Classifications

• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02K—JET-PROPULSION PLANTS
  • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
  • F02K1/04—Mounting of an exhaust cone in the jet pipe
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02K—JET-PROPULSION PLANTS
  • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
  • F02K1/78—Other construction of jet pipes
  • F02K1/82—Jet pipe walls, e.g. liners
  • F02K1/827—Sound absorbing structures or liners
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2230/00—Manufacture
  • F05D2230/60—Assembly methods
  • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
  • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2250/00—Geometry
  • F05D2250/40—Movement of components
  • F05D2250/41—Movement of components with one degree of freedom
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2260/00—Function
  • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
  • F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2260/00—Function
  • F05D2260/96—Preventing, counteracting or reducing vibration or noise
  • F05D2260/963—Preventing, counteracting or reducing vibration or noise by Helmholtz resonators
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2300/00—Materials; Properties thereof
  • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
  • F05D2300/603—Composites; e.g. fibre-reinforced
  • F05D2300/6033—Ceramic matrix composites [CMC]
• • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
  • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
  • Y02T50/00—Aeronautics or air transport
  • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

• TITLE Fixing an exhaust cone in a turbomachine turbine
• the invention relates to the means for fixing an ejection cone in a turbomachine turbine, in particular the means for fixing an ejection cone made of ceramic matrix composite.
• This presentation concerns an assembly located at the rear (downstream end) of an aircraft turbojet engine to optimize the flow of hot gases expelled by the turbojet engine, and possibly absorb at least part of the noise generated by the interaction of these hot gases, coming from the internal engine parts (combustion chamber, turbine(s)), with the ambient air and with the flow of cold air expelled by the fan of the turbojet engine.
• internal engine parts combustion chamber, turbine(s)
• this presentation concerns the connection between what is often referred to as the "ejection cone” and, located just upstream, a gas outlet from the turbojet engine.
• the exhaust cone is completed (surrounded) by a so-called “primary nozzle” part.
• the "ejection cone” is intended to be positioned downstream of the turbine (part) of the turbojet, around which the primary nozzle is placed concentrically.
• the exhaust cone and the primary nozzle are both fixed to a casing of the turbojet by a system of fixing by flanges.
• An assembly for an aircraft turbojet engine shown in FIG. 1 comprising:
• connection flange interposed between, upstream, a so-called metal outlet of a turbojet engine and, downstream, the central element, to connect them together.
• axis X is the longitudinal axis, or axis of rotation, of the turbomachine, in particular of the fan 20 and of the moving blades of the engine 12.
• the central gas ejection element may correspond to the aforementioned ejection cone (marked 1 below), or at least to the upstream part 1a below.
• a conventional ejection cone 1 is shown in Figure 1, on which the upstream (AM) and downstream (AV) of the structure along a motor axis (axis X above) are located respectively to the left and to right of the figure.
• FIG. 1 an aircraft gas turbojet engine 10 is illustrated in FIG. 1, the central part of which, forming the gas turbine engine 12, is mounted inside an engine nacelle assembly 14, as is typical of an aircraft designed for subsonic operation, such as a turboprop or turbofan engine.
• Set 14 of nacelle generally comprises an engine nacelle 16 and a fan nacelle 18 surrounding a fan 20 located axially upstream of the engine 12.
• the engine 12 comprises at least one turbine which may be a low pressure turbine and, further downstream, an exhaust casing 22 comprising an internal annular shroud 22a and an external annular shroud 22b delimiting between them a downstream part of the primary annular stream 24 in which the combustion gases from the combustion chamber of the engine 12 circulate.
• FIG. 2 shows a schematic view of an enlargement of part II of FIG. 1.
• the inner annular shroud 22a is connected, at its downstream end, to an upstream part 1a of the ejection cone 1, which may comprise the upstream part 1a, of substantially cylindrical shape, and a downstream part 1b of conical.
• an acoustic box 3 is arranged inside the ejection cone 1 to reduce the noise pollution of the outlet gases.
• the acoustic box 3 is connected at its upstream end to the internal annular shroud 22a and at its downstream end to the downstream part of the ejection cone.
• the aforementioned metal outlet of the turbojet which may be said inner annular shroud 22a, and said central element, which may be said upstream part 1a of the exhaust cone 1.
• at least one part of the ejection cone is made of a different material from the exhaust casing and/or from the other part of the ejection cone or at least part of the ejection cone is subjected to temperatures different from the temperatures at which subject the exhaust casing and / or the other part of the exhaust cone, which induces thermomechanical stresses, resulting from the differential thermal expansion between said part of the exhaust cone and the exhaust casing.
• the connection of the acoustic box to the exhaust casing and/or to the ejection cone is also complex due to the difference in material and the difference in temperature and therefore the thermomechanical stresses generated.
• This presentation proposes to use an assembly of the annular box to the ejection cone which is more reliable and more robust to thermal gradients by the very fact of its connection to one and the other of the aforementioned parts.
• a first assembly for a turbomachine turbine with a longitudinal axis comprising:
• an ejection cone comprising an outer annular wall for the flow of a primary air flow and an annular box arranged radially inside said outer annular wall
• the annular box may be an acoustic annular box making it possible to reduce sound emissions.
• the outer annular wall of the ejection cone or the annular box can move at least axially under the effect of thermal expansion without risking their rupture and/or while limiting the level of thermomechanical stresses responsible for the damage or breaking.
• This makes it possible to limit the impact of the differences in materials and/or the differences in temperature between the annular box, the ejection cone and the exhaust casing.
• the present presentation therefore proposes an architecture allowing free expansion, axial and radial, of the external annular wall with respect to the annular box by a decoupling, located upstream or downstream of the ejection cone, between the annular box and the outer annular wall.
• upstream and downstream are defined in relation to the air inlet and outlet of the turbine, upstream corresponding to the air inlet and downstream to the turbine outlet. air.
• the axial direction corresponds to the direction of the axis of revolution of the turbine of the ejection cone, which corresponds to the axis of rotation of said turbine, and a radial direction is a perpendicular direction, i.e. i.e. radial, to the axis of revolution.
• one end of the outer annular wall or of the annular box may designate an axially peripheral part of the outer annular wall or of the annular box.
• An end of the external annular wall or of the annular box free in displacement relative to the ejection cone or to the exhaust casing can be an end of the external annular wall or of the annular box devoid of mechanical connection with the ejection cone or the exhaust housing.
• the annular box can be connected on the one hand to the ejection cone and on the other hand to the exhaust casing, and the upstream end of the outer annular wall can be free to move, in particular in axial and radial displacement, relative to the exhaust casing.
• the ejection cone is connected to the exhaust casing through the annular box.
• the outer annular wall of the discharge cone may have an upstream end capable of moving to maintain low levels of thermal expansion. This makes it possible to limit the impact of differences in materials and/or thermal gradients between the annular box, the ejection cone and the exhaust casing.
• the outer annular wall of the ejection cone can be connected on the one hand to the ejection cone and on the other hand to the exhaust casing, and the upstream end of the annular box can be free to move, in particular axial movement, relative to the exhaust casing.
• the ejection cone is connected to the exhaust casing through the outer annular wall.
• the annular box may have an upstream end capable of moving to maintain low levels of thermal expansion. This makes it possible to limit the impact of differences in materials and/or thermal gradients between the annular box, the ejection cone and the exhaust casing.
• the outer annular wall of the ejection cone can be connected on the one hand to the ejection cone and on the other hand to the exhaust casing, and the downstream end of the annular box can be free in displacement, in particular in axial and radial displacement, relative to the ejection cone.
• the ejection cone is connected to the exhaust casing through the outer annular wall.
• the annular box may have a downstream end capable of moving to maintain low levels of thermal expansion. This makes it possible to limit the impact of differences in materials and/or thermal gradients between the annular box, the ejection cone and the exhaust casing.
• the annular box may comprise an internal annular wall arranged concentric with the external annular wall, and the upstream end of the annular box may correspond to the upstream end of the internal annular wall and the downstream end of the annular box may correspond to the downstream end of the inner annular wall.
• the annular box may comprise a plurality of partitions extending radially from the inner annular wall of the annular box, in particular towards the outer annular wall, and axially along the inner annular wall.
• the partitions thus form acoustic partitions.
• the first assembly may comprise a connecting member fixed to the exhaust casing and connected to the external annular wall of the ejection cone and/or to the annular box.
• the fixing member may comprise an annular flange around the longitudinal axis fixed to a corresponding flange of the exhaust housing.
• the fixing member may further comprise a plurality of flexible fixing lugs distributed circumferentially around the longitudinal axis and connected to the annular flange.
• the fixing lugs can be connected to the external annular wall of the ejection cone and/or to the acoustic box.
• the ejection cone can be made of a composite material with a ceramic matrix.
• the outer annular wall can be made of a composite material with a ceramic matrix.
• the annular box which may be an acoustic annular box, in particular the internal annular wall and the acoustic partitions, can be made of a material ceramic matrix composite.
• the acoustic partitions can be metallic.
• This presentation proposes a second assembly for a longitudinal axis turbomachine turbine comprising:
• an ejection cone comprising an outer annular wall for the flow of a primary air flow and a box arranged comprising an inner annular wall arranged radially inside said outer annular wall
• connecting member interposed longitudinally between the exhaust casing and the ejection cone, the connecting member being fixed to the exhaust casing and comprising first flexible fixing lugs distributed circumferentially around the longitudinal axis and second flexible fixing lugs distributed circumferentially around the longitudinal axis.
• the first fixing lugs can be connected to an upstream annular part of the outer annular wall, and the second fixing lugs are connected to an upstream annular part of the inner annular wall of the box.
• connection of the ejection cone and the box is made by flexible legs which make it possible to absorb part of the differential thermal expansions by their deformation. This makes it possible to limit the impact of the differences in materials between the casing, the ejection cone and the exhaust casing.
• the connecting member of the second set can be used as the connecting member of the first set.
• Each first fixing lug and each second fixing lug can comprise a middle portion arranged between a first end and a second end of said first fixing lug, respectively of said second fixing lug.
• the central portion can be configured to confer properties of flexibility to said first fixing lug, respectively of said second fixing lug.
• the middle portion may have a different thickness from the thickness of the first and second ends.
• upstream and downstream are defined in relation to the air inlet and outlet of the turbine, upstream corresponding to the air inlet and downstream to the turbine outlet. air.
• the axial direction corresponds to the direction of the axis of revolution of the blade wheel, which corresponds to the axis of rotation of said blade wheel, and a radial direction is a perpendicular direction, i.e. i.e. radial, to the axis of revolution.
• an axial plane is a plane containing the axis of revolution of the paddle wheel and a radial plane is a plane perpendicular to this axis.
• the first fixing lugs may have a stiffness less than a stiffness of the outer annular wall of the ejection cone.
• the first fixing lugs make it possible to limit the thermomechanical stresses on the exhaust casing and the box due to their deformation.
• the lower stiffness of the first fixing lugs can in particular be obtained by material properties and geometric parameters of the first fixing lugs.
• the internal annular wall of the box can be made of a metallic material or of a composite material with a ceramic matrix.
• the second fixing lugs may have a stiffness less than a stiffness of the internal annular wall of the box.
• the second fixing lugs make it possible to limit the thermomechanical stresses on the exhaust casing and the ejection cone due to their deformation.
• the lower stiffness of the second fixing lugs can in particular be obtained by material properties and geometric parameters of the second fixing lugs.
• the internal annular wall of the casing may have a downstream part connected to a downstream part of the external annular wall of the ejection cone.
• the downstream part of the internal annular wall of the casing can be connected, for example by screwing, to the downstream part of the external annular wall of the ejection cone.
• a downstream connecting member can be fixed on the one hand to the downstream part of the internal annular wall of the casing and on the other hand to the downstream part of the external annular wall of the ejection cone.
• the downstream connecting member can be formed by a flexible plate. This allows relative movements between the casing and the ejection cone and reduces the impact of thermomechanical stresses.
• downstream part of the annular wall can be free.
• the downstream part of the inner annular wall of the box can be devoid of connection, in particular with the downstream part of the outer annular wall of the ejection cone.
• the downstream part of the internal annular wall of the casing is free to move, which allows relative displacements between the casing and the ejection cone and reduces the impact of thermomechanical stresses.
• the box may be annular.
• the box may include a plurality of acoustic baffles extending radially outward from the inner annular wall of the box.
• the acoustic partitions can be made of a metallic material or of a composite material with a ceramic matrix.
• the box may be an acoustic box. The acoustic box makes it possible to limit noise pollution due to the flow of gases from the turbine.
• the number of second fixing lugs may be greater than the number of first fixing lugs.
• the connecting member may comprise an annular flange extending radially and connected to the exhaust casing, the first fixing tabs and the second fixing tabs being connected to said annular flange.
• the annular flange can be connected to a corresponding annular flange of the exhaust casing.
• the first fixing lugs and the second fixing lugs can be connected to a radially outer annular part of the annular flange.
• the first fixing tabs and the second fixing tabs can be connected to a radially outer end of the annular flange.
• the first fixing lugs and the second fixing lugs can be connected to a radially internal annular part of the annular flange.
• the first fixing lugs and the second fixing lugs can be connected to a radially inner end of the annular flange.
• the first fixing lugs and the second fixing lugs may extend perpendicular to the annular flange of the connecting member.
• Each of the first mounting tabs may be circumferentially spaced from one of the second mounting tabs.
• the first fixing lugs and the second fixing lugs can be distributed circumferentially, for example regularly, around the longitudinal axis.
• Each of the second fixing lugs can have a first end connected to said annular flange and each of the first fixing lugs can have a first end connected to the first end of one of the second fixing lugs.
• Several, in particular two, of the first fixing lugs can be connected to a first end of a single second fixing lug.
• connecting a part to another or fixing a part to another means fixing the parts together by a mechanical means (screwing, welding in particular) or creating a one-piece connection so that the two parts are integral with each other.
• the first fixing lugs can be connected to an annular part, in particular at one end, radially outer of the annular flange and the second fixing lugs can be connected to an annular part, in particular at one end, radially inner of the flange annular.
• first fixing lugs and the second fixing lugs are better decoupled.
• Each of the first fixing lugs may have a first end connected to the annular flange and a second end connected to the upstream annular part of the outer annular wall of the discharge cone, and each of the second fixing lugs may have a first end connected at the second end of one of the first fixing lugs and a second end connected to the upstream annular part of the internal annular wall of the box.
• each second fixing lug can be connected by screwing to the second end of one of the first fixing lugs.
• the first end of each second fixing lug can coincide with the second end of one of the first fixing lugs, so that the first fixing lug and the second fixing lug form a single piece.
• each of the second fixing lugs may be arranged upstream of, and radially inward with respect to, the first end of said second fixing lug.
• each of the second fixing lugs may be arranged downstream of, and radially inward with respect to, the first end of said second fixing lug.
• Each first end of one of the first fixing lugs can be connected to an annular part, in particular an end, radially outer of the annular flange.
• Each of the second fixing lugs can have a first end connected to the annular flange and a second end connected to the upstream annular part of the internal annular wall of the box, and each of the first fixing lugs can have a first end connected to the second end of one of the second fixing lugs and a second end connected to the upstream annular part of the outer annular wall.
• each first fixing lug can be connected by screwing to the second end of one of the second fixing lugs.
• each first fixing lug can be combined with the second end of one of the second fixing lugs, so that the first fixing lug and the second fixing lug form a single piece.
• each of the first fixing lugs may be arranged upstream of, and radially outwardly with respect to, the first end of said first fixing lug.
• each of the first fixing lugs may be arranged downstream of, and radially outwardly relative to, the first end of said first fixing lug.
• Each first end of the second fixing lugs can be connected to an annular part, in particular an end, radially inside the annular flange.
• At least one, in particular each, of the first fixing lugs can extend radially outwards and in a first direction of the circumferential direction around the longitudinal axis.
• At least one, in particular each, of the first fixing lugs may extend radially outwards and in a second direction of the circumferential direction around the longitudinal axis opposite to the first direction.
• Each first fixing lug extending in the first direction can be alternated with a first fixing lug extending in the second direction.
• the first end of each first, first-direction extending bracket may be arranged adjacent the first end of a first, second-direction extending bracket.
• the ejection cone in particular the outer annular wall of the ejection cone, can be made of a composite material with a ceramic matrix.
• the exhaust casing can be made of a metallic material.
• the connecting member can be made of a metallic material.
• the upstream annular end of the outer annular wall of the exhaust cone may be longitudinally aligned with an annular ring of the exhaust housing. This shroud externally delimits an internal annular surface for the flow of the primary air flow exiting the turbine.
• This presentation also relates to a turbine comprising the first or the second assembly of the aforementioned type.
• FIG. 1 Figure 1, already described, shows a schematic profile section of a turbomachine for aircraft.
• FIG. 2 Figure 2, already described, shows a schematic side view of a downstream part of the turbomachine of Figure 1.
• figure 3 is a schematic representation of a side view of a first example of assembly of an ejection cone to an exhaust casing.
• Figure 4 is a schematic representation of a side view of an alternative embodiment of the first example of assembly of an ejection cone to the exhaust casing.
• figure 5 is a schematic representation of a side view of a second example of assembly of an ejection cone to an exhaust casing.
• Figure 6 is a schematic representation of a side view of a third example of assembly of an ejection cone to an exhaust housing.
• Figures 7a and 7b show respectively a schematic perspective view of a first example of a connecting member and a schematic perspective view of an ejection cone fitted with the first example of a connecting member.
• FIGS. 8a, 8b and 8c represent respectively a schematic perspective view of the ejection cone fitted with a second example of a connecting member, a schematic perspective view of the second example of a connecting member and a schematic view in side section of the second connecting member.
• Figures 9a and 9b show a schematic side sectional view of a third example of a connecting member.
• Figures 10a and 10b show respectively a partial schematic perspective view of a fourth example of a connecting member and a schematic side sectional view of the fourth example of a connecting member.
• Figures 11a and 11b show respectively a partial schematic perspective view of a fifth example of a connecting member and a schematic side sectional view of the fifth example of a connecting member.
• Figures 12a, 12b and 12c respectively represent a schematic side sectional view, a schematic front sectional view along the axis AA and a schematic perspective view of a sixth example of a connecting member.
• FIGS. 13a and 13b represent respectively a schematic cross-sectional front view and a schematic perspective view of a seventh example of a connecting member.
• Figures 14a and 14b show respectively a schematic side sectional view and a schematic perspective view of an eighth example of a connecting member.
• Figure 15 shows a schematic perspective view of a ninth example of a connecting member.
• Figures 16a and 16d show schematic sectional side views of a tenth example of a connecting member and Figures 16b and 16c show schematic perspective views of the tenth example of a connecting member.
• Figures 17a and 17b show schematic sectional side views of an eleventh example of a connecting member.
• Figures 18a and 18b show schematic sectional side views of a twelfth example of a connecting member.
• Figures 19a and 19b show schematic sectional side views of a thirteenth example of a connecting member and Figure 19c shows a schematic perspective view of the thirteenth.
• the ejection cone 102 may be the ejection cone 1 of the turbomachine 1 of Figure 1 and comprises an outer annular wall 104 around a longitudinal axis X and forming a vein of the primary flow leaving a turbine arranged upstream of the ejection cone 102.
• the ejection cone 102 is made of a composite material with a ceramic matrix while the outer annular wall 104 is made of a composite material with a ceramic matrix.
• An annular acoustic box 106 is also arranged in the exhaust cone 102 to absorb part of the noise generated by the turbomachine comprising the exhaust cone 102.
• the acoustic box 106 comprises an internal annular wall 108 arranged in the external annular wall 104 of the ejection cone 102.
• the acoustic box 106 also includes a plurality of partitions 110 extending radially from the internal annular wall 108 of the acoustic box 106 and axially along the wall 108.
• the internal annular wall 108 and/or the acoustic partitions are made from a composite material with a ceramic matrix or from a metallic material.
• the internal annular wall 108 is fixed for example by screwing to the ejection cone 102 and is connected to a ferrule 112 of an exhaust casing 111 of the turbomachine.
• the shroud 112 of the exhaust casing 111 is arranged in the continuity of the outer annular wall 104 so as to define an upstream part of the flow path of the primary flow leaving the turbine.
• the internal annular wall 108 is connected to the ferrule 12 of the exhaust casing 111 through a connecting member 114.
• the outer annular wall 104 is connected at its downstream end to the ejection cone 102.
• the upstream end of the outer annular wall 104 is devoid of any mechanical connection and it is free to move, in particular axial and radial movement, by relative to the ferrule 112, or relative to the exhaust casing.
• the upstream end of the outer annular wall 104 is arranged in sliding contact with the shroud 112.
• the outer annular wall 104 of the ejection cone 102 has an upstream end able to move axially and radially when the thermal expansions are significant. This limits the impact of differences in materials and/or thermal gradients between the acoustic box, the exhaust cone and the exhaust casing.
• the outer annular wall 104 can also have an upstream end going as far as the exhaust casing 111.
• the ferrule 112 is not necessary and the connecting member 114 is directly attached to the exhaust casing 111, in particular to a flange of the exhaust casing 111.
• the upstream end of the outer annular wall 104 is thus free of contact.
• the outer annular wall 104 then defines the upstream part of the flow path of the primary flow leaving the turbine.
• the upstream end of the outer annular wall 104 is connected to the connecting member 114 while the upstream end of the inner annular wall 108 of the acoustic box 106 is devoid of connection with said connecting member 114.
• the upstream end of the internal annular wall 108 of the acoustic box 106 is free to move, in particular axial and radial movement, with respect to the shroud 112, or with respect to the exhaust casing.
• the internal annular wall 108 of the acoustic box 106 has an upstream end able to move axially and radially when the thermal expansions are significant. This limits the impact of differences in materials and/or thermal gradients between the acoustic box, the exhaust cone and the exhaust casing.
• the ejection cone 102 is connected to the exhaust casing 111 through the outer annular wall 104.
• the upstream end of the outer annular wall 104 is connected to the connecting member 114 and the upstream end of the inner annular wall 108 of the acoustic box 106 is also connected to the member connection 114.
• the downstream end of the internal annular wall 108 of the acoustic box 106 is itself devoid of connection with the ejection cone 102.
• the downstream end of the internal annular wall 108 of the acoustic box 106 is free in displacement, in particular in axial and radial displacement, with respect to the ejection cone 102.
• the internal annular wall 108 of the acoustic box 106 has a downstream end capable of moving axially and radially when the thermal expansions are significant. This limits the impact of differences in materials and/or thermal gradients between the acoustic box, the exhaust cone and the exhaust casing.
• the ejection cone 102 is connected to the exhaust casing 111 through the outer annular wall 104.
• FIG. 7 represents an upstream part of a turbomachine turbine, for example the turbomachine of FIG. primary air leaving the turbine.
• a shroud 106-1 is arranged upstream AM of the external annular wall arranged in the continuity of an exhaust casing not shown in FIG. 7 and of the external annular wall 104 of the ejection cone 102 and delimiting an annular surface flow rate of the primary air flow exiting the turbine.
• a box 106 is arranged in the exhaust cone 102 and is configured to absorb part of the noise generated by the turbomachine.
• the box 106 comprises an inner annular wall 108 arranged concentric with the outer annular wall 104 of the ejection cone 102.
• the box 106 comprises partitions 110 extending radially from the inner annular wall 108 in the direction of the outer annular wall 104.
• the outer annular wall 104 of the ejection cone 102 is made of a composite material with a ceramic matrix or of metal.
• the box 106, in particular the internal annular wall 108 and the partitions 110 are made of a composite material with a ceramic matrix or of metal.
• a connecting member 100 is provided to fix the ejection cone 102 and box 106 assembly to the exhaust casing.
• the connecting member 100 comprises a plurality of first fixing lugs 112-1 and second fixing lugs 114-1 flexible and distributed circumferentially around the longitudinal axis X.
• the connecting member comprises an annular flange 116 extending radially and comprising orifices to be fixed to the exhaust casing in particular to a corresponding flange of the exhaust casing.
• a first end of each first fixing lug 112-1 is connected to a radially outer end of the annular flange 116 through an outer annular part 113.
• a first end of each second fixing lug 114-1 is connected to a radially internal of the annular flange 116 through an internal annular part 115.
• each first fixing lug 112-1 is connected, by screwing, to an upstream end 103 of the ejection cone 102, in particular to an upstream end 103 of the outer annular wall 104 of the ejection cone 102, and a second end of each second fixing lug 114-1 is connected, by screwing, to the internal annular wall 108 of the box 106.
• the annular flange 116 is formed by a plurality of beams 117 distributed circumferentially around the longitudinal axis X and connecting the external annular part 113 and the internal annular part 115.
• the annular flange can be solid and include holes to be assembled by screwing to ferrule 106-1 of the exhaust casing.
• each first fixing lug 112-1 is arranged radially inward, i.e. in the direction of the longitudinal axis X with respect to the first end of said first fixing lug 112-1.
• the first fixing lugs ensure the connection of the ejection cone 102 to the exhaust casing and the second fixing lugs ensure the connection of the box 106 to the exhaust casing.
• the first brackets and the second brackets are flexible and decoupled. Thus, they make it possible to absorb part of the thermodynamic stresses due to the difference in materials, on the one hand, between the ejection cone and the exhaust casing, and on the other hand, between the box and the casing. 'exhaust.
• the connecting lugs also make it possible to absorb part of the thermodynamic stresses undergone by the outer annular wall and the box due to their differential thermal expansions.
• the connecting member 200 comprises the same elements as the connecting member 100. Unlike the annular flange 116 is formed of a single tenon.
• Each first fixing lug 112-1 is formed by a plate having a second end 202 connected to an upstream part of the outer annular wall 104 located downstream of the upstream end 103 of the outer annular wall 104.
• Each first fixing lug 112-1 further comprises a first end 210 connected directly to the annular flange 116, in particular to the radially outer end 214 of the annular flange 116.
• Each first fixing lug 112-1 comprises a central portion 212 between the second end 202 and the first end 210.
• the second end 202 is arranged to project radially outwardly relative to the first end 210.
• the second end 202 is longitudinally aligned with the first end 210.
• the second end 202 has a radial thickness less than the radial thickness of the central portion 212 and the radial thickness of the first end 210. This difference in radial thicknesses makes the first fixing lug 112-1 flexible.
• Each second fixing lug 114-1 comprises a first end 208 connected to the annular flange 116 through the inner annular part 115 which extends from the radially inner end 216 of the annular flange 116.
• Each second fixing lug 114- 1 comprises a second end 204 connected by screwing to the internal annular wall 108 of the box 106.
• Each second fixing lug 114-1 comprises a central portion 206 between the second end 204 and the first end 208.
• the central portion 206 has a radial thickness less than the radial thickness of the first end 208 and the radial thickness of the second end 204. This difference in radial thicknesses makes the second fixing lug 114-1 flexible.
• each second fixing lug 114-1 has a width in a circumferential direction less than a width in the circumferential direction of the first end 208 of the second fixing lug 114-1.
• the outer annular wall 104 can extend upstream to ensure continuity with the exhaust casing in place of the ferrule 106-1.
• the number of first fixing lugs 112-1 can be less than the number of second fixing lugs 114-1. In this case, each first fixing lug 112-1 can be arranged circumferentially opposite one of the second fixing lugs 114-1.
• each first fixing lug 112-1 is removable and is connected by screwing to the annular flange 116, in particular in a central part of the connecting flange 116.
• each second fixing lug 114-1 is removable and is connected by screwing to the annular flange 116, in particular in a central part of the flange connection 116.
• each second fixing lug 114-1 has a uniform radial thickness at its first end 208, its second end 204 and its central portion 206.
• first fixing lugs 112-1 in the case of FIG. 9a or the second fixing lugs 114-1 in the case of FIG. 9b can be replaced more easily.
• the upstream annular end 103 of the outer annular wall 104 of the ejection cone 102 is arranged in continuity with an annular part 304 of the exhaust casing to form a flow surface for the primary flow exiting the turbine.
• the connecting member 400i comprises the same elements as the connecting member 200 of Figure 8. Unlike the first fixing lugs 112-1 and the second fixing lugs 114-1 are connected to the radially outer end 214 of the annular flange 116. The first end 210 of each first fixing lug 112-1 extends from the outer annular part 113 of the annular flange. The first end 210 of each second fixing lug 114-1 also extends from the outer annular part 113 of the annular flange.
• Each first fixing lug 112-1 is interposed with a second fixing lug 114-1.
• Each first fixing lug 112-1 is also spaced circumferentially from the second fixing lugs 114-1 arranged on either side of said first fixing lug 112-1.
• FIG. 16d A variant of the connecting member 400i is shown in Figure 16d, in which each first fixing lug 112-1 is superimposed with a second fixing lug 114-1.
• the first end 210 of the first fixing lug 112-1 is screwed to the first end 208 of the second fixing lug superposed with said first fixing lug 112-1 at the level of the radially outer end 214 of the annular flange 116 .
• the connecting member 4002 comprises the same elements as the connecting member 400i of Figure 10. Unlike the first fixing lugs 112-1 and the second fixing lugs 114-1 are connected to the radially internal end 216 of the annular flange 116. The first end 210 of each first fixing lug 112-1 extends from the internal annular part 115 of the annular flange 116. The first end 210 of each second fixing lug 114-1 also extends from the outer annular portion 115 of the annular flange 116.
• Each first fixing lug 112-1 is interposed with a second fixing lug 114-1.
• Each first fixing lug 112-1 is also spaced circumferentially from the second fixing lugs 114-1 arranged on either side of said first fixing lug 112-1.
• FIG. 16a A variant of the connecting member 4002 is shown in Figure 16a, in which each first fixing lug 112-1 is superimposed with a second fixing lug 114-1.
• the first end 210 of the first fixing lug 112-1 is screwed to the first end 208 of the second fixing lug 114-1 superposed with said first fixing lug 112-1 at the level of the radially inner end 216 of the ring flange 116.
• Each first fixing lug 112-1 as represented in FIG. 16b, can be formed by a plate.
• Each first fixing lug 112-1 as represented in FIG. 16c, can be formed by two fingers that are radially separate and connected at the level of the first end 210 of the first fixing lug.
• the fingers have second ends 2022 and 202i connected to the outer annular wall 104 of the ejection cone 102.
• the connecting member 500 comprises the same elements as the connecting member 400. Unlike each first fixing lug 112-1 extends in a first direction from a circumferential direction B around the longitudinal axis X. The second end 202 of each first fixing lug 112-1 is arranged projecting radially with respect to the first end 210 of said first fixing lug 112-1. Moreover, the second end 202 of each first fixing lug 112-1 is circumferentially offset with respect to the first end 210 of said first fixing lug 112-1.
• the connecting member 500 further comprises at least one first fixing lug 112-11 extending in the first direction of the circumferential direction B and at least one first fixing lug 112- 12 extending in a second direction opposite to the first direction of the circumferential direction B.
• a pair of first fixing lugs 112-11 and 112-12 are arranged head to tail.
• a second end 210i of the first mounting bracket 112-11 extending in the first direction is adjacent to a second end 2102 of the first mounting bracket 112-12 extending in the second direction.
• a first end 202i of the first mounting bracket 112-11 extending in the first direction is opposed to a first end 2022 of the first mounting bracket 112-12 extending in the second direction.
• the second end 210i of the first fixing lug 112-11 extending in the first direction and the second end 2102 of the first fixing lug 112-12 extending in the second direction are connected to the same first end 208 d a second bracket 114-1.
• each first fixing lug 112- 1 extends simultaneously in the direction of the longitudinal axis X and in the first direction of the circumferential direction B.
• the second end 202 of each first fixing lug 112-1 is offset circumferentially and in the direction of the longitudinal axis X with respect to the first end 210 of said first fixing lug 112-1.
• the variant of the connecting member 600 shown in Figure 15 comprises the same elements as the connecting member 500 of Figure 13. Unlike and similar to the connecting member 600 of Figure 14, a first fixing lug 112-11 extends simultaneously in the direction of the longitudinal axis X and in the first direction of the circumferential direction B and is interposed with a first fixing lug 112-12 extends simultaneously in the direction of the longitudinal axis X and in the second direction of the circumferential direction B.
• the second end 202i and 2022 of each first fixing lug 112-11 and 112-12 is offset circumferentially and in the direction of the longitudinal axis X with respect to the first end 210i and 21 ⁇ 2 of said first bracket 112-1 i and 112-12.
• the connecting member 700 comprises the same elements as the connecting member 4002 of Figure 16. Unlike, the first end 210 of each first fixing lug 112-1 is fixed by screwing at the second end 204 of a second bracket 114-1.
• each second fixing lug 114-1 is connected to the internal annular wall 108.
• the second end 202 of each first fixing lug 112-1 is connected to the outer annular wall 104.
• each second fixing lug 114-1 is connected to the annular flange 116 at its radially inner end 216.
• each first fixing lug 112-1 is arranged radially projecting outwards and downstream from the first end 210 of said first fixing lug 112-1.
• each first fixing lug 112-1 is arranged projecting radially outwards and upstream from the first end 210 of said first fixing lug 112-1.
• each first fixing lug 112-1 is integral with the second end 204 of a second fixing lug 114-1, so that the first fixing lug 112 -1 forms a single piece with said second fixing lug 114-1.
• the connecting member 800 comprises the same elements as the connecting member 700 of Figure 17. Unlike, the first end 208 of each second fixing lug 114-1 is fixed by screwing at the second end 202 of a first bracket 112-1.
• each second fixing lug 114-1 is connected to the internal annular wall 108.
• each first fixing lug 112-1 is connected to the outer annular wall 104.
• each first fixing lug 112-1 is connected to the annular flange 116 at its radially outer end 214.
• each second bracket 114-1 is arranged projecting radially inward and downstream of the first end 208 of said second bracket 114-1.
• each second bracket 114-1 is arranged projecting radially inward and upstream from the first end 208 of said second bracket 114-1.
• each second fixing lug 114-1 is integral with the second end 202 of a first fixing lug 112-1, so that the first fixing lug 112- 1 forms a single piece with said second fixing lug 114-1.

Landscapes

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

Applications Claiming Priority (3)

Publications (1)

Family

ID=78806546

Family Applications (1)

Country Status (3)

Family Cites Families (8)

• 2021
  • 2021-11-04 WO PCT/FR2021/051948 patent/WO2022096832A1/fr active Application Filing
  • 2021-11-04 EP EP21815569.5A patent/EP4240958A1/de active Pending
  • 2021-11-04 US US18/251,965 patent/US20230407814A1/en active Pending

Also Published As

Similar Documents

Legal Events