EP1721064B1 - Ring structure with a metal design having a run-in lining - Google Patents

Ring structure with a metal design having a run-in lining Download PDF

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Publication number
EP1721064B1
EP1721064B1 EP05715035A EP05715035A EP1721064B1 EP 1721064 B1 EP1721064 B1 EP 1721064B1 EP 05715035 A EP05715035 A EP 05715035A EP 05715035 A EP05715035 A EP 05715035A EP 1721064 B1 EP1721064 B1 EP 1721064B1
Authority
EP
European Patent Office
Prior art keywords
wall
metal
ring
ring structure
structure 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.)
Expired - Fee Related
Application number
EP05715035A
Other languages
German (de)
French (fr)
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EP1721064A1 (en
Inventor
Manfred A. DÄUBLER
Ulrike Hain
Werner Humhauser
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MTU Aero Engines AG
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MTU Aero Engines GmbH
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Publication date
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Publication of EP1721064A1 publication Critical patent/EP1721064A1/en
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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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/127—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with a deformable or crushable structure, e.g. honeycomb
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F05D2230/236—Diffusion bonding
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F05D2230/237—Brazing
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F05D2230/238—Soldering
    • 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
    • F05D2250/20—Three-dimensional
    • F05D2250/28—Three-dimensional patterned
    • F05D2250/283—Three-dimensional patterned honeycomb
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/601—Fabrics

Definitions

  • the invention relates to a ring structure in metal construction according to the preamble of patent claim 1.
  • the wall structure should initially be sufficiently dimensionally stable and geometrically accurate. Thermal and mechanical influences should change the geometry as little as possible. Essentially, only the inside of the structure should be exposed to the usually hot working gas, leakage losses through the structure should be minimized. In steady-state operation, it is advantageous if the particular thermally induced dimensional change of the wall structure are adjusted in terms of time and size to those of the bladed rotor. Since mechanical contacts between the blade tips and the wall structure can hardly be avoided under special loads, the inside of the wall structure should at least be designed to be deformable on the point of the blade tip or resilient or capable of running.
  • the DE 100 20 673 C2 discloses a ring structure in metal construction for the blade area of axially flowed compressor and turbine stages.
  • the ring structure disclosed therein has an annular outer wall, which is designed as a closed, mechanically stable housing wall of the compressor or turbine stage.
  • the ring structure disclosed therein comprises an inner wall of annular shape and a connecting structure designed as a hollow chamber structure, wherein the connecting structure formed as a hollow chamber structure is sandwiched between the outer wall and the inner wall.
  • the connecting structure formed as a hollow chamber structure is connected on the one hand to the outer wall and on the other hand to the inner wall.
  • the annulus structure according to DE 100 20 673 C2 has an inner wall which is repeatedly interrupted over its circumference by axially or predominantly axially extending expansion joints.
  • Such an inner wall segmented by expansion joints has the disadvantage that flow losses can occur. Furthermore, increased by such a segmented inner wall, the complexity of the ring structure and thus the assembly and manufacturing costs. In addition, flaking, erosion or erosion damage may occur at the edges of the expansion joints during operation, causing the flow losses to increase again.
  • the DE 198 28 065 A1 relates to a honeycomb seal, in particular for a gas turbine, comprising a base plate, an air-evacuated honeycomb structure section (2), an intermediate plate (3) and a squealer section (4).
  • the abrading section (4) ie the inlet lining, may be embodied, inter alia, as metal felt.
  • the intermediate plate (3) is used to seal the evacuated honeycomb structure section (2). That is the hollow chamber structure, and forms a support for the abrading portion (4), for example for the metal felt.
  • the object of the present invention is to create a ring structure in metal construction which has a simplified construction.
  • This object is achieved by a ring structure in metal construction according to claim 1.
  • the inner wall is formed as a closed and mechanically stable structure of a metal fabric and / or a metal felt.
  • Fig. 1 and 2 show a first embodiment of a ring structure 10 according to the invention, wherein Fig. 2 the detail II of the Fig. 1 on an enlarged scale.
  • the ring structure 10 of the embodiment of Fig. 1 and 2 includes a circular outer wall 11, a circular inner wall 12 and a sandwiched between the outer wall 11 and the inner wall 12 connecting structure 13.
  • the outer wall 11 is formed as a closed, mechanically stable housing wall of a compressor stage or turbine stage of a gas turbine, in particular an aircraft engine.
  • the connecting structure 13 positioned between the outer wall 11 and the inner wall 12 is formed as a hollow chamber structure.
  • the hollow chamber structure 13 may have hexagonal, rectangular or even round chambers in cross-section in a cutting direction parallel to the inner wall or outer wall of the ring structure 10 in cross-section. In cross-section hexagonal chambers one speaks of a so-called honeycomb structure.
  • the inner wall 12 is formed as a closed and mechanically stable structure.
  • the inner wall 12 serves on the one hand for the mechanical stabilization of the ring structure 10 and on the other hand as an inlet lining for rotor blades (not shown) of rotating blades.
  • the internal wall 12 formed as a self-contained structure in the sense of the present invention is formed from a metal mesh and / or a metal felt.
  • a metal mesh is a structure in which metallic fibers or threads run systematically structured.
  • a metal felt is a structure in which metallic fibers are randomly or stochastically aligned.
  • the term metal mesh should also be understood to mean a knitted fabric made from metal fibers.
  • the formed as a closed structure inner wall 12 has characterized a simple construction.
  • connection structure 13 can be soldered to the inner wall 12 and the outer wall 11. Furthermore, it is possible to connect the connection structure 13 with the inner wall 12 and the outer wall 11, for example by so-called surface diffusion welding or by sintering.
  • the outer wall 11, the inner wall 12 and the connecting structure 13 are therefore connected to a total structure, namely to the ring structure 10 according to the invention, firmly together.
  • the inner wall 12 serves on the one hand to mechanically stabilize the ring structure 10 according to the invention and on the other hand as an inlet lining.
  • the inner wall 12 or the metal fabric and / or the metal felt of the inner wall 12 is made of a material which is resistant to oxidation at high temperatures.
  • the metal mesh or the metal felt for example, be made of a metal alloy based on a nickel material, iron material or cobalt material.
  • the metal mesh or the metal felt is joined together to form at least one joint to the annular inner wall 12.
  • a joint 14 of two mutually contacting edges of the metal fabric or metal felt for providing the inner wall 12 in the embodiment of the Fig. 2 the edges of the joint 14 extend in the radial direction, so that the two edges touch each other in the region of the joint 14, but no overlap occurs.
  • Fig. 3 to 6 show two further embodiments of inventive ring structures 15 and 16.
  • the embodiments of the Fig. 3 to 6 differ from the embodiment of Fig. 1 and 2
  • the exemplary embodiments are identical, so that the same reference numerals are used to avoid unnecessary repetitions for the same components.
  • a joint 17 which extends obliquely to the radial direction, that extends on the one hand in the radial direction and on the other hand in the circumferential direction of the ring structure 15.
  • a shock point 17 formed in this way an overlap of the corresponding edges takes place without material thickening.
  • FIGS. 5 and 6 show an embodiment of a ring structure 16 according to the invention, in which a shock point 18 is present in the region of the inner wall 12, in which abutting edges to form a material thickening 19 overlap each other.
  • the material thickening 19 is directed radially outward, the material thickening 19 thus extends into the region of the connecting structure 13 inside.
  • the chambers of the connecting structure 13 can be shortened accordingly in the region in which the material thickening 19 extends.
  • a metallic ring structure is proposed in which the inner wall is closed and further made of a metal mesh and / or a metal felt. Due to the closed structure of the inner wall flow losses can be minimized. By using the metal mesh or metal felt thermal strains can be intercepted without cracking. As a result, a much simpler construction of a ring structure is possible.
  • the inner wall of the metal felt or metal fabric continues to serve as inlet lining.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Description

Die Erfindung betrifft eine Ringstruktur in Metallbauweise nach dem Oberbegriff des Patentanspruchs 1.The invention relates to a ring structure in metal construction according to the preamble of patent claim 1.

Für die strömungstechnischen Eigenschaften von axial durchströmten Verdichter- und Turbinenstufen ist es wichtig, dass der Radialspalt zwischen den Laufschaufelspitzen und der äußeren Strömungskanalswand möglichst klein und möglichst konstant gehalten wird. Dafür sollte die Wandstruktur zunächst ausreichend formstabil und geometrisch genau sein. Thermische und mechanische Einflüsse sollten die Geometrie möglichst wenig verändern. Mit dem zumeist heißen Arbeitsgas sollte im Wesentlichen nur die Innenseite der Struktur beaufschlagt sein, Leckageverluste durch die Struktur sind zu minimieren. Im stationären Betrieb ist es vorteilhaft, wenn die insbesondere thermisch induzierte Maßänderung der Wandstruktur zeitlich und größenmäßig an diejenigen des beschaufelten Rotors angeglichen sind. Da sich mechanische Kontakte zwischen den Schaufelspitzen und der Wandstruktur unter besonderen Belastungen kaum vermeiden lassen, sollte die Innenseite der Wandstruktur zumindest schaufelspitzenseitig verformbar bzw. nachgiebig bzw. einlauffähig ausgebildet sein.For the fluidic properties of axial compressor and turbine stages, it is important that the radial gap between the blade tips and the outer flow channel wall is kept as small and as constant as possible. For this, the wall structure should initially be sufficiently dimensionally stable and geometrically accurate. Thermal and mechanical influences should change the geometry as little as possible. Essentially, only the inside of the structure should be exposed to the usually hot working gas, leakage losses through the structure should be minimized. In steady-state operation, it is advantageous if the particular thermally induced dimensional change of the wall structure are adjusted in terms of time and size to those of the bladed rotor. Since mechanical contacts between the blade tips and the wall structure can hardly be avoided under special loads, the inside of the wall structure should at least be designed to be deformable on the point of the blade tip or resilient or capable of running.

Die DE 100 20 673 C2 offenbart eine Ringstruktur in Metallbauweise für den Laufschaufelbereich von axial durchströmten Verdichter- und Turbinenstufen. Die dort offenbarte Ringstruktur verfügt über eine kreisringförmige Außenwand, die als geschlossene, mechanisch stabile Gehäusewand der Verdichter- oder Turbinenstufe ausgebildet ist. Weiterhin umfasst die dort offenbarte Ringstruktur eine kreisringförmig ausgebildete Innenwand sowie eine als Hohlkammerstruktur ausgebildete Verbindungsstruktur, wobei die als Hohlkammerstruktur ausgebildete Verbindungsstruktur sandwichartig zwischen der Außenwand und der Innenwand positioniert ist. Die als Hohlkammerstruktur ausgebildete Verbindungsstruktur ist einerseits mit der Außenwand und andererseits mit der Innenwand verbunden. Die Ringraumstruktur gemäß DE 100 20 673 C2 verfügt über eine Innenwand, die über ihren Umfang mehrfach durch axial oder vorwiegend axial verlaufende Dehnfugen unterbrochen ist. Eine derart durch Dehnfugen segmentierte Innenwand verfügt über den Nachteil, dass sich Strömungsverluste einstellen können. Weiterhin erhöht sich durch eine derart segmentierte Innenwand die Komplexität der Ringstruktur und damit der Montage- sowie Fertigungsaufwand. Außerdem können an den Kanten der Dehnfugen im Betrieb Abplatzungen, Auswaschungen oder Erosionsbeschädigungen auftreten, wodurch die Strömungsverluste abermals zunehmen.The DE 100 20 673 C2 discloses a ring structure in metal construction for the blade area of axially flowed compressor and turbine stages. The ring structure disclosed therein has an annular outer wall, which is designed as a closed, mechanically stable housing wall of the compressor or turbine stage. Furthermore, the ring structure disclosed therein comprises an inner wall of annular shape and a connecting structure designed as a hollow chamber structure, wherein the connecting structure formed as a hollow chamber structure is sandwiched between the outer wall and the inner wall. The connecting structure formed as a hollow chamber structure is connected on the one hand to the outer wall and on the other hand to the inner wall. The annulus structure according to DE 100 20 673 C2 has an inner wall which is repeatedly interrupted over its circumference by axially or predominantly axially extending expansion joints. Such an inner wall segmented by expansion joints has the disadvantage that flow losses can occur. Furthermore, increased by such a segmented inner wall, the complexity of the ring structure and thus the assembly and manufacturing costs. In addition, flaking, erosion or erosion damage may occur at the edges of the expansion joints during operation, causing the flow losses to increase again.

Die DE 198 28 065 A1 betrifft eine Wabenstruktur-Dichtung, insbesondere für eine Gasturbine, mit einer Grundplatte, einem luftevakuierten Wabenstruktur-Abschnitt (2), einer Zwischenplatte (3) und einem Anstreif-Abschnitt (4). Gemäß Beschreibung (Spalte 2, Zeile 55) kann der Anstreif-Abschnitt (4), d.h. der Einlaufbelag, u.a. als Metalfilz ausgeführt sein. Die Zwischenplatte (3) dient zur Abdichtung des evakuierten Wabenstruktur-Abschnitts (2).d.h. der Hohlkammerstruktur, und bildet einen Träger für den Anstreif-Abschnitt (4), z.B. für den Metallfilz.The DE 198 28 065 A1 relates to a honeycomb seal, in particular for a gas turbine, comprising a base plate, an air-evacuated honeycomb structure section (2), an intermediate plate (3) and a squealer section (4). According to the description (column 2, line 55), the abrading section (4), ie the inlet lining, may be embodied, inter alia, as metal felt. The intermediate plate (3) is used to seal the evacuated honeycomb structure section (2). That is the hollow chamber structure, and forms a support for the abrading portion (4), for example for the metal felt.

Hiervon ausgehend liegt der vorliegenden Erfindung die Aufgabe zu Grunde eine Ringstruktur in Metallbauweise zu schaffen, die eine verreinfachte Bauweise aufweist. Diese Aufgabe wird durch eine Ringstruktur in Metallbauweise gemäß Patentanspruch 1 gelöst. Erfindungsgemäß ist die Innenwand als geschlossene und mechanisch stabile Struktur aus einem Metallgewebe und/oder einem Metallfilz ausgebildet.Proceeding from this, the object of the present invention is to create a ring structure in metal construction which has a simplified construction. This object is achieved by a ring structure in metal construction according to claim 1. According to the invention the inner wall is formed as a closed and mechanically stable structure of a metal fabric and / or a metal felt.

Durch die geschlossene Struktur der Innenwand können Strömungsverluste minimiert werden. Weiterhin ergibt sich gegenüber der aus dem Stand der Technik bekannten segmentierten Bauweise eine einfachere Bauweise für die erfindungsgemäße Ringstruktur. Durch die Verwendung eines Metallgewebes bzw. eines Metallfilzes für die geschlossene Innenwand kann einerseits eine hohe mechanische Stabilität erzielt werden, andererseits führen Umfangsdehnungen jedoch nicht zu Ausbildung von Rissen in der Innenwand. Das Metallgewebe bzw. der Metallfilz kann nämlich thermisch erzeugte Dehnungen ohne Rissbildung aufnehmen.Due to the closed structure of the inner wall flow losses can be minimized. Furthermore, a simpler design for the ring structure according to the invention results over the segmented construction known from the prior art. By using a metal fabric or a metal felt for the closed inner wall, on the one hand, a high mechanical stability can be achieved, on the other hand, circumferential strains do not lead to the formation of cracks in the inner wall. Namely, the metal mesh or the metal felt can absorb thermally generated strains without cracking.

Bevorzugte Weiterbildungen der Erfindung ergeben sich aus den Unteransprüchen und der nachfolgenden Beschreibung. Ausführungsbeispiele der Erfindung werden, ohne hierauf beschränkt zu sein, an Hand der Zeichnung näher erläutert. Dabei zeigt:

Fig. 1
eine erfindungsgemäße Ringstruktur in Metallbauweise nach einem ersten Ausführungsbeispiel der Erfindung in schematisierter Seitenansicht;
Fig. 2
das Detail II der Ringstruktur gemäß Fig. 1;
Fig. 3
eine erfindungsgemäße Ringstruktur in Metallbauweise nach einem zweiten Ausführungsbeispiel der Erfindung in schematisierter Seitenansicht;
Fig. 4
das Detail IV der Ringstruktur gemäß Fig. 3;
Fig. 5
eine erfindungsgemäße Ringstruktur in Metallbauweise nach einem dritten Ausführungsbeispiel der Erfindung in schematisierter Seitenansicht; und
Fig. 6
das Detail VI der Ringstruktur gemäß Fig. 5.
Preferred embodiments of the invention will become apparent from the dependent claims and the description below. Embodiments of the invention will be described, without being limited thereto, with reference to the drawings. Showing:
Fig. 1
a ring structure according to the invention in metal construction according to a first embodiment of the invention in a schematic side view;
Fig. 2
the detail II of the ring structure according to Fig. 1 ;
Fig. 3
a ring structure according to the invention in metal construction according to a second embodiment of the invention in a schematic side view;
Fig. 4
the detail IV of the ring structure according to Fig. 3 ;
Fig. 5
a ring structure according to the invention in metal construction according to a third embodiment of the invention in a schematic side view; and
Fig. 6
the detail VI of the ring structure according to Fig. 5 ,

Nachfolgend wird die hier vorliegende Erfindung unter Bezugnahme auf Fig. 1 bis 6 in größerem Detail beschrieben.Hereinafter, the present invention will be described with reference to FIG Fig. 1 to 6 described in more detail.

Fig. 1 und 2 zeigen ein erstes Ausführungsbeispiel einer erfindungsgemäßen Ringstruktur 10, wobei Fig. 2 das Detail II der Fig. 1 in vergrößertem Maßstab zeigt. Fig. 1 and 2 show a first embodiment of a ring structure 10 according to the invention, wherein Fig. 2 the detail II of the Fig. 1 on an enlarged scale.

Die Ringstruktur 10 des Ausführungsbeispiels der Fig. 1 und 2 umfasst eine kreisförmige Außenwand 11, eine kreisförmige Innenwand 12 sowie eine zwischen der Außenwand 11 und der Innenwand 12 sandwichartig positionierte Verbindungsstruktur 13. Die Außenwand 11 ist als eine geschlossene, mechanisch stabile Gehäusewand einer Verdichterstufe oder Turbinenstufe einer Gasturbine, insbesondere eines Flugtriebwerks, ausgebildet. Die zwischen der Außenwand 11 und der Innenwand 12 positionierte Verbindungsstruktur 13 ist als eine Hohlkammerstruktur ausgebildet. Die Hohlkammerstruktur 13 kann dabei in einer Schnittrichtung parallel zur Innenwand bzw. Außenwand der Ringstruktur 10 im Querschnitt sechseckförmige, rechteckige oder auch runde Kammern aufweisen. Bei im Querschnitt sechseckigen Kammern spricht man von einer sogenannten Honigwabenstruktur.The ring structure 10 of the embodiment of Fig. 1 and 2 includes a circular outer wall 11, a circular inner wall 12 and a sandwiched between the outer wall 11 and the inner wall 12 connecting structure 13. The outer wall 11 is formed as a closed, mechanically stable housing wall of a compressor stage or turbine stage of a gas turbine, in particular an aircraft engine. The connecting structure 13 positioned between the outer wall 11 and the inner wall 12 is formed as a hollow chamber structure. The hollow chamber structure 13 may have hexagonal, rectangular or even round chambers in cross-section in a cutting direction parallel to the inner wall or outer wall of the ring structure 10 in cross-section. In cross-section hexagonal chambers one speaks of a so-called honeycomb structure.

Im Sinne der hier vorliegenden Erfindung ist die Innenwand 12 als eine geschlossene und mechanisch stabile Struktur ausgebildet. Die Innenwand 12 dient einerseits der mechanischen Stabilisierung der Ringstruktur 10 und andererseits als Einlaufbelag für nicht-gezeigte Laufschaufelspitzen rotierender Laufschaufeln. Die im Sinne der hier vorliegenden Erfindung als in sich geschlossene Struktur ausgebildete Innenwand 12 ist aus einem Metallgewebe und/oder einem Metallfilz ausgebildet. Bei einem Metallgewebe handelt es sich um eine Struktur, in welcher metallische Fasern bzw. Fäden systematisch strukturiert verlaufen. Bei einem Metallfilz hingegen handelt es sich um eine Struktur, in welcher metallische Fasern zufällig bzw. stochastisch verteilt ausgerichtet sind. Unter dem Begriff Metallgewebe soll auch ein Gewirk aus Metallfasern verstanden werden.For the purposes of the present invention, the inner wall 12 is formed as a closed and mechanically stable structure. The inner wall 12 serves on the one hand for the mechanical stabilization of the ring structure 10 and on the other hand as an inlet lining for rotor blades (not shown) of rotating blades. The internal wall 12 formed as a self-contained structure in the sense of the present invention is formed from a metal mesh and / or a metal felt. A metal mesh is a structure in which metallic fibers or threads run systematically structured. By contrast, a metal felt is a structure in which metallic fibers are randomly or stochastically aligned. The term metal mesh should also be understood to mean a knitted fabric made from metal fibers.

Durch die Verwendung einer in sich geschlossenen Struktur aus Metallgewebe und/oder Metallfilz als Innenwand 12 werden Spalte oder Fugen innerhalb der Innenwand 12 vermieden. Dadurch können Strömungsverluste minimiert werden. Das Metallgewebe bzw. der Metallfilz können thermisch erzeugte Dehnungen ohne die Gefahr von Rissbildungen aufnehmen. Dadurch wird es möglich auf Dehnfugen innerhalb der Innenwand 12 zu verzichten.By using a self-contained structure of metal fabric and / or metal felt as the inner wall 12 gaps or joints within the inner wall 12 are avoided. As a result, flow losses can be minimized. The metal mesh or felt can absorb thermally generated strains without the risk of cracking. This makes it possible to dispense with expansion joints within the inner wall 12.

Die als geschlossene Struktur ausgebildete Innenwand 12 verfügt dadurch über eine einfache Bauweise.The formed as a closed structure inner wall 12 has characterized a simple construction.

Die sandwichartige Struktur aus Außenwand 11, Innenwand 12 sowie Verbindungsstruktur 13 ist fest miteinander verbunden. So ist die Verbindungsstruktur 13 einerseits am radial außenliegenden Ende mit der Außenwand 11 und andererseits am radial innenliegenden Ende mit der Innenwand 12 fest verbunden. So kann die Verbindungsstruktur 13 mit der Innenwand 12 sowie der Außenwand 11 verlötet sein. Weiterhin ist es möglich, die Verbindungsstruktur 13 mit der Innenwand 12 und der Außenwand 11 zum Beispiel durch sogenanntes Oberflächendiffusionsschweißen bzw. durch Sintern miteinander zu verbinden. Die Außenwand 11, die Innenwand 12 sowie die Verbindungsstruktur 13 sind demnach zu einer Gesamtstruktur, nämlich zu der erfindungsgemäßen Ringstruktur 10, fest miteinander verbunden.The sandwich-like structure of outer wall 11, inner wall 12 and connecting structure 13 is firmly connected to each other. Thus, the connecting structure 13 on the one hand at the radially outer end with the outer wall 11 and on the other hand at the radially inner end with the inner wall 12 is firmly connected. Thus, the connection structure 13 can be soldered to the inner wall 12 and the outer wall 11. Furthermore, it is possible to connect the connection structure 13 with the inner wall 12 and the outer wall 11, for example by so-called surface diffusion welding or by sintering. The outer wall 11, the inner wall 12 and the connecting structure 13 are therefore connected to a total structure, namely to the ring structure 10 according to the invention, firmly together.

Wie bereits erwähnt, dient die Innenwand 12 einerseits der mechanischen Stabilisierung der erfindungsgemäßen Ringstruktur 10 sowie andererseits als Einlaufbelag. In diesem Zusammenhang sei darauf hingewiesen, dass die Innenwand 12 bzw. das Metallgewebe und/oder der Metallfilz der Innenwand 12 aus einem bei hohen Temperaturen oxidationsbeständigen Werkstoff hergestellt ist. So kann das Metallgewebe bzw. der Metallfilz zum Beispiel aus einer Metalllegierung auf Basis eines Nickelwerkstoffs, Eisenwerkstoffs oder auch Kobaltwerkstoffs hergestellt sein.As already mentioned, the inner wall 12 serves on the one hand to mechanically stabilize the ring structure 10 according to the invention and on the other hand as an inlet lining. In this context, it should be noted that the inner wall 12 or the metal fabric and / or the metal felt of the inner wall 12 is made of a material which is resistant to oxidation at high temperatures. Thus, the metal mesh or the metal felt, for example, be made of a metal alloy based on a nickel material, iron material or cobalt material.

Das Metallgewebe bzw. der Metallfilz wird unter Bildung mindestens einer Stoßstelle zu der kreisringförmigen Innenwand 12 miteinander verbunden. So zeigen Fig. 1 und 2 eine Stossstelle 14 von zwei einander berührenden Kanten des Metallgewebes bzw. Metallfilzes zur Bereitstellung der Innenwand 12. Im Ausführungsbeispiel der Fig. 2 verlaufen die Kanten der Stoßstelle 14 in radialer Richtung, sodass die beiden Kanten sich im Bereich der Stossstelle 14 zwar einander berühren, jedoch keine Überlappung derselben erfolgt.The metal mesh or the metal felt is joined together to form at least one joint to the annular inner wall 12. To show Fig. 1 and 2 a joint 14 of two mutually contacting edges of the metal fabric or metal felt for providing the inner wall 12 in the embodiment of the Fig. 2 the edges of the joint 14 extend in the radial direction, so that the two edges touch each other in the region of the joint 14, but no overlap occurs.

Fig. 3 bis 6 zeigen zwei weitere Ausführungsbeispiele erfindungsgemäßer Ringstrukturen 15 und 16. Die Ausführungsbeispiele der Fig. 3 bis 6 unterscheiden sich vom Ausführungsbeispiel der Fig. 1 und 2 lediglich durch die Ausbildung der Stoßstelle im Bereich der Innenwand 12. Hinsichtlich der sonstigen Details stimmen die Ausführungsbeispiele überein, sodass zur Vermeidung unnötiger Wiederholungen für gleiche Baugruppen gleiche Bezugsziffern verwendet werden. Fig. 3 to 6 show two further embodiments of inventive ring structures 15 and 16. The embodiments of the Fig. 3 to 6 differ from the embodiment of Fig. 1 and 2 With regard to the other details, the exemplary embodiments are identical, so that the same reference numerals are used to avoid unnecessary repetitions for the same components.

Beim Ausführungsbeispiel der Fig. 3 und 4 ist eine Stoßstelle 17 gezeigt, die schräg zur Radialrichtung verläuft, sich also einerseits in Radialrichtung und andererseits in Umfangsrichtung der Ringstruktur 15 erstreckt. Bei einer derart ausgebildeten Stossstelle 17 erfolgt eine Überlappung der entsprechenden Kanten ohne Materialaufdickung.In the embodiment of 3 and 4 a joint 17 is shown which extends obliquely to the radial direction, that extends on the one hand in the radial direction and on the other hand in the circumferential direction of the ring structure 15. In a shock point 17 formed in this way, an overlap of the corresponding edges takes place without material thickening.

Fig. 5 und 6 zeigen ein Ausführungsbeispiel einer erfindungsgemäßen Ringstruktur 16, bei der eine Stossstelle 18 im Bereich der Innenwand 12 vorhanden ist, bei welcher aneinanderstoßende Kanten unter Ausbildung einer Materialaufdickung 19 einander überlappen. Wie Fig. 5 und 6 entnommen werden kann, ist die Materialaufdickung 19 dabei nach radial außen gerichtet, die Materialaufdickung 19 erstreckt sich demnach in den Bereich der Verbindungsstruktur 13 hinein. Die Kammern der Verbindungsstruktur 13 können in dem Bereich, in welchem die Materialaufdickung 19 verläuft, entsprechend gekürzt werden. FIGS. 5 and 6 show an embodiment of a ring structure 16 according to the invention, in which a shock point 18 is present in the region of the inner wall 12, in which abutting edges to form a material thickening 19 overlap each other. As FIGS. 5 and 6 can be removed, the material thickening 19 is directed radially outward, the material thickening 19 thus extends into the region of the connecting structure 13 inside. The chambers of the connecting structure 13 can be shortened accordingly in the region in which the material thickening 19 extends.

Im Sinne der hier vorliegenden Erfindung wird eine metallische Ringstruktur vorgeschlagen, bei welcher die Innenwand geschlossen und weiterhin aus einem Metallgewebe und/oder einem Metallfilz hergestellt ist. Durch die geschlossene Struktur der Innenwand können Strömungsverluste minimiert werden. Durch die Verwendung des Metallgewebes bzw. Metallfilzes können thermische Dehnungen rissfrei abgefangen werden. Hierdurch ist eine deutlich einfachere Bauweise einer Ringstruktur möglich. Die Innenwand aus dem Metallfilz bzw. Metallgewebe dient weiterhin als Einlaufbelag.For the purposes of the present invention, a metallic ring structure is proposed in which the inner wall is closed and further made of a metal mesh and / or a metal felt. Due to the closed structure of the inner wall flow losses can be minimized. By using the metal mesh or metal felt thermal strains can be intercepted without cracking. As a result, a much simpler construction of a ring structure is possible. The inner wall of the metal felt or metal fabric continues to serve as inlet lining.

Claims (10)

  1. A ring structure of metal construction for a rotor-blade region of compressor- and turbine-stages through which there is axial flow, in particular in gas-turbine engines, having an outer wall (11) that is circular-ring-shaped, having an inner wall (12) that is circular-ring-shaped and also at a short radial distance from rotor-blade tips, and having a connecting structure (13) arranged between the outer wall (11) and the inner wall (12) and formed as a hollow-chamber structure, wherein the outer wall (11) is formed as a closed, mechanically stable housing wall of the compressor- or turbine-stage, wherein the connecting structure (13) that is formed as a hollow-chamber structure is connected to the outer wall (11) and the inner wall (12), and wherein the inner wall (12) constitutes a run-in lining for the rotor-blade tips,
    characterised in that
    the inner wall (12) as a whole is realized as a closed and mechanically stable structure made from a metal gauze and/or a metal felt.
  2. A ring structure according to claim 1,
    characterised in that
    the metal gauze and/or the metal felt is formed from a metal alloy that is oxidation-resistant at high temperatures, in particular from an iron-, nickel- or cobalt-based alloy.
  3. A ring structure according to claim 1 or 2,
    characterised in that
    the metal gauze and/or the metal felt forms the self-contained, circular-ring-shaped inner wall (12), wherein the metal gauze and/or the metal felt are connected together with the formation of at least one junction point (14; 17; 18) to form the circular-ring-shaped inner wall (12).
  4. A ring structure according to claim 3,
    characterised in that
    the or each junction point (17; 18) is formed by in each case two opposing edges, with the edges preferably overlapping each other.
  5. A ring structure according to claim 4,
    characterised in that
    the edges overlap each other without material thickening.
  6. A ring structure according to claim 4,
    characterised in that
    the edges overlap each other with the formation of a material thickening (19), wherein the material thickening (19) is directed radially outwards in the direction of the connecting structure (13) that is formed as a hollow-chamber structure.
  7. A ring structure according to one or more of claims 1 to 6,
    characterised in that
    the inner wall (12) that is formed from the metal gauze and/or the metal felt is fixedly connected to the connecting structure (13), formed as a hollow-chamber structure, by sintering or by surface-diffusion welding.
  8. A ring structure according to claim 7,
    characterised in that
    the connecting structure (13) that is formed as a hollow-chamber structure is fixedly connected to the outer wall (11) by sintering or by surface-diffusion welding.
  9. A ring structure according to one or more of claims 1 to 8,
    characterised in that
    the inner wall (12) that is formed from the metal gauze and/or the metal felt is fixedly connected to the connecting structure (13), formed as a hollow-chamber structure, by soldering.
  10. A ring structure according to claim 9, characterised in that
    the connecting structure (13) that is formed as a hollow-chamber structure is fixedly connected to the outer wall (11) by soldering.
EP05715035A 2004-03-03 2005-02-28 Ring structure with a metal design having a run-in lining Expired - Fee Related EP1721064B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102004010236A DE102004010236A1 (en) 2004-03-03 2004-03-03 Metal ring structure for sealing gap between rotor blade tips and stator in e.g. gas turbine, has inner wall formed by metal fabric or felt
PCT/DE2005/000333 WO2005085600A1 (en) 2004-03-03 2005-02-28 Ring structure with a metal design having a run-in lining

Publications (2)

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EP1721064A1 EP1721064A1 (en) 2006-11-15
EP1721064B1 true EP1721064B1 (en) 2010-06-02

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US (1) US8061965B2 (en)
EP (1) EP1721064B1 (en)
DE (2) DE102004010236A1 (en)
WO (1) WO2005085600A1 (en)

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Also Published As

Publication number Publication date
US20090263239A1 (en) 2009-10-22
EP1721064A1 (en) 2006-11-15
WO2005085600A1 (en) 2005-09-15
DE102004010236A1 (en) 2005-09-15
DE502005009677D1 (en) 2010-07-15
US8061965B2 (en) 2011-11-22

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