EP3306196A1 - Assemblage de chambre de combustion d'une turbine à gaz ainsi que turbine à gaz d'avion - Google Patents

Assemblage de chambre de combustion d'une turbine à gaz ainsi que turbine à gaz d'avion Download PDF

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Publication number
EP3306196A1
EP3306196A1 EP17194774.0A EP17194774A EP3306196A1 EP 3306196 A1 EP3306196 A1 EP 3306196A1 EP 17194774 A EP17194774 A EP 17194774A EP 3306196 A1 EP3306196 A1 EP 3306196A1
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EP
European Patent Office
Prior art keywords
air holes
combustion chamber
admixing air
admixing
ring wall
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.)
Granted
Application number
EP17194774.0A
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German (de)
English (en)
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EP3306196B1 (fr
Inventor
Carsten Clemen
Torsten Voigt
Thomas Dörr
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Rolls Royce Deutschland Ltd and Co KG
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Rolls Royce Deutschland Ltd and Co KG
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Publication of EP3306196A1 publication Critical patent/EP3306196A1/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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube
    • 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
    • F23R3/02—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
    • F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies

Definitions

  • the present invention relates to a combustion chamber arrangement, in particular an aircraft gas turbine, and a gas turbine with a combustion chamber arrangement.
  • the combustion chamber is, for example, annularly formed with an inner and an outer combustion chamber wall.
  • fuel is supplied with a plurality of fuel nozzles.
  • admixing air holes are provided which supply admixed air into the combustion chamber for complete combustion of the fuel.
  • cooling air openings are provided in the combustion chamber walls, wherein in double-walled combustion chamber walls so-called impingement cooling holes are provided in the outer wall and effusion cooling holes in the inner wall of the double-walled combustion chamber wall. These cooling holes form a cooling air film to protect the combustion chamber walls from the hot combustion gases.
  • the admixing air holes are arranged in a row along the circumference of the combustion chamber walls.
  • the admixing air holes are alternately Zumisch Kunststofflöcher arranged with larger and smaller diameter.
  • cooling air holes are arranged in a second row along the circumference at a very small distance from the admixing air holes in the circumferential direction offset from the admixing air holes.
  • the combustion chamber arrangement according to the invention of a gas turbine with the features of claim 1 comprises an annular combustion chamber with an inner ring wall and an outer ring wall. At one end of the combustion chamber, a combustion chamber head is arranged with a plurality of fuel nozzles, which introduce the fuel into the combustion chamber. Furthermore, a first Zumischluft #2 and a second Zumischluft #2 is provided.
  • the first admixed air row comprises a multiplicity of first admixing air holes formed as passage openings, wherein the first admixing air holes are arranged in the inner ring wall and / or the outer ring wall.
  • the second admixing air row comprises a multiplicity of second admixing air holes, likewise designed as passage openings, which are likewise arranged in the inner ring wall and / or the outer ring wall.
  • Zumisch poverty is fed into the combustion chamber via the Zumisch povertylöcher the first and second Zumischluft #2.
  • the first admixing air holes have first inner and first outer centers, and the second admixing air holes have second inner and second outer centers.
  • the inner centers are each located on a side facing the combustion chamber side of the Zumisch Kunststoffmaschinecher.
  • the inner centers thus form the puncture points of the respective central axes of the Zumisch povertylöcher to the combustion chamber.
  • the outer centers are located on a side facing away from the combustion chamber side of the Zumischluftlöcher.
  • L is a distance between the first and second inner centers and / or the first and second outer centers of the first and second admixing air holes.
  • D1 is a first flow diameter of the first admixing air holes at an entrance side and / or an exit side to the combustion chamber
  • D2 is a second flow diameter of the second admixing air holes at the entrance side and / or exit side to the combustion chamber.
  • the second flow diameter D2 is greater than the first flow diameter D1.
  • C is a mean flow coefficient of the first and second admixing air holes.
  • the average flow coefficient C of a Zumischluftlochs is a measure of the effective flow tube through the Zumisch povertyloch and thus describes which proportion of a cross-sectional area of the Zumisch Kunststofflochs is flowed through in the middle of an inflow side to an outflow side.
  • the flow coefficient of a Zumischlochs is a measure of the effective flow tube through the Zumischloch and thus describes what proportion of Zumischlochqueritess realization flows through in the middle of annulus to flame tube.
  • the mass flow (momentum flow) through such a mixing hole depends on the adjacent driving pressure gradient across the mixing hole, on the shape and shape of the mixing hole and on the Reynolds and Mach number.
  • a Zumischlochs Under the form and shape of a Zumischlochs here is the average cross-sectional shape (eg circle, ellipse) to understand the inlet geometry at the upstream end of the Zumischlochs (eg rounded inlet or stepped inlet), the orientation of the hole relative to the flow (relevant for non-circular cross-sectional shapes and for circular cross-sectional shapes, which have an average position relative to the surface (outer channel structure (Annulus) / combustion chamber (flame tube)), which is not perpendicular to the surface) and the effective guide length of the Zumischlochs. Under effective guide length is to be understood the length, which leads to improved guidance of the flow within the Zumischlochs.
  • the average cross-sectional shape eg circle, ellipse
  • the orientation of the hole relative to the flow relevant for non-circular cross-sectional shapes and for circular cross-sectional shapes, which have an average position relative to the surface (outer channel structure (Annulus) / combustion chamber (flame tube)
  • the flow coefficient is a variable, which can be different for each mixing hole, since the influence of the flow state upstream and downstream of the admixing hole influences the already mentioned influencing variables.
  • the inflow state to the admixing hole for example, in a fat-lean combustion chamber arrangement is influenced by components such as the injector, the injector arm, cooling components dependent on the cooling scheme mechanical components such as screws in the case of a liner-shingle cooling, possibly structurally relevant components such as mounting pins and igniters.
  • components such as the injector, the injector arm, cooling components dependent on the cooling scheme mechanical components such as screws in the case of a liner-shingle cooling, possibly structurally relevant components such as mounting pins and igniters.
  • deviations in construction and cooling differences as occurs, for example, in a shingled combustion chamber between the shingles, are decisive for the homogeneity of the flow.
  • uncontrollable leakage currents affect the Due to the assembly and the tolerant manufacturing occur the flow.
  • a grease-lean combustion chamber usually has a flow guide in the form of an inlet hood to the injector added Annuli, the geometric variations of such inlet hood and the acceleration conditions around such a hood are crucial for the formation of a flow profile in the annulus.
  • the inflow state is not homogeneous in the radial or in the circumferential direction, which influences the flow coefficient of a mixing hole.
  • These considerations are not limited to the state upstream of the Zumischlochs, as a Zumischloch from all sides so, for example, can also be from downstream inflow.
  • the flow coefficient must also be distinguished whether it is a single Zumischloch or multiple Zumischlöcher. The latter case is the case relevant to the present invention.
  • the flow coefficient depends on how the admixing holes are oriented and arranged relative to one another, since each admixing hole itself influences the flow in the annulus and in the flame tube.
  • each admixing hole itself influences the flow in the annulus and in the flame tube.
  • the flame tube it is particularly important whether the rays of adjacent Zumischlöcher interact.
  • the beams of different Zumischlöcher can combine, for example, to form a common beam, the beam trajectory can differ from the nominal course because of the pressure field forming with the beam and not least is to distinguish whether rays from the opposite Annuli interact with each other.
  • the present invention contemplates blending arrangements of opposing annuli which result in configurations whereby the rays are passed substantially past one another but also configurations where the rays are located directly opposite one another.
  • the flow within the flame tube of a lean-fat combustion chamber is twisted, highly turbulent and due to the locally varying heat release local temperature differences and thus density differences.
  • the turbulence influences the viscous behavior of the flow and the density differences lead to a non-homogeneous momentum distribution.
  • flow diameter is not limited to circle diameter, but flow diameter according to the invention both circle diameter and ellipse diameter are understood.
  • the first flow diameter is a first circle diameter of the first admixing air holes.
  • the first flow diameter is a first ellipse diameter of the first admixing air holes.
  • the second flow diameter D2 may likewise be a second circle diameter of the admixing air holes or a second ellipse diameter of the second admixing air holes.
  • the mean flow coefficient C is a measure of the effective flow rate in the mean of all admixing air holes and is preferably in a range of 0.60 to 0.75 and is particularly preferably 0.69.
  • the first flow diameter and / or the second flow diameter are different within the respective Zumisch Kunststoffschschitz #2n, in which case the first flow diameter or the second flow diameter is determined as an average of the different sized first and second flow diameters for each Zumischluft #2.
  • a particularly good inflow of the admixing air through the first and second admixing air holes is achieved when the flow diameters of the first and second admixing air holes in the direction of flow through the admixing air holes are constant.
  • a number of the first admixing air holes is equal to a double number of fuel nozzles.
  • a particularly good NOx reduction is achieved if the second admixing air holes are arranged on the outer ring wall and / or on the inner ring wall in the circumferential direction offset from the first admixing air holes.
  • the second admixing air holes are particularly preferably offset from the first admixing air holes such that the second admixing air holes lie centrally between the first admixing air holes with the axial distance L in the circumferential direction.
  • first admixing air holes have first central axes lying in a first plane and the second admixing air holes have second central axes lying in a second plane.
  • first and second planes are preferably arranged parallel to one another.
  • first and second center axes of the first and second admixing air holes are perpendicular to a center cone of a cone-shaped combustion chamber.
  • the first and / or second center axes are perpendicular to a tangent to the inner ring wall and / or perpendicular to a tangent to the outer ring wall of the combustion chamber.
  • the combustion chamber has a barrel-shaped ring shape with a barrel-shaped middle lateral surface and the first and second center axes of the first and second admixing air holes are arranged perpendicular to the barrel-shaped middle lateral surface.
  • the combustion chamber has a barrel-shaped shape and / or the first and / or second admixing air holes have a central axis, which are arranged at an angle not equal to 90 ° to a tangent to the outer ring wall of the combustion chamber.
  • the NOx emissions can be additionally reduced if each fuel nozzle of the combustion chamber is assigned to the combustion chamber in the axial direction of a first Zumisch Kunststoffloch. If the number of first admixing air holes is preferably twice as large as the number of fuel nozzles, a further first admixing hole is arranged in the circumferential direction between the respective first admixing air holes assigned to each fuel nozzle.
  • the first and / or second Zumischlöcher in the outer ring wall are each coaxial with the first and / or second Zumischmaschinechern in the inner ring wall.
  • each admixing air hole in the first admixed air row of the outer ring wall is assigned an admixing air hole in the first admixed air row of the inner ring wall.
  • the distance L on the inner ring wall is the same as on the outer ring wall.
  • the interpretation of Zumisch povertylöcher can also be such that the Zumischluftlöcher be designed in the inner ring wall of the annular combustion chamber according to the equation L and carried a transfer of the axial positions on the Zumischluftlöcher the outer ring wall. Also so that the distance L on the inner ring wall between the Zumischluftlöchern is the same as on the outer ring wall.
  • first and / or second admixing air holes preferably project partially into the combustion chamber.
  • the admixing air holes thus have a peripheral flange projecting into the combustion chamber, so that the outlet of the admixing air from the first and / or second admixing air holes takes place at a certain distance from the inner combustion chamber wall of the combustion chamber. More preferably, the height of the flange varies in the circumferential direction of the flange.
  • the present invention relates to a gas turbine, in particular an aircraft gas turbine, with a combustion chamber arrangement according to the present invention.
  • FIGS. 1 to 4 a gas turbine engine 100 and a combustion chamber assembly 1 according to a first embodiment of the invention described in detail.
  • the gas turbine engine 100 according to FIG. 1 is an example of a turbomachine to which the invention may find application.
  • the invention can also be used in other gas turbines, for example aircraft gas turbines.
  • the gas turbine engine 100 has, in the flow direction A, an air inlet 110, a fan 12 circulating in a housing, a medium-pressure compressor 13, a high-pressure compressor 14, an annular combustion chamber 15, a high-pressure turbine 16, a medium-pressure turbine 17 and a low-pressure turbine 18 and an exhaust nozzle 19, all of which are arranged about a central engine axis XX.
  • the medium pressure compressor 13 and the high pressure compressor 14 each include a plurality of stages, each of which includes a circumferentially extending array of fixed stationary vanes 20, commonly referred to as stator vanes, extending radially inward from the engine casing 21 in an annular flow passage through the medium pressure compressor 13 and Projecting high pressure compressor 14.
  • the compressors further include an array of compressor blades 22 projecting radially outward from a rotatable drum or disc 26 coupled to hubs 27 of the high pressure turbine 16 and the mid pressure turbine 17.
  • the three turbine sections of the high pressure turbine 16, the intermediate pressure turbine 17, and the low pressure turbine 18 have similar stages comprising an array of fixed vanes 23 projecting radially inward from the housing 21 into an annular flow passage through the three turbine sections and a subsequent array of turbine blades 24 protruding outward from the rotatable hub 27.
  • the compressor drum or compressor disk 26 and the compressor rotor blades 22 thereon and the turbine rotor hub 27 and the turbine blades 24 disposed thereon rotate about the engine axis X-X during operation.
  • FIG. 2 shows in detail the combustion chamber assembly 1.
  • the combustion chamber assembly 1 includes the combustion chamber assembly 1, as in FIG. 2 shown one Combustor head 3 with a plurality of fuel nozzles 6. Fuel is supplied via a fuel line 2 to the fuel nozzles 6.
  • the annular combustion chamber 15 comprises an inner ring wall 7 and an outer ring wall 8.
  • the inner ring wall 7 is double-walled and comprises an inner shingle support 71 and an inner combustion chamber shingle 72.
  • the outer ring wall 8 is likewise double-walled and comprises an outer shingle support 81 and an outer combustion shingle 82. It should be noted that, alternatively, the inner ring wall and the outer ring wall can also be made single-walled.
  • a top plate 4 and a heat shield 5 for thermal protection of the combustion chamber head 3 are arranged on the combustion chamber head 3.
  • combustion chamber 15 is arranged inclined to the engine axis XX, so that a center of the combustion chamber 15 is defined by a central cone jacket 9.
  • reference numeral 80 denotes a combustor suspension
  • reference numeral 90 denotes a combustor flange
  • the combustion chamber arrangement comprises a second admixing air row Z2 with a multiplicity of second admixing air holes 11 designed as passage openings.
  • the first and second admixing air holes are each in the inner ring wall 7 and the outer ring wall 8 is arranged.
  • Each of the first admixing air holes 10 has a first inner center 10a
  • each of the second admixing air holes 11 has a second inner center 11a. How out FIG. 3 and 4 it can be seen, all first inner centers 10a are arranged in a first plane E1 and all second inner centers 11a are arranged in a second plane E2.
  • the first and second inner center points 10a, 11a lie in each case on a side of the admixing air holes 10, 11 facing the combustion chamber 15.
  • L is a distance between the first and second inner centers 10a, 11a of the first and second admixing air holes 10, 11 in the axial direction of the combustion chamber 15, wherein D1 is a first flow diameter of the first admixing air holes 10 at the exit side to the combustion chamber 15, and D2 is a second flow diameter of the second admixing air holes 11 at the exit side to the combustor 15.
  • C is also a mean flow coefficient of the first and second admixing holes.
  • the flow diameter D1 and D2 of the first embodiment is selected such that the flow diameter D1 of the first admixing air holes 10 and the second admixing air holes 11 is circular.
  • the flow diameters are designed as a circle diameter.
  • a first diameter D1 is smaller than the second diameter D2.
  • the admixing air holes 10 of the first admixing air row Z1 are equally spaced and have a distance U from mutually adjacent first inner center points 10a (cf. FIG. 3 ) on.
  • the second admixing air holes 11 of the second admixing air row Z2 have the same distance in the circumferential direction U.
  • the first and second inner center points 10a, 11a are each offset by the distance U / 2 in the circumferential direction (cf. FIG. 3 ).
  • first mixing air holes 10 are arranged such that always a first Zumischluftloch 10 is arranged in alignment in the flow direction A of the combustion chamber on a central axis 60 of each fuel nozzle 6 (see. FIG. 3 ).
  • this condition is met only on the inner ring wall or only on the outer ring wall.
  • the mean flow coefficient C of the first and second admixing holes is in a range from 0.60 to 0.75 and is particularly preferably 0.69.
  • the flow coefficient C is approximately the same for each of the admixing air holes 10, 11, so that the flow coefficient C can always be selected to be 0.69, even considering tolerance bands.
  • the flow diameter D1, D2 does not necessarily have to be a circle diameter, but may be, for example, an ellipse diameter.
  • the first and second admixing air holes 10, 11 are cylindrical (see. FIG. 4 ). If the first and second admixing air holes are not cylindrical, but, for example, conical or convex, the smallest diameter of the admixing hole is selected as the first and second flow diameters.
  • the number of the first admixing holes 10 is equal to the number of the second admixing holes 11.
  • the second admixing holes 11 of the second admixing row Z2 are circumferentially respectively arranged centrally offset to the mixing air holes 10 of the first Zumischluft Little Z1, which is schematically in FIG. 3 is shown.
  • the first diameter D1 is 10.9 mm
  • the second diameter D2 is 14.1 mm
  • the length L is 8.74 mm.
  • first center axes M1 of the first admixing air holes 10 are arranged such that they lie in the plane E1. Further, the center axes M2 of the second admixing air holes 11 are in the second plane E2. Since the distance L is determined at each of the inner centers 10a, 11a of the first and second admixing air holes 10, 11, it is also possible to determine the distance L when the center axes M1, M2 of FIG Zumisch Kunststofflöcher 10, 11 inclined to the center cone jacket 9 are. In the first exemplary embodiment, the first center axes M1 and the second center axes M2 intersect the central cone jacket 9 of the combustion chamber 15 in each case vertically.
  • a connection between the flow diameters D1, D2 of the first and second admixing air holes 10, 11 and the distance L in the flow direction A of the combustion chamber 15 is established in order to optimize the reduction of NOx emissions.
  • FIG. 5 shows a combustion chamber assembly 1 according to a second embodiment of the invention.
  • the combustion chamber 15 of the second embodiment has a barrel-shaped ring shape. This results in different inflow of Zumisch poverty the first Zumisch poverty #2 Z1 and the second Zumischluft #2 Z2 in the combustion chamber 15th
  • the first admixing air holes 10 are arranged such that it is arranged perpendicular to a first tangent T1 of the combustion chamber outer wall 8.
  • the second admixing holes 11 are arranged perpendicular to a second tangent T2 on the combustion chamber outer wall 8.
  • the first and second admixing air holes are formed such that they project partially into the interior of the combustion chamber 15.
  • the first admixing air hole 10 has an inner flange 10 b, which protrudes into the combustion chamber 15.
  • the second admixing hole 11 has an inner flange 11 b, which projects into the combustion chamber 15.
  • FIG. 6 shows a combustion chamber assembly 1 according to a third embodiment of the invention.
  • the third embodiment substantially corresponds to the second embodiment, in contrast to which the second admixing air holes 11 are arranged inclined to a second tangent T2 on the combustion chamber outer wall 8.
  • the piercing point shifts at the outlet of the second admixing air holes 11, so that the second inner center 11a is arranged closer to the first admixing air row Z1. This shortens the distance L.
  • the first and second admixing air holes 10, 11 are again formed such that they project partially into the combustion chamber 15.
  • the flange 11 b of the second admixing holes 11 projects further into the combustion chamber than the flange 10 b of the first admixing air holes 10.
  • FIG. 7 schematically shows a combustion chamber arrangement according to a fourth embodiment of the invention.
  • the flow diameters of the first and second admixing air holes 10, 11 are no longer provided as a circle diameter, but as an ellipse diameter.
  • an ellipse surface of the second admixing air holes 11 is larger than that of the first admixing air holes 10.
  • a1 and b1 are the half-axes of the ellipse of the first admixing holes 10.
  • a2 and b2 are the half-axes of the ellipse of the second admixing air holes 11.
  • the second admixing air holes 11 of the second admixing air row Z2 are centrally offset in the circumferential direction to the admixing air holes 10 of the first admixing air row Z1.
  • the inner first and second centers 10a and 11a are in turn in a first plane E1 and a second plane E2.
  • Each second first admixing hole 10 of the first admixing hole row Z1 lies again in alignment with the central axis 60 of the fuel nozzles 6.
  • each fuel nozzle 6 is associated with a first admixing air hole 10 in the axial direction.
  • Fig. 8 schematically shows a combustion chamber assembly according to a fifth embodiment of the invention.
  • the first admixing air holes 10 are provided in a circular shape and the second admixing air holes 11 are elliptical in shape.
  • the circle diameter and the ellipse diameter are the same along the respective Zumisch Kunststoff #21, Z2 at each Zumisch Kunststoffloch.
  • the longer semiaxis of the ellipses is aligned in the direction of flow A.
  • the first admixing air row Z1 can also have elliptical admixing air holes and the second admixing air row Z2 can have circular admixing air holes.
  • circle diameters and ellipse diameters are possible.
  • the longer semiaxis of the ellipses can be arranged perpendicular to the flow direction A.
  • circle diameter and ellipse diameter are at least a Zumisch Kunststoffsch arranged alternately, or in two Zumisch Kunststoffschtechnik Herbertn Z1, Z2 Zumisch Kunststoffmaschinecher are alternately formed with a circle diameter and ellipse diameter, which can also be offset in the circumferential direction.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
EP17194774.0A 2016-10-06 2017-10-04 Assemblage de chambre de combustion d'une turbine à gaz ainsi que turbine à gaz d'avion Active EP3306196B1 (fr)

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DE102016219424.0A DE102016219424A1 (de) 2016-10-06 2016-10-06 Brennkammeranordnung einer Gasturbine sowie Fluggasturbine

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EP3306196A1 true EP3306196A1 (fr) 2018-04-11
EP3306196B1 EP3306196B1 (fr) 2022-08-10

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DE102016219424A1 (de) 2018-04-12
US10712006B2 (en) 2020-07-14
US20180100650A1 (en) 2018-04-12
EP3306196B1 (fr) 2022-08-10

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