooling air, which flows through cooling air holes 15 of the top plate 2, is used to cool the heat shield 3.
  • the heat shield 3 is, as in Fig. 2 shown, mounted on the head plate 2 by means of bolts 10 and nuts 11.
  • Both the top plate 2 and the heat shield 3 have a recess in which a burner seal 6 is arranged.
  • a fuel nozzle 5, which is only shown schematically, is introduced from the outside through the burner seal 6. This is carried out through a recess in the combustion chamber head 4 and positioned in the burner seal 6.
  • the burner seal 6 is floatingly mounted between the head plate 2 and the heat shield 3. This allows the fuel nozzle 5 to move relative to the combustion chamber and at the same time has the purpose of the fuel nozzle 5 to be placed in such a way that no leakage occurs between the fuel nozzle 5 and the top plate 2 or the heat shield 3.
  • the Fig. 2 shows the dashed lines in a simplified representation of the flow path of cooling air which flows from the interior of the combustion chamber head 4 along the burner seal 6.
  • the Fig. 3 shows the structure of the burner seal 6 according to the prior art in a simplified representation.
  • the burner seal 6 comprises an inlet lip 18, which is adjoined in the axial direction (in relation to a central axis of the fuel nozzle 5) by a diameter region with a larger inner diameter. This results in flow paths to in the Fig. 3 initiate cooling air flow shown in dashed lines and discharge it through cooling holes 9.
  • the cooling holes 9 are arranged in the axial direction in front of a sealing surface 16.
  • the sealing surface 16 lies against the fuel nozzle 5 in a sealing manner.
  • a funnel 17 (funnel-shaped lip) is provided which extends into the interior of the combustion chamber, as shown in FIG Fig. 2 is shown.
  • the burner seal 6 comprises an annular web 19 which is used to fasten and mount the burner seal 6 on the head plate 2 or the heat shield 3.
  • the burner seal 6 is aerodynamically favorable upstream of the combustion chamber head 4 in order to prevent the inflow of the cooling air (see Fig. Fig. 3 ) to improve.
  • the inlet lip 18, which guides the flow from the combustion chamber head 4 to the fuel nozzle 5, is used for this purpose.
  • the burner seal 6 has a funnel-shaped shape (funnel 17) in order to allow the flow from the fuel nozzle to open radially as far as possible.
  • the funnel 17, which protrudes into the combustion chamber, must be cooled sufficiently to prevent it from burning off.
  • the cooling air is passed through the discrete cooling air holes 9.
  • the cooling holes 9 serve to guide the flow from the combustion chamber head 4 radially outwards from the inside of the burner seal 6 to the outside thereof and to flow around the funnel 17 from its rear side.
  • the funnel 17 is cooled on its rear side by the cooling air before the cooling air flows between the heat shield 3 and the burner seal 6 into the combustion chamber.
  • the funnel 17 of the burner seal 6 is only cooled on its rear side, which is facing away from the combustion chamber. As a result, it cannot be sufficiently ensured that the funnel 17 and thus the burner seal 6 will overheat and wear out, for example due to burning. Thus, the burner seal 6 must be replaced when worn. This requires extensive assembly work that is costly and time consuming.
  • Another disadvantage is that the air flowing out of the burner seal 6 cannot be used to control emissions from the combustion chamber, since the air flow is very indeterminate and non-targeted.
  • US 2015/260409 A1 a gas turbine combustion chamber with a head plate and an outer and an inner combustion chamber wall, the combustion chamber being formed by segments or subsegments which are manufactured in one piece by means of a DLD process and are welded to one another.
  • US 2015/260409 A1 shows a burner seal according to the preamble of claim 1.
  • FIG. 12 shows a gas turbine combustor provided with a dome heat shield with a fuel nozzle opening, the opening receiving a floating collar assembly to allow relative movement between the nozzle and the heat shield.
  • the floating collar is provided with an air flap in order to provide the surface of the combustion chamber heat shield with film cooling and thus improve its cooling.
  • US 2014/367494 A1 shows a fuel injector for a gas turbine engine, which comprises a nozzle tip arrangement with a nozzle body, wherein the nozzle body is formed essentially monolithically by additive manufacturing and wherein at least one fuel circuit and at least one air circuit are defined in the nozzle body.
  • the invention is based on the object of creating a burner seal of the type mentioned at the outset which, with a simple structure and simple, inexpensive producibility, avoids the disadvantages of the prior art and enables both improved cooling and improved air flow.
  • Another object of the invention is to provide a method of making an improved burner seal. According to the invention, the object is achieved by the combinations of features in the independent claims.
  • the subclaims show further advantageous embodiments of the invention.
  • the cooling channels are each formed in the base body in the area of the sealing surface and the funnel and each exit from the funnel in an end region of the funnel in an exit hole.
  • the object is achieved in that the burner seal is manufactured using an additive manufacturing method, for example using a laser application method (DLD) or a similar method.
  • DLD laser application method
  • the solution according to the invention creates the possibility of internally cooling in particular the area of the sealing surface and the funnel of the burner seal and the essentially radially outwardly directed area of the funnel up to the end area of the funnel.
  • the cooling channels according to the invention which can be implemented simply and inexpensively using an additive method, serve this purpose. Such cooling channels cannot be created by a conventional drilling process, since their course and their geometry are very complex.
  • the cooling channels are designed in such a way that, viewed in the direction of flow, based on the fuel nozzle, they are arranged inside the burner seal in the area of the sealing surface and exit in the end area of the funnel. As a result, the cooling air flowing through the cooling channels can flow out at the end area of the funnel and effectively cool the entire funnel.
  • the air flow can preferably be designed so that the exiting air is introduced into the interior of the combustion chamber in order to reduce emissions.
  • the exit hole opens into an outermost end region of the funnel. This can ensure that the cooling channel is passed through the entire funnel and emerges at the tip of the funnel, which is essentially directed radially outward. Burning of the funnel tip during operation can thus be avoided in a simple and inexpensive manner. Since the cooling channel thus runs completely through the funnel, the side of the funnel lying in the direction of flow to the combustion chamber and the side of the funnel facing away from the combustion chamber can be effectively cooled to the tip of the funnel.
  • a further improved effective cooling can be achieved if a center line of the outlet hole of the cooling channel at the end region of the funnel is at an angle of 70 to 90 ° a center line of the funnel.
  • the center line of the exit hole is particularly preferably in a range from 70 ° to 80 ° and is more preferably 75 °. In particular in the range between 70 and 80 ° inclination of the center line, exiting cooling air can be mixed into the main flow of the combustion chamber in a streamlined manner.
  • the cooling channel each has an inlet hole which is arranged in a region of the larger inner diameter of the base body of the burner seal. It is particularly advantageous if the entry hole is positioned on an upstream side of the sealing area. As a result, the cooling air can flow into the burner seal through the area with the larger inner diameter and be introduced into the cooling channels in an optimal manner.
  • the cooling channel can be designed in different ways. It can extend in a straight line, at an angle to the central axis of the burner seal, or curved or spiral-shaped.
  • the cooling channel can also be composed of a plurality of straight sections or different curved or curved sections. According to the invention, a wide variety of variants thus arise in order to ensure optimal cooling of the burner seal, in particular the sealing area and the funnel.
  • the cross section of the inlet hole and / or the outlet hole in such a way that an optimized flow occurs.
  • the holes can be circular, elliptical, diamond-shaped or teardrop-shaped.
  • the cooling channels can be of variable cross-sectional shape between the inlet hole and the outlet hole, for example with an elliptical inlet hole and a round outlet hole.
  • the cross-sectional profile of the respective cooling channel can also be designed to be constant between the inlet hole and the outlet hole.
  • the cross section of the cooling channel can also be designed in such a way that the inlet hole represents the smallest area with regard to its cross section and the cooling channel widens in cross section. It can form a cavity and in turn taper towards the exit hole.
  • the burner seal preferably has a number of cooling holes between ten and forty.
  • the narrowest hole diameter (entry hole or exit hole) is, for example, 0.5 mm to 1 mm with a circular cross-section and / or has an area of 0.8 mm 2 to 3 mm 2 .
  • the measures according to the invention improve the cooling of the burner seal, so that there is less wear and tear and lower maintenance costs.
  • the air guidance according to the invention results in improved emission control. In this way, soot emissions in particular can be reduced.
  • the burner seal can be produced with very complex geometries of the cooling channels and their inlet and outlet holes. This is not possible with other manufacturing processes.
  • the gas turbine engine 110 of FIG Fig. 1 Figure 3 is a generally illustrated example of a turbomachine in which the invention may be used.
  • the engine 110 is designed in a conventional manner and comprises, one behind the other in the direction of flow, an air inlet 111, a fan 112 rotating in a housing, a medium-pressure compressor 113, a high-pressure compressor 114, a combustion chamber 115, a high-pressure turbine 116, a medium-pressure turbine 117 and a low-pressure turbine 118 as well as a Exhaust nozzle 119, which are all arranged around a central engine center axis 101.
  • Medium pressure compressor 113 and high pressure compressor 114 each include multiple stages, each of which has a circumferential array of fixed stationary vanes 120, commonly referred to as stator vanes, which extend radially inward from core engine casing 121 into an annular flow passage through compressors 113, 114 protrude.
  • the compressors further have an arrangement of compressor rotor blades 122 which protrude radially outward from a rotatable drum or disk 125, which are coupled to hubs 126 of the high pressure turbine 116 and the medium pressure turbine 117, respectively.
  • the turbine sections 116, 117, 118 have similar stages, including an array of fixed vanes 123 protruding radially inward from the casing 121 into the annular flow passage through the turbines 116, 117, 118, and a subsequent array of turbine blades 124, the protrude outward from a rotatable hub 126.
  • the compressor drum or compressor disk 125 and the blades 122 arranged thereon as well as the turbine rotor hub 126 and the turbine rotor blades 124 arranged thereon rotate about the engine center axis 101 during operation.
  • the Fig. 4 shows different exemplary embodiments of the burner seal 6 according to the invention in a representation analogous to FIG Fig. 3 . It can be seen in particular that adjacent to the area with a larger internal diameter through which the cooling air flows in (see Fig. Fig. 3 ) an inlet hole 20 of a cooling channel 22 is arranged in front of the sealing surface 16 in the axial direction. The air is discharged from the cooling channel 22 through an outlet hole 21.
  • the different design variants of the Fig. 4 show that the outlet hole 21 is positioned on the side of the funnel 17 facing the combustion chamber. As a result, the cooling air exits on the hot side of the funnel 17 and can lay down as a film of cooling air on the surface of the funnel.
  • FIG. 4 shows that the cooling channel 22 can be dimensioned and designed in different ways with regard to its geometry.
  • the cooling channel 22 is arcuately curved
  • the Figure 4b shows an S-shaped curvature, similar to the embodiment according to FIG Figure 4c .
  • the exit hole 21 is provided with an enlarged cross section.
  • the Figure 4e shows a cross section of the cooling channel 22, which has a cavity 23 in its central region.
  • the outlet hole 21 is positioned in a radially outer region of the funnel 17.
  • the Fig. 4g shows a stepped cross-sectional shape of the cooling channel 22 composed of rectilinear components
  • Figure 4h an embodiment shows in which the cooling channel 22 is designed in a helical manner in order to optimize the cooling of the burner seal 6 or the funnel 17.
  • FIG. 11 shows views A and B which are included in FIGS Figures 5 and 6 are based.
  • the Figure 5a each shows round entry holes 20 to which straight ( Figure 5a ), slanted ( Figure 5b ), arched ( Figure 5c ), coiled ( Fig. 5d ), diffuser-like expanded ( Figure 5e ) or provided with a cavity 23 ( Fig. 5f ) Connect the courses of the cooling channels 22.
  • the Fig. 6 shows in view A and view B possible configurations of the inlet holes 20 and the outlet holes 21. These can be circular ( Figure 6a ), oval ( Figures 6b and 6c ) or diamond-shaped ( Fig. 6d ) be designed.
  • the Fig. 7 shows a perspective partial sectional view of the burner seal according to the invention, from which, in particular, the arrangement of the inlet hole 20, the outlet hole 21 and the cooling channel 22 results.
  • FIGS 8 and 9 each show perspective representations of different configuration variants which differ in particular with regard to the configuration and dimensions of the inlet hole 20 and the outlet hole 21.
  • FIGS. 10 to 12 show different variants of a particularly preferred embodiment of the present invention.
  • the burner seal 6 seals on the fuel nozzle 5 with the sealing surface 16.
  • the sealing surface 16 is designed with a smaller inner diameter than the region of the inflow side with the annular inlet lip 18 lying in front of it in the direction of flow.
  • the inlet holes 20 are distributed around the circumference in the transition area between the inflow side and the sealing surface 16. Starting from the inlet hole 20, the cooling channel 22 runs in the funnel 17 up to an outermost end area 17a of the funnel 17 and exits from an outlet hole 21 from the outermost end area 17a.
  • the outermost end region 17a of the funnel 17 is, as in particular from Fig. 10 can be seen, in section arc-shaped, in particular semicircular.
  • the exit hole 21 lies in this arcuate, outermost end region 17a.
  • a central axis 24, which leads through a center point of the outlet hole 21 is arranged at an angle ⁇ to a main axis 25 of the burner seal 6.
  • the angle ⁇ is 75 °. In this way, the cooling air can be guided particularly well through the funnel 17 and when the funnel emerges.
  • the entire funnel 17 can be cooled both on its side facing the combustion chamber and on its side facing away from the combustion chamber.
  • the cooling duct 22 is guided through the funnel 17 in such a way that a wall thickness is the same on the side facing the combustion chamber and on the side facing away from the combustion chamber. This enables particularly good stability of the funnel.
  • a diameter of the cooling channel tapers in the direction of flow 22. The cooling channel is thus designed as a nozzle.
  • the cooling channel can, on the one hand, cool the sealing area 16, at which the burner seal 6 is in contact with the fuel nozzle, and also effectively cool the funnel 17 up to the end area 17a of the funnel.
  • FIGS 11a to 11h show different variants for the shape of the funnel. It becomes clear here that the cooling channel 22 can be dimensioned in the most varied of ways and designed with regard to its geometry.
  • the cooling channel is curved in an arc shape, starting from the inlet hole 20, a straight area is initially formed essentially parallel to the sealing surface 16 and, after the arc, an essentially straight area is again provided up to the outermost end area 17a of the funnel.
  • the exit hole 21 is provided at the extreme tip of the funnel 17.
  • Figure 11b shows an S-shaped curvature of the cooling channel 22, the funnel 17 protruding somewhat further into the combustion chamber.
  • Figure 11c shows an embodiment similar to FIG Figure 11b , wherein the outlet hole 21 is aligned almost at a 90 ° angle to the central axis 25 of the burner seal.
  • Figure 11d shows an embodiment in which a cross section of the cooling channel 22 tapers continuously starting from the inlet hole 20 to the outlet hole 21.
  • Figure 11e shows a cooling channel 22 which has a cavity 23 in a central area.
  • Fig. 11f shows a cooling channel 22, in which a diameter of the entry hole 20 is smaller than a diameter of the exit hole 21.
  • the cooling channel from FIG Fig. 11f a diffuser effect.
  • FIG. 3 shows a stepped cross-sectional shape of the cooling channel 22 composed of straight components.
  • Figure 11h shows a preferred embodiment in which the cooling channel 22 is helical in order to optimize the cooling of the burner seal 6 of the funnel 17, in particular at the end of the burner seal 6 directed towards the combustion chamber.
  • Fig. 12 shows a further particularly preferred embodiment of the invention, which essentially corresponds to that in Fig. 10 corresponds to the embodiment shown.
  • the outermost end region 17a is straight.
  • the outermost end region 17a forms a surface E which is parallel to the central axis 25 of the burner seal 6.
  • the angle ⁇ is exactly 90 °.
  • the shown burner seal 6 of a gas turbine thus provides a significant improvement in the cooling of the burner seal, so that there is less wear and in particular also lower maintenance costs, since the burner seal 6 no longer has to be replaced as frequently as in the prior art.
  • the solution according to the invention of providing the outlet hole 21 at the end region 17a of the funnel 17 results in the possibility of complete cooling of the funnel. It can also be avoided that areas of the funnel 17 that are too hot appear both on the side of the funnel facing the combustion chamber and on the side of the funnel facing away from the combustion chamber.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (10)

  1. Joint d'étanchéité de brûleur d'une turbine à gaz comprenant un corps de base de forme essentiellement tubulaire, qui présente, au niveau d'un côté d'alimentation, une lèvre d'entrée de forme annulaire (18) et, au niveau de son côté d'évacuation, un entonnoir (17), un diamètre intérieur du côté d'alimentation étant supérieur à un diamètre intérieur d'une surface d'étanchéité (16) disposée axialement devant l'entonnoir,
    caractérisé en ce que des canaux de refroidissement (22) sont réalisés dans le corps de base de manière répartie sur la périphérie, les canaux de refroidissement (22) présentant chacun un trou d'entrée (20) et les canaux de refroidissement (22) étant réalisés à chaque fois dans le corps de base dans la région de la surface d'étanchéité (16) et de l'entonnoir (17) et débouchant à chaque fois dans un trou de sortie (21) dans une région d'extrémité (17a) de l'entonnoir (17).
  2. Joint d'étanchéité de brûleur selon la revendication 1, dans lequel le trou de sortie (21) débouche dans une région d'extrémité la plus extérieure (17a) de l'entonnoir.
  3. Joint d'étanchéité de brûleur selon l'une quelconque des revendications précédentes, dans lequel un axe médian (24) du trou de sortie (21) est orienté suivant un angle (a) de 70° à 90°, en particulier de 70° à 80° et plus particulièrement de 75°, par rapport à un axe médian (25) du joint d'étanchéité de brûleur.
  4. Joint d'étanchéité de brûleur selon la revendication 1, dans lequel le trou d'entrée (20) est disposé dans une région du plus grand diamètre intérieur du corps de base.
  5. Joint d'étanchéité de brûleur selon la revendication 1 ou 2, dans lequel le trou d'entrée (20) est disposé dans la région d'étanchéité (16).
  6. Joint d'étanchéité de brûleur selon l'une quelconque des revendications 1 à 5, dans lequel le canal de refroidissement (22) est pourvu d'une section transversale circulaire, elliptique, en forme de losange et/ou en forme de goutte.
  7. Joint d'étanchéité de brûleur selon l'une quelconque des revendications 1 à 6, dans lequel la section transversale du canal de refroidissement (22) est réalisée de manière variable sur sa longueur.
  8. Joint d'étanchéité de brûleur selon l'une quelconque des revendications 1 à 7, dans lequel le canal de refroidissement (22) est réalisé sous forme courbe, cintrée et/ou rectiligne sur sa longueur.
  9. Joint d'étanchéité de brûleur selon l'une quelconque des revendications 1 à 8, dans lequel les surfaces du trou d'entrée (20) et du trou de sortie (21) sont dimensionnées à chaque fois de manière identique ou différente.
  10. Procédé de fabrication d'un joint d'étanchéité de brûleur (6) selon l'une quelconque des revendications 1 à 9, dans lequel des canaux de refroidissement (22) sont réalisés dans le corps de base de manière répartie sur la périphérie, les canaux de refroidissement (22) présentant chacun un trou d'entrée (20) et les canaux de refroidissement (22) étant réalisés à chaque fois dans le corps de base dans la région de la surface d'étanchéité (16) et de l'entonnoir (17) et débouchant à chaque fois dans un trou de sortie (21) dans une région d'extrémité (17a) de l'entonnoir (17), le procédé étant un procédé additif.
EP17201073.8A 2017-11-10 2017-11-10 Joint d'étanchéité du brûleur d'une turbine à gaz et son procédé de fabrication Active EP3483503B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP17201073.8A EP3483503B1 (fr) 2017-11-10 2017-11-10 Joint d'étanchéité du brûleur d'une turbine à gaz et son procédé de fabrication

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Application Number Priority Date Filing Date Title
EP17201073.8A EP3483503B1 (fr) 2017-11-10 2017-11-10 Joint d'étanchéité du brûleur d'une turbine à gaz et son procédé de fabrication

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EP3483503A1 EP3483503A1 (fr) 2019-05-15
EP3483503B1 true EP3483503B1 (fr) 2021-01-06

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Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19508111A1 (de) * 1995-03-08 1996-09-12 Bmw Rolls Royce Gmbh Hitzeschild-Anordnung für eine Gasturbinen-Brennkammer
US7861530B2 (en) * 2007-03-30 2011-01-04 Pratt & Whitney Canada Corp. Combustor floating collar with louver
US20140367494A1 (en) * 2013-06-14 2014-12-18 Delavan Inc Additively manufactured nozzle tip for fuel injector
DE102014204468A1 (de) * 2014-03-11 2015-10-01 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammer sowie Verfahren zu deren Herstellung

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* Cited by examiner, † Cited by third party
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