EP3705686B1 - Gehäuse eines turbotriebwerks - Google Patents

Gehäuse eines turbotriebwerks Download PDF

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Publication number
EP3705686B1
EP3705686B1 EP20159352.2A EP20159352A EP3705686B1 EP 3705686 B1 EP3705686 B1 EP 3705686B1 EP 20159352 A EP20159352 A EP 20159352A EP 3705686 B1 EP3705686 B1 EP 3705686B1
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EP
European Patent Office
Prior art keywords
arm
casing
boss
shroud
turbomachine
Prior art date
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EP20159352.2A
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English (en)
French (fr)
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EP3705686A1 (de
Inventor
Patrick Jean Laurent Sultana
Gaël Frédéric Claude Cyrille EVAIN
Olivier Arnaud Fabien Lambert
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Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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Publication of EP3705686A1 publication Critical patent/EP3705686A1/de
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/30—Exhaust heads, chambers, or the like
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/26—Double casings; Measures against temperature strain in casings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/14—Casings or housings protecting or supporting assemblies within
    • 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
    • F05D2240/00—Components
    • F05D2240/90—Mounting on supporting structures or systems
    • F05D2240/91—Mounting on supporting structures or systems on a stationary structure
    • 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
    • F05D2260/30—Retaining components in desired mutual position
    • 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

Definitions

  • the present invention relates to turbomachines, in particular aeronautical turbine engines, and more particularly to an aircraft turbomachine exhaust casing.
  • a turbomachine exhaust casing generally includes an inner hub and an outer shroud extending around the hub.
  • the shroud is configured to define with the hub an annular stream for the flow of a gas flow and is rigidly connected to the hub by arms substantially radial with respect to a longitudinal axis of the turbomachine.
  • an exhaust casing is mounted downstream of a turbine and the gas flow which passes through the exhaust casing is therefore the flow of exhaust gases leaving the turbine .
  • a turbomachine may comprise other similar casings such as an intermediate casing or an interturbine casing better known by its English designation TVF for “Turbine Vane Frame”, or even a TCF designating in English a “Turbine Center Frame”.
  • An intermediate casing is interposed between a low pressure compressor and a high pressure compressor of the turbomachine, and is therefore traversed by a flow of gas leaving the low pressure compressor and intended to supply the high pressure compressor.
  • a conventional turbomachine notably involves the passage of electrical cables and the circulation of various fluids through the turbomachine.
  • these fluids can be air, oil, or oily air.
  • pipes in the very structure of the turbomachine.
  • Some of these ducts, called service tubes, must connect radially external parts of the turbomachine to radially internal parts, and thus cross the primary and secondary air flows.
  • the document EP 2 610 442 A1 describes such a configuration.
  • the hollow arms of the exhaust casing thus allow the passage of auxiliary elements, such as auxiliary tubes, without disturbing the flow of the flow inside the vein thanks to their internal cavity.
  • each of the ancillary elements makes it possible to connect at least one first piece of equipment located radially inside the passage to at least one second piece of equipment located radially outside the passage of the casing.
  • FIG. 1 On the figure 1 is illustrated an example of a part of an exhaust casing 1 of a turbomachine comprising an ancillary element in the form of a tube 2 disposed inside a longitudinal cavity 3 provided inside a hollow arm 4 connecting an inner hub 5 to an outer shroud 6 of the exhaust casing 1.
  • the tube 2 is generally inserted into the longitudinal cavity 3 of the hollow arm 4 at the junction between the hollow arm 4 and the outer shroud 6.
  • the tube 2 is then slid inside the cavity 3 until it extends there completely.
  • the tube 2 has two ends 8 and 9 which can be fixed respectively to the inner hub 5 and to the outer shroud 6 in order to secure the tube 2 to the inner hub 5 and to the outer shroud 6.
  • the ends 8 and 9 of the tube are then assembled to tubes included in hydraulic or air circuits arranged in radially external or internal parts, so as to ensure fluid communication between radially external parts of the turbomachine and radially internal parts.
  • the outer surface of the tube is not in contact with the longitudinal cavity wall 3.
  • the tube 2 thus arranged is therefore free to vibrate.
  • the tube 2 has natural frequencies of vibration. Tube 2 vibrates most violently when excited at these frequencies. This induces rapid fatigue which may go as far as rupture. These frequencies depend on the length of the tube 2, but also on the material of which it is made, on its thickness, or on its temperature, among other things. The longer the tube 2, the lower the lowest natural frequency, and closer to the frequencies of rotation of the low and high pressure bodies of the turbomachine. These vibrations lead to problems of robustness and safety within the turbomachines. This is especially true in the case of large engines.
  • an ancillary element such as tube 2 generally comprises a longitudinal body defining an axis of elongation and at least one wedging damper inside the cavity, this damper making it possible in particular to avoid that the ancillary element does not come into resonance, and thus does not deteriorate, when it is subjected to the various vibratory stresses generated by the turbomachine in operation.
  • shock absorbers exist in the state of the art.
  • each blade comprises, on the one hand, a portion fixed to the body of the element, and on the other hand, a free portion.
  • Each blade is positioned flat on the service element, it extends along a transverse axis perpendicular to the axis of elongation of the element and is configured to deform in a plane perpendicular to the axis of elongation.
  • the service element is configured to be mounted in the cavity in a direction substantially parallel to the axis of elongation of the element. During its assembly, the free portions are constrained so that the latter each exert on a wall delimiting the cavity a return force necessary for the dampers to be able to fully perform their function.
  • the sharp edges present on the sides of the dampers come into contact with the wall of the cavity and thus oppose its introduction.
  • the operator is then obliged to operate by a back and forth movement and/or to force excessively at the risk of damaging the shock absorbers and/or the wall of the cavity, and to the detriment of productivity.
  • the assembly is all the more critical because the free portions each exert a return force on the wall of the cavity.
  • Elastic return stiffeners are known from the document FR 3 064 302 and document FR 3 050 229 . They are used so that the natural modes of the ancillary elements on which they are mounted are not in the operating range of the turbomachine. These stiffeners have similar drawbacks to shock absorbers, in particular with respect to the sensitivity of the compression of the stiffeners during assembly. Indeed, the excessive compression of the latter during assembly can lead to their deterioration and therefore to the absence of contact between the stiffeners and the wall, thus rendering them ineffective.
  • the invention aims to overcome the above drawbacks and to overcome the difficulties mentioned above by proposing a turbomachine casing making it possible to ensure the support of the stiffeners or shock absorbers of the service elements on the interior wall of its hollow arms. with certainty and without sensitivity to the assembly procedure, and more particularly by avoiding any compression of the stiffeners of the service element during assembly.
  • An object of the invention proposes a turbomachine casing, the casing having the shape of a crown defining an axial direction and a radial direction and comprising an inner shroud, an outer shroud extending around and at a distance from the inner shroud, and hollow arms connecting the outer shroud to the inner shroud and each intended to receive a tubular service element, each hollow arm defining an internal housing connecting a first passage orifice passing through the inner shroud in the radial direction to a second passage orifice passing through the outer shroud in the radial direction, and comprising an inner wall delimiting the inner housing.
  • each arm comprises at least one boss on said internal wall of the arm projecting from the internal wall towards the internal housing and defining a constriction of the internal housing in a section plane orthogonal to the direction in which the arm extends, said at least one boss being intended to cooperate with the tubular service element, said at least one boss forming a support means for the tubular service element.
  • Said at least one boss even preferably constitutes the only support means for the tubular service element situated in the housing of the arm radially between the first and the second passage orifice.
  • the constriction has in said section plane a passage section smaller than the section of said second passage orifice.
  • the interior arrangement of the arms with a boss makes it possible, firstly, to stiffen the retention of the service element within the arm and thus to limit the risks of resonance.
  • the interior arrangement of the arms with a boss makes it possible, secondly, to provide stiffeners on the service tubes that are shorter and therefore stiffer and thus more effective in their role as dynamic stiffeners than the stiffeners known in the state of the art, because the distance between the tube and the arm is reduced locally and the operator does not have to deform the stiffeners himself, the stiffeners deforming without assistance when mounting the tube along its axis.
  • the internal arrangement of the arms with a boss makes it possible, thirdly, to avoid any plasticization of the stiffeners during their compression during assembly. Indeed, since the operator does not need to compress and plasticize the stiffeners during assembly, their width can easily be dimensioned.
  • said at least one boss of each arm can be made of the same material as the arm with which it is associated.
  • the arm and said at least one boss can be made of metal or Inconel 7180 for example.
  • each arm may comprise a boss extending over at least half the perimeter of said internal wall of the internal housing in said section plane orthogonal to the direction in which the arm extends, or at least a pair of bosses arranged facing each other, to reduce the dimensions of the section of the passage of the constriction at least in one direction.
  • said at least one boss of each arm can extend, in the direction in which the arm extends between the inner shroud and the outer shroud, over a height of between 5 and 10 mm in order to constitute an effective support zone for the shock absorbers or the stiffeners of the service element.
  • said at least one boss of each arm can extend, in a direction orthogonal to the internal wall of the arm, over a thickness of between 1 and 10 mm.
  • said at least one boss of each arm can be made in a single piece with the arm with which it is associated.
  • said at least one boss of each arm can form, in a section plane comprising the axial direction and the radial direction, a constriction of the internal housing of isosceles trapezoidal shape with the largest base disposed between the the smallest base and the second through hole.
  • Such a form of boss allows compression of the stiffeners or dampers of the easement element when it is fitted into the arm and tightened with screws at its top for example.
  • edges between the large base and the small base may be fillets that do not have a flat surface.
  • said at least one boss is made in a single piece with the arm, its machining makes it possible to compensate for the foundry defects of the arms and the bosses and thus to ensure the quality of the contact between the stiffeners of the service element and the arm.
  • said casing is an exhaust casing of a turbomachine turbine.
  • the invention also relates to a turbine comprising a casing as defined above.
  • turbomachine comprising a turbomachine turbine as defined above.
  • Another subject of the invention is an aircraft comprising at least one turbine engine as defined above.
  • FIG. 1 On the picture 2 is shown a first sectional view along a first section plane II-II of a casing 10 of a dual-flow turbomachine 11, the casing 10 comprising an exhaust casing 12 located between a low-pressure turbine 13 and a nozzle 14 for ejecting the combustion gases from the turbine 13.
  • the turbomachine 11 defines an axial direction DA corresponding to the axis of revolution X of the turbomachine 11 and the axis of rotation of the low pressure turbine 13, and a radial direction DR.
  • the first section plane II-II of the turbomachine 11 on the figure 2 includes the axial direction DA and the radial direction DR.
  • the second cutting plane III-III is orthogonal to the axial direction DA and includes the radial direction DR.
  • the second cutting plane III-III is located in the free space between the low pressure turbine 13 and the exhaust casing 12.
  • the exhaust casing 12 comprises an inner shroud 15 and an outer shroud 16 extending around and at a distance from the inner shroud 15.
  • the outer shroud 16 is configured to define with the inner shroud 15 an annular flow vein 17 of a combustion gas flow F.
  • the exhaust casing 12 further comprises arms 18 rigidly connecting the outer shroud 16 to the inner shroud 15. The arms 18 extend mainly in the radial direction DR with respect to the axis of revolution X of the turbomachine 11.
  • turbomachine 11 can comprise other casings having a similar structure, and thus the exhaust casing 12 could for example be an intermediate casing located between a low pressure compressor and a compressor high pressure (not visible on the figure 2 ).
  • the exhaust casing 12 comprises a plurality of hollow tubular arms 18 each allowing the passage of a service element 21.
  • the passage of the service elements 21 in the arms 18 has the particular advantage of not disturbing the flow of the flow of gas F inside the stream 17, that is to say of avoiding the loss of charge.
  • An easement element 21 connects at least a first piece of equipment located radially inside the section 17 to at least a second piece of equipment located radially outside the section 17.
  • Such an element 21 can for example comprise one or several air ducts and/or one or more oil ducts and/or one or more electrical cables, etc.
  • FIG. 4 On the figure 4 is shown a sectional view of an arm 18 of the exhaust casing 12 according to a first embodiment.
  • the arm 18 has a length in a substantially radial direction DR, a width in the axial direction DA and a thickness in a circumferential direction DC.
  • the length of the arm is greater than the width of the arm which is greater than its thickness.
  • the arm 18 thus has the shape of a hollow blade, the blade extending mainly in a plane comprising the radial direction DR and the axial direction DA and having a thickness in the circumferential direction DC.
  • the tubular arm 18 comprises a cavity 180 extending substantially radially between the inner shroud 15 and the outer shroud 16.
  • the cavity 180 is delimited by an internal wall 182 of the arm 18.
  • the cavity 180 opens both on the inner shroud 15 via a first passage orifice 150 and on the outer shroud 16 via a second passage orifice 160.
  • the internal wall 182 comprises two parts 182a, 182b extending opposite one another.
  • each arm 18 comprises two bosses 185 arranged facing each other and separated by a free space extending in the circumferential direction DC.
  • a first boss 185a is made on the first internal wall part 182a while the second boss 185b is made on the second internal wall part 182b.
  • the two bosses 185a and 185b are made in the middle of the arm 18, namely halfway between the inner shroud 15 and the outer shroud 16.
  • FIG 6 On the figure 6 is shown a schematic sectional view of the arm of the exhaust housing of the figure 4 .
  • the two bosses 185a and 185b define a passage of smaller dimension than the dimension in the same direction of the passage formed by the second passage orifice 160 of the outer shroud 16.
  • the two bosses 185a and 185b thus form a constriction 188 of the cavity 180 in the middle of the arm 18 makes it possible to ensure contact between a stiffener 210 of an easement element 21 and the internal wall 182 of the arm 18 at at least a height of the arm 18, that of the bosses 185a and 185b.
  • the distance between the service element 21 and the internal wall 182 being reduced to this height thanks to the bosses of the stiffeners 210 provided on the service elements 21 can be shorter than in the state of the art and thus stiffer which makes it possible to improve their effectiveness in their role of dynamic stiffener.
  • the two bosses 185a and 185b could be formed by a single boss made over the entire perimeter of the internal wall 182.
  • FIG. 7 On the figure 7 is shown a schematic sectional view of the arm 18 of the exhaust casing 12 according to a second embodiment of the invention.
  • the two bosses 1850a and 1850b of each arm 18 form, in a section plane comprising the axial direction DA and the radial direction DR, a constriction 1880 of the cavity 180 of isosceles trapezoidal shape with the largest base disposed between the base the smallest and the second through hole.
  • the largest basis is arranged radially outside the smaller base to facilitate insertion of the arm from the outside.
  • each boss 1850a and 1850b has a generally triangular shape in a section plane orthogonal to the axial direction DA, and more particularly the shape of a right triangle, with one of the sides forming a right angle with the internal wall 182, a first end of its hypotenuse 1852 oriented towards the constriction 1880, that is to say towards the service element 21, and the second opposite end of the hypotenuse which forms a point is oriented radially towards the outside of the constriction 1880 and towards the second passage orifice 160 made in the outer shroud 16.
  • the slope of the triangular shape of the boss 1850 allows compression of the stiffeners 210 of the easement element 21 easier when it is fitted into the arm and to compensate for the foundry defects of the arms 18 and the bosses 1850a and 1850b and so on. ensure the quality of the contact between the stiffeners 210 of the service element 21 and the arm 18.
  • the invention thus provides a turbomachine casing making it possible to ensure the support of the stiffeners or dampers of the ancillary elements on the inner wall of its hollow arms in a certain manner while facilitating assembly, and more particularly avoiding any damage by compression. stiffeners of the service element during assembly.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Supercharger (AREA)

Claims (10)

  1. Gehäuse eines Turbotriebwerks (11), wobei das Gehäuse (12) die Form eines Kranzes hat, der eine axiale Richtung (DA) und eine radiale Richtung (DR) definiert und einen Innenring (15), einen Außenring (16), der sich um und beabstandet vom Innenring (15) erstreckt, und hohle Arme (18) aufweist, die den Außenring (16) mit dem Innenring (15) verbinden und jeweils dazu bestimmt sind, ein rohrförmiges Hilfselement (21) aufzunehmen, wobei jeder hohle Arm (18) eine innere Aufnahme (180) definiert, die eine erste Durchgangsöffnung (150), die den Innenring (15) in der radialen Richtung (DR) durchquert, mit einer zweiten Durchgangsöffnung (160) verbindet, die den Außenring (16) in der radialen Richtung (DR) durchquert, und eine Innenwand (182) aufweist, die die innere Aufnahme (180) begrenzt,
    wobei jeder Arm (18) mindestens eine Verdickung (185a, 185b, 1850a, 1850b) auf der Innenwand (182) des Arms (18) umfasst, die sich von der Innenwand (182) hervorstehend zur inneren Aufnahme (180) erstreckt und eine Verengung (188, 1880) der inneren Aufnahme (180) in einer zu der Richtung, in der sich der Arm (18) erstreckt, orthogonalen Schnittrichtung definiert, wobei die mindestens eine Verdickung bestimmt ist, mit dem rohrförmigen Hilfselement (21) zusammenzuwirken, wobei die mindestens eine Verdickung (185a, 185b, 1850a, 1850b) ein Stützmittel des rohrförmigen Hilfselements (21) bildet.
  2. Gehäuse (12) nach Anspruch 1, wobei die mindestens eine Verdickung (185a, 185b, 1850a, 1850b) jedes Arms (18) aus demselben Material wie der Arm (18) hergestellt ist, dem sie zugeordnet ist.
  3. Gehäuse (12) nach einem der Ansprüche 1 oder 2, wobei jeder Arm eine Verdickung umfasst, die sich auf mindestens der Hälfte des Umfangs der Innenwand (182) der inneren Aufnahme (180) in der zu der Richtung, in der sich der Arm (18) erstreckt, orthogonalen Schnittebene erstreckt oder mindestens ein Paar Verdickungen (185a, 185b, 1850a, 1850b), die einander zugewandt angeordnet sind, um die Abmessungen des Querschnitts des Durchgangs der Verengung (188, 1880) in mindestens einer Richtung zu reduzieren.
  4. Gehäuse (12) nach einem der Ansprüche 1 bis 3, wobei sich die mindestens eine Verdickung (185a, 185b, 1850a, 1850b) jedes Arms (18) in der Richtung, in der sich der Arm (18) zwischen dem Innenring (150) und dem Außenring (160) erstreckt, über eine Höhe erstreckt, die zwischen 5 und 10 mm liegt.
  5. Gehäuse (12) nach einem der Ansprüche 1 bis 4, wobei sich die mindestens eine Verdickung (185a, 185b, 1850a, 1850b) jedes Arms (18) in einer Richtung, die zu der Innenwand (182) des Arms (18) orthogonal ist, über eine Dicke erstreckt, die zwischen 1 und 10 mm liegt.
  6. Gehäuse (12) nach einem der Ansprüche 1 bis 5, wobei die mindestens eine Verdickung (185a, 185b, 1850a, 1850b) jedes Arms (18) aus einem einzigen Teil mit dem Arm (18) hergestellt ist, dem sie zugeordnet ist.
  7. Gehäuse (12) nach einem der Ansprüche 1 bis 6, wobei die mindestens eine Verdickung (1850a, 1850b) jedes Arms (18) in einer Querschnittsebene, die die axiale Richtung (DA) und die radiale Richtung (DR) umfasst, eine Verengung (1880) der inneren Aufnahme (180) in Form eines gleichschenkligen Trapezes mit der größten Basis, die zwischen der kleinsten Basis und der zweiten Durchgangsöffnung (160) angeordnet ist, bildet.
  8. Gehäuse (12) nach einem der Ansprüche 1 bis 7, wobei das Gehäuse ein Abgasgehäuse einer Turbine eines Turbotriebwerks ist.
  9. Turbine, umfassend ein Gehäuse (12) nach einem der Ansprüche 1 bis 8.
  10. Turbotriebwerk (11), umfassend eine Turbine nach Anspruch 9.
EP20159352.2A 2019-02-25 2020-02-25 Gehäuse eines turbotriebwerks Active EP3705686B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1901889A FR3093128B1 (fr) 2019-02-25 2019-02-25 Carter de turbomachine

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EP3705686A1 EP3705686A1 (de) 2020-09-09
EP3705686B1 true EP3705686B1 (de) 2023-07-05

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US (1) US11156129B2 (de)
EP (1) EP3705686B1 (de)
CN (1) CN111608750B (de)
FR (1) FR3093128B1 (de)

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CN112253262B (zh) * 2020-10-21 2022-11-22 中国航发沈阳发动机研究所 一种集成式供油引气结构
CN112211683B (zh) * 2020-10-21 2022-11-22 中国航发沈阳发动机研究所 一种涡轮后机匣隔热罩
FR3116859B1 (fr) * 2020-11-27 2022-10-14 Safran Aircraft Engines Carter comprenant des raidisseurs internes et/ou externes
CN114562472B (zh) * 2021-11-18 2023-08-25 中国航空发动机研究院 一种压气机测试结构
US20240141802A1 (en) * 2022-10-28 2024-05-02 Pratt & Whitney Canada Corp. Conduit bushing with cellular material

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FR3036437B1 (fr) * 2015-05-22 2017-05-05 Snecma Ensemble de turbomachine pour lubrifier un support de palier
FR3050229B1 (fr) 2016-04-18 2018-04-27 Safran Aircraft Engines Carter d'echappement de turbomachine
US10465561B2 (en) * 2016-07-13 2019-11-05 Safran Aircraft Engines Optimized aerodynamic profile for an arm of a structural casing of a turbine, and structural casing having such an arm
FR3055655B1 (fr) * 2016-09-06 2019-04-05 Safran Aircraft Engines Carter intermediaire de turbine de turbomachine
FR3061928B1 (fr) 2017-01-18 2019-11-15 Safran Aircraft Engines Turbine de turbomachine comprenant un etage distributeur en materiau composite a matrice ceramique
FR3064302B1 (fr) 2017-03-23 2019-06-07 Safran Aircraft Engines Appuis centraux de tubes servitude a retour elastique
US10727656B2 (en) * 2017-11-08 2020-07-28 Raytheon Technologies Corporation Igniter cable conduit for gas turbine engine

Also Published As

Publication number Publication date
US11156129B2 (en) 2021-10-26
US20200291822A1 (en) 2020-09-17
FR3093128A1 (fr) 2020-08-28
CN111608750A (zh) 2020-09-01
EP3705686A1 (de) 2020-09-09
FR3093128B1 (fr) 2021-05-14
CN111608750B (zh) 2024-04-19

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