EP2860361B1 - Support d'élément et turbomachine - Google Patents

Support d'élément et turbomachine Download PDF

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Publication number
EP2860361B1
EP2860361B1 EP13187698.9A EP13187698A EP2860361B1 EP 2860361 B1 EP2860361 B1 EP 2860361B1 EP 13187698 A EP13187698 A EP 13187698A EP 2860361 B1 EP2860361 B1 EP 2860361B1
Authority
EP
European Patent Office
Prior art keywords
ring surface
recesses
component support
component
support according
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.)
Not-in-force
Application number
EP13187698.9A
Other languages
German (de)
English (en)
Other versions
EP2860361A1 (fr
Inventor
Rudolf Stanka
Christoph Lauer
Hans Stricker
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines AG
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 MTU Aero Engines AG filed Critical MTU Aero Engines AG
Priority to ES13187698.9T priority Critical patent/ES2620486T3/es
Priority to EP13187698.9A priority patent/EP2860361B1/fr
Priority to US14/508,675 priority patent/US9752455B2/en
Publication of EP2860361A1 publication Critical patent/EP2860361A1/fr
Application granted granted Critical
Publication of EP2860361B1 publication Critical patent/EP2860361B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D25/16—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
    • F01D25/246—Fastening of diaphragms or stator-rings

Definitions

  • the invention relates to a component support according to the preamble of patent claim 1 and a turbomachine.
  • FIG. 1 is outlined a known component support between two in-abutment stator components. The components are only sketched in sections and greatly simplified.
  • the one component 1 is a housing ring which is aligned coaxially to a machine axis X extending in the plane of the drawing.
  • the second component is, for example, an intermediate turbine housing, which is also aligned coaxially with the machine axis X and is supported on a support ring surface 6 of the first component via a plurality of radially outwardly extending bearing sections 2, 4.
  • a plurality of recesses 8, 10, 12 are introduced in the support ring surface 6, with which the bearing sections 2, 4 with their side edge portions 14, 16 are in overlap.
  • the recesses 8, 10, 12 are uniformly spaced in the circumferential direction and each spaced over an uncontoured and the bearing sections 2, 4 receiving support surface portion 18, 20 from each other. They are oriented radially to the machine axis X and thus in the direction of movement of the intermediate turbine housing.
  • the recesses 8, 10, 12 are each groove-like and have two steep side walls 22, 24, which are connected to each other via a flat base 26. Transition regions 28, 30 between the side walls 22, 24 and the support ring surface portions 18, 20 are relatively sharp-edged.
  • the groove-like recesses lead to a change in the structural mechanics of the housing ring in the area of the support ring surface.
  • stresses can be introduced into the housing ring.
  • a turbomachine is shown with an annular groove for receiving a vane ring.
  • the ring groove has a flat groove bottom and two steep side walls. In the transition areas between the side walls and the groove bottom cavities are introduced.
  • the object of the invention is to provide an alternative component support a turbomachine, which eliminates the aforementioned disadvantages and in which an edge effect between two in-abutment stator components is prevented. Furthermore, it is an object of the invention to provide a turbomachine with an optimized component support.
  • a component support according to the invention of a turbomachine has at least two stator-side substantially annular components, which are in axial contact with each other and are preferably formed coaxially with each other.
  • the first component has a support ring surface and the second component has a plurality of circumferentially distributed bearing portions with which it is in contact with the support ring surface.
  • a multiplicity of substantially radial groove-like recesses having a depth to width ratio of 1: 5 to 1:20 are introduced into the support ring surface, each bearing section being in overlap with a recess with its two side edge regions, and between the respective adjacent bearing sections an unconstricted support ring surface area, in which an original contour of the support surface is continued extends.
  • the support according to the invention Due to the support according to the invention edge effects on the support ring surface and on the bearing portions in a relative movement of the components, for example due to different thermal expansions, each other prevented. Due to the groove-like recesses in combination with the non-contoured Stauerring vom Kunststoff Kunststoff Kunststoffen between the bearing sections there is no significant or no change in the structural mechanics of the first component, so that no additional stresses in the first component are introduced by the groove-like recesses, not even when they are introduced into the first component , In addition, the groove-like recesses can be manufacture easily manufactured. For example, the groove-like recesses are machined by means of a mechanical processing such as milling or electrochemical or galvanic machining.
  • the depth of the savings is thereby removed in the axial direction and the width in the circumferential direction.
  • the depth-width ratio is 1:10.
  • the width is thereby removed from a radial center plane of the recesses, so that the recesses have, similar to a diameter to a radius, an overall width equal to twice the width.
  • the recesses have a total width which is 0.25 times to 2 times a width of the bearing sections.
  • An optimal adaptation of the first component to a male support load can be achieved in that the recesses each have different transition radii in the transition region to the uncontoured Stauerringinci Schemeen and Stauerring lakeabroughen on which the bearing sections are supported and which receive the bearing sections.
  • the recesses each have equal transition radii in the transition region to the non-contoured Stauerring vom Hoch Kunststoffen and the bearing sections receiving support annular surface portions.
  • Such an embodiment is easier to manufacture because of the same transition radii than the previous embodiment with the different transition radii.
  • transition radii correspond to 0, lmal to 1 times a basic radius of the recesses.
  • the transition areas from the recesses to the non-contoured support ring surface areas and to the bearing portions receiving support ring surface portions are formed as chamfers or edges. Chamfers or edges are easy to design in terms of manufacturing technology.
  • the base radius is interrupted by a flat.
  • the at least two components are aligned coaxially with each other.
  • the at least two components can be rotationally symmetrical. This facilitates the alignment of the components to each other.
  • a turbomachine according to the invention has at least one component support according to the invention, whereby edge effects between abutting stator components are prevented.
  • FIG. 2 a section of a component support according to the invention of a turbomachine is shown.
  • the turbomachine is preferably a stationary gas turbine and in particular an aircraft engine.
  • the component support is located on the turbine side in the turbomachine and is formed for example by a stator-side annular housing 32 and a stator-side annular intermediate turbine housing.
  • the intermediate turbine housing has a plurality of radially outwardly extending projections 34, 36, which serve as bearing sections and by means of which it at a axial support ring surface 38 of the housing 32 is supported.
  • the housing 32 and the intermediate turbine housing are oriented in the embodiment shown here rotationally symmetrical and coaxial with the machine axis X of the turbomachine, which extends in the plane, namely orthogonal to the support ring surface 38th
  • a plurality of groove-like recesses 40, 42, 44, 46 are introduced into the support ring surface 38.
  • the recesses 40, 42, 44, 46 are equally spaced circumferentially and spaced from one another via uncontoured backup ring surface areas 48, 50, 52.
  • the term "uncontoured" in the sense of the present invention means that the support ring surface areas 48, 50, 52 essentially continue an original contour of the support ring surface 38. Of course, local depressions are included in the backup ring surface areas 48, 50, 52. Also, the Stauerring vomareale 48, 50, 52 have a production-related surface roughness, which was not smoothed or only partially by subsequent machining. For example, the surfaces of the backup ring surface areas 48, 52 that support the bearing portions 34, 36 may be smoothed by finishing operations, such as finish grinding and / or by coating, while the surface of the intermediate support ring surface area 50 is substantially a production-related original surface roughness having.
  • the bearing sections 34, 36 are distributed uniformly over the circumference. They have such a division in the circumferential direction that they each rest against a support ring surface area 48, 52 and are each spaced apart from each other via a support ring surface area 50. Between the respective adjacent bearing sections 34, 36 there is thus always an uncontoured support ring surface area 50.
  • the support ring surface areas 48, 52, on which the bearing sections 34, 36 are supported are referred to as support ring surface sections.
  • the bearing section-free support ring surface areas 50 are referred to as support ring surface areas.
  • bearing portions 34, 36 have such an extent in the circumferential direction or width B that they are with their side edge portions 58, 60 in overlap with a respective recess 40, 42.
  • the bearing portions 34, 36 with their side edge portions 58, 60 quasi spaced from the support ring surface 38, so that in a relative movement of the intermediate turbine housing to the housing 32, the side edge portions 58, 60 can not work into the housing or even can not be damaged.
  • the bearing portions 34, 36 here have a rectangular cross-section with a flat bearing surface 62, via which it is in contact with the respective support ring surface portion 48, 52 and two radially extending side surfaces 64, 66, each with the contact surface 62, the side edge regions 58, 60 form.
  • the recess 40, 42, 44, 46 each have a groove-like profile and extend with respect to the machine axis X in the radial direction. They are thus oriented in the direction of a relative movement of the intermediate turbine housing. In the radial direction, this groove-like contour is constant. They each have a base 68 with a basic radius R1, which in the exemplary embodiment shown here runs directly into the respective support ring surface section 48 and the support ring surface region 50.
  • the recesses 40, 42, 44, 46 thus have virtually no side walls or go the side walls of the recesses 40, 42, 44, 46 stepless or flush in the bottom 68 over.
  • Transition areas 70, 72 between the recesses 40, 42, 44, 46 and the respective support ring surface portion 48 and support ring surface area 50 are preferably each provided with a transition radius R2, R3.
  • the recesses 40, 42, 44, 46 have a depth-to-width ratio d: w of 1: 5 to 1:20, preferably of about 1:10.
  • the width w is thereby removed by a radial center plane 74 of the recesses 40, 42, 44, 46.
  • the depth is removed from the midplane 74 intersection region with the base 68 to the adjacent support ring surface portion 48 and support ring surface region 50, respectively.
  • the recesses 40, 42, 44, 46 have a total width W which is 0.25 times to 2 times the width B of the bearing portions 34, 36.
  • the depth-to-width ratio d: w is set in particular via the basic radius R1.
  • the base radius R1 can be interrupted in each case by a flat, not shown.
  • the transition radii R2, R3 may be the same as in the embodiment shown here. In an alternative, not shown embodiment, the transition radii R2, R3 are different. The transition radii R2, R3 preferably correspond to 0.1 times to 1 times in the basic radius R1. Alternatively, the transition regions 70, 72 may be designed as a chamfer or edge.
  • the component support can of course also be used on other stator-side components.
  • the components can not be rotationally symmetrical.
  • a component support of a turbomachine in particular an aircraft engine with at least two stator-side substantially annular components, which are in axial contact with each other, and are preferably aligned coaxially to the machine axis, wherein the first component has a plurality of radial groove-like recesses with which the second component with its projection-like positioning portions is laterally in overlap, and wherein between the respectively adjacent locating portions an uncontoured support annular surface portion is formed, and a turbomachine.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Mounting Of Bearings Or Others (AREA)

Claims (11)

  1. Support d'élément d'une turbomachine, comportant au moins deux éléments (32) essentiellement annulaires du côté du stator, qui se trouvent en appui axial l'un par rapport à l'autre, dans lequel le premier élément (1) a une surface d'appui annulaire (38) et le deuxième élément a une multiplicité de portions de palier (34, 36) réparties sur son pourtour avec lesquelles il se trouve en appui avec la surface d'appui annulaire (38), caractérisé en ce que, dans la surface d'appui annulaire (38) est insérée une multiplicité d'évidements essentiellement radiaux de type annulaire (40, 42, 44, 46) qui ont un rapport de profondeur à largeur (d:w) de 1:5 à 1:20, dans lequel chaque portion de palier (34, 36) avec ses deux zones de bord latéral (58, 60) se trouve en chevauchement avec un évidement (40, 42, 44, 46) et entre les portions de palier (34, 36) voisines respectives (34, 36) s'étend une zone de surface d'appui annulaire sans contour (50) dans laquelle se poursuit un contour initial de la surface d'appui annulaire (38).
  2. Support d'élément selon la revendication 1, dans lequel les évidements (40, 42,44,46) ont un rapport de profondeur à largeur (d:w) d'environ 1:10.
  3. Support d'élément selon la revendication 1 ou 2, dans lequel les évidements (40, 42, 44, 46) ont une largeur totale (W) qui est 0,25 fois à 2 fois une largeur (B) des portions de palier (34, 36).
  4. Support d'élément selon la revendication 1, 2 ou 3, dans lequel les évidements (40,42,44,46) ont respectivement des rayons de transitions différents (R2, R3) dans la zone de transition (70, 72) aux zones de surface d'appui annulaire sans contour (50) et aux sections de surface d'appui annulaire (48, 52) recevant les portions de palier (34, 36).
  5. Support d'élément selon la revendication 1, 2 ou 3, dans lequel les évidements (40, 42, 44, 46) ont respectivement des rayons de transitions identiques (R2, R3) dans la zone de transition (70, 72) aux zones de surface d'appui annulaire sans contour (50) et aux sections de surface d'appui annulaire (48, 52) recevant les portions de palier.
  6. Support d'élément selon la revendication 4 ou 5, dans lequel les rayons de transition (R2, R3) correspondent à 0,1 fois à 1 fois un rayon de base (R1) des évidements (40, 42, 44, 46).
  7. Support d'élément selon la revendication 1, 2 ou 3, dans lequel des zones de transition (70, 72) sont formées, sous la forme de chanfreins ou de bords, par les évidements (40, 42, 44, 46) aux zones de surface d'appui annulaire sans contour (50) et par des sections de surface d'appui annulaire (48, 52) recevant les portions de palier (34, 36).
  8. Support d'élément selon l'une des revendications précédentes, dans lequel le rayon de base (R1) est interrompu par une zone plane.
  9. Support d'élément selon l'une des revendications précédentes, dans lequel les au moins deux éléments (32) du côté du stator sont orientés essentiellement sur un plan coaxial l'un par rapport à l'autre.
  10. Support d'élément selon l'une des revendications précédentes, dans lequel les au moins deux éléments (32) du côté du stator sont formés essentiellement de façon symétrique en rotation.
  11. Turbomachine comportant un support d'élément selon l'une des revendications précédentes.
EP13187698.9A 2013-10-08 2013-10-08 Support d'élément et turbomachine Not-in-force EP2860361B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
ES13187698.9T ES2620486T3 (es) 2013-10-08 2013-10-08 Soporte de componente y turbomáquina
EP13187698.9A EP2860361B1 (fr) 2013-10-08 2013-10-08 Support d'élément et turbomachine
US14/508,675 US9752455B2 (en) 2013-10-08 2014-10-07 Component support and turbomachine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP13187698.9A EP2860361B1 (fr) 2013-10-08 2013-10-08 Support d'élément et turbomachine

Publications (2)

Publication Number Publication Date
EP2860361A1 EP2860361A1 (fr) 2015-04-15
EP2860361B1 true EP2860361B1 (fr) 2017-03-01

Family

ID=49356208

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13187698.9A Not-in-force EP2860361B1 (fr) 2013-10-08 2013-10-08 Support d'élément et turbomachine

Country Status (3)

Country Link
US (1) US9752455B2 (fr)
EP (1) EP2860361B1 (fr)
ES (1) ES2620486T3 (fr)

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Also Published As

Publication number Publication date
US9752455B2 (en) 2017-09-05
US20150098799A1 (en) 2015-04-09
ES2620486T3 (es) 2017-06-28
EP2860361A1 (fr) 2015-04-15

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