EP3462089B1 - Ensemble chambre de combustion pourvu de bouclier thermique et joint de brûleur ainsi que procédé de fabrication - Google Patents

Ensemble chambre de combustion pourvu de bouclier thermique et joint de brûleur ainsi que procédé de fabrication Download PDF

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Publication number
EP3462089B1
EP3462089B1 EP18196251.5A EP18196251A EP3462089B1 EP 3462089 B1 EP3462089 B1 EP 3462089B1 EP 18196251 A EP18196251 A EP 18196251A EP 3462089 B1 EP3462089 B1 EP 3462089B1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
heat shield
combustor seal
longitudinal axis
chamber assembly
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
EP18196251.5A
Other languages
German (de)
English (en)
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EP3462089A1 (fr
Inventor
Carsten Clemen
Ruud Eggels
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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Publication date
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Publication of EP3462089A1 publication Critical patent/EP3462089A1/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
    • F23R3/002—Wall structures
    • 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
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • 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
    • F23R2900/00017—Assembling 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
    • 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

Definitions

  • the invention relates in particular to a combustion chamber assembly with a burner seal and a heat shield, and to a method for producing such a combustion chamber assembly.
  • a fuel nozzle for injecting a fuel-air mixture into the combustion chamber of the combustion chamber by means of a burner seal on the combustion chamber.
  • the burner seal has a bearing section which extends along a longitudinal axis and which has a continuous passage opening in which the fuel nozzle is positioned.
  • a heat shield is also provided on the combustion chamber side, which, when properly installed on the combustion chamber of the engine, lies within the combustion chamber and has a through hole through which the bearing section of the burner seal extends.
  • the bearing section of the burner seal protrudes with an opening edge through the through hole of the heat shield so that the opening edge of the burner seal pointing radially outwards with respect to the longitudinal axis and thus widening in the axial direction lies behind the heat shield.
  • the opening angle and diameter of the opening edge at the end of the through opening are limited by the fact that the heat shield has to be pushed over the opening edge when the combustion chamber assembly is mounted on the combustion chamber. So usually the combustion chamber seal from the combustion chamber the combustion chamber, for example on a top plate of the combustion chamber, before the heat shield is then subsequently attached in order to fix the combustion chamber assembly to the combustion chamber.
  • the DE 10 2014 204 468 A1 discloses a combustor assembly according to the preamble of the first claim.
  • the burner seal and the heat shield form an additively manufactured structural unit in which the heat shield is at least partially accommodated between the radially outward opening edge and the at least one radially outwardly extending web, so that (non-destructive) separation of the heat shield from the burner seal the longitudinal axis is excluded.
  • the burner seal and the heat shield thus form an integral unit to be manufactured in advance, which is connected to a combustion chamber, e.g. is to be installed in the area of a head plate of the combustion chamber without the heat shield being able to be attached independently of the burner seal. Rather, the heat shield is held between the opening edge formed by the burner seal and the at least one web formed by the burner seal and extending radially outward on the burner seal, so that removal of the heat shield is not possible without destroying the burner seal. The heat shield can consequently not be displaced over the opening edge or the web along the longitudinal axis relative to the burner seal.
  • the heat shield and the burner seal form an integral structural unit, in which the heat shield is accommodated between the two radially projecting sections of the burner seal (opening edge and web), so that a non-destructive separation of the two components from one another is not possible, the question of subsequent installation arises the heat shield to the burner seal no longer.
  • the design of the opening edge and in particular its opening angle and its diameter are no longer limited by the fact that the heat shield with its through hole has to be pushed over the opening edge.
  • the burner seal and the heat shield are produced additively in a common manufacturing process, for example built up in layers, so that any requirements regarding the mountability of the heat shield to the burner seal no longer have to be taken into account.
  • the assembly consisting of the burner seal and the heat shield is manufactured additively by means of a laser sintering process.
  • the burner seal is floating on the heat shield.
  • the burner seal and the heat shield form an (integral) structural unit, in this embodiment variant the burner seal is consequently kept at least axially displaceable relative to the heat shield. In this way, an axial displacement of the burner seal relative to the heat shield fixed to the combustion chamber is possible during operation of the engine.
  • the floating mounting of the burner seal on the heat shield can also include the fact that the burner seal is held on the heat shield in a radially displaceable manner with respect to the longitudinal axis of the bearing section.
  • the through opening of the burner seal at its end (in the assembled state) lying inside the combustion chamber has a diameter which is larger than a diameter of the through hole in the heat shield due to the radially outward-pointing opening edge.
  • An (end) diameter of the opening edge is thus larger than a maximum diameter of the through hole in the heat shield.
  • the opening edge (axially spaced apart from the heat shield) can extend radially outward to the level of a radially outermost edge of the heat shield or beyond this radially outermost edge of the heat shield. In this way, the opening edge of the burner seal completely covers the heat shield when viewed from the combustion chamber along the longitudinal axis. In such a variant, the opening edge of the burner seal which is drawn further outwards can at least partially assume the function of a heat shield.
  • the design and expansion of the heat shield within the combustion chamber can then be greatly simplified. For example, any cooling knobs, cooling fins and / or cooling holes on the heat shield can be omitted. If necessary, it can be provided in particular in this context that the burner seal is provided with cooling air holes or internal cooling in the region of the opening edge, in particular with cooling air holes and / or internal cooling as shown in FIG DE 10 2016 212 649.0 are described.
  • the opening edge extends at an opening angle in the range from 20 ° to 50 ° to the longitudinal axis of the burner seal.
  • an opening angle ⁇ for example, 20 ° ⁇ ⁇ ⁇ 50 °.
  • An inner circumferential surface of the through opening, into which the fuel nozzle is inserted, defined by the opening edge thus extends at its end projecting into the combustion chamber at an angle of 20 ° to 50 °, for example at an opening angle of 20 °, 30 °, 40 ° or 50 ° to the longitudinal axis.
  • the opening edge can expand continuously along the longitudinal axis and have an annular cross section.
  • the heat shield can form a wrap-around section which engages around the at least one radially outwardly extending web of the burner seal.
  • the heat shield and the burner seal are thus held in a defined position relative to one another by this wrap-around section, in that at least one section of the heat shield extends over the radially outwardly extending web of the burner seal and engages around it.
  • the wrap-around section defines a gap in which the at least one radially outwardly extending web of the burner seal is at least partially (positively) received.
  • This gap runs, for example, in the form of a segment of a circle or in a circle around the longitudinal axis.
  • the gap can be formed as an annular gap on a wrap-around section of the heat shield that runs around the longitudinal axis. The depth of the gap can in principle be dimensioned such that the burner seal can still be displaced radially with respect to the heat shield.
  • the structural unit comprising the burner seal and the heat shield can be fixed via the heat shield to a combustion chamber component bordering the combustion chamber.
  • This combustion chamber component is, for example, part of the combustion chamber assembly and is provided in the region of a combustion chamber head of the combustion chamber.
  • this combustion chamber component is a head plate of the combustion chamber.
  • the heat shield can, for example, form fastening elements which pass through fastening openings on the combustion chamber component. Bolts can thus be formed on the heat shield, for example, through fastening openings on a head plate of the Of the combustion chamber head and fix the assembly consisting of the burner seal and the heat shield to the head plate using the nuts.
  • an end face of the wrap-around section can face the combustion chamber component to which the structural unit comprising the burner seal and the heat shield is fixed.
  • the structural unit thus adjoins the combustion chamber component via an end face of the wrap-around section and hereby comes into contact with the combustion chamber component via the end face of the wrap-around section, possibly after thermal expansion possible during operation of the engine.
  • a wrap-around section formed on the heat shield can thus replace a front positioning part, for example in the form of a positioning ring, which is usually present in combustion chamber assemblies which have been customary in practice on a side of a head plate facing the combustion chamber between the head plate (as the combustion chamber component) and the burner seal and in particular a radially projecting web formed thereon is provided.
  • a front positioning part for example in the form of a positioning ring, which is usually present in combustion chamber assemblies which have been customary in practice on a side of a head plate facing the combustion chamber between the head plate (as the combustion chamber component) and the burner seal and in particular a radially projecting web formed thereon is provided.
  • only the heat shield is then used to mount the burner seal on the combustion chamber component and to rest the structural unit on the combustion chamber component. Consequently, no separate (front or rear) positioning part is provided here, which would be arranged between a section of the heat shield and the combustion chamber component or a section of the heat shield and the burner seal.
  • Such a combustion chamber assembly is thus free of positioning rings, for example.
  • the structural unit can also be combined with at least one separate positioning part.
  • the combustion chamber assembly comprises, for example, at least one separate positioning part, which therefore does not form part of the structural unit comprising the heat shield and burner seal, which is arranged between the radially outwardly extending web of the burner seal and a section of the combustion chamber component to which the structural unit is fixed .
  • the positioning part is thus, for example, a (front) positioning ring which is arranged on the combustion chamber component from the combustion chamber before the structural unit comprising the heat shield and burner seal is attached.
  • the opening edge can in principle be designed symmetrically with respect to the longitudinal axis, for example in the form of a ring with a constant wall thickness.
  • the opening edge is not fixed to such a design and can for example also be designed asymmetrically with respect to the longitudinal axis.
  • Such an asymmetrical design includes in particular locally different wall thicknesses and / or turning points in the course.
  • the heat shield and / or the burner seal have at least one cooling air hole and / or at least one cooling fin or cooling knob.
  • the combustion chamber assembly comprises at least two burner seals and the heat shield has at least two through holes through which a bearing section of one of the at least two burner seals extends.
  • the heat shield has at least two through holes through which a bearing section of one of the at least two burner seals extends.
  • two or more burner seals are combined with a single heat shield with two through holes.
  • the proposed solution also includes the provision of an engine, in particular a gas turbine engine with at least one combustion chamber assembly according to the invention.
  • the burner seal here also has a bearing section which extends along a longitudinal axis and which has a through opening for the positioning of a fuel nozzle on a combustion chamber of an engine.
  • the heat shield is also present within the combustion chamber of the combustion chamber and has (at least) one through hole through which the bearing section of the burner seal extends.
  • the burner seal and the heat shield are manufactured additively in such a way that the heat shield on the structural unit is at least partially between (a) an opening edge of the through-opening formed by the burner seal and pointing radially outwards with respect to the longitudinal axis and ( b) at least one web formed by the burner seal and extending radially outwards, also with respect to the longitudinal axis, is received.
  • the heat shield is thus located between two radially projecting sections of the burner seal, via which the heat shield cannot be separated from the burner seal without being destroyed.
  • the burner seal and the heat shield are manufactured additively in such a way that the heat shield and the burner seal on the finished structural unit can be axially, possibly also radially, displaceable relative to one another with respect to the longitudinal axis.
  • an embodiment variant of a combustion chamber assembly according to the invention can also be produced by means of an embodiment variant of a manufacturing method according to the invention. Accordingly, advantages and features explained above and below also apply to design variants of a combustion chamber assembly according to the invention and also for design variants of a production method according to the invention and vice versa.
  • the Figure 11 illustrates schematically and in a sectional view a (turbofan) engine T, in which the individual engine components are arranged one behind the other along an axis of rotation or central axis M and the engine T is designed as a turbofan engine.
  • a fan F At an inlet or intake E of the engine T, air is sucked in along an inlet direction by means of a fan F.
  • This fan F which is arranged in a fan housing FC, is driven by a rotor shaft S, which is set in rotation by a turbine TT of the engine T.
  • the turbine TT is connected to a compressor V, which has, for example, a low-pressure compressor 111 and a high-pressure compressor 112, and optionally also a medium-pressure compressor.
  • the fan F feeds air to the compressor V in a primary air flow F1 and, on the other hand, to generate the thrust, in a secondary air flow F2 a secondary flow duct or bypass duct B.
  • the bypass duct B here runs around a core engine comprising the compressor V and the turbine TT, which comprises a primary flow duct for the air supplied to the core engine by the fan F.
  • the air conveyed into the primary flow duct via the compressor V reaches a combustion chamber section BKA of the core engine, in which the drive energy for driving the turbine TT is generated.
  • the turbine TT has a high-pressure turbine 113, a medium-pressure turbine 114 and a low-pressure turbine 115.
  • the turbine TT drives the rotor shaft S and thus the fan F via the energy released during the combustion in order to generate the required thrust via the air conveyed into the bypass duct B.
  • Both the air from the bypass duct B and the exhaust gases from the primary flow duct of the core engine flow out via an outlet A at the end of the engine T.
  • the outlet A usually has a thrust nozzle with a centrally arranged outlet cone C.
  • Figure 12 shows a longitudinal section through the combustion chamber section BKA of the engine T.
  • This shows in particular in a (ring) combustion chamber BK of the engine T.
  • a nozzle assembly is provided for injecting fuel or an air-fuel mixture into a combustion chamber 23 of the combustion chamber BK.
  • This comprises a combustion chamber ring, on which a plurality of fuel nozzles 17 are arranged along a circular line around the central axis M.
  • the nozzle outlet openings of the respective fuel nozzles 17, which lie within the combustion chamber BK are provided on the combustion chamber ring.
  • Each fuel nozzle 17 comprises a flange, via which a fuel nozzle 17 is screwed to an outer housing 22 of the combustion chamber section BKA.
  • the Figure 13 shows in opposite to the Figure 12 On an enlarged scale and in a sectional view, a combustion chamber BK known from the prior art and in particular the design of a burner seal 4 and a heat shield 2 provided in the region of a combustion chamber head 3 of the combustion chamber BK.
  • the combustion chamber BK shown here is, for example, a (full) ring combustion chamber as used in gas turbine engines.
  • the combustion chamber BK is arranged in the interior of the outer housing 22.
  • the combustion chamber BK comprises (radially) outer and (radially) inner combustion chamber walls 1a and 1b. Depending on the construction, these combustion chamber walls 1a, 1b are shielded from the combustion chamber 23, if necessary, with a second wall 6.
  • This second wall 6 can be connected to the inner and outer combustion chamber walls 1a, 1b, for example, by means of bolts 10 and nuts 11.
  • the combustion chamber walls 1a and 1b usually have cooling holes 12 and mixed air holes 7.
  • the inner wall 6 can also be provided with effusion cooling holes 13.
  • the outer combustion chamber wall 1a is connected to the outer housing 22 via an arm 8 and a flange 9.
  • a combustion chamber head 3 In a front end of the combustion chamber BK with respect to a longitudinal axis L there is a combustion chamber head 3 with a combustion chamber component in the form of a head plate 5 intended.
  • the outer and inner combustion chamber walls 1a and 1b are connected to one another via this combustion chamber head 3 and the head plate 5.
  • the head plate 5 shown here has cooling holes 15. Furthermore, a through hole is formed on the head plate 25, which provides access to the combustion chamber 23 and to which the fuel nozzle 27 is provided.
  • a burner seal 4 ensures the positioning of the fuel nozzle 27 in the head plate 5 and in particular the through hole of the head plate 5.
  • the burner seal 4, which is optionally also provided with cooling holes 16, is in this case floating and is supported in the embodiment variant shown from the prior art with the aid of a front Positioning part in the form of a front positioning ring 24 and positioned on the head plate 5 with the aid of a rear positioning part in the form of a rear positioning ring 28.
  • the burner seal 4 is screwed to a heat shield 2 located in the combustion chamber 23.
  • the heat shield 2 forms bolts 17 which are guided through fastening openings on the head plate 5 and onto which nuts 11 are screwed from the side of the combustion chamber head 3.
  • the heat shield 2 can in principle also have cooling air holes 14 and cooling fins or cooling knobs 29.
  • the bolts 17 can moreover also be designed as separate components and therefore not be formed by the heat shield 2. Such bolts 17 are then screwed, for example, from the side of the combustion chamber head 3 into threaded openings in the heat shield 2.
  • the burner seal 4 projects with the bearing section 41 through the through opening 26 of the respective heat shield 2 when the combustion chamber assembly is installed as intended.
  • the bearing section 41 then projects into the combustion chamber 23 with an opening edge 40 forming the end of a through-opening 400 on the combustion chamber side for the positioning of the fuel nozzle 17.
  • This opening edge 40 widens along the longitudinal axis L, along which the bearing section 41 extends to a diameter D and thus points radially outward.
  • the bearing section 41 forms on its outer circumferential surface a ring 42 which extends in a ring shape and extends radially outwards.
  • the web extending radially outwards thus forms an (annular) protrusion or radial web 42 on the burner seal 4.
  • the radial web 42 is received between the two positioning rings 24 and 28 in a form-fitting manner and is floatingly supported on the head plate 5.
  • the burner seal 4 is thus held displaceable in the axial direction (with respect to the longitudinal axis L) relative to the head plate 5 during operation of the engine T and can also expand in the radial direction.
  • the heat shield 2 screwed to the head plate 5 is supported on the one hand on an inside of the head plate 5 facing the combustion chamber 23.
  • a radially outer outer edge 2b of the heat shield 2 bears against the inside of the head plate 5 when the combustion chamber assembly is installed as intended.
  • the heat shield 2 forms a radially inner inner edge 2a against which the rear positioning ring 28 can rest.
  • the protruding radial web 42 of the burner seal 4 is thus partially received between the two front and rear positioning rings 24 and 28, while the rear positioning ring 28 lies at least partially between the protruding radial web 42 and the inner edge 2a of the heat shield 2.
  • the individual components, front positioning ring 24, burner seal 4, rear positioning ring 28 and heat shield 2 are thus arranged one after the other along a first attachment direction R1 from the combustion chamber 23 on the head plate 5 and in particular its through hole.
  • first attachment direction R1 from the combustion chamber 23 on the head plate 5 and in particular its through hole.
  • the nuts 11 and thus the heat shield 2 of the head plate 5 were fixed along an opposite attachment direction R2, as a result of which the burner seal 4 is positioned as intended and is floating.
  • the solution according to the invention provides a remedy here.
  • the embodiment variants shown are provided to add the burner seal 4 and the heat shield 2 together in one production process as an integral structural unit.
  • the burner seal 4 and the heat shield 2 in the illustrated embodiment variants are inseparably connected to one another in such a way that the heat shield 2 is at least partially received between the radially outwardly pointing opening edge 40 and the radially outwardly extending radial web 42.
  • the integration of the burner seal 4 and the heat shield 2 in one structural unit eliminates the limitation that the diameter D of the through hole 26 in the heat shield 2 must not be exceeded by the diameter of the opening edge of the 40.
  • the variant of the Figures 1A and 1B a first embodiment of a combustion chamber assembly, with the opening edge 40 compared to that previously known from the prior art Figures 15A and 15B known variant is expanded significantly more, namely to a diameter D O.
  • the Diameter D O is significantly larger than the diameter D of the through hole 26 in the heat shield 2 and exceeds this, for example, by at least 5%.
  • the opening edge 40 here also extends at an opening angle ⁇ in the range of 20 ° and 50 °, for example in the range of 35 ° to 50 ° and in particular of approximately 40 ° to the longitudinal axis L. This also enables the guidance of the fuel-air mixture and improve mixing in the primary zone.
  • a front positioning ring 24 which may still be present, is only inserted from the combustion chamber side before the assembly consisting of burner seal 4 and heat shield 2 is then attached to the head plate 5 and then fixed (assembly steps 1, 2 and 3. in the Figures 1A and 1B ).
  • a rear position ring 28 is integrated in the heat shield 2, so that the heat shield 2 with a positioning section 20a on its inner edge 2a is directly opposite the edge web 42 of the burner seal 4.
  • the heat shield 2 can also integrate the front position ring 24 and consequently encompass the radial web 42. This is in particular below with reference to the variant Figures 3A and 3B explained in more detail.
  • the positioning ring 24 is also retained.
  • the heat shield 2 and the burner seal 4 are also designed as an additively manufactured unit.
  • the opening edge 40 of the burner seal 4 also has an opening angle ⁇ between 20 ° and 50 °.
  • the widening opening edge 40 extends into the combustion chamber 23 with a comparatively large axial length in order to specifically guide the fuel-air mixture out of the fuel nozzle 17 into the interior of the combustion chamber 23.
  • the radial extension of the opening edge 40 then also leads to a larger diameter here than in the through hole 26 in the heat shield 2 and the through hole in the top plate 5.
  • the heat shield 2 is designed with a wrap-around section 2c which surrounds the radial web 42 of the burner seal 4.
  • the wrap-around section 2c defines a circular circumferential annular gap 200, in which the radial web 42 is received in a form-fitting manner.
  • the encompassing section 2c also ensures, in particular, that the burner seal 2 can be axially displaced along the longitudinal axis L during operation of the engine T, so that the burner seal 2 is also floatingly supported here.
  • the contour of the heat skull 2 follows the contour of the opening edge 40.
  • a contact section 21b of the outer edge 2b for contacting a radially outer area of the head plate 5 (on the inside of the head plate 5 facing the combustion chamber 23) is then formed with a greater axial length.
  • the opening edge 40 of the burner seal 4 is drawn radially outwards to such an extent that the opening edge 40 takes over the function of the heat shield 2 (at least partially).
  • the opening edge 40 extends at least to the radially outermost outer edge 2b of the heat shield 2, so that the opening edge 40 completely covers the heat shield 2 as seen from the combustion chamber 23 along the longitudinal axis L. Since the opening edge 40 takes over the function of the heat shield 2 (at least partially), it can be provided with cooling air holes 14 or a corresponding internal cooling according to FIG DE 10 2016 212 649.0 be designed.
  • the heat shield 2 can also be made simpler, for example without cooling air holes 14 and / or without cooling fins or cooling knobs 29.
  • FIGS. 7A and 7B illustrate further developments of the embodiment variants of FIGS Figures 5A and 5B respectively the Figures 3A and 3B .
  • the further developments illustrated illustrate that, in deviation from the design variants of the Figures 5A and 5B 3A and 3B, it is not imperative that the opening edge 40 is formed symmetrically to the longitudinal axis L.
  • the opening edge 40 can also be designed asymmetrically and have locally different wall thicknesses and / or turning points in the course.
  • FIG. 8A and 8B an additive manufacturing process for the structural unit consisting of heat shield 2 and burner seal 4 is schematically illustrated.
  • the assembly is built up in layers on a base plate 30, for example as part of a laser sintering machine.
  • Component areas and component sections that are not in direct contact with other component sections or areas or the base plate 30 are supported with the aid of one or more support structures 31 .
  • Such a support structure 31 can also be built up layer by layer, for example, but then forms
  • the completed assembly of heat shield 2 and burner seal 4 does not form part of the combustion chamber assembly and is removed for this purpose, for example.
  • the design variants of Figures 1A to 7A Be part of a combustion chamber assembly, in which exactly one heat hole 2 having a through hole 26 is provided for screwing on the head plate 5 for each fuel nozzle 17 and thus for each burner seal 4 ( Figure 9 ).
  • the combustion chamber assembly can comprise a heat shield 2, on which two through holes 26 are provided for each of at least two combustion chamber seals 4. In this way, the number of fastening elements to be used, here in the form of the bolts 17, which are necessary for fixing a head plate 5, can be significantly reduced.
  • cooling holes or cooling air holes 14 in the burner seal 4 and / or the heat shield 2 and any cooling fins or cooling knobs 29 on the heat shield 2 can be produced integrally by means of an additive manufacturing process.
  • cooling holes and cooling channels correspond to the DE 10 2016 212 649.0 can be formed on the burner seal 4 and / or the heat shield 2.

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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 (15)

  1. Module de chambre de combustion, comprenant
    - un joint d'étanchéité de brûleur (4) avec une portion de palier (41) s'étendant le long d'un axe longitudinal (L), qui présente une ouverture de passage (400) pour le positionnement d'une buse de carburant (17) au niveau d'une chambre de combustion (BK) d'un moteur (T),
    (a) la portion de palier (41) présentant un bord d'ouverture (40) orienté radialement vers l'extérieur par rapport à l'axe longitudinal (L), au niveau d'une extrémité de l'ouverture de passage (400), qui, lors du montage conforme sur la chambre de combustion (BK) du moteur (T), est situé à l'intérieur d'un espace de combustion (23) de la chambre de combustion (BK), et
    (b) au moins une nervure (42) s'étendant radialement vers l'extérieur, par rapport à l'axe longitudinal (L), étant réalisée au niveau de la portion de palier (41), et
    - un bouclier thermique (2) qui, lors d'un montage conforme sur la chambre de combustion (BK) du moteur (T), est situé à l'intérieur de l'espace de combustion (23) de la chambre de combustion (BK) et présente un trou traversant (26) à travers lequel s'étend la portion de palier (41) du joint d'étanchéité de brûleur (4),
    caractérisé en ce que
    le joint d'étanchéité de brûleur (4) et le bouclier thermique (2) forment une unité structurelle fabriquée par un processus additif, dans laquelle le bouclier thermique (2) est reçu au moins en partie entre le bord d'ouverture (40) orienté radialement vers l'extérieur et l'au moins une nervure (42) s'étendant radialement vers l'extérieur de telle sorte qu'une séparation du bouclier thermique (2) du joint d'étanchéité de brûleur (4) le long de l'axe longitudinal (L) soit exclue.
  2. Module de chambre de combustion selon la revendication 1, caractérisé en ce que le joint d'étanchéité de brûleur (4) est supporté de manière flottante au niveau du bouclier thermique (2).
  3. Module de chambre de combustion selon la revendication 1 ou 2, caractérisé en ce que l'ouverture de passage (400) du joint d'étanchéité de brûleur (4) présente, au niveau de son extrémité située à l'intérieur de l'espace de combustion (23), à travers le bord d'ouverture (40) orienté radialement vers l'extérieur, un diamètre (Do) qui est supérieur à un diamètre (D) du trou traversant (26) dans le bouclier thermique (2).
  4. Module de chambre de combustion selon l'une quelconque des revendications précédentes, caractérisé en ce que
    - le bord d'ouverture (40) s'étend radialement vers l'extérieur jusqu'à la hauteur d'un bord radialement le plus extérieur (2b) du bouclier thermique (2) ou au-delà de ce bord radialement le plus extérieur (25ba) du bouclier thermique (2) de telle sorte que le bord d'ouverture (40), vu depuis l'espace de combustion (23) le long de l'axe longitudinal (L), recouvre complètement le bouclier thermique (2), et/ou
    - le bord d'ouverture (40) s'étend suivant un angle d'ouverture (α) dans une plage de 20° à 50° par rapport à l'axe longitudinal (L).
  5. Module de chambre de combustion selon l'une quelconque des revendications précédentes, caractérisé en ce que le bouclier thermique (2) constitue une portion d'engagement périphérique (2c) qui vient en prise autour de l'au moins une nervure (42) du joint d'étanchéité de brûleur (4) s'étendant radialement vers l'extérieur.
  6. Module de chambre de combustion selon la revendication 5, caractérisé en ce que la portion d'engagement périphérique (2c) définit une fente (200) dans laquelle l'au moins une nervure (42) s'étendant radialement vers l'extérieur est reçue au moins en partie.
  7. Module de chambre de combustion selon l'une quelconque des revendications précédentes, caractérisé en ce que l'unité structurelle constituée du joint d'étanchéité de brûleur (4) et du bouclier thermique (2) est fixée par le biais du bouclier thermique (2) à un composant (5) de la chambre de combustion qui entoure l'espace de combustion (23).
  8. Module de chambre de combustion selon la revendication 7, caractérisé en ce que pour la fixation de l'unité structurelle constituée du joint d'étanchéité de brûleur (4) et du bouclier thermique (2) au bouclier thermique (2), des éléments de fixation (17) sont réalisés, lesquels s'engagent à travers des ouvertures de fixation au niveau du composant (5) de la chambre de combustion.
  9. Module de chambre de combustion selon l'une quelconque des revendications 5 et 6 et selon l'une quelconque des revendications 7 et 8, caractérisé en ce qu'un côté frontal de la portion d'engagement périphérique (2c) est orienté vers le composant (5) de la chambre de combustion.
  10. Module de chambre de combustion selon la revendication 7 ou 8, caractérisé en ce que le module de chambre de combustion comprend au moins une partie de positionnement séparée (24) qui est disposée entre la nervure (42) du joint d'étanchéité de brûleur (4) s'étendant radialement vers l'extérieur et une portion du composant (5) de la chambre de combustion.
  11. Module de chambre de combustion selon l'une quelconque des revendications 7 à 9, caractérisé en ce que pour le support sur palier du joint d'étanchéité de brûleur (4) au niveau du composant (5) de la chambre de combustion, et pour l'appui contre le composant (5) de la chambre de combustion, on utilise seulement le bouclier thermique (2).
  12. Module de chambre de combustion selon l'une quelconque des revendications précédentes, caractérisé en ce que
    - le bord d'ouverture (40) est réalisé sous forme symétrique ou asymétrique par rapport à l'axe longitudinal (L) et/ou
    - le bouclier thermique (2) et/ou le joint d'étanchéité de brûleur (4) présentent au moins un trou d'air de refroidissement (14) et/ou au moins une ailette de refroidissement ou une noppe de refroidissement (29) et/ou
    - le module de chambre de combustion comprend au moins deux joints d'étanchéité de brûleur (4) et le bouclier thermique (2) présente au moins deux trous traversants (26) à travers lesquels s'étend à chaque fois une portion de palier (41) de l'un des au moins deux joints d'étanchéité de brûleur (4).
  13. Moteur comprenant au moins un module de chambre de combustion selon l'une quelconque des revendications 1 à 12.
  14. Procédé de fabrication d'un module de chambre de combustion comprenant un joint d'étanchéité de brûleur (4) avec une portion de palier (41) s'étendant le long d'un axe longitudinal (L), qui présente une ouverture de passage (400) pour le positionnement d'une buse de carburant (17) au niveau d'une chambre de combustion (BK) d'un moteur (T) et un bouclier thermique (2) qui, lors du montage conforme sur la chambre de combustion (BK) du moteur (T), est situé à l'intérieur de l'espace de combustion (23) de la chambre de combustion (BK) et présente un trou traversant (26) à travers lequel s'étend la portion de palier (41) du joint d'étanchéité de brûleur (4),
    caractérisé en ce que
    le joint d'étanchéité de brûleur (4) et le bouclier thermique (2) sont fabriqués par un processus additif sous forme d'unité structurelle, dans laquelle le joint d'étanchéité de brûleur (4) et le bouclier thermique (2) ne sont pas séparables l'un de l'autre sans destruction.
  15. Procédé selon la revendication 14, caractérisé en ce que
    - le joint d'étanchéité de brûleur (4) et le bouclier thermique (2) sont fabriqués par un processus additif de telle sorte que le bouclier thermique (2) soit reçu au niveau de l'unité structurelle au moins en partie entre (a) un bord d'ouverture (40) de l'ouverture de passage (400) réalisé par le joint d'étanchéité de brûleur (4) et orienté radialement vers l'extérieur par rapport à l'axe longitudinal (L), et (b) au moins une nervure (42) réalisée par le joint d'étanchéité de brûleur (4) et s'étendant radialement vers l'extérieur, également par rapport à l'axe longitudinal (L), et/ou
    - le joint d'étanchéité de brûleur (4) et le bouclier thermique (2) sont fabriqués par un processus additif de telle sorte que le bouclier thermique (2) et le joint d'étanchéité de brûleur (2) puissent être décalés axialement l'un par rapport à l'autre par rapport à l'axe longitudinal (L) au niveau de l'unité structurelle finie.
EP18196251.5A 2017-09-28 2018-09-24 Ensemble chambre de combustion pourvu de bouclier thermique et joint de brûleur ainsi que procédé de fabrication Active EP3462089B1 (fr)

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DE102017217330.0A DE102017217330A1 (de) 2017-09-28 2017-09-28 Brennkammerbaugruppe mit Hitzeschild und Brennerdichtung sowie Herstellungsverfahren

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US10619856B2 (en) * 2017-03-13 2020-04-14 Rolls-Royce Corporation Notched gas turbine combustor cowl
US10982852B2 (en) 2018-11-05 2021-04-20 Rolls-Royce Corporation Cowl integration to combustor wall
FR3096725B1 (fr) * 2019-05-29 2021-05-14 Safran Helicopter Engines Module de turbomachine d’aeronef
GB202019222D0 (en) 2020-12-07 2021-01-20 Rolls Royce Plc Lean burn combustor
GB202019219D0 (en) * 2020-12-07 2021-01-20 Rolls Royce Plc Lean burn combustor
CN116928695A (zh) * 2022-03-31 2023-10-24 通用电气公司 用于燃烧器的环形圆顶组件

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US4686823A (en) * 1986-04-28 1987-08-18 United Technologies Corporation Sliding joint for an annular combustor
US4934145A (en) * 1988-10-12 1990-06-19 United Technologies Corporation Combustor bulkhead heat shield assembly
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DE102016212649A1 (de) 2016-07-12 2018-01-18 Rolls-Royce Deutschland Ltd & Co Kg Brennerdichtung einer Gasturbine und Verfahren zu deren Herstellung

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EP3462089A1 (fr) 2019-04-03
US20190093893A1 (en) 2019-03-28

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