EP2860361A1 - Component support and fluid flow engine - Google Patents

Component support and fluid flow engine Download PDF

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Publication number
EP2860361A1
EP2860361A1 EP20130187698 EP13187698A EP2860361A1 EP 2860361 A1 EP2860361 A1 EP 2860361A1 EP 20130187698 EP20130187698 EP 20130187698 EP 13187698 A EP13187698 A EP 13187698A EP 2860361 A1 EP2860361 A1 EP 2860361A1
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EP
European Patent Office
Prior art keywords
recesses
component
ring surface
support ring
component support
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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.)
Granted
Application number
EP20130187698
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German (de)
French (fr)
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EP2860361B1 (en
Inventor
Rudolf Stanka
Christoph Lauer
Hans Stricker
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MTU Aero Engines AG
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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.)
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Publication date
Application filed by MTU Aero Engines AG filed Critical MTU Aero Engines AG
Priority to EP13187698.9A priority Critical patent/EP2860361B1/en
Priority to ES13187698.9T priority patent/ES2620486T3/en
Priority to US14/508,675 priority patent/US9752455B2/en
Publication of EP2860361A1 publication Critical patent/EP2860361A1/en
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Publication of EP2860361B1 publication Critical patent/EP2860361B1/en
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    • 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
    • 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

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 plurality of essentially radial, groove-like recesses are introduced into the support ring surface, wherein each bearing section is in overlap with a recess with its two side edge regions, and an uncontoured support ring surface region extends between the respectively adjacent bearing sections.
  • 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 recesses have a depth-to-width ratio of 1: 5 to 1:20.
  • the depth 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 to 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 0.1 times 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.

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  • 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)

Abstract

Offenbart ist eine Bauteilabstützung einer Strömungsmaschine, insbesondere ein Flugtriebwerk mit zumindest zwei statorseitigen im Wesentlichen ringförmigen Bauteilen, die sich in axialer Anlage miteinander befinden, und vorzugsweise koaxial zur Maschinenachse ausgerichtet sind, wobei das erste Bauteil (1) eine Vielzahl von radialen rinnenartigen Aussparungen (40, 42, 44, 46) aufweist, mit denen sich das zweite Bauteil mit seinen vorsprungartigen Lageabschnitten seitlich in Überlappung befindet, und wobei zwischen den jeweils benachbarten Lageabschnitten (34, 36) ein unkonturierter Stützringflächenabschnitt ausgebildet ist, sowie eine Strömungsmaschine.Disclosed is 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 (1) has a plurality of radial groove-like recesses (40 , 42, 44, 46), with which the second component with its projection-like locating portions is laterally in overlap, and wherein between the respectively adjacent bearing portions (34, 36) an uncontoured support ring surface portion is formed, and a turbomachine.

Description

Die Erfindung betrifft eine Bauteilabstützung nach dem Oberbegriff des Patentanspruchs 1 und eine Strömungsmaschine.The invention relates to a component support according to the preamble of patent claim 1 and a turbomachine.

In Strömungsmaschinen wie Dampfturbinen, stationären Gasturbinen oder Flugtriebwerken können zwischen zwei statorseitigen Bauteilen, die sich in Kontakt miteinander befinden, aufgrund von Vibration, unterschiedlichen Wärmeausdehnungen und der gleichen relative Bewegungen auftreten. In Figur 1 ist eine bekannte Bauteilabstützung zwischen zwei sich in Anlage befindenden statorseitigen Bauteilen skizziert. Die Bauteile sind dabei nur ausschnittsweise und stark vereinfacht skizziert. Das eine Bauteil 1 ist ein Gehäusering, der koaxial zu einer in der Zeichenebene verlaufenden Maschinenachse X ausgerichtet ist. Das zweite Bauteil ist beispielsweise ein Zwischenturbinengehäuse, das ebenfalls koaxial zur Maschinenachse X ausgerichtet ist und über eine Vielzahl von sich radial nach außen erstreckenden Lagerabschnitten 2, 4 an einer Stützringfläche 6 des ersten Bauteils abgestützt ist. Zur Vermeidung von Kanteneffekten zwischen den Lagerabschnitten 2, 4 und der Stützringfläche 6 sind in der Stützringfläche 6 eine Vielzahl von Aussparungen 8, 10, 12 eingebracht, mit denen sich die Lagerabschnitte 2, 4 mit ihren Seitenkantenbereichen 14, 16 in Überlappung befinden. Die Aussparungen 8, 10, 12 sind in Umfangsrichtung gleichmäßig voneinander beabstandet und jeweils über einen unkonturierten und die Lagerabschnitte 2, 4 aufnehmenden Stützringflächenabschnitt 18, 20 voneinander beabstandet. Sie sind radial zur Maschinenachse X und somit in Bewegungsrichtung des Zwischenturbinengehäuses orientiert. Die Aussparungen 8, 10, 12 sind jeweils nutenartig und haben zwei steile Seitenwandungen 22, 24, die über einen flachen Grund 26 miteinander verbunden sind. Übergangsbereiche 28, 30 zwischen den Seitenwandungen 22, 24 und den Stützringflächenabschnitten 18, 20 sind verhältnismäßig scharfkantig ausgebildet. Mittels dieser nutenartigen Aussparungen lassen sich zwar Kanteneffekte zumindest verringern, jedoch führen die nutenartigen Aussparungen zu einer Veränderung der Strukturmechanik des Gehäuserings im Bereich der Stützringfläche. Zudem können beim Einbringen der Aussparungen Spannungen in den Gehäusering eingebracht werden.In turbomachines such as steam turbines, stationary gas turbines or aircraft engines, between two stator-side components which are in contact with each other may occur due to vibration, different thermal expansions and the same relative movements. In 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. To avoid edge effects between the bearing sections 2, 4 and the support ring surface 6 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. Although edge effects can at least be reduced by means of these groove-like recesses, the groove-like recesses lead to a change in the structural mechanics of the housing ring in the area of the support ring surface. In addition, when inserting the recesses, stresses can be introduced into the housing ring.

In der JP 59018213 A ist eine Strömungsmaschine mit einer Ringnut zur Aufnahme eines Leitschaufelkranzes gezeigt. Die Ringnut hat einen flachen Nutgrund und zwei steile Seitenwandungen. In den Übergangsbereichen zwischen den Seitenwandungen und dem Nutgrund sind Aushöhlungen eingebracht.In the JP 59018213 A 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.

Aufgabe der Erfindung ist es, eine alternative Bauteilabstützung einer Strömungsmaschine zu schaffen, die die vorgenannten Nachteile beseitigt und bei der ein Kanteneffekt zwischen zwei sich in Anlage befindenden statorseitigen Bauteilen verhindert wird. Des Weiteren ist es Aufgabe der Erfindung, eine Strömungsmaschine mit einer optimierten Bauteilabstützung zu schaffen.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.

Diese Aufgabe wird gelöst durch eine Bauteilabstützung mit den Merkmalen des Patentanspruchs 1 und durch eine Strömungsmaschine mit den Merkmalen des Patentanspruchs 11.This object is achieved by a component support having the features of patent claim 1 and by a turbomachine having the features of patent claim 11.

Eine erfindungsgemäße Bauteilabstützung einer Strömungsmaschine hat zumindest zwei statorseitige im Wesentlichen ringförmige Bauteile, die sich in axialer Anlage miteinander befinden und vorzugsweise koaxial zueinander ausgebildet sind. Das erste Bauteil hat eine Stützringfläche und das zweite Bauteil hat eine Vielzahl von über seinen Umfang verteilten Lagerabschnitten, mit denen es sich in Anlage mit der Stützringfläche befindet. Erfindungsgemäß ist in die Stützringfläche eine Vielzahl von im Wesentlichen radialen, rinnenartigen Aussparungen eingebracht, wobei sich jeder Lagerabschnitt mit seinen beiden Seitenkantenbereichen in Überlappung mit einer Aussparung befindet, und sich zwischen den jeweils benachbarten Lagerabschnitten ein unkonturierter Stützringflächenbereich erstreckt.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. According to the invention, a plurality of essentially radial, groove-like recesses are introduced into the support ring surface, wherein each bearing section is in overlap with a recess with its two side edge regions, and an uncontoured support ring surface region extends between the respectively adjacent bearing sections.

Durch die erfindungsgemäße Abstützung werden Kanteneffekte an der Stützringfläche und an den Lagerabschnitten bei einer Relativbewegung der Bauteile, beispielsweise aufgrund von unterschiedlichen Wärmeausdehnungen, zueinander verhindert. Durch die rinnenartigen Aussparungen in Kombination mit den unkonturierten Stützringflächenbereichen zwischen den Lagerabschnitten erfolgt keine wesentliche bzw. keine Veränderung der Strukturmechanik des ersten Bauteils, sodass durch die rinnenartigen Aussparungen keine zusätzlichen Spannungen in das erste Bauteil eingebracht werden, auch nicht bei deren Einbringung in das erste Bauteil. Zudem lassen sich die rinnenartigen Aussparungen fertigungstechnisch einfach herstellen. Beispielsweise werden die rinnenartigen Aussparungen mittels einer mechanischen Bearbeitung wie Fräsen oder einer elektrochemischen bzw. galvanischen Bearbeitung herausgearbeitet.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 Stützringflächenbereichen 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.

Bei einem bevorzugten Ausführungsbeispiel haben die Aussparungen ein Tiefen-Breiten-Verhältnis von 1: 5 bis 1:20. Die Tiefe wird dabei in axialer Richtung und die Breite in Umfangsrichtung abgetragen. Bei einem besonders günstigen Ausführungsbeispiel beträgt das Tiefen- Breiten-Verhältnis 1:10. Die Breite wird dabei von einer radialen Mittelebene der Aussparungen abgetragen, so dass die Aussparungen ähnlich einem Durchmesser zu einem Radius eine Gesamtbreite haben, die gleich 2mal der Breite ist.In a preferred embodiment, the recesses have a depth-to-width ratio of 1: 5 to 1:20. The depth is thereby removed in the axial direction and the width in the circumferential direction. In a particularly favorable embodiment, 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.

Bevorzugterweise haben die Aussparungen eine Gesamtbreite, die 0,25mal bis 2mal einer Breite der Lagerabschnitte ist.Preferably, the recesses have a total width which is 0.25 times to 2 times a width of the bearing sections.

Eine optimale Anpassung des ersten Bauteils an eine aufzunehmende Stützlast kann dadurch erreicht werden, dass die Aussparungen jeweils unterschiedliche Übergangsradien im Übergangsbereich zu den unkonturierten Stützringflächenbereichen und zu Stützringflächenabschnitten aufweisen, an denen die Lagerabschnitte abgestützt sind bzw. die die Lagerabschnitte aufnehmen.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 Stützringflächenbereichen and Stützringflächenabschnitten on which the bearing sections are supported and which receive the bearing sections.

Bei einem alternativen Ausführungsbeispiel haben die Aussparungen jeweils gleiche Übergangsradien im Übergangsbereich zu den unkonturierten Stützringflächenbereichen und zu den Lagerabschnitten aufnehmenden Stützringflächenabschnitten. Ein derartiges Ausführungsbeispiel ist aufgrund der gleichen Übergangsradien einfacher herzustellen als das vorhergehende Ausführungsbeispiel mit den unterschiedlichen Übergangsradien.In an alternative embodiment, the recesses each have equal transition radii in the transition region to the non-contoured Stützringflächenbereichen and to 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.

Aus strukturmechanischer Sicht ist es günstig, wenn die Übergangsradien 0,1mal bis 1mal einem Grundradius der Aussparungen entsprechen.From a structural mechanical point of view, it is favorable if the transition radii correspond to 0.1 times to 1 times a basic radius of the recesses.

Alternativ sind die Übergangsbereiche von den Aussparungen zu den unkonturierten Stützringflächenbereichen und zu den die Lagerabschnitte aufnehmenden Stützringflächenabschnitten als Fasen oder Kanten ausgebildet. Fasen bzw. Kanten sind fertigungstechnisch einfach auszubilden.Alternatively, 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.

Bei einem Ausführungsbeispiel ist der Grundradius durch eine Flachstelle unterbrochen.In one embodiment, the base radius is interrupted by a flat.

Vorteilhafterweise sind die zumindest zwei Bauteile koaxial zueinander ausgerichtet.Advantageously, the at least two components are aligned coaxially with each other.

Insbesondere können die zumindest zwei Bauteile rotationssymmetrisch ausgebildet sein. Dies erleichtert die Ausrichtung der Bauteile zueinander.In particular, the at least two components can be rotationally symmetrical. This facilitates the alignment of the components to each other.

Eine erfindungsgemäße Strömungsmaschine hat zumindest eine erfindungsgemäße Bauteilabstützung, wodurch Kanteneffekte zwischen sich in Anlage befindenden statorseitigen Bauteilen verhindert werden.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.

Sonstige vorteilhafte Ausführungsbeispiele der Erfindung sind Gegenstand weiterer Unteransprüche.Other advantageous embodiments of the invention are the subject of further subclaims.

Im Folgenden wird ein bevorzugtes Ausführungsbeispiel der Erfindung anhand schematischer Darstellungen näher erläutert. Es zeigen:

Figur 1
einen Ausschnitt einer bekannten Abstützung von zwei Bauteilen einer Strömungsmaschine,
Figur 2
einen Ausschnitt einer erfindungsgemäßen Bauteilabstützung einer Strömungsmaschine, und
Figur 3
eine Detaildarstellung aus Figur 2.
In the following, a preferred embodiment of the invention is explained in more detail with reference to schematic representations. Show it:
FIG. 1
a section of a known support of two components of a turbomachine,
FIG. 2
a section of a component support according to the invention a turbomachine, and
FIG. 3
a detailed view FIG. 2 ,

In Figur 2 ist ein Ausschnitt einer erfindungsgemäßen Bauteilabstützung einer Strömungsmaschine gezeigt. Die Strömungsmaschine ist bevorzugterweise eine stationäre Gasturbine und insbesondere ein Flugtriebwerk. Die Bauteilabstützung befindet sich turbinenseitig in der Strömungsmaschine und wird beispielsweise von einem statorseitigen ringförmigen Gehäuse 32 und einem statorseitigen ringförmigen Zwischenturbinengehäuse gebildet. Das Zwischenturbinengehäuse hat eine Vielzahl von sich radial nach außen erstreckende Vorsprünge 34, 36, die als Lagerabschnitte dienen und mittels denen es an einer axialen Stützringfläche 38 des Gehäuses 32 abgestützt ist. Das Gehäuse 32 und das Zwischenturbinengehäuse sind in dem hier gezeigten Ausführungsbeispiel rotationssymmetrisch und koaxial zur Maschinenachse X der Strömungsmaschine orientiert, die sich in der Zeichenebene erstreckt, und zwar orthogonal zur Stützringfläche 38.In 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

Zur Vermeidung von Kanteneffekten im Bereich der Lagerabschnitte 34, 36 sind in der Stützringfläche 38 eine Vielzahl von rinnenartigen Aussparungen 40, 42, 44, 46 eingebracht. Die Aussparungen 40, 42, 44, 46 sind in Umfangsrichtung gleichmäßig voneinander beabstandet und über unkonturierte Stützringflächenareale 48, 50, 52 voneinander beabstandet.To avoid edge effects in the region of the bearing portions 34, 36, 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.

Der Begriff "unkonturiert" bedeutet im Sinne der vorliegenden Erfindung, dass die Stützringflächenareale 48, 50, 52 im Wesentlichen eine ursprüngliche Kontur der Stützringfläche 38 fortführen. Selbstverständlich sind lokale Vertiefungen in den Stützringflächenarealen 48, 50, 52 umfasst. Auch können die Stützringflächenareale 48, 50, 52 eine fertigungsbedingte Oberflächenrauhigkeit aufweisen, welche nicht oder nur abschnittsweise durch Nachbearbearbeitung geglättet wurde. Beispielsweise können die Oberflächen der Stützringflächenareale 48, 52, die die Lagerabschnitte 34, 36 abstützen, durch Feinbearbeitungsschritte, wie zum Beispiel Feinschleifen und/oder durch Beschichten geglättet werden bzw. worden sein, während die Oberfläche des dazwischenliegenden Stützringflächenareals 50 im Wesentlichen eine herstellungsbedingte ursprüngliche Oberflächenrauhigkeit aufweist.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 Stützringflächenareale 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.

Die Lagerabschnitte 34, 36 sind gleichmäßig über den Umfang verteilt. Sie haben in Umfangsrichtung eine derartige Teilung, dass sie jeweils an einem Stützringflächenareal 48, 52 anliegen und dabei jeweils über ein Stützringflächenareal 50 voneinander beabstandet sind. Zwischen den jeweils benachbarten Lagerabschnitten 34, 36 befindet sich somit stets ein unkonturiertes Stützringflächenareal 50. Aus Gründen der Übersichtlichkeit werden die Stützringflächenareale 48, 52, an denen die Lagerabschnitte 34, 36 abgestützt sind, als Stützringflächenabschnitte bezeichnet. Die lagerabschnittsfreien Stützringflächenareale 50 werden als Stützringflächenbereiche bezeichnet.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. For reasons of clarity, 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.

Aus Gründen der Übersichtlichkeit ist im Folgenden lediglich der in Figur 2 gezeigte linke Lagerabschnitt 34 entsprechend beziffert. Die Lagerabschnitte 34, 36 haben eine derartige Erstreckung in Umfangsrichtung bzw. Breite B, das sie sich mit ihren Seitenkantenbereichen 58, 60 in Überlappung mit jeweils einer Aussparung 40, 42 befinden. Hierdurch sind die Lagerabschnitte 34, 36 mit ihren Seitenkantenbereichen 58, 60 von der Stützringfläche 38 quasi beabstandet, so dass sich bei einer Relativbewegung des Zwischenturbinengehäuses zum Gehäuse 32 die Seitenkantenbereiche 58, 60 nicht in das Gehäuse einarbeiten können bzw. selbst nicht beschädigt werden können. Die Lagerabschnitte 34, 36 haben hier einen rechteckigen Querschnitt mit einer ebenen Anlagefläche 62, über die sie sich in Kontakt mit dem jeweiligen Stützringflächenabschnitt 48, 52 befindet und zwei sich in radialer Richtung erstreckende Seitenflächen 64, 66, die jeweils mit der Anlagefläche 62 die Seitenkantenbereiche 58, 60 bilden.For the sake of clarity, only the in FIG. 2 shown left bearing section 34 accordingly numbered. The 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. As a result, 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.

Wie in der Detaildarstellung in Figur 3 anhand der Aussparung 42 stellvertretend für alle Aussparungen 40, 42, 44, 46 verdeutlicht, haben die Aussparungen 40, 42, 44, 46 jeweils ein rinnenartiges Profil und erstrecken sich bezogen auf die Maschinenachse X in Radialrichtung. Sie sind somit in Richtung einer Relativbewegung des Zwischenturbinengehäuses orientiert. In Radialrichtung ist diese rinnenartige Kontur konstant. Sie haben jeweils einen Grund 68 mit einem Grundradius R1, der in dem hier gezeigten Ausführungsbeispiel direkt in den jeweiligen Stützringflächenabschnitt 48 und den Stützringflächenbereich 50 ausläuft. Die Aussparungen 40, 42, 44, 46 weisen somit quasi keine Seitenwandungen auf bzw. gehen die Seitenwandungen der Aussparungen 40, 42, 44, 46 stufenlos bzw. bündig in den Grund 68 über. Übergangsbereiche 70, 72 zwischen den Aussparungen 40, 42, 44, 46 und dem jeweiligen Stützringflächenabschnitt 48 und Stützringflächenbereich 50 sind bevorzugterweise mit jeweils einem Übergangsradius R2, R3 versehen.As in the detailed presentation in FIG. 3 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.

Die Aussparungen 40, 42, 44, 46 haben eine Tiefen-Breiten-Verhältnis d:w von 1:5 bis 1: 20, bevorzugterweise von etwa 1:10. Die Breite w wird dabei von einer radialen Mittelebene 74 der Aussparungen 40, 42, 44, 46 abgetragen. Die Tiefe wird vom Schnittbereich der Mittelebene 74 mit dem Grund 68 zum angrenzenden Stützringflächenabschnitt 48 bzw. Stützringflächenbereich 50 abgetragen. Bevorzugterweise haben die Aussparungen 40, 42, 44, 46 eine Gesamtbreite W, die 0,25mal bis 2mal der Breite B der Lagerabschnitte 34, 36 ist. Das Tiefen-Breiten-Verhältnis d:w wird insbesondere über den Grundradius R1 eingestellt.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. Preferably, 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.

Der Grundradius R1 kann dabei jeweils von einer nicht gezeigten Flachstelle unterbrochen sein.The base radius R1 can be interrupted in each case by a flat, not shown.

Die Übergangsradien R2, R3 können wie in dem hier gezeigten Ausführungsbeispiel gleich ausgeführt sein. Bei einem alternativen, nicht gezeigten Ausführungsbeispiel sind die Übergangsradien R2, R3 unterschiedlich. Bevorzugterweise entsprechen die Übergangsradien R2, R3 0,1mal bis 1mal im Grundradius R1. Alternativ können die Übergangsbereiche 70, 72 als Fase oder Kante ausgeführt sein.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.

Neben der hier beispielhaft erläuterten Anwendung der erfindungsgemäßen Bauteilabstützung zur Abstützung eines Zwischenturbinengehäuses an einem Gehäusering, kann die Bauteilabstützung selbstverständlich auch an anderen statorseitigen Bauteilen verwendet werden. Insbesondere können die Bauteile nicht rotationssymmetrisch sein.In addition to the example exemplified here application of the component support according to the invention for supporting a Zwischenturbinengehäuses on a housing ring, the component support can of course also be used on other stator-side components. In particular, the components can not be rotationally symmetrical.

Offenbart ist eine Bauteilabstützung einer Strömungsmaschine, insbesondere ein Flugtriebwerk mit zumindest zwei statorseitigen im Wesentlichen ringförmigen Bauteilen, die sich in axialer Anlage miteinander befinden, und vorzugsweise koaxial zur Maschinenachse ausgerichtet sind, wobei das erste Bauteil eine Vielzahl von radialen rinnenartigen Aussparungen aufweist, mit denen sich das zweite Bauteil mit seinen vorsprungartigen Lageabschnitten seitlich in Überlappung befindet, und wobei zwischen den jeweils benachbarten Lageabschnitten ein unkonturierter Stützringflächenabschnitt ausgebildet ist, sowie eine Strömungsmaschine.Disclosed is 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.

BezugszeichenlisteLIST OF REFERENCE NUMBERS

11
Gehäuseringhousing ring
22
Vorsprung / LagerabschnittLedge / bearing section
44
Vorsprung / LagerabschnittLedge / bearing section
66
StützringflächeSupport ring surface
88th
nutenartigen Aussparunggroove-like recess
1010
nutenartigen Aussparunggroove-like recess
1212
nutenartigen Aussparunggroove-like recess
1414
SeitenkantenbereichSide edge region
1616
SeitenkantenbereichSide edge region
1818
StützringflächenabschnittSupport ring surface section
2020
StützringflächenabschnittSupport ring surface section
2222
Seitenwandungsidewall
2424
Seitenwandungsidewall
2626
Grundreason
2828
ÜbergangsbereichTransition area
3030
ÜbergangsbereichTransition area
3232
Gehäusecasing
3434
Lagerabschnittbearing section
3636
Lagerabschnittbearing section
3838
StützringflächeSupport ring surface
4040
Aussparungrecess
4242
Aussparungrecess
4444
Aussparungrecess
4646
Aussparungrecess
4848
Stützringflächenareal / StützringflächenabschnittSupport Ring Area / Support Ring Area Section
5050
Stützringflächenareal / StützringflächenbereichSupport Ring Area / Support Ring Area
5252
Stützringflächenareal / StützringflächenabschnittSupport Ring Area / Support Ring Area Section
5858
SeitenkantenbereichSide edge region
6060
SeitenkantenbereichSide edge region
6262
Anlageflächecontact surface
6464
Seitenflächeside surface
6666
Seitenflächeside surface
6868
Grundreason
7070
ÜbergangsbereichTransition area
7272
ÜbergangsbereichTransition area
7474
Mittelebenemidplane
R1R1
Grundradiusbase radius
R2R2
ÜbergangsradiusTransition radius
R3R3
ÜbergangsradiusTransition radius
BB
Breite LagerabschnittWide bearing section
dd
Tiefe AussparungDeep recess
ww
Breite Aussparung, abgetragen von MittellinieWide recess, worn away from centerline
WW
Gesamtbreite AussparungOverall width recess
XX
Maschinenachsemachine axis

Claims (11)

Bauteilabstützung einer Strömungsmaschine, mit zumindest zwei statorseitigen, im Wesentlichen ringförmigen Bauteilen (32), die sich in axialer Anlage miteinander befinden, wobei das erste Bauteil (1) eine Stützringfläche (38) hat und das zweite Bauteil eine Vielzahl von über seinen Umfang verteilten Lagerabschnitten (34, 36) hat, mit denen es sich in Anlage mit der Stützringfläche (38) befindet, dadurch gekennzeichnet, dass in die Stützringfläche (38) eine Vielzahl von im Wesentlichen radialen rinnenartigen Aussparungen (40, 42, 44, 46) eingebracht ist, wobei sich jeder Lagerabschnitt (34, 36) mit seinen beiden Seitenkantbereichen (58, 60) in Überlappung mit einer Aussparung (40, 42, 44, 46) befindet und sich zwischen den jeweils benachbarten Lagerabschnitten (34, 36) ein unkonturierter Stützringflächenbereich (50) erstreckt.Component support of a turbomachine, having at least two stator-side, substantially annular components (32) which are in axial contact with each other, wherein the first component (1) has a support ring surface (38) and the second component has a plurality of spaced about its circumference bearing portions (34, 36), with which it is in contact with the support ring surface (38), characterized in that in the support ring surface (38) has a plurality of substantially radial groove-like recesses (40, 42, 44, 46) is introduced , wherein each bearing section (34, 36) with its two side edge regions (58, 60) is in overlap with a recess (40, 42, 44, 46) and between the respectively adjacent bearing sections (34, 36) an uncontoured support ring surface region (34). 50) extends. Bauteilabstützung nach Anspruch 1, wobei die Aussparungen (40, 42, 44, 46) ein Tiefenzu Breitenverhältnis (d:w) von 1:5 bis 1:20, bevorzugterweise von etwa 1:10 haben.The component support of claim 1, wherein the recesses (40, 42, 44, 46) have a depth to width ratio (d: w) of 1: 5 to 1:20, preferably about 1:10. Bauteilabstützung nach Anspruch 1 oder 2, wobei die Aussparungen (40, 42, 44, 46) eine Gesamtbreite (W) haben, die 0,25mal bis 2mal einer Breite (B) der Lagerabschnitte (34, 36) ist.A component support according to claim 1 or 2, wherein the recesses (40, 42, 44, 46) have a total width (W) that is 0.25 times to 2 times a width (B) of the bearing portions (34, 36). Bauteilabstützung nach Anspruch 1, 2 oder 3, wobei die Aussparungen (40, 42, 44, 46) jeweils unterschiedliche Übergangsradien (R2, R3) im Übergangsbereich (70, 72) zu den unkonturierten Stützringflächenbereichen (50) und zu die Lagerabschnitte (34, 36) aufnehmenden Stützringflächenabschnitten (48, 52) haben.Component support according to claim 1, 2 or 3, wherein the recesses (40, 42, 44, 46) each have different transition radii (R2, R3) in the transition region (70, 72) to the non-contoured support annular surface regions (50) and to the bearing sections (34, 36) receiving support ring surface portions (48, 52) have. Bauteilabstützung nach Anspruch 1, 2 oder 3, wobei die Aussparungen (40, 42, 44, 46) jeweils gleiche Übergangsradien (R2, R3) im Übergangsbereich (70, 72) zu den unkonturierten Stützringflächenbereichen (50) und zu die Lagerabschnitte aufnehmenden Stützringflächenabschnitten (48, 52) haben.Component support according to claim 1, 2 or 3, wherein the recesses (40, 42, 44, 46) in each case equal transition radii (R2, R3) in the transition region (70, 72) to the uncontoured Stützringflächenbereichen (50) and to the bearing portions receiving Stützringflächenabschnitten ( 48, 52). Bauteilabstützung nach Anspruch 4 oder 5, wobei die Übergangsradien (R2, R3) 0,1mal bis 1mal einem Grundradius (R1) der Aussparungen (40, 42, 44, 46) entsprechen.A component support according to claim 4 or 5, wherein the transition radii (R2, R3) correspond to 0.1 times to 1 times a base radius (R1) of the recesses (40, 42, 44, 46). Bauteilabstützung nach Anspruch 1, 2 oder 3, wobei Übergangsbereiche (70, 72) von den Aussparungen (40, 42, 44, 46) zu den unkonturierten Stützringflächenbereichen (50) und zu die Lagerabschnitte (34, 36) aufnehmenden Stützringflächenabschnitten (48, 52) als Fasen oder Kanten ausgebildet sind.A component support according to claim 1, 2 or 3, wherein transition regions (70, 72) of the recesses (40, 42, 44, 46) to the non-contoured Stützringflächenbereichen (50) and the bearing portions (34, 36) receiving support annular surface portions (48, 52 ) are formed as chamfers or edges. Bauteilabstützung nach einem der vorhergehenden Ansprüche, wobei der Grundradius (R1) durch eine Flachstelle unterbrochen ist.Component support according to one of the preceding claims, wherein the base radius (R1) is interrupted by a flat position. Bauteilabstützung nach einem der vorhergehenden Ansprüche, wobei die zumindest zwei statorseitigen Bauteile (32) im Wesentlichen koaxial zueinander ausgerichtet sind.Component support according to one of the preceding claims, wherein the at least two stator-side components (32) are aligned substantially coaxially with each other. Bauteilabstützung nach einem der vorhergehenden Ansprüche, wobei die zumindest zwei statorseitigen Bauteile (32) im Wesentlichen rotationssymmetrisch ausgebildet sind.Component support according to one of the preceding claims, wherein the at least two stator-side components (32) are formed substantially rotationally symmetrical. Strömungsmaschine mit einer Bauteilabstützung nach einem der vorhergehenden Ansprüche.Turbomachine with a component support according to one of the preceding claims.
EP13187698.9A 2013-10-08 2013-10-08 Component support and fluid flow engine Not-in-force EP2860361B1 (en)

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ES13187698.9T ES2620486T3 (en) 2013-10-08 2013-10-08 Component and turbomachinery support
US14/508,675 US9752455B2 (en) 2013-10-08 2014-10-07 Component support and turbomachine

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