US20190093893A1 - Combustion chamber assembly comprising thermal shield and burner gasket as well as manufacturing method - Google Patents

Combustion chamber assembly comprising thermal shield and burner gasket as well as manufacturing method Download PDF

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Publication number
US20190093893A1
US20190093893A1 US16/141,342 US201816141342A US2019093893A1 US 20190093893 A1 US20190093893 A1 US 20190093893A1 US 201816141342 A US201816141342 A US 201816141342A US 2019093893 A1 US2019093893 A1 US 2019093893A1
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United States
Prior art keywords
combustion chamber
heat shield
burner seal
assembly group
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.)
Abandoned
Application number
US16/141,342
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English (en)
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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Filing date
Publication date
Application filed by Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Assigned to ROLLS-ROYCE DEUTSCHLAND LTD & CO KG reassignment ROLLS-ROYCE DEUTSCHLAND LTD & CO KG ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: Eggels, Ruud, CLEMEN, CARSTEN
Publication of US20190093893A1 publication Critical patent/US20190093893A1/en
Abandoned legal-status Critical Current

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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 in particular relates to a combustion chamber assembly group with a burner seal and a heat shield as well as to a method for manufacturing such a combustion chamber assembly group.
  • a fuel nozzle for injecting a fuel-air mixture into the combustion space of the combustion chamber by means of a burner seal at the combustion chamber.
  • the burner seal has a bearing section that extends along a longitudinal axis and has a continuous passage hole inside of which the fuel nozzle is positioned.
  • a heat shield is provided on the combustion space side, which is located inside the combustion space when mounted according to the intended use at the combustion chamber of the engine and which has a passage hole through which the bearing section of the burner seal extends.
  • the bearing section of the burner seal projects through the passage hole of the heat shield with an opening edge, so that the opening edge of the burner seal, which points radially outwards with respect to the longitudinal axis and thus widens in the axial direction, is positioned behind the heat shield.
  • the opening angles and diameters of the opening edge at the end of the passage hole are limited by the heat shield having to be pushed over the opening edge as the combustion chamber assembly group is being mounted at the combustion chamber.
  • the combustion chamber seal is usually arranged at the combustion chamber, e.g. at a head plate of the combustion chamber, from the side of the combustion space before the heat shield is subsequently attached to affix the combustion chamber assembly group at the combustion chamber.
  • This objective is achieved through a combustion chamber assembly group according to claim 1 as well as through a manufacturing method according to claim 19 .
  • combustion chamber assembly group that comprises at least the following:
  • the burner seal and the heat shield form a constructional unit which is manufactured in an additive manner and in which the heat shield is at least partially received between the radially outward pointing opening edge and the at least one radially outwardly extending web, so that a (non-destructive) separation of the heat shield from the burner seal along the longitudinal axis is excluded.
  • the burner seal and the heat shield form an integral constructional unit that is to be manufactured in advance and that is to be mounted to a combustion chamber, e.g. in the area of a head plate of the combustion chamber, with the heat shield not being mountable independently of the burner seal. Rather, the heat shield is supported at the burner seal between the opening edge formed by the burner seal and the at least one web formed by the burner seal and extending radially outwards, so that the heat shield cannot be removed without destroying the burner seal. Thus, the heat shield cannot be displaced relative to the burner seal over the opening edge or the web along the longitudinal axis.
  • the heat shield and the burner seal form an integral constructional unit, in which the heat shield is received 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 each other is not possible, the issue of a subsequent mounting of the heat shield at the burner seal no longer arises.
  • the design of the opening edge and in particular of its opening angle and its diameter are no longer limited by the fact that the heat shield has to be pushed over the opening edge with its passage hole.
  • the burner seal and the heat shield are manufactured in an additive manner in a joint manufacturing process, for example by being built up layer by layer, so that it is no longer necessary to observe any requirements regarding the mountability of the heat shield at the burner seal.
  • the constructional unit of burner seal and heat shield is manufactured in an additive manner by means of a laser sintering method.
  • the burner seal is floatingly mounted at the heat shield.
  • the burner seal and the heat shield form an (integral) constructional unit
  • the burner seal is accordingly still supported in such a way that it is at least axially displaceable relative to the heat shield. In this manner, an axial displacement of the burner seal relative to the heat shield affixed at the combustion chamber is still possible during operation of the engine.
  • the floating mounting of the burner seal at the heat shield can further also include that the burner seal is supported at the heat shield in a radially displaceable manner with respect to the longitudinal axis of the bearing section.
  • the passage hole of the burner seal has a diameter at its end that is located (in the mounted state) inside the combustion space that is larger than a diameter of the passage hole in the heat shield.
  • an (end) diameter of the opening edge is larger than a maximum diameter of the passage hole in the heat shield.
  • the opening edge can extend (at an axial distance to the heat shield) up to the height of a radially outermost edge of the heat shield or radially outwards beyond this radially outer edge of the heat shield.
  • the opening edge of the burner seal completely covers the heat shield as viewed from the combustion space along the longitudinal axis.
  • the opening edge of the burner seal which has been shifted further outwards, can at least partially take over the function of a heat shield.
  • the design and expansion of the heat shield inside the combustion space can be strongly simplified. For example, any cooling nubs, cooling ribs and/or cooling holes at the heat shield can be omitted. If necessary, it can in particular be provided in this context that the burner seal is provided with cooling air holes or an internal cooling in the area of the opening edge, in particular with cooling air holes and/or an internal cooling as they are described in DE 10 2016 212 649.0.
  • the opening edge extends at an opening angle in the range of 20° to 50° with respect to the longitudinal axis of the burner seal.
  • an opening angle ⁇ it for example applies that 20° a 50°.
  • an inner surface area of the passage hole that is defined by the opening edge and into which the fuel nozzle is inserted thus extends, at its end that projecting into the combustion space, at an angle of 20° to 50°, for example at an opening angle of 20°, 30°, 40° or 50°, with respect to the longitudinal axis.
  • the opening edge can continuously widen along the longitudinal axis and have a circular cross section.
  • the heat shield can form an embracing section, that engages around the at least one web of the burner seal extending radially outwards. Via this embracing section, the heat shield and the burner seal are thus held in a defined position to each other by at least one section of the heat shield extending beyond the radially outwards extending web of the burner seal and engaging around the same.
  • the embracing section defines a gap inside of which the at least one web of the burner seal that extends radially outwards is at least partially received (in a form-fit manner).
  • This gap extends for example in the shape of a circular segment or a circle about the longitudinal axis.
  • the gap can be formed as an annular gap at an embracing section of the heat shield that extends circumferentially about the longitudinal axis.
  • the depth of the gaps can be dimensioned in such a manner that the burner seal is still radially displaceable with respect to the heat shield.
  • the constructional unit of burner seal and heat shield can be affixed via the heat shield at a combustion chamber component that borders the combustion space.
  • This combustion chamber component may for example be a part of the combustion chamber assembly group and can be provided in the area of a combustion chamber head of the combustion chamber.
  • this combustion chamber component can be a head plate of the combustion chamber.
  • the heat shield can for example form attachment elements that are passed through attachment openings at the combustion chamber component.
  • bolts can be formed at the heat shield, which are inserted through attachment openings at a head plate of the combustion chamber head and which affix the constructional unit of burner seal and heat shield at the head plate by means of nuts that are screwed onto them.
  • a face side of the embracing section can be facing towards the combustion chamber component at which the constructional unit of burner seal and heat shield is affixed.
  • the constructional unit adjoins the combustion chamber component via a face side of the embracing section and thus comes to rest—possibly after a thermal expansion that is possible during operation of the engine—at the combustion chamber component via the face side of the embracing section.
  • an embracing section formed at the heat shield can replace a front positioning part, for example in the form of a positioning ring, which is usually provided in combustion chamber assembly groups as they are customary in practice on a side of a head plate that is facing towards the combustion space between the head plate (as a combustion chamber component) and the burner seal, and is in particular provided at a radial projecting web that is formed thereat.
  • a front positioning part for example in the form of a positioning ring, which is usually provided in combustion chamber assembly groups as they are customary in practice on a side of a head plate that is facing towards the combustion space between the head plate (as a combustion chamber component) and the burner seal, and is in particular provided at a radial projecting web that is formed thereat.
  • the heat shield is used for positioning the burner seal at the combustion chamber component and for abutment of the constructional unit at the combustion chamber component. Accordingly, 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.
  • a combustion chamber assembly group thus has no positioning ring, for example.
  • the constructional unit can also be combined with at least one separate positioning part.
  • the combustion chamber assembly group comprises for example at least one separate positioning part, and thus a positioning part that does not form a part of the constructional unit of heat shield and burner seal, and that is arranged between the radially outwards extending web of the burner seal and a section of the combustion chamber component at which the constructional unit is affixed.
  • the positioning part may for example be a (front) positioning ring that is arranged at the combustion chamber component from the side of the combustion space before the constructional unit of heat shield and burner seal is mounted.
  • the opening edge can be formed to be symmetrical with respect to the longitudinal axis, for example circular with a constant wall thickness.
  • the opening edge is not limited to such a design and can for example also be formed to be asymmetrical with respect to the longitudinal axis.
  • Such an asymmetrical design in particular includes locally different wall thicknesses and/or inflection 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 rib or cooling nub.
  • the combustion chamber assembly group comprises at least two burner seals
  • the heat shield has at least two passage holes through which respectively a bearing section of one of the at least two burner seals extends.
  • the proposed solution includes providing an engine, in particular a gas turbine engine, with at least one combustion chamber assembly group according to the invention.
  • a further aspect of the proposed solution relates to a method for manufacturing a combustion chamber assembly group with a burner seal and a heat shield.
  • the burner seal has a bearing section that extends along a longitudinal axis and has a passage hole for positioning a fuel nozzle at a combustion chamber of an engine.
  • the heat shield is present inside the combustion space of the combustion chamber and has (at least) one passage hole through which the bearing section of the burner seal extends.
  • the burner seal and the heat shield are manufactured in an additive manner in such a way that the heat shield at the constructional unit is at least partially received between (a) an opening edge of the passage hole 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 also extending radially outwards with respect to the longitudinal axis.
  • the heat shield is located between two radially projecting sections of the burner seal over which the heat shield cannot be separated from the burner seal in a non-destructive manner.
  • the burner seal and the heat shield are manufactured in an additive manner in such a way that, at the finished constructional unit, the heat shield and the burner seal are axially, and where necessary also radially, displaceable with respect to each other with regard to the longitudinal axis.
  • an embodiment variant of a combustion chamber assembly group according to the invention can also be manufactured by means of an embodiment variant of a manufacturing method according to the invention. Consequently, the advantages and features described previously and in the following for the embodiment variants of a combustion chamber assembly group according to the invention also apply to the embodiment variants of manufacturing methods according to the invention, and vice versa.
  • FIGS. 1A-1B show, respectively in sections and in sectional views along two section lines A-A and B-B (compare FIGS. 9, 10 and 14 ), a first embodiment variant of a combustion chamber assembly group according to the invention in the area of a combustion chamber head of a combustion chamber;
  • FIGS. 2A-2B show a second embodiment variant, in views that correspond to FIGS. 1A and 1B ;
  • FIGS. 3A-3B show a third embodiment variant, in views that correspond to FIGS. 1A and 1B ;
  • FIGS. 4A-4B show a fourth embodiment variant, in views that correspond to FIGS. 1A and 1B ;
  • FIGS. 5A-5B show a fifth embodiment variant, in views that correspond to FIGS. 1A and 1B ;
  • FIGS. 6A-6B show a sixth embodiment variant, in views that correspond to FIGS. 1A and 1B ;
  • FIGS. 7A-7B show a seventh embodiment variant, in views that correspond to FIGS. 1A and 1B ;
  • FIGS. 8A-8B schematically show an additive manufacturing method for manufacturing an integral constructional unit of a burner seal and a heat shield according to FIGS. 4A and 4B along the steps A-A and B-B;
  • FIG. 9 shows a back view of two heat shields of a combustion chamber assembly group with respectively one burner seal, also showing different section lines A-A and B-B for the sectional views of FIGS. 1A to 7B ;
  • FIG. 10 shows a back view of a heat shield of a combustion chamber assembly group with two passage holes for respectively one burner seal, also showing different section lines A-A and B-B for the sectional views of FIGS. 1A to 7B ;
  • FIG. 11 shows an engine in which a combustion chamber assembly group according to FIGS. 1A to 10 is used
  • FIG. 12 shows, in sections and on an enlarged scale, the combustion chamber of the engine of FIG. 11 ;
  • FIG. 13 shows, in a cross-sectional view, the basic structure of a combustion chamber from the state of the art on a scale that is more strongly enlarged with respect to FIG. 12 ;
  • FIG. 14 shows a back view of two heat shields of a combustion chamber assembly group, also showing different section lines A-A and B-B;
  • FIGS. 15A-15B show sectional views of a combustion chamber assembly group of the state of the art along the section lines A-A and B-B of FIG. 14 .
  • FIG. 11 schematically illustrates, in a sectional view, a (turbofan) engine T in which the individual engine components are arranged in succession along a rotational axis or central axis M and the engine T is embodied as a turbofan engine.
  • a fan F By means of a fan F, air is suctioned in along an entry direction at an inlet or an intake E of the engine T.
  • This fan F which is arranged inside a fan housing FC, is driven via a rotor shaft S that is set into rotation by a turbine TT of the engine T.
  • the turbine TT connects to a compressor V, which for example has a low-pressure compressor 111 and a high-pressure compressor 112 , and where necessary also a medium-pressure compressor.
  • the fan F supplies air to the compressor V in a primary air flow F 1 , on the one hand, and, on the other, to a secondary flow channel or bypass channel B in a secondary air flow F 2 for creating a thrust.
  • the bypass channel B extends about a core engine that comprises the compressor V and the turbine TT, and also comprises a primary flow channel for the air that is supplied to the core engine by the fan F.
  • the air that is conveyed via the compressor V into the primary flow channel is transported into the combustion chamber section BKA of the core engine where the driving power 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 by means of the energy that is released during combustion in order to generate the necessary thrust by means of the air that is conveyed into the bypass channel B.
  • the air from the bypass channel B as well as the exhaust gases from the primary flow channel of the core engine are discharged 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.
  • FIG. 12 shows a longitudinal section through the combustion chamber section BKA of the engine T.
  • a nozzle assembly group is provided for injecting fuel or an air-fuel-mixture into a combustion space 23 of the combustion chamber BK. It comprises a combustion chamber ring along which multiple nozzles 17 are arranged along a circular line about the central axis M.
  • the nozzle exit openings of the respective nozzles 17 that are positioned inside the combustion chamber BK are provided at the combustion chamber ring.
  • each nozzle 17 comprises a flange by means of which a nozzle 17 is screwed to an outer housing 22 of the combustion chamber section BKA.
  • FIG. 13 shows, on a scale that is once more enlarged with respect to FIG. 12 and in sectional rendering, a combustion chamber BK as it is known from the state of the art, and in particular the design of a burner seal 4 and a heat shield 2 in the area of a combustion chamber head 3 of the combustion chamber BK, as it is provided in this context.
  • the shown combustion chamber BK may for example be a (full) annular combustion chamber, as it is 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 1 a and 1 b . Depending on the construction, these combustion chamber walls 1 a , 1 b are shielded off against the combustion space 23 with a second wall 6 , where necessary.
  • This second wall 6 can be connected to the inner and outer combustion chamber walls 1 a , 1 b by means of bolts 10 and nuts 11 , for example.
  • the combustion chamber walls 1 a and 1 b usually have cooling holes 12 and mixing air holes 7 .
  • the inner wall 6 can be provided with effusion cooling holes 13 .
  • the outer combustion chamber wall 1 a is connected to the outer housing 22 via an arm 8 and a flange 9 .
  • a combustion chamber head 3 with a combustion chamber component in the form of a head plate 5 is provided.
  • the outer and inner combustion chamber walls 1 a and 1 b are connected to each other by means of this combustion chamber head 3 and the head plate 5 .
  • the head plate 5 shown herein has cooling holes 15 .
  • a passage hole which provides access to the combustion space 23 and [inside of which] the fuel nozzle 27 is provided is formed at the head plate 25 .
  • the burner seal 4 ensures a positioning of the fuel nozzle 27 in the head plate 5 and in particular inside the passage hole of the head plate 5 .
  • the burner seal 4 which may also be provided with cooling holes 16 where necessary, is floatingly mounted, and in the shown embodiment variant from the state of the art is positioned at the head plate 5 by means of a front positioning part in the form of a front positioning ring 24 and by means of a rear positioning part in the form of a rear positioning ring 28 . Further, the burner seal 4 is screwed together with a heat shield 2 that is positioned inside a combustion space 23 .
  • the heat shield 2 forms bolts 17 which are passed through attachment openings at the head plate 5 and onto which nuts 11 are screwed in from the side of the combustion chamber head 3 .
  • the access for mounting the nuts 11 is facilitated through holes 19 provided in the combustion chamber head 3 .
  • the heat shield 2 can in principle also have cooling air holes 14 and cooling ribs or cooling nubs 29 .
  • the bolts 17 can be embodied as separate structural components and thus not be formed by the heat shield 2 . Such bolts 17 are then screwed into threaded openings of the heat shield 2 from the side of the combustion chamber head 3 , for example.
  • the burner seal 4 projects with the bearing section 41 through the passage hole 26 of the respective heat shield 2 when the combustion chamber assembly group is mounted according to the intended use.
  • the bearing section 41 projects into the combustion space 23 with an opening edge 40 that forms the combustion-space-side end of a passage hole 400 for positioning of the fuel nozzle 17 .
  • This opening edge 40 widens up to a diameter D along the longitudinal axis L along which the bearing section 41 extends, and thus points radially outwards.
  • the bearing section 41 For positioning and mounting the burner seal 4 at the head plate 5 according to the intended use, the bearing section 41 forms a web 42 at its outer surface area, with the web 42 extending circumferentially in a ring-like manner and radially outwards.
  • the radially outwardly extending web forms a (ring-shaped) projection or a radial web 42 at the burner seal 4 .
  • the radial web 42 is received between the two positioning rings 24 and 28 in a form-fit manner, and in this way is floatingly mounted at the head plate 5 .
  • the burner seal 4 is thus supported so as to be displaceable in the axial direction (with respect to the longitudinal axis L) relative to the head plate 5 , and can also extend in the radial direction.
  • the heat shield 2 that is screwed together with the head plate 5 is supported, on the one side, on an inner side of the head plate 5 that faces towards the combustion space 23 .
  • a radially outwardly positioned outer edge 2 b of the heat shield 2 is located at the inner side of the head plate 5 , when the combustion chamber assembly group is mounted according to the intended use. Further, the heat shield 2 forms a radially inwardly located inner edge 2 a at which the rear positioning ring 28 can abut. The projecting 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 is positioned at least partially between the projecting radial web 42 and the inner edge 2 a 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 at the head plate 5 and in particular inside its passage hole in succession along a first attachment direction R 1 beginning in the combustion space 23 . Subsequently, the placement of the nuts 11 and thus the affixing of the heat shield 2 of the head plate 5 was performed along an opposite attachment direction R 2 , whereby the burner seal 4 is positioned and floatingly mounted according to the intended use.
  • the solution according to the invention remedies this problem.
  • the burner seal 4 and the heat shield 2 are manufactured together in an additive manner as an integral constructional unit in one manufacturing process.
  • the burner seal 4 and heat shield 2 are inseparably connected to each other in such a way that the heat shield 2 is received at least partially between the radially outward pointing opening edge 40 and the radially outwardly extending radial web 42 .
  • FIGS. 1A and 1B illustrates a first embodiment variant of a combustion chamber assembly group, in which the opening edge 40 is widened considerably stronger as compared to the variant as it has so far been known from the state of the art of FIGS. 15 A and 15 B, and namely up to a diameter D O .
  • the diameter D O is considerably larger than the diameter D of the passage hole 26 in the heat shield 2 and exceeds it e.g. by at least 5%.
  • the opening edge 40 extends at an opening angle ⁇ in the range of 20° and 50°, e.g. in the range of 35° to 50° and in particular of approximately 40°, with respect to the longitudinal axis L. Also in this way, the guidance of the fuel-air mixture and the intermixing in the primary zone can be improved.
  • a possibly still present front positioning ring 24 is inserted from the side of the combustion space, before then the constructional unit of burner seal 4 and heat shield 2 is placed at the head plate 5 and subsequently affixed (mounting sections 1 ., 2 . and 3 . in FIGS. 1A and 1B ).
  • a rear position ring 28 is correspondingly integrated into the heat shield 2 , so that, with a positioning section 20 a at its inner edge 2 a , the heat shield 2 is positioned 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 radially engage around the web 42 . This will be explained in more detail in the following in particular by referring to the embodiment variant of FIGS. 3A and 3B .
  • the positioning ring 24 is also maintained.
  • the heat shield 2 and the burner seal 4 are also formed as a constructional unit that is manufactured in an additive manner.
  • the opening edge 40 of the burner seal 4 further has an opening angle ⁇ of between 20° and 50°.
  • the widening opening edge 40 extends into the combustion space 23 with a comparatively great axial length to guide the fuel-air mixture in a targeted manner from the fuel nozzle 17 into the interior of the combustion space 23 .
  • the radial extension of the opening edge 40 also leads to a larger diameter than the passage hole 26 in the heat shield 2 and the passage hole in the head plate 5 .
  • the heat shield 2 is embodied with an embracing section 2 c that engages around the radial web 42 of the burner seal 4 .
  • the embracing section 2 c defines an annular gap 200 which extends circumferentially in a circular manner and inside of which the radial web 42 is received in a form-fit manner.
  • the embracing section 2 c in particular still ensures axial displaceability of the burner seal 2 along the longitudinal axis L during operation of the engine T, so that the burner seal 2 is floatingly mounted here, as well.
  • the contour of the [heat shield] 2 follows the contour of the opening edge 40 .
  • an abutment section 21 b of the outer edge 2 b for abutment at a radially outer area of the head plate 5 (at the inner side of the head plate 5 that is facing towards the combustion space 23 ) is also formed with a larger axial length.
  • the opening edge 40 of the burner seal 4 is displaced radially outwards so far that the opening edge 40 takes over the function of the heat shield 2 (at least partially).
  • the opening edge 40 extends at least up to the radially outermost outer edge 2 b of the heat shield 2 , so that the opening edge 40 , as viewed from the combustion space 23 along the longitudinal axis L, completely covers the heat shield 2 .
  • the opening edge 40 can be designed with cooling air holes 14 or a corresponding internal cooling according to DE 10 2016 212 649.0.
  • the heat shield 2 can further be designed in a simpler manner, for example without any cooling air holes 14 and/or without cooling ribs or cooling nubs 29 .
  • FIGS. 6A and 6B as well as 7 A and 7 B illustrate further developments of the embodiment variants of FIGS. 5A and 5B or of FIGS. 3A and 3B .
  • the shown further developments illustrate that, in contrast to the embodiment variants of FIGS. 5A and 5B as well as 3 A and 3 B, it is not obligatory that the opening edge 40 is formed symmetrically to the longitudinal axis L.
  • the opening edge 40 can also be designed asymmetrically and can have locally different wall thicknesses and/or inflection points in its course.
  • FIGS. 8A and 8B an additive manufacturing method for the constructional unit of heat shield 2 and burner seal 4 is schematically illustrated.
  • the constructional unit is built up layer by layer on a base plate 30 , for example as a part of a laser sinter machine.
  • component areas and structural component sections that are not in direct contact with other structural component sections or areas or the base plate 30 are supported by means of one or multiple support constructions 31 .
  • such a support construction 31 can also be built up in an additive manner layer by layer, for example. However, in that case it does not form a part of the combustion chamber assembly group at the finished constructional unit of heat shield 2 and burner seal 4 , and may for example be removed again for this purpose.
  • the embodiment variants of FIGS. 1A to 7A can be part of a combustion chamber assembly group in which a heat shield 2 having exactly one passage hole 26 for screwing on at the head plate 5 is provided per fuel nozzle 17 and thus per burner seal 4 ( FIG. 9 ).
  • the combustion chamber assembly group can comprise a heat shield 2 at which two passage holes 26 for respectively one of at least two combustion chamber seals 4 is provided. In this way, the number of the attachment elements to be used—here in the form of bolts 17 —that are necessary for affixing a head plate 5 can be considerably reduced.
  • cooling holes or cooling air holes 14 in the burner seal 4 and/or the heat shield 2 as well as any cooling ribs or cooling nubs 29 at the heat shield 2 can be manufactured integrally by an additive manufacturing method.
  • cooling holes and cooling channels can in particular be formed according to DE 10 2016 212 649.0 at 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)
US16/141,342 2017-09-28 2018-09-25 Combustion chamber assembly comprising thermal shield and burner gasket as well as manufacturing method Abandoned US20190093893A1 (en)

Applications Claiming Priority (2)

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

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EP (1) EP3462089B1 (de)
DE (1) DE102017217330A1 (de)

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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
US11339970B1 (en) 2020-12-07 2022-05-24 Rolls-Royce Plc Combustor with improved aerodynamics
US11353215B1 (en) * 2020-12-07 2022-06-07 Rolls-Royce Plc Lean burn combustor
US20220213808A1 (en) * 2019-05-29 2022-07-07 Safran Helicopter Engines Module of an aircraft turbine engine
US20230313996A1 (en) * 2022-03-31 2023-10-05 General Electric Company Annular dome assembly for a combustor
US12025315B2 (en) * 2022-03-31 2024-07-02 General Electric Company Annular dome assembly for a combustor

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EP0153842B1 (de) * 1984-02-29 1988-07-27 LUCAS INDUSTRIES public limited company Brennkammer für Gasturbinen
US4870818A (en) * 1986-04-18 1989-10-03 United Technologies Corporation Fuel nozzle guide structure and retainer for a gas turbine engine
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
US5974805A (en) * 1997-10-28 1999-11-02 Rolls-Royce Plc Heat shielding for a turbine combustor
GB0705458D0 (en) * 2007-03-22 2007-05-02 Rolls Royce Plc A Location ring arrangement
GB201107095D0 (en) * 2011-04-28 2011-06-08 Rolls Royce Plc A head part of an annular combustion chamber
DE102014204468A1 (de) * 2014-03-11 2015-10-01 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammer sowie Verfahren zu deren Herstellung
DE102015212573A1 (de) * 2015-07-06 2017-01-12 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammer mit integriertem Turbinenvorleitrad sowie Verfahren zu deren Herstellung
DE102016212649A1 (de) 2016-07-12 2018-01-18 Rolls-Royce Deutschland Ltd & Co Kg Brennerdichtung einer Gasturbine und Verfahren zu deren Herstellung

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
US20220213808A1 (en) * 2019-05-29 2022-07-07 Safran Helicopter Engines Module of an aircraft turbine engine
US11339970B1 (en) 2020-12-07 2022-05-24 Rolls-Royce Plc Combustor with improved aerodynamics
US11353215B1 (en) * 2020-12-07 2022-06-07 Rolls-Royce Plc Lean burn combustor
US11402099B2 (en) 2020-12-07 2022-08-02 Rolls-Royce Plc Combustor with improved aerodynamics
US11603993B2 (en) 2020-12-07 2023-03-14 Rolls-Royce Plc Combustor with improved aerodynamics
US20230313996A1 (en) * 2022-03-31 2023-10-05 General Electric Company Annular dome assembly for a combustor
US12025315B2 (en) * 2022-03-31 2024-07-02 General Electric Company Annular dome assembly for a combustor

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EP3462089B1 (de) 2020-05-13
DE102017217330A1 (de) 2019-03-28
EP3462089A1 (de) 2019-04-03

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