EP3999721B1 - Logement de turbine doté d'une bride de raccordement à faible tension et turbine de gaz d'échappement dotée d'un tel logement de turbine - Google Patents

Logement de turbine doté d'une bride de raccordement à faible tension et turbine de gaz d'échappement dotée d'un tel logement de turbine

Info

Publication number
EP3999721B1
EP3999721B1 EP20733442.6A EP20733442A EP3999721B1 EP 3999721 B1 EP3999721 B1 EP 3999721B1 EP 20733442 A EP20733442 A EP 20733442A EP 3999721 B1 EP3999721 B1 EP 3999721B1
Authority
EP
European Patent Office
Prior art keywords
turbine
casing
housing
connection
turbine casing
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP20733442.6A
Other languages
German (de)
English (en)
Other versions
EP3999721A1 (fr
Inventor
Matthias Richner
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Accelleron Switzerland Ltd
Original Assignee
Accelleron Switzerland Ltd
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Accelleron Switzerland Ltd filed Critical Accelleron Switzerland Ltd
Publication of EP3999721A1 publication Critical patent/EP3999721A1/fr
Application granted granted Critical
Publication of EP3999721B1 publication Critical patent/EP3999721B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • 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
    • F01D25/243—Flange connections; Bolting arrangements
    • 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
    • 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
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings 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
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • F01D25/162—Bearing supports
    • 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
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or 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
    • F05D2220/00—Application
    • F05D2220/40—Application in turbochargers
    • 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
    • F05D2240/10—Stators
    • F05D2240/15—Heat shield
    • 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
    • F05D2260/31—Retaining bolts or nuts
    • 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
    • F05D2260/39—Retaining components in desired mutual position by a V-shaped ring to join the flanges of two cylindrical sections, e.g. casing sections of a turbocharger
    • 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
    • F05D2260/97—Reducing windage losses
    • F05D2260/972—Reducing windage losses in radial flow machines

Definitions

  • the invention relates to a turbine housing with a low-stress connecting flange and an exhaust gas turbine with such a turbine housing.
  • the exhaust gas turbine can, for example, be a turbocharger turbine for a turbocharger or a utility turbine.
  • a one-piece exhaust system for a gas turbine is known.
  • This exhaust system comprises a turbine outlet housing and a turbine exhaust manifold, the turbine outlet housing being connected to the turbine exhaust manifold via outward-facing interface flanges. This allows the turbine exhaust manifold to be easily detached from the turbine outlet housing and replaced with a new component if necessary.
  • a turbocharger is known in which sealing agents are arranged between a turbine inlet spiral and a turbine nozzle ring defining a circular passage.
  • a typical turbocharger has a turbine housing, a bearing housing and a compressor housing, with the turbine housing being connected to the bearing housing and the bearing housing further connected to the compressor housing.
  • connection between the turbine housing and the bearing housing must meet several requirements. These include ensuring gas tightness, preventing twisting between the two housings due to external forces, and guaranteeing the cohesion of the two housings even in the event of a burst. To meet these requirements, the connection between the turbine housing and the bearing housing must be designed to withstand large temperature differences between the two housings and high forces in a burst.
  • a reliable safety containment — also known as "containment" – is a crucial and therefore highly demanding design requirement for an exhaust gas turbine in such a burst scenario.
  • FIG. 1 shows a first sectional view illustrating a turbine housing according to the prior art.
  • This turbine housing has a connecting flange 2, via which the turbine housing 1 is connected to the bearing housing 14 of a turbocharger.
  • This connection is achieved using connecting elements screwed into housing connection bores of the connecting flange.
  • These connecting elements by means of nuts 17, press clamping tabs 16 onto the connecting flange 2 of the turbine housing 1 and onto the bearing housing 14, thereby further pressing the bearing housing 14 against the turbine housing.
  • the aforementioned housing connection bores are spaced apart from each other (i.e., spatially separated) and are arranged circumferentially along a circle.
  • the clamping tabs are also arranged circumferentially along a circle of the turbine housing.
  • FIG. 1 shows a second sectional view illustrating a turbine housing according to the prior art.
  • This second sectional view illustrates the turbine housing at an interface where a connecting element 15 is screwed into a housing connection bore 3 of the connecting flange 2 of the turbine housing.
  • a clamping tab 16 is pressed onto both the turbine housing 2 and the bearing housing 14, which is achieved using a nut 17 and a washer 18.
  • the object of the invention is to provide a turbine housing and an exhaust gas turbine in which the disadvantages mentioned above with reference to a turbocharger are reduced.
  • Such a turbine housing for an exhaust gas turbine has a connecting flange for connecting it to a bearing housing on the bearing housing side.
  • Circumferentially spaced housing connection bores are provided in the connecting flange, with material recesses opening radially inwards towards a longitudinal center axis of the turbine housing between adjacent housing connection bores.
  • the connecting flange is a bearing housing-side side wall of the turbine housing and has a clamping rim and an annular recess.
  • the annular recess is located in a radially inner edge region of the clamping rim.
  • the annular recess extends circumferentially over the entire circumference of the turbine housing and has a recess base.
  • the material recesses are formed in the recess base of the annular recess.
  • the turbine housing can also be multi-part.
  • a heat shield or a nozzle ring can be arranged between the turbine housing and the bearing housing.
  • bore in this entire description is to be interpreted functionally and not as referring to a mechanical processing using a drilling machine or milling machine.
  • the spaced-apart housing connection bores are arranged in the connecting flange along at least one circle.
  • the turbine housing has a clamping edge which is arranged adjacent to the housing connection bores in the radial direction.
  • annular recess is provided in the clamping edge, which has a recess bottom, wherein the adjacent housing connection bores are provided in the recess bottom and wherein the material recesses provided between each two adjacent housing connection bores are provided in the recess bottom.
  • the clamping edge in the area between two adjacent housing connection bores has a clamping edge recess that widens the annular recess.
  • the depth of the clamping edge recess corresponds to the sum of the depth of the annular recess and the depth of the material recesses provided in the annular recess.
  • the turbine housing is designed in multiple parts.
  • the clamping edge forms a separate part of the turbine housing.
  • a heat shield or a nozzle ring forms a separate part of the turbine housing.
  • the clamping edge is part of the heat shield or the nozzle ring.
  • an exhaust gas turbine has a turbine housing with the features according to the invention.
  • an exhaust gas turbine has a bearing housing connected to the turbine housing, wherein the turbine housing is connected to the bearing housing by means of connecting elements.
  • an exhaust gas turbine has clamping elements which are each pressed onto the connecting flange of the turbine housing and onto the bearing housing by one or more connecting elements.
  • the clamping elements of the exhaust turbine are pressed against the clamping edge.
  • the connecting elements are screws or threaded studs.
  • the advantages of the invention lie particularly in the fact that the material recesses provided between the housing connection bores enable faster and more uniform heating of the connection flange area during operation of the respective exhaust gas turbine. Furthermore, these material recesses result in reduced stiffness of the turbine housing in the area of the connection flange. This leads to lower thermal transient stresses during operation of the exhaust gas turbine. This, in turn, extends the service life of the turbine housing and thus also the service life of the entire exhaust gas turbine.
  • FIG. 1 shows a sketch illustrating a turbine housing according to the invention, wherein in the Figure 3 Only a portion of this turbine housing is shown.
  • the turbine housing has a connecting flange 2 arranged coaxially to a longitudinal center axis of the turbine housing, which is equipped with a clamping edge 7.
  • Connecting webs 19 extending radially inwards in the direction 8 are provided in this clamping edge 7, into which housing connection bores 3 are provided.
  • the aforementioned connecting webs 19, and thus also the housing connection bores 3 provided in them, are spaced apart from one another in the circumferential direction 9 of the turbine housing. They are arranged in the connecting flange along one or more circles in the circumferential direction 9.
  • material recesses 4 opening radially inwards are provided in the clamping edge 7 of the connecting flange 2.
  • These material recesses 4 can be produced by removing material from the clamping edge of the connecting flange or, if a forming manufacturing process is used, can be directly modeled.
  • the geometry of the material cutouts can be chosen differently.
  • the material cutouts can be semicircular, elliptical, bell-shaped, or rectangular.
  • connection of the turbine housing with one in the Figure 3 The bearing housing of a turbocharger, not shown, is replaced in the same way as described above in connection with the Figure 2 This was explained using connecting elements that are inserted into a housing connection bore 3 of the connecting flange 2, Furthermore, clamping elements arranged circumferentially along a circle of the turbine housing, which in one embodiment are clamping tabs, are pressed onto both the turbine housing and the bearing housing, each using a nut and a washer.
  • FIG. 4 Figure 1 shows a sectional view in the radial direction to illustrate an embodiment of the invention. Shown are the connecting flange 2 of the turbine housing and the bearing housing 14 connected to the connecting flange 2 and thus to the turbine housing. Furthermore, the following can be seen from the Figure 4 It is evident that in the depicted section plane, the connection between the turbine housing and the bearing housing is realized using a clamping tab 16. This clamping tab 16 is pressed onto the connecting flange 2 of the turbine housing and onto the bearing housing 14. This pressing action is achieved using a nut 17 and a washer 18 arranged between the nut 17 and the clamping tab 16.
  • the Figure 5 shows a sectional view according to the one in the Figure 4 Section line CC shown. From this illustration it is particularly evident that between each pair of housing connection bores 3 spaced apart in the circumferential direction 9, into which connecting elements 15 are inserted, material recesses 4 are provided in the clamping edge 7 of the connecting flange 2 of the turbine housing, which are located in the section plane shown in the radial direction 8 outside the bearing housing 14 and are open radially inwards.
  • FIG. 6 Figure 1 shows a sketch illustrating another embodiment of the invention.
  • an annular recess 5 is provided in the radially inner edge region of the clamping edge 7 of the connecting flange 2 of the turbine housing, extending in the circumferential direction 9 over the entire circumference of the turbine housing.
  • This annular recess 5 has a recess base 6.
  • the housing connection bores 3, spaced apart from each other in the circumferential direction 9, are inserted into the base 6 of the annular recess 5.
  • the material recesses 4 provided between each pair of adjacent housing connection bores 3 are also incorporated into the base 6 of the annular recess 5. These material recesses 4 extend radially 8 across the entire base 6 of the recess.
  • the thickness of the connecting flange 2 of the turbine housing in the connection area of the turbine housing with the bearing housing and thus the thermally transient stresses occurring in the connecting flange 2 during operation of the turbocharger are further reduced.
  • the Figure 7 shows a cross-sectional view in the direction of the Figure 6 shown section line A - A.
  • the depth of the housing connection bores 3 in the recess base 6 is designated by the reference numeral 12.
  • the depth of the material recesses 4 corresponds to the depth 12 of the housing connection bores 3 in the recess base 6.
  • the depth of the material recesses 4 may also differ from the depth of the housing connection bores 3.
  • the depth of the annular recess 5 is designated by the reference numeral 11.
  • the sum of the depth 11 of the annular recess and the depth 12 of the housing connection bores in the recess base is designated by the reference numeral 20.
  • FIG. 8 Figure 1 shows a sketch illustrating a further embodiment of the invention.
  • an annular recess 5 is again provided in the radially inner edge region of the clamping edge 7 of the connecting flange 2 of the turbine housing, extending circumferentially 9 over the entire circumference of the turbine housing.
  • Housing connection bores 3, spaced apart from one another circumferentially 9, are again provided in the base 6 of the annular recess 5, between which the material recesses 4 are located.
  • These recesses 4 are open inwards in the radial direction 8 and extend into the region of the clamping edge 7. Consequently, in this further development, the clamping edge 7 has clamping edge recesses 10, each provided between two adjacent housing connection bores 3. In the illustrated embodiment, these clamping edge recesses 10 extend radially 8 through the entire clamping edge 7.
  • the Figure 9 shows a cross-sectional view in the direction of the Figure 8 shown section line B - B.
  • the clamping edge recess 10 provided in the clamping edge 7 has a first depth 20.
  • the annular recess 5 has a second depth 11.
  • the housing connection bores 3 introduced into the recess base 6 have a third depth 12.
  • the first depth 20 of the clamping edge recess 10 corresponds to the The sum of the second depth 11 of the annular recess 5 and the third depth 12 of the casing connection bore 3 provided in the annular recess 5 coincide.
  • the depths 20, 11 and 12 each extend in the axial direction 13 of the turbine casing.
  • the flange thickness 19 of the connecting flange 2 is reduced due to the recesses 4 and 10, respectively, which are incorporated into the connecting flange 2 in addition to the housing connection bores 3. This reduces the thermally transient stresses occurring in the connecting flange 2 compared to the prior art, leading to an extended service life of the turbine housing and thus of the entire turbocharger.
  • This turbocharger has a turbine housing as described above.
  • this turbocharger has a bearing housing connected to the turbine housing, wherein the turbine housing is connected to the bearing housing by means of connecting elements 15 inserted into the housing connection bores 3 of the turbine housing, which are, for example, screws or threaded studs.
  • the turbocharger features clamping elements implemented as clamping tabs 16, each of which is pressed against the connecting flange 2 of the turbine housing and against the bearing housing 14 by one or more connecting elements.
  • the clamping elements are pressed against a clamping edge of the connecting flange.
  • clamping discs or clamping rings instead of clamping tabs, clamping discs or clamping rings, for example, can also be used.
  • the clamping elements are preferably designed to be at least slightly elastic so that they can yield at least slightly when the nuts are tightened.
  • the spaced-apart housing connection bores 3 in the connection flange 2 are arranged circumferentially along at least one circle, preferably at most three or at most two (concentric to each other and/or to the turbine axis), and extend along the entire circumference of the at least one circle, preferably distributed at regular intervals.
  • the number of required housing connection bores depends on the strength requirements in the event of damage (containment) and the sealing requirements.
  • the spaced-apart housing connection bores 3 in the connection flange 2 can also be arranged circumferentially along two or more circles, wherein, for example, every second housing connection bore 3 is arranged along a first circle and every intermediate housing connection bore 3 is arranged along a second circle.
  • the flange has at least five housing connection bores 3 and/or at least two, preferably at least four, particularly preferably at least five material recesses 4 between adjacent housing connection bores 3.
  • material recesses 4 are provided between all housing connection bores.
  • the material recesses 4 are open radially inwards.
  • the material recesses 4 are preferably closed in the axial direction by a (e.g., annular) rear side of the connecting flange, i.e., they are not continuous in the axial direction.
  • material recesses 4 can be provided not between all housing connection bores 3, but only where the influence on the service life is relevant, for example in the area of the entry into the spiral.
  • the flange is arranged coaxially to the longitudinal center axis of the turbine housing.
  • the flange is aligned towards a bearing housing of the exhaust turbine or arranged for the connection of the turbine housing with the bearing housing (optionally with part of a heat shield and/or a diffuser ring between the flange and the corresponding part of the bearing housing).
  • the recess 4 has an arc length in the circumferential direction of more than half the distance between the centers of the two housing connection bores 3.
  • the connecting flange 2 has connecting webs 19 which directly surround the housing connecting bores 3 at least partially and which are arranged in the circumferential direction between the adjacent housing connecting bores 3 and the intermediate material recess 4.
  • the connecting flange 2 has a clamping edge 7 which is arranged adjacent to the housing connecting bores 3 in radial direction 8.
  • the connecting webs 19 extend radially inwards from the clamping edge 7.
  • the clamping edge can be provided as a separate part of the turbine housing or integrally with the rest of the turbine housing or connecting flange.
  • the turbine housing can be multi-part.
  • a heat shield or nozzle ring can form a separate part of the turbine housing.
  • the clamping edge of the turbine housing can then be part of the heat shield or nozzle ring, i.e., integrated into the heat shield or nozzle ring.
  • the connecting webs are recessed axially relative to the clamping edge 7.
  • the clamping edge protrudes axially beyond the connecting webs (e.g., by less than 1 mm or even by a maximum of 0.5 mm and/or by more than 0.1 mm) (e.g., away from the turbine housing or towards the bearing housing of the exhaust turbine).
  • the connecting webs form part of a recessed base.
  • the material recesses 4 provided between each pair of adjacent housing connection bores are recessed even further axially relative to the connecting webs.
  • the clamping edge can run continuously (without interruption) in the circumferential direction or have recesses.
  • the connecting flange 2 has an annular recess 5 which has a recess bottom 6.
  • the adjacent housing connection bores 3 are inserted into the bottom of the recess.
  • the material recesses 4 provided between each pair of adjacent housing connection bores are provided in the base of the recess.
  • a preferred aspect of the present invention relates to a turbine housing for an exhaust gas turbine, which has a connecting flange for connecting the turbine housing to a bearing housing of the exhaust gas turbine on the bearing housing side.
  • This connecting flange is preferably a bearing housing-side side wall of the turbine housing.
  • the side wall of the turbine housing is preferably designed to form a direct connection with a turbine-side side wall of the bearing housing, or is directly connected to the turbine-side side wall of the bearing housing.
  • the side wall of the turbine housing is preferably designed to form a connection with a turbine-side side wall of the bearing housing by means of a (penetrating into the housing connection bores of the turbine housing)
  • the turbine housing is connected to the bearing housing by means of a common connecting element, e.g., a connecting screw.
  • a common connecting element e.g., a connecting screw.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)
  • Control Of Turbines (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (15)

  1. Carter (1) de turbine pour une turbine à gaz d'échappement, qui présente une bride de raccordement (2) pour une liaison côté carter de palier à un carter de palier, dans laquelle sont prévus des trous de raccordement (3) au carter écartés les uns des autres dans la direction périphérique (9), des évidements de matériau (4) ouverts radialement vers l'intérieur en direction d'un axe longitudinal central du carter de turbine étant prévus dans la bride de liaison, entre des trous de liaison au carter adjacents les uns aux autres, la bride de liaison étant une paroi latérale côté carter de palier du carter de turbine, caractérisé en ce que la bride de liaison présente un bord de serrage (7) et un renfoncement annulaire (5), le renfoncement annulaire étant prévu dans une zone de bord radialement vers l'intérieur du bord de serrage (7), le renfoncement annulaire (5) s'étendant dans la direction périphérique (9) sur toute la périphérie du carter de turbine et présentant un fond (6) de renfoncement et les évidements de matériau (4) étant réalisés dans le fond (6) de renfoncement du renfoncement annulaire (5).
  2. Carter de turbine selon la revendication 1, dans lequel les trous de raccordement (3) au carter écartés les uns des autres sont agencés dans la bride de raccordement (2) dans la direction périphérique (9) le long d'au moins un cercle.
  3. Carter de turbine selon la revendication 2, dans lequel le bord de serrage (7) est agencé de manière adjacente aux trous de raccordement (3) au carter dans la direction radiale (8).
  4. Carter de turbine selon la revendication 3, dans lequel les trous de raccordement (3) au carter adjacents sont entourés au moins par sections d'âmes de raccordement (19) qui sont agencées de manière renfoncée par rapport au bord de serrage (7) dans la direction axiale (13) du carter de turbine, les évidements de matériau (4) prévus entre à chaque fois deux trous de raccordement de carter adjacents étant agencés de manière renfoncée par rapport aux âmes de raccordement (19) dans la direction axiale (13) du carter de turbine.
  5. Carter de turbine selon la revendication 4, dans lequel le bord de serrage (7) présente, dans la zone entre deux trous de raccordement (3) au carter adjacents, à chaque fois un évidement (10) de bord de serrage élargissant un renfoncement annulaire (5).
  6. Carter de turbine selon la revendication 5, dans lequel une première profondeur (20) de l'évidement (10) de bord de serrage correspond à la somme d'une deuxième profondeur (11) du renfoncement annulaire (5) et d'une troisième profondeur (12) des trous de raccordement (3) au carter prévus dans le renfoncement annulaire, ces profondeurs s'étendant dans la direction axiale (13) du carter de turbine.
  7. Carter de turbine selon l'une des revendications précédentes, le carter de turbine étant réalisé en plusieurs éléments.
  8. Carter de turbine selon la revendication 7, dans lequel le bord de serrage (7) forme un composant séparé du carter de turbine.
  9. Carter de turbine selon la revendication 7, dans lequel un bouclier thermique ou une couronne directrice forme un composant séparé du carter de turbine.
  10. Carter de turbine selon la revendication 9, dans lequel le bord de serrage (7) fait partie du bouclier thermique ou de la couronne directrice.
  11. Turbine (15) à gaz d'échappement, qui présente un carter (1) de turbine selon l'une des revendications 1 - 10.
  12. Turbine à gaz d'échappement selon la revendication 11, qui présente un carter de palier (14) raccordé au carter (1) de turbine, le carter de turbine étant raccordé au carter de palier au moyen d'éléments de raccordement (15).
  13. Turbine à gaz d'échappement selon la revendication 12, qui présente des éléments de serrage (16) qui sont à chaque fois pressés par un ou plusieurs éléments de raccordement (15) sur la bride de raccordement (2) du carter (1) de turbine et sur le carter de palier (14).
  14. Turbine à gaz d'échappement selon la revendication 11, dans laquelle les éléments de serrage (16) sont pressés sur le bord de serrage (7).
  15. Turbine à gaz d'échappement selon l'une des revendications 11 - 14, dans laquelle les éléments de raccordement (15) sont des vis ou des tiges filetées.
EP20733442.6A 2019-07-15 2020-06-22 Logement de turbine doté d'une bride de raccordement à faible tension et turbine de gaz d'échappement dotée d'un tel logement de turbine Active EP3999721B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP19186327.3A EP3767081A1 (fr) 2019-07-15 2019-07-15 Logement de turbine doté d'une bride de raccordement à faible tension et turbine de gaz d'échappement dotée d'un tel logement de turbine
PCT/EP2020/067326 WO2021008816A1 (fr) 2019-07-15 2020-06-22 Carter de turbine comportant une bride de liaison à faible tension et une turbine de gaz d'échappement comportant un tel carter de turbine

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EP3999721A1 EP3999721A1 (fr) 2022-05-25
EP3999721B1 true EP3999721B1 (fr) 2026-01-28

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EP19186327.3A Withdrawn EP3767081A1 (fr) 2019-07-15 2019-07-15 Logement de turbine doté d'une bride de raccordement à faible tension et turbine de gaz d'échappement dotée d'un tel logement de turbine
EP20733442.6A Active EP3999721B1 (fr) 2019-07-15 2020-06-22 Logement de turbine doté d'une bride de raccordement à faible tension et turbine de gaz d'échappement dotée d'un tel logement de turbine

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EP19186327.3A Withdrawn EP3767081A1 (fr) 2019-07-15 2019-07-15 Logement de turbine doté d'une bride de raccordement à faible tension et turbine de gaz d'échappement dotée d'un tel logement de turbine

Country Status (6)

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US (1) US11852030B2 (fr)
EP (2) EP3767081A1 (fr)
JP (1) JP7535566B2 (fr)
KR (1) KR102902189B1 (fr)
CN (1) CN114144574B (fr)
WO (1) WO2021008816A1 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3122900A1 (fr) * 2021-05-11 2022-11-18 Safran Ventilation Systems Dispositif pour la realisation d’un ventilateur ou compresseur pour l’industrie aeronautique
KR20240000854A (ko) 2022-06-24 2024-01-03 무진정밀(주) 향상된 고온 특성을 가지는 내열강 및 이를 포함하는 화력발전 터빈 케이싱용 볼트 너트 체결 부재
EP4720475A1 (fr) * 2023-06-01 2026-04-08 Accelleron Switzerland Ltd. Turbine axiale pour turbomachine, procédé de démontage associé et utilisation

Family Cites Families (12)

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Publication number Priority date Publication date Assignee Title
JPS4612407Y1 (fr) * 1967-07-28 1971-04-30
US6287091B1 (en) * 2000-05-10 2001-09-11 General Motors Corporation Turbocharger with nozzle ring coupling
EP1353041A1 (fr) * 2002-04-12 2003-10-15 ABB Turbo Systems AG Turbocompresseur avec moyens sur l'arbre pour le confinement axial dudit arbre en cas d'éclatement de la roue de compresseur
DE50312707D1 (de) * 2003-03-19 2010-06-24 Abb Turbo Systems Ag Abgasturbinengehäuse
EP1536103B1 (fr) * 2003-11-28 2013-09-04 BorgWarner, Inc. Turbomachine avec aubes de guidage et agencement de fixation
DE102009052961A1 (de) * 2009-11-12 2011-05-19 Continental Automotive Gmbh Abgasturbolader, Kraftfahrzeug und Verfahren zur Montage eines Abgasturboladers
JP5832090B2 (ja) 2010-12-15 2015-12-16 三菱重工業株式会社 ターボチャージャハウジングのシール構造
DE112013000435T5 (de) * 2012-01-26 2014-09-18 Borgwarner Inc. Abgasturbolader
US9512740B2 (en) * 2013-11-22 2016-12-06 Siemens Energy, Inc. Industrial gas turbine exhaust system with area ruled exhaust path
US9856753B2 (en) * 2015-06-10 2018-01-02 United Technologies Corporation Inner diameter scallop case flange for a case of a gas turbine engine
DE102016117960A1 (de) * 2016-09-23 2018-03-29 Man Diesel & Turbo Se Turbolader
FR3122900A1 (fr) 2021-05-11 2022-11-18 Safran Ventilation Systems Dispositif pour la realisation d’un ventilateur ou compresseur pour l’industrie aeronautique

Also Published As

Publication number Publication date
EP3767081A1 (fr) 2021-01-20
WO2021008816A1 (fr) 2021-01-21
CN114144574B (zh) 2024-10-29
US20220268177A1 (en) 2022-08-25
KR20220025240A (ko) 2022-03-03
JP7535566B2 (ja) 2024-08-16
JP2022541034A (ja) 2022-09-21
KR102902189B1 (ko) 2025-12-19
CN114144574A (zh) 2022-03-04
US11852030B2 (en) 2023-12-26
EP3999721A1 (fr) 2022-05-25

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