EP3293369B1 - Élément de revêtement pour carter intermédiaire de turbine - Google Patents

Élément de revêtement pour carter intermédiaire de turbine Download PDF

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Publication number
EP3293369B1
EP3293369B1 EP17182051.7A EP17182051A EP3293369B1 EP 3293369 B1 EP3293369 B1 EP 3293369B1 EP 17182051 A EP17182051 A EP 17182051A EP 3293369 B1 EP3293369 B1 EP 3293369B1
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EP
European Patent Office
Prior art keywords
reinforcement
section
lining element
connection
reinforcement portion
Prior art date
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Active
Application number
EP17182051.7A
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German (de)
English (en)
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EP3293369A1 (fr
Inventor
Thomas Flatscher
Alois Eichinger
Wolfgang Bickmeier
Manfred Feldmann
Daniel Kirchner
Johannes Geisler
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MTU Aero Engines AG
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MTU Aero Engines AG
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Publication date
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Publication of EP3293369A1 publication Critical patent/EP3293369A1/fr
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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
    • 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
    • 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
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/75—Shape given by its similarity to a letter, e.g. T-shaped
    • 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

Definitions

  • the present invention relates to a cladding element of a duct carrying hot gas of a turbine center frame of a gas turbine according to claim 1.
  • Directional indications such as “axial” or “axial”, “radial” or “radial” and “circumferential” are to be understood as referring to the machine axis of the intermediate turbine housing or the gas turbine.
  • the term “turbine intermediate housing” includes housings that directly adjoin the housing of a turbine stage in the axial direction of the gas turbine, and are preferably arranged between two turbine stages, the gas turbine, depending on the design, having two or more turbine stages.
  • the term “turbine housing” thus also includes a so-called “turbine center frame”.
  • the provision of stiffening ribs on components, in particular cladding elements, of intermediate turbine housings or of gas turbines is known.
  • Known stiffening ribs generally run in the axial direction or in the circumferential direction.
  • the known stiffening ribs are coupled to edge sections of the respective component, so that the stiffening ribs generally run in the axial direction or in the circumferential direction along the entire component.
  • Such cladding components are from US 2005/0254939 A1 and the CN 105 756 726A known.
  • stiffening ribs can achieve a high level of rigidity in the components, but the connection of the stiffening ribs to the edge sections generates high thermally induced stresses on the component. Furthermore, the material requirements for such known stiffening ribs are high.
  • the central section has at least one first reinforcing section protruding away from the channel, which extends essentially in a straight line between an axially front end and an axially rear end, with a in the direction of at least one of the two axial ends from the channel protruding second reinforcing section is connected, which is inclined or curved relative to the straight course of the first reinforcing section, wherein the first reinforcing section and the second reinforcing section together form a reinforcing element, wherein the entire reinforcing element is arranged within the outer surface of the central section, such that the reinforcing element is at a distance from the lateral edge sections of the cladding element, from the first connection section and from the second connection section and with the connection sections and the lateral edge sections of the cladding gselements is not directly connected.
  • the first reinforcement section which runs essentially in a straight line between the axially front end and the axially rear end, thus has a main direction of extent with an axial directional component, that is to say a directional component that is oriented in the axial direction of the turbomachine.
  • the main direction of extent of the first reinforcement section preferably has no or only a smaller circumferential directional component than the axial directional component, that is to say a directional component in the circumferential direction of the turbomachine.
  • connection sections The arrangement of two reinforcement sections which together form the reinforcement element, the second reinforcement section being inclined or curved in relation to the first rectilinear reinforcement section, enables a material-saving design. Furthermore, the distances to the connection sections can prevent constraints, so that high thermally induced stresses can be avoided.
  • a free end of the first reinforcement section which is not connected to a second reinforcement section, can be designed to taper at least in the radial direction, such that the first reinforcement section merges essentially continuously into the outer surface of the central section. Forms the free end of the first reinforcement section thus a kind of seamless or flowing transition between the first reinforcement section and the outer surface of the central section.
  • the second reinforcement section can be designed essentially symmetrically with respect to the first reinforcement section connected to it, in particular in such a way that the first reinforcement section and the second reinforcement section form a Y-shaped reinforcement element.
  • the free ends of the second reinforcement section can in particular be oriented in such a way that they point in the direction of mounting points of the cladding element at which the cladding element is connected to other structures of the intermediate turbine housing or the gas turbine.
  • the symmetrical design, in particular in the manner of a Y, is also particularly suitable for optimally distributing acting forces and tensions.
  • the second reinforcement section can have two free ends which are designed to taper at least in the radial direction, such that the second reinforcement section merges essentially continuously into the outer surface of the central section.
  • the entire reinforcement element if it is formed, for example, by a first reinforcement section and a second reinforcement section, has three free ends which merge essentially seamlessly or smoothly into the outer surface of the central section.
  • the first reinforcement section can be arranged essentially centrally on the central section with respect to the circumferential direction.
  • the middle area of the central section is subject to the greatest deformations, in particular bending loads, as a result of pressure differences between the hot gas flowing in the ring channel and the secondary air system located outside the ring channel. Accordingly, this central area is preferably to be reinforced in order to counteract a radial bulging or bending of the central section.
  • the first connection section, the second connection section and the central section can be curved at least in the circumferential direction.
  • the curvature serves to adapt the cladding element with regard to the assembled state of an intermediate turbine housing.
  • several adjacent cladding elements form the cladding of the ring channel, so that it is advantageous if the individual cladding elements already have a corresponding curvature.
  • the reinforcing element is at a distance in the circumferential direction from lateral edge sections of the cladding element which protrude at least in the radial direction from the outer surface of the central section.
  • Such edge sections generally form the transition to an adjacent component in the circumferential direction, in particular an adjacent cladding element. If the reinforcement element is also at a distance from these edge sections, in addition to the distance from the first connection section and the second connection section, the entire reinforcement element is only provided in the area of the (outer) surface of the central section. As a result, the central section can be reinforced in the desired manner without thermally induced stresses being transferred to the edge sections or the two connection sections to a large extent.
  • a respective second reinforcement section can be arranged at each end of the first reinforcement section. This creates a kind of double Y or a kind of stick figure without a head with legs spread apart and arms stretched out.
  • the first reinforcement section is arranged centrally and the two second reinforcement sections each have two arms which extend away from the first reinforcement section.
  • the entire reinforcement element can be made in one piece with the central section of the cladding element. This can be achieved, for example, by a corresponding casting mold in which the reinforcing element is already taken into account.
  • the cladding element is preferably produced by means of a casting process. Alternatively, the component could also be produced entirely or partially by a generative process.
  • the reinforcement element can be applied to the outer surface of the central section by laser deposition welding.
  • the invention also relates to an intermediate turbine housing for a gas turbine, in particular an aircraft gas turbine, with an annular duct carrying hot gas, the annular duct having a plurality of cladding elements described above on the radially outward side.
  • the cladding elements can be arranged adjacent to one another in the circumferential direction.
  • the above-described cladding elements and cladding elements configured differently can also be used alternately in the circumferential direction.
  • a cladding element 10 of an intermediate turbine housing (not shown) is shown in a simplified and schematic perspective illustration.
  • the present example according to Fig. 1 shows a so-called inner duct panel, i.e. a cladding element which is designed to delimit the hot gas duct of the turbine intermediate housing radially on the inside.
  • Fig. 1 shows the surface of the cladding element facing away from the hot gas duct, which in the installed state points essentially radially inward to the machine axis of the gas turbine.
  • the cladding element 10 has a first, axially front connection section 12 and a second, axially rear connection section 14.
  • connection sections 12, 14 serve to connect the cladding element 10 to axially adjoining components of the intermediate turbine housing or an associated gas turbine.
  • a central section 16 extends along the axial direction AR between the first connection section 12 and the second connection section 14. In the circumferential direction UR, the central section 16 is delimited by edge sections 18.
  • the central section 16 has an outer surface 20.
  • the outer surface 20 is delimited in particular by the two edge sections 18, which protrude in the radial direction from the outer surface 20, and by the two connection sections 12, 14.
  • a reinforcing element 22 is provided so that the central section 16 is not severely deformed, in particular bulged or bent, by pressure differences between the hot gas flowing in the ring channel and the secondary air system located outside the ring channel.
  • the reinforcement element 22 comprises a first reinforcement portion 24 and a second reinforcement portion 26.
  • the reinforcing element 22 is arranged in a central or central region of the cladding element 10 or of the central section 16 in relation to the circumferential direction. It points the reinforcement element 22 is at a distance from the first connection section 12 as well as at a distance from the second connection section 14.
  • the cladding element 22 is also arranged at a distance from the edge sections 18. In other words, it can also be said that the reinforcement element 22 is arranged completely within the outer surface 20 of the central section 16. The reinforcement element 22 is therefore not in direct contact with the connection sections 12, 14 or the edge sections 18.
  • the first reinforcement section 24 extends along the axial direction along the outer surface 20 of the central section 16.
  • the first reinforcement section 24 has a free end 28. This free end 28 is designed to taper at least in the radial direction RR. In other words, the free end 28 of the first reinforcing section 24 has a wedge shape. This enables a seamless or flowing transition from the first reinforcing element 24 to the outer surface 20 of the central section 16.
  • the second reinforcement section 26 comprises two arms 30a and 30b which are arranged at an angle to the first reinforcement section 24.
  • the reinforcement element 22 thus has a type of Y-shape.
  • the second reinforcement section 26 has two free ends 32a, 32b. These free ends 32a, 32b are also designed to taper in the radial direction. This also enables a seamless or flowing transition to the outer surface 20 of the central section 16.
  • the reinforcement element 22 or its reinforcement sections 24, 26 protrude in the radial direction from the central section 16 or from the outer surface 20.
  • the reinforcement sections 24, 26 form a type of ribs which reinforce the central section 16 with respect to bending stresses.
  • All reinforcement sections 24, 26 have a respective upper surface 34 and side surfaces 36 extending from the upper surface in an inclined or curved manner to the outer surface 20 of the central portion 16.
  • the surface 34 has a maximum width B at each of the free ends 28, 32a, 32b. The maximum width is provided in the area of the transition from the corresponding reinforcement section 24, 26 to the outer surface 20.
  • the continuous transition from the outer surface to the reinforcement sections 24, 26 enables the central section 16 or the cladding element 10 to be easily manufactured by means of a casting process. Due to the continuous transition in the area of the free ends 28, 32a, 32b, the reinforcing element 22 is only formed within the outer surface 22 without direct contact with other, in particular structurally load-bearing components, such as the connection sections 12, 14 or the edge sections 18.
  • a somewhat differently designed cladding element 110 is shown, namely a so-called outer duct panel, that is, a cladding element which is designed to delimit the hot gas duct of the turbine intermediate housing radially on the outside.
  • Fig. 3 shows the surface of the cladding element facing away from the hot gas duct, which in the installed state essentially points radially outwards to the machine axis of the gas turbine.
  • the cladding element 110 also comprises a first, axially front connection section 112 and a second, axially rear connection section 114.
  • the central section 116 and the edge sections 118 are also visible.
  • a reinforcing element 122 is arranged in the central section 116.
  • This reinforcement element comprises a first reinforcement section 124 and two second reinforcement sections 126.
  • This reinforcement element 122 is also arranged within the outer surface 120 of the central section 116. It therefore has a respective distance from the connection sections 112 and 114 and from the edge sections 118.
  • the reinforcement element 122 is enlarged in FIG Fig. 4 shown.
  • the first reinforcement section 124 does not have a free end, but is connected to a second reinforcement section 126 on both sides.
  • the Indian Fig. 4 axially front (second) reinforcing section 126 has two substantially straight arms 130a and 130b with respective free ends 132a and 132b. The two arms 130a and 130b run inclined relative to the straight first reinforcing section 124.
  • the in Fig. 4 axially rearward (second) reinforcing portion 126 has two curved arms 130c and 130d. These arms 130c and 130d also have free ends 132c and 132d.
  • the above with reference to the Figs. 1 and 2 What has been said with regard to the tapering configurations of the free ends (wedge shape) also applies analogously to the free ends 132a, 132b, 132c, 132c.
  • the reinforcement element 122 also has an upper surface 134 and side surfaces 136 which run inclined or curved in relation to this and which merge into the outer surface 120 of the central section.
  • the cladding element with stiffening element presented here allows sufficient rigidity of the central section or of the cladding element to be achieved with little use of material. Furthermore, the thermally induced stress in the cladding element and in particular in the connection sections or the edge sections can be kept low because the reinforcement element is not directly connected to them.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (9)

  1. Élément de revêtement d'un canal transportant un gaz chaud d'un carter intermédiaire d'une turbine à gaz, en particulier d'une turbine à gaz d'aéronef, avec
    une première partie de raccordement (12 ; 112) axialement antérieure par rapport à un axe de machine de la turbine à gaz,
    une seconde partie de raccordement (14 ; 114) axialement postérieure,
    une partie centrale (16 ; 116), qui est reliée à la première partie de raccordement (12 ; 112) et à la seconde partie de raccordement (14 ; 114) et est disposée entre celles-ci dans la direction axiale (AR), la partie centrale (16 ; 116) comportant une surface extérieure (20 ; 120) opposée au canal, et
    la première partie de raccordement (12 ; 112) pouvant être accouplée à des composants axialement antérieurs du carter intermédiaire de turbine ou de la turbine à gaz, et la seconde partie de raccordement (14 ; 114) pouvant être accouplée à des composants axialement postérieurs du carter intermédiaire de turbine ou de la turbine à gaz,
    la partie centrale (16 ; 116) comportant au moins une première partie de renforcement (24 ; 124) faisant saillie dans la direction s'éloignant du canal, laquelle première partie de renforcement s'étend de manière sensiblement rectiligne entre une extrémité axialement antérieure (28) et une extrémité axialement postérieure, au moins l'une des deux extrémités axiales étant raccordée à une seconde partie de renforcement (26 ; 126) faisant saillie dans la direction s'éloignant du canal, laquelle seconde partie de renforcement s'étend de manière inclinée ou courbée par rapport au tracé rectiligne de la première partie de renforcement (24 ; 124), la première partie de renforcement (24 ; 124) et la seconde partie de renforcement (26 ; 126) formant ensemble un élément de renforcement (22 ; 122),
    l'élément de renforcement (22 ; 122) étant espacé de la première partie de raccordement (12 ; 112) et de la seconde partie de raccordement(14 ; 114), caractérisé en ce que l'élément de renforcement (22 ; 122) est espacé des parties de bord latérales (18 ; 118) de l'élément de revêtement (10 ; 110) dans la direction circonférentielle (UR), lesdites parties de bord latérales faisant saillie depuis la surface extérieure (20 ; 120) de la partie centrale (16 ; 116) au moins dans la direction radiale (RR), de telle sorte que l'ensemble de l'élément de renforcement (22 ; 122) est disposé au sein de la surface extérieure (20 ; 120) de la partie centrale (16 ; 116) et n'est pas directement relié aux parties de raccordement et aux parties de bord latérales de l'élément de revêtement.
  2. Élément de revêtement selon la revendication 1, caractérisé en ce qu'une extrémité libre (28) de la première partie de renforcement (24) qui n'est pas reliée à une seconde partie de renforcement (26) est conçue pour se rétrécir au moins dans la direction radiale (RR), de telle sorte que la première partie de renforcement (24) passe sensiblement de manière continue dans la surface extérieure (20) de la partie centrale (16).
  3. Élément de revêtement selon la revendication 1 ou 2, caractérisé en ce que la seconde partie de renforcement (26 ; 126) est conçue sensiblement symétriquement par rapport à la première partie de renforcement (24 ; 124) qui est reliée à celle-ci, en particulier de telle sorte que la première partie de renforcement (24 ; 124) et la seconde partie de renforcement (26 ; 126) forment un élément de renforcement en forme de Y (22 ; 122).
  4. Élément de revêtement selon l'une des revendications précédentes, caractérisé en ce que la seconde partie de renforcement (26 ; 126) comporte deux extrémités libres (32a, 32b ; 132a, 132b, 132c, 132d) qui sont conçues pour se rétrécirau moins dans la direction radiale (RR), de telle sorte que la seconde partie de renforcement (26 ; 126) passe sensiblement de manière continue dans la surface extérieure (20 ; 120) de la partie centrale (16 ; 116).
  5. Élément de revêtement selon l'une des revendications précédentes, caractérisé en ce que la première partie de renforcement (24 ; 124) est disposée sensiblement au centre de la partie centrale (16 ; 116) par rapport à la direction circonférentielle (UR).
  6. Élément de revêtement selon l'une des revendications précédentes, caractérisé en ce que la première partie de raccordement (12 ; 112), la seconde partie de raccordement (14 ; 114) et la partie centrale (16 ; 116) sont courbées au moins dans la direction circonférentielle (UR).
  7. Élément de revêtement selon la revendication 1, caractérisé en ce qu'une seconde partie de renforcement (126) respective est disposée à chaque extrémité de la première partie de renforcement (124).
  8. Élément de revêtement selon l'une des revendications précédentes, caractérisé en ce que l'ensemble de l'élément de renforcement (22 ; 122) est réalisé d'une seule pièce avec la partie centrale (16 ; 116) de l'élément de revêtement (10 ; 110).
  9. Carter intermédiaire de turbine pour une turbine à gaz, en particulier une turbine à gaz d'aéronef, avec un canal annulaire transportant un gaz chaud, caractérisé en ce que le canal annulaire comporte plusieurs éléments de revêtement (10 ; 110) selon l'une des revendications précédentes.
EP17182051.7A 2016-07-27 2017-07-19 Élément de revêtement pour carter intermédiaire de turbine Active EP3293369B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102016213810.3A DE102016213810A1 (de) 2016-07-27 2016-07-27 Verkleidungselement für ein Turbinenzwischengehäuse

Publications (2)

Publication Number Publication Date
EP3293369A1 EP3293369A1 (fr) 2018-03-14
EP3293369B1 true EP3293369B1 (fr) 2021-04-07

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US (1) US10392972B2 (fr)
EP (1) EP3293369B1 (fr)
DE (1) DE102016213810A1 (fr)
ES (1) ES2870018T3 (fr)

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DE102016213810A1 (de) 2018-02-01
US20180038244A1 (en) 2018-02-08
ES2870018T3 (es) 2021-10-26
EP3293369A1 (fr) 2018-03-14
US10392972B2 (en) 2019-08-27

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