EP1766193B1 - Run-in coating - Google Patents

Run-in coating Download PDF

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Publication number
EP1766193B1
EP1766193B1 EP05749930A EP05749930A EP1766193B1 EP 1766193 B1 EP1766193 B1 EP 1766193B1 EP 05749930 A EP05749930 A EP 05749930A EP 05749930 A EP05749930 A EP 05749930A EP 1766193 B1 EP1766193 B1 EP 1766193B1
Authority
EP
European Patent Office
Prior art keywords
layer
run
compressor housing
inlet lining
coating
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
EP05749930A
Other languages
German (de)
French (fr)
Other versions
EP1766193A1 (en
Inventor
Manfred DÄUBLER
Wilfried Smarsly
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines GmbH
MTU Aero Engines AG
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Publication date
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Publication of EP1766193A1 publication Critical patent/EP1766193A1/en
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Publication of EP1766193B1 publication Critical patent/EP1766193B1/en
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • 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
    • F01D11/125—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 with a reinforcing structure
    • 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
    • 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
    • F05D2300/614—Fibres or filaments
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
    • Y10T428/24355—Continuous and nonuniform or irregular surface on layer or component [e.g., roofing, etc.]
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
    • Y10T428/24479—Structurally defined web or sheet [e.g., overall dimension, etc.] including variation in thickness
    • Y10T428/24521—Structurally defined web or sheet [e.g., overall dimension, etc.] including variation in thickness with component conforming to contour of nonplanar surface
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
    • Y10T428/24479—Structurally defined web or sheet [e.g., overall dimension, etc.] including variation in thickness
    • Y10T428/24521—Structurally defined web or sheet [e.g., overall dimension, etc.] including variation in thickness with component conforming to contour of nonplanar surface
    • Y10T428/24537—Parallel ribs and/or grooves
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
    • Y10T428/24479—Structurally defined web or sheet [e.g., overall dimension, etc.] including variation in thickness
    • Y10T428/24612—Composite web or sheet

Definitions

  • the present invention relates to an inlet lining according to the preamble of patent claim 1.
  • Deterioration i. an increase in the gap between the rotor and the compressor housing, affects both the efficiency and the surge limit of the compressor with increasing operating time.
  • the compressor must be designed for all operating times and be able to produce sufficient efficiency in all operating ranges without damaging individual components.
  • the blade tips are usually provided with a hard abrasive coating.
  • the housing can be coated with so-called inlet linings. Inlet linings have the particular advantage that these result in a material removal due to the contact with the blade tips not to a gap enlargement over the entire circumference and thus only to a lower power loss of the engine.
  • the compressor housing is provided with slots, which are inclined in the rule with respect to the axis of rotation of the rotor and are provided in the region of at least one blade ring on the inside of the housing.
  • the distribution of the slots and their geometry have an influence on the surge margin and the efficiency of the compressor. Since in the region of the compressor housing in which these slots are provided, that is to say in the region of the rotor, also the aforementioned inlet lining should be provided, the distribution and geometry of these slots is additionally determined by the nature of the inlet lining.
  • the document U.S.-A-4,405,284 protects a heat-insulating inlet lining for a compressor housing.
  • the inlet lining is applied via an adhesive layer on the inside of the housing and may have a honeycomb structure, which is completely or partially filled with einlaufpersonem material.
  • the document EP-A-0 965 730 relates to a ceramic inlet lining with a relatively dense, erosion-resistant layer and with an enterable layer.
  • the erosion-resistant layer is applied with constant thickness to a recessed substrate.
  • the document EP-A-1 253 294 relates to a comparable ceramic inlet lining with two different layers, wherein the layer adjacent to the substrate is also held positively on substrate-solid, spherical or mushroom-shaped elevations.
  • the document US-B1-6,203,021 protects an enema surface with a laser-made regular pattern to improve enmeshment.
  • the pattern may holes, grooves, webs u. ⁇ . Include.
  • EP-A-0 192 162 discloses an enema coating having a ceramic layer bonded to a metallic substrate via evenly distributed metallic anchoring elements in the form of wires, meshes, spirals, honeycombs, fibers, and the like. ä.
  • Object of the present invention is to provide an applied to the inside of a compressor housing inlet lining, which allows a flexible design of the compressor housing, in particular a targeted casing treatment, and having at least two layers, a first layer dimensionally stable and at least one further layer einlaufpener is.
  • the first layer has a profile with webs and recesses such that the at least one, further layer surrounds the first layer in such a way that there is a groove in the region of each depression, and that the inlet lining over the at least one , Another layer is connected to the compressor housing.
  • the coating, in particular a seal, which is applied to the inside of the compressor housing is referred to as inlet lining.
  • This inlet lining may be limited to the area of the individual rotors, but may also extend beyond this area in the axial direction, in particular covering or lining the entire compressor housing.
  • the inlet lining does not exclusively comprise the uppermost layer of a coating of the compressor housing, but rather all layers which are applied to a base material of the compressor housing.
  • the combination of the at least two layers mentioned, namely the einlaufpen and the dimensionally stable layer, a flexible design and design of the compressor housing is made possible.
  • properties of different materials as well as different geometries can be ideally combined by the different layers.
  • the first, more dimensionally stable layer consists of a material with high dimensional stability.
  • both woven materials, fibers or felts as well as porous or full materials can be used.
  • the first layer may for example be made of hollow titanium balls or constitute a ring of a fiber braid.
  • At least one further layer consists of a shrinkable material. This further layer is preferably the second layer adjacent to the first layer.
  • the inlet lining is given the property necessary to ensure a gap between the rotor and the stator in different operating conditions.
  • the provision of the einlaufdon material damage to the dimensionally stable material of the first layer and the rotors, in particular the compressor blade can be avoided.
  • known enema capable materials can be used.
  • materials with fillers, such as hollow spheres, can be used.
  • At least the first of the layers of the inlet lining is profiled in a defined manner.
  • At least one further, more einlaufpentopere layer is provided. This is directly adjacent to the first profiled layer.
  • This second layer thus represents a sheathing of the profile formed by the first layer.
  • the second layer is also provided on the side of the first layer, on which these elevations and / or depressions, that is on the side facing away from the compressor housing inner wall.
  • the advantage of applying a uniform layer is in particular in a simplification of the production of the inlet lining.
  • the second layer may have a greater thickness at the positions at which elevations are provided in the first layer.
  • the inlet lining is designed such that it has at least partially grooves on one side, which are formed by depressions in the first layer.
  • the grooves may be in the installed position obliquely to the rotor axis or axially aligned.
  • the shape of the entire inlet lining is determined essentially by the shape or by the profile of the first layer. Since this layer is made of dimensionally stable material, the retention of the shape of the profile can be ensured.
  • the grooves can be used optimally for influencing the flow behavior and for setting different pressure conditions in the inlet lining according to the invention. The grooves can thus be used as a means for a casing treatment.
  • the geometry of the grooves can be made flexible in the inlet lining according to the invention. According to the invention, it is possible to design the grooves in such a way that they have a large depth in comparison to their width. In particular, ratios of the width of the grooves to the depth of at most 0.5, preferably at most 0.3, can be set.
  • a low ratio of width to depth of the grooves may be advantageous in order to ensure a sufficient groove depth after the abrasion of a certain amount of the einlauftransporten material can.
  • the abraded material can be absorbed in the grooves while still ensuring sufficient groove depth.
  • the second layer completely surrounds the first layer.
  • the second layer is provided both on the profiled side of the first layer and on the smooth side of the first layer.
  • the first layer serves as a core and is encased by the second layer.
  • the sheath is continuous, i. also covers the ends of the core.
  • the embodiments according to the invention in which the first dimensionally stable layer of the inlet lining is profiled are also referred to below as macro-profiled inlet linings. These can be used in particular in the low-pressure region of a compressor, in particular a compressor of an aircraft engine or a gas turbine.
  • fibrous or porous material may be used as the material for the more settable layer.
  • a material for the first, more dimensionally stable layer is for example fibrous, porous or full material into consideration.
  • the first, more dimensionally stable and / or the at least one further, more einlauftransportere layer provided with reinforcing means, in particular interspersed can represent balls, for example.
  • the einlaufSchere layer here are balls of brittle material, which may be included, for example, in a layer of oriented fibers.
  • an inlay 10 comprising a first layer 12 and a second layer 14. This inlet lining 10 is applied to a base material 16 of a compressor housing.
  • the first layer 12 has a profile in which a number of webs 18 are provided over the surface of the first layer 12, between which depressions 20 are formed in the first layer 12.
  • the webs 18 may be applied to the layer 12 or the recesses 20 are introduced into the layer 12.
  • depressions 20 and webs 18, respectively may be formed by non-cutting methods, e.g. Casting or pressing, are generated.
  • the profile of the first layer 12 surrounds a second layer 14 that has substantially a uniform layer thickness.
  • the layer 14 thus the profile of the first layer 12, which forms the core of the inlet lining 10, and in particular whose webs 18 are sheathed.
  • the webs 18 facing away from the smooth side 22 of the first layer 12 is also covered by the second layer 14.
  • the inlet lining 10 is connected to the base material 16 via a joining zone 24.
  • the fixation of the inlet lining 10 on the base material 16 can be done by conventional methods, such as welding or gluing.
  • the depth of the grooves 26, which are formed by the recesses 20 and the sheath through the layer 14, in relation to the width of the grooves 26 is large.
  • This shape can be realized in the inlet lining 10 according to the invention due to the dimensionally stable core.
  • FIG. 1 only a part of the inlet lining 10 is shown. This can represent a ring according to the invention, which can be introduced into the compressor housing.

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

Abstract

The invention relates to a running-in coating (10) for a compressor housing, said coating comprising at least two layers (12, 14, 28, 30, 32) and being characterized in that a first layer (12, 28) is dimensionally stable and that at least an additional layer (14, 30, 32) is abradable.

Description

Die vorliegende Erfindung betrifft einen Einlaufbelag gemäß dem Oberbegriff des Patentanspruchs 1.The present invention relates to an inlet lining according to the preamble of patent claim 1.

In Flugtriebwerken und Gasturbinen ist ein wesentlicher Faktor, der auf den wirkungsgrad und die Zuverlässigkeit des Systems Einfluss nimmt, die Spalthaltung zwischen einem Rotor und einem Stator. Besonders schwierig gestaltet sich diese Spalthaltung zwischen einem Verdichterrotor, insbesondere Hochdruckverdichterrotor, und dem Verdichtergehäuse. Bei den Verdichterschaufeln muss anders als bei der Turbine auf Deckbänder verzichtet werden. Zudem werden immer geringere Stufen- und Schaufelzahlen in integraler Bauweise angestrebt, um die Herstellungs- und wartungskosten zu minimieren. Hieraus ergeben sich aber im Gegenzug höhere Drehzahlen und Umfangsgeschwindigkeiten der Rotoren und somit eine höhere Belastung.In aircraft engines and gas turbines, a significant factor affecting the efficiency and reliability of the system is the gap between a rotor and a stator. This gap is particularly difficult between a compressor rotor, in particular high-pressure compressor rotor, and the compressor housing. In the case of the compressor blades, it is necessary to dispense with cover bands, unlike the turbine. In addition, ever lower levels and number of blades in integral design are sought in order to minimize the manufacturing and maintenance costs. This, however, results in return higher speeds and peripheral speeds of the rotors and thus a higher load.

Eine Verschlechterung, d.h. eine Vergrößerung des Spalts zwischen dem Rotor und dem Verdichtergehäuse, beeinflusst mit zunehmender Betriebszeit sowohl den wirkungsgrad als auch die Pumpgrenze des verdichters. Allerdings muss der verdichter für alle Betriebszeitpunkte ausgelegt sein und in allen Betriebsbereichen einen ausreichenden Wirkungsgrad ohne Beschädigung von einzelnen Komponenten erzeugen können.Deterioration, i. an increase in the gap between the rotor and the compressor housing, affects both the efficiency and the surge limit of the compressor with increasing operating time. However, the compressor must be designed for all operating times and be able to produce sufficient efficiency in all operating ranges without damaging individual components.

Dies ist insbesondere problematisch, da aufgrund von Fliehkraft und thermischer Ausdehnung des Rotors sowie aufgrund von Montagetoleranzen und Exzentritäten von Rotor und Gehäuse ein Anstreifen des Rotors an dem Stator nicht verhindert werden kann.This is particularly problematic because due to centrifugal force and thermal expansion of the rotor as well as due to mounting tolerances and eccentricities of the rotor and housing, a rubbing of the rotor on the stator can not be prevented.

Bei der Spalthaltung muss bei stationärer Volllast und hoher Teillast ein minimaler Spalt erzielbar sein. Weiterhin muss aber der Spalt während der Beschleunigung des kalten Triebwerks so klein sein, dass bei Volllast der Rotor gerade einläuft. In allen anderen Betriebspunkten, wie beispielsweise der erneuten Beschleunigung eines warmen Triebwerks, muss ein Einlaufen des Rotors vermieden werden.When maintaining the gap, a minimal gap must be achievable with stationary full load and high partial load. Furthermore, however, the gap during acceleration of the cold engine must be so small that at full load, the rotor just runs in. In all other operating points, such as the re-acceleration of a warm engine, a run-in of the rotor must be avoided.

Zur Verhinderung der Beschädigung der Schaufelspitzen, die anders als bei der Turbine nicht durch ein Deckband geschützt sind, werden in der Regel die Schaufelspitzen mit einem harten abrasivem Belag versehen. Alternativ oder zusätzlich kann zur Verhinderung des Schaufelspitzenverschleißes bei Einstellung minimaler Radialspalte das Gehäuse mit sogenannten Einlaufbelägen beschichtet werden. Einlaufbeläge weisen insbesondere den Vorteil auf, dass diese bei einem Materialabtrag aufgrund des Kontakts mit den schaufelspitzen nicht zu einer Spaltvergrößerung über den gesamten Umfang und somit nur zu einem geringeren Leistungsverlust des Triebwerks führen.To prevent the damage of the blade tips, which are not protected by a shroud, unlike the turbine, the blade tips are usually provided with a hard abrasive coating. Alternatively or additionally, in order to prevent the blade tip wear when setting minimum radial gaps, the housing can be coated with so-called inlet linings. Inlet linings have the particular advantage that these result in a material removal due to the contact with the blade tips not to a gap enlargement over the entire circumference and thus only to a lower power loss of the engine.

Weiterhin ist bekannt, dass es in Verdichtern zu einem sogenannten Pumpen kommen kann, wenn die Luftströmung durch den Verdichter gestört wird und es zu einem vollständigen Abreißen der Förderung im gesamten Verdichter kommt. Ein Verdichter muss daher so ausgelegt sein, dass ein guter Sicherheitsabstand zwischen der sogenannten Pumpgrenze, das heißt dem Zustand, bei dem es bei den herrschenden Luftdurchsatz- und Druckverhältniswerten zu Pumpschwingungen kommt, und der Arbeirslinie, das heißt den Luftdurchsatz- und Druckverhältniswerten, bei denen der Verdichter normalerweise betrieben wird, gegeben ist. Es ist daher notwendig, den Durchsatz so zu steuern, dass das Triebwerk über einen weiten Drehzahlbereich effizient, insbesondere mit geringem wirkungsgradverlust, betrieben werden kann und der Abstand zur Pumpgrenze aufrechterhalten werden kann. Um dieses Ziel zu erreichen, kann ein sogenanntes "Casing Treatment" eingesetzt werden. Hierbei wird das Verdichtergehäuse mit Schlitzen versehen, die in der Regel in Bezug auf die Drehachse des Rotors schräg verlaufen und im Bereich von mindestens einem Schaufelkranz an der Innenseite des Gehäuses vorgesehen sind. Die Verteilung der Schlitze und deren Geometrie haben einen Einfluss auf den Pumpgrenzenabstand und den Wirkungsgrad des Verdichters. Da in dem Bereich des Verdichtergehäuses, in dem diese Schlitze vorgesehen sind, das heißt im Bereich des Rotors, auch der erwähnte Einlaufbelag vorgesehen sein sollte, ist die Verteilung und Geometrie dieser Schlitze zusätzlich durch die Beschaffenheit des Einlaufbelags bestimmt.Furthermore, it is known that in compressors, a so-called pumping can occur if the air flow through the compressor is disturbed and the production of the entire compressor is completely torn off. A compressor must therefore be designed so that there is a good safety margin between the so-called surge limit, that is to say the state in which pumping oscillates at the prevailing air flow and pressure ratio values, and the operating line, ie the air flow and pressure ratio values the compressor is normally operated, is given. It is therefore necessary to control the flow rate so that the engine can be operated efficiently over a wide speed range, particularly with low efficiency loss, and maintain the distance to the surge line. To achieve this goal, a so-called "Casing Treatment" can be used. In this case, the compressor housing is provided with slots, which are inclined in the rule with respect to the axis of rotation of the rotor and are provided in the region of at least one blade ring on the inside of the housing. The distribution of the slots and their geometry have an influence on the surge margin and the efficiency of the compressor. Since in the region of the compressor housing in which these slots are provided, that is to say in the region of the rotor, also the aforementioned inlet lining should be provided, the distribution and geometry of these slots is additionally determined by the nature of the inlet lining.

Aus dem Dokument EP-A-1 375 696 ist ein Schichtsystem für die Rotor-/Statordichtung mit einem zweischichtigen Einlaufbelag bekannt, dessen erste Schicht relativ zu einer zweiten, einlauffähigen Schicht härter ist. Bei guter Einlauffähigkeit werden dadurch die Erosionsbeständigkeit und die Thermowechselbeständigkeit erhöht, somit letztlich die Lebensdauer des Systems.From the document EP-A-1 375 696 a layer system for the rotor / stator seal with a two-layer inlet lining is known, the first layer is harder relative to a second, einlauffähigen layer. With good drainability, this increases the erosion resistance and the thermal shock resistance, thus ultimately the life of the system.

Das Dokument US-A-4 405 284 schützt einen wärmeisolierenden Einlaufbelag für ein verdichtergehäuse. Der Einlaufbelag ist über eine Haftschicht auf die Innenseite des Gehäuses aufgebracht und kann eine Honigwabenstruktur aufweisen, welche ganz oder teilweise mit einlauffähigem Material gefüllt ist.The document U.S.-A-4,405,284 protects a heat-insulating inlet lining for a compressor housing. The inlet lining is applied via an adhesive layer on the inside of the housing and may have a honeycomb structure, which is completely or partially filled with einlauffähigem material.

Das Dokument EP-A-0 965 730 betrifft einen keramischen Einlaufbelag mit einer relativ dichten, erosionsbeständigen Schicht und mit einer einlauffähigen Schicht. Die erosionsbeständige Schicht ist mit konstanter Dicke auf ein mit einer Vertiefung versehenes Substrat aufgebracht.The document EP-A-0 965 730 relates to a ceramic inlet lining with a relatively dense, erosion-resistant layer and with an enterable layer. The erosion-resistant layer is applied with constant thickness to a recessed substrate.

Das Dokument EP-A-1 253 294 betrifft einen vergleichbaren keramischen Einlaufbelag mit zwei unterschiedlichen Schichten, wobei die an das Substrat angrenzende Schicht über substratfeste, kugel- bzw. pilzförmige Erhebungen auch formschlüssig gehalten wird.The document EP-A-1 253 294 relates to a comparable ceramic inlet lining with two different layers, wherein the layer adjacent to the substrate is also held positively on substrate-solid, spherical or mushroom-shaped elevations.

Das Dokument US-B1-6 203 021 schützt einen Einlaufbelag mit einem lasergefertigten, regelmäßigen Muster zur Verbesserung der Einlauffähigkeit. Das Muster kann Löcher, Nuten, Stege u. ä. umfassen.The document US-B1-6,203,021 protects an enema surface with a laser-made regular pattern to improve enmeshment. The pattern may holes, grooves, webs u. Ä. Include.

Das Dokument EP-A-0 192 162 offenbart einen Einlaufbelag mit Anbindung einer keramischen Schicht an ein metallisches Substrat über gleichmäßig verteilte, metallische verankerungselemente in der Form von Drähten, Gittern, Spiralen, Honigwaben, Fasern u. ä.The document EP-A-0 192 162 discloses an enema coating having a ceramic layer bonded to a metallic substrate via evenly distributed metallic anchoring elements in the form of wires, meshes, spirals, honeycombs, fibers, and the like. ä.

Aufgabe der vorliegenden Erfindung ist es, einen auf die Innenseite eines Verdichtergehäuses aufgebrachten Einlaufbelag zu schaffen, der eine flexible Gestaltung des Verdichtergehäuses, insbesondere ein gezieltes Casing Treatment erlaubt, und der zumindest zwei Schichten aufweist, wobei eine erste Schicht formstabiler und mindestens eine weitere Schicht einlauffähiger ist.Object of the present invention is to provide an applied to the inside of a compressor housing inlet lining, which allows a flexible design of the compressor housing, in particular a targeted casing treatment, and having at least two layers, a first layer dimensionally stable and at least one further layer einlauffähiger is.

Diese Aufgabe wird erfindungsgemäß dadurch gelöst, dass die erste Schicht ein Profil mit Stegen und Vertiefungen aufweist, dass die mindestens eine, weitere Schicht die erste Schicht so ummantelt, dass im Bereich jeder Vertiefung eine Nut vorhanden ist, und dass der Einlaufbelag über die mindestens eine, weitere Schicht mit dem Verdichtergehäuse verbunden ist.This object is achieved according to the invention in that the first layer has a profile with webs and recesses such that the at least one, further layer surrounds the first layer in such a way that there is a groove in the region of each depression, and that the inlet lining over the at least one , Another layer is connected to the compressor housing.

Als Einlaufbelag wird hierbei die Beschichtung, insbesondere eine Dichtung, bezeichnet, die auf die Innenseite des Verdichtergehäuses aufgebracht wird. Dieser Einlaufbelag kann auf den Bereich der einzelnen Rotoren begrenzt sein, kann sich aber auch in axialer Richtung über diesen Bereich hinaus erstrecken, insbesondere das gesamte Verdichtergehäuse bedecken beziehungsweise auskleiden. Der Einlaufbelag umfasst nicht ausschließlich die oberste Schicht einer Beschichtung des Verdichtergehäuses, sondern sämtliche Schichten, die auf einen Grundwerkstoff des Verdichtergehäuses aufgebracht werden.In this case, the coating, in particular a seal, which is applied to the inside of the compressor housing is referred to as inlet lining. This inlet lining may be limited to the area of the individual rotors, but may also extend beyond this area in the axial direction, in particular covering or lining the entire compressor housing. The inlet lining does not exclusively comprise the uppermost layer of a coating of the compressor housing, but rather all layers which are applied to a base material of the compressor housing.

Durch die Kombination der mindestens zwei genannten Schichten, nämlich der einlauffähigeren und der formstabileren Schicht, wird eine flexible Ausgestaltung und Auslegung des Verdichtergehäuses ermöglicht. Insbesondere können durch die unterschiedlichen Schichten Eigenschaften unterschiedlicher Materialien sowie unterschiedliche Geometrien ideal kombiniert werden. Die erste, formstabilere Schicht besteht aus einem Material mit hoher Formstabilität. Hierzu können sowohl gewebte Materialien, Fasern oder Filze als auch poröse oder volle Materialien verwendet werden. Die erste Schicht kann beispielsweise aus Titanhohlkugeln hergestellt sein oder einen Ring aus einem Fasergeflecht darstellen. Mindestens eine weitere Schicht besteht aus einem einlauffähigen Material. Diese weitere Schicht stellt vorzugsweise die zweite Schicht dar, die an die erste Schicht angrenzt. Durch Vorsehen eines einlauffähigen Materials wird dem Einlaufbelag die Eigenschaft verliehen, die notwendig ist, um eine Spalthaltung zwischen dem Rotor und dem Stator in unterschiedlichen Betriebszuständen gewährleisten zu können. Gleichzeitig kann durch das Vorsehen des einlauffähigen Materials eine Beschädigung des formstabilen Materials der ersten Schicht und der Rotoren, insbesondere der Verdichterschaufel, vermieden werden. Hierbei können bekannte einlauf fähige Materialien verwendet werden. Auch Materialien mit Füllstoffen, wie beispielsweise Hohlkugeln, können eingesetzt werden.The combination of the at least two layers mentioned, namely the einlauffähigeren and the dimensionally stable layer, a flexible design and design of the compressor housing is made possible. In particular, properties of different materials as well as different geometries can be ideally combined by the different layers. The first, more dimensionally stable layer consists of a material with high dimensional stability. For this purpose, both woven materials, fibers or felts as well as porous or full materials can be used. The first layer may for example be made of hollow titanium balls or constitute a ring of a fiber braid. At least one further layer consists of a shrinkable material. This further layer is preferably the second layer adjacent to the first layer. By providing a shrinkable material, the inlet lining is given the property necessary to ensure a gap between the rotor and the stator in different operating conditions. At the same time, the provision of the einlauffähigen material damage to the dimensionally stable material of the first layer and the rotors, in particular the compressor blade can be avoided. Here, known enema capable materials can be used. Also materials with fillers, such as hollow spheres, can be used.

Erfindungsgemäß ist zumindest die erste der Schichten des Einlaufbelags in definierter Weise profiliert. Durch eine Profilierung können sowohl eine strömungstechnisch vorteilhafte Geometrie erzeugt werden, als auch die thermischen Eigenschaften des Einlaufbelags positiv beeinflusst werden.According to the invention, at least the first of the layers of the inlet lining is profiled in a defined manner. By profiling both a fluidically advantageous geometry can be generated, and the thermal properties of the inlet lining can be positively influenced.

Erfindungsgemäß ist mindestens eine weitere, einlauffähigere Schicht vorgesehen. Diese liegt unmittelbar an der ersten profilierten Schicht an. Diese zweite Schicht stellt somit eine Ummantelung des durch die erste Schicht gebildeten Profils dar. Die zweite Schicht ist auch auf der Seite der ersten Schicht vorgesehen, an der diese Erhöhungen und/oder Vertiefungen aufweist, das heißt an der der Verdichtergehause-Innenwand abgewandten Seite. Der Vorteil des Aufbringens einer gleichmäßigen Schicht liegt insbesondere in einer Vereinfachung der Herstellung des Einlaufbelags. Erfindungsgemäß ist es aber auch möglich, eine zweite Schicht mit unterschiedlichen Dicken auf die erste Schicht aufzubringen. So kann beispielsweise die zweite Schicht an den Positionen eine größere Dicke aufweisen, an denen in der ersten Schicht Erhebungen vorgesehen sind.
Durch die Wahl des Materials der ersten Schicht, wie beispielsweise Titanhohlkugeln oder einem anderen formstabilen Material, kann das durch die erste Schicht gebildete Profil auch unter mechanischer Belastung zuverlässig beibehalten werden.According to the invention, at least one further, more einlauffähigere layer is provided. This is directly adjacent to the first profiled layer. This second layer thus represents a sheathing of the profile formed by the first layer. The second layer is also provided on the side of the first layer, on which these elevations and / or depressions, that is on the side facing away from the compressor housing inner wall. The advantage of applying a uniform layer is in particular in a simplification of the production of the inlet lining. However, according to the invention it is also possible to apply a second layer with different thicknesses to the first layer. Thus, for example, the second layer may have a greater thickness at the positions at which elevations are provided in the first layer.
By choosing the material of the first layer, such as hollow titanium spheres or other dimensionally stable material, the profile formed by the first layer can be reliably maintained even under mechanical stress.

Nach der erfindungsgemäßen Ausführungsform, die insbesondere für das Casing Treatment geeignet ist, ist der Einlaufbelag so ausgestaltet, dass dieser an einer Seite zumindest teilweise Nuten aufweist, wobei diese durch Vertiefungen in der ersten Schicht gebildet werden. Die Nuten können in der eingebauten Position schräg zu der Rotorachse liegen oder axial ausgerichtet sein.According to the embodiment of the invention, which is particularly suitable for the casing treatment, the inlet lining is designed such that it has at least partially grooves on one side, which are formed by depressions in the first layer. The grooves may be in the installed position obliquely to the rotor axis or axially aligned.

Durch diese Ausführung wird die Form des gesamten Einlaufbelags im Wesentlichen durch die Form beziehungsweise durch das Profil der ersten Schicht bestimmt. Da diese Schicht aus formstabilem Material hergestellt ist, kann die Beibehaltung der Form des Profils gewährleistet werden. Die Nuten können bei dem erfindungsgemäßen Einlaufbelag optimal zur Beeinflussung des Strömungsverhaltens und zur Einstellung unterschiedlicher Druckverhältnisse verwendet werden. Die Nuten sind somit als Mittel für ein Casing Treatment einsetzbar.By this embodiment, the shape of the entire inlet lining is determined essentially by the shape or by the profile of the first layer. Since this layer is made of dimensionally stable material, the retention of the shape of the profile can be ensured. The grooves can be used optimally for influencing the flow behavior and for setting different pressure conditions in the inlet lining according to the invention. The grooves can thus be used as a means for a casing treatment.

Die Geometrie der Nuten kann bei dem erfindungsgemäßen Einlaufbelag flexibel gestaltet werden. Erfindungsgemäß ist es möglich, die Nuten so auszugestalten, dass diese eine große Tiefe im Vergleich zu deren Breite aufweisen. Insbesondere können Verhältnisse von der Breite der Nuten zu deren Tiefe von maximal 0,5, vorzugsweise maximal 0,3, eingestellt werden.The geometry of the grooves can be made flexible in the inlet lining according to the invention. According to the invention, it is possible to design the grooves in such a way that they have a large depth in comparison to their width. In particular, ratios of the width of the grooves to the depth of at most 0.5, preferably at most 0.3, can be set.

Diese kleinen Verhältnisse von Profilbreite zu Profilhöhe können mit herkömmlichen Einlaufbelägen, die ausschließlich aus einlauffähigem Material bestehen, nicht realisiert werden, da die Formstabilität bei diesen Einlaufbelägen nicht gegeben ist. Die Vergrößerung der Profiltiefe beziehungsweise Nutentiefe bringt erfindungsgemäß Vorteile mit sich. Insbesondere kann eine Erhöhung des Pumpgrenzenabstands erzielt werden. Weiterhin ist für den Pumpgrenzenabstand auch das Verhältnis von Oberfläche zu Nut an der Oberfläche des Einlaufbelags maßgeblich. Durch eine Verringerung des Oberflächen-Nut Verhältnisses kann der Pumpgrenzenabstand verbessert werden. Das Vorsehen einer großen Anzahl von Nuten über den Umfang des Verdichtergehäuses kann bei dem erfindungsgemäßen Einlaufbelag realisiert werden.These small ratios of profile width to profile height can not be realized with conventional inlet linings, which consist exclusively of einlauffähigem material, since the dimensional stability of these inlet linings is not given. The enlargement of the tread depth or groove depth brings advantages according to the invention. In particular, an increase in the surge margin can be achieved. Furthermore, the ratio of surface to groove on the surface of the inlet lining is decisive for the surge margin. By reducing the surface-to-groove ratio, the surge margin can be improved. The provision of a large number of grooves over the circumference of the compressor housing can be realized in the inlet lining according to the invention.

Weiterhin kann ein geringes Verhältnis von Breite zu Tiefe der Nuten von Vorteil sein, um nach dem Abrieb eines gewissen Betrags des einlauffähigen Materials eine ausreichende Nutentiefe gewährleisten zu können. Das abgeriebene Material kann in den Nuten aufgenommen werden und dennoch eine ausreichende Nutentiefe sichergestellt werden.Furthermore, a low ratio of width to depth of the grooves may be advantageous in order to ensure a sufficient groove depth after the abrasion of a certain amount of the einlauffähigen material can. The abraded material can be absorbed in the grooves while still ensuring sufficient groove depth.

Erfindungsgemäß umgibt die zweite Schicht die erste Schicht vollständig. Dies bedeutet, dass die zweite Schicht sowohl auf der profilierten Seite der ersten Schicht als auch auf der glatten Seite der ersten Schicht vorgesehen ist. Somit dient die erste Schicht als Kern und wird von der zweiten Schicht ummantelt. Diese Ausführung weist insbesondere bezüglich des Herstellungsverfahrens Vorteile auf. Hierbei ist die Ummantelung durchgehend, d.h. bedeckt auch die Enden des Kerns.According to the invention, the second layer completely surrounds the first layer. This means that the second layer is provided both on the profiled side of the first layer and on the smooth side of the first layer. Thus, the first layer serves as a core and is encased by the second layer. This embodiment has advantages, in particular with regard to the production method. Here, the sheath is continuous, i. also covers the ends of the core.

Die erfindungsgemäßen Ausführungsformen, bei denen die erste formstabile Schicht des Einlaufbelags profiliert ist, werden im folgenden auch als makro-profilierte Einlaufbeläge bezeichnet. Diese können insbesondere in dem Niederdruckbereich eines Verdichters, insbesondere eines Verdichters eines Flugtriebwerk oder einer Gasturbine eingesetzt werden.The embodiments according to the invention in which the first dimensionally stable layer of the inlet lining is profiled are also referred to below as macro-profiled inlet linings. These can be used in particular in the low-pressure region of a compressor, in particular a compressor of an aircraft engine or a gas turbine.

Als Material für die einlauffähigere Schicht kann beispielsweise faseriges oder poröses Material verwendet werden.
Als Material für die erste, formstabilere Schicht kommt beispielsweise faseriges, poröses oder aber volles Material in Betracht.For example, fibrous or porous material may be used as the material for the more settable layer.
As a material for the first, more dimensionally stable layer is for example fibrous, porous or full material into consideration.

Gemäß einer Ausführungsform kann die die erste, formstabilere und/oder die mindestens eine weitere, einlauffähigere Schicht mit verstärkungsmitteln versehen, insbesondere durchsetzt sein. Diese können beispielsweise Kugeln darstellen. Für die einlauffähigere Schicht bieten sich hierbei Kugeln aus sprödem Material an, die beispielsweise in einer Schicht aus gerichteten Fasern aufgenommen sein können.According to one embodiment, the first, more dimensionally stable and / or the at least one further, more einlauffähigere layer provided with reinforcing means, in particular interspersed. These can represent balls, for example. For the einlauffähigere layer here are balls of brittle material, which may be included, for example, in a layer of oriented fibers.

Die Erfindung wird im Folgenden anhand der beiliegenden Zeichnung genauer beschrieben, wobei

Figur 1
eine perspektivische Schnittansicht eines Ausführungsbei- spiels des erfindungsgemäßen Einlaufbelags mit Makro-Profil zeigt.
The invention will be described in more detail below with reference to the accompanying drawings, wherein
FIG. 1
a perspective sectional view of an exemplary embodiment of the inlet lining according to the invention with macro-profile shows.

In der Figur 1 ist ein Einlaufbelag 10 dargestellt, der eine erste Schicht 12 und eine zweite Schicht 14 umfasst. Dieser Einlaufbelag 10 ist auf einem Grundwerkstoff 16 eines Verdichtergehäuses aufgebracht.In the FIG. 1 an inlay 10 is shown comprising a first layer 12 and a second layer 14. This inlet lining 10 is applied to a base material 16 of a compressor housing.

Die erste Schicht 12 weist in der dargestellten Ausführungsform ein Profil auf, bei dem über die Fläche der ersten Schicht 12 eine Anzahl von Stegen 18 vorgesehen ist, zwischen denen Vertiefungen 20 in der ersten Schicht 12 ausgebildet sind. Die Stege 18 können auf die Schicht 12 aufgebracht sein oder die Vertiefungen 20 in die Schicht 12 eingebracht werden. Vorzugsweise können die Vertiefungen 20 bzw. die Stege 18 bei der Herstellung der Schicht 12 durch nicht spanende verfahren, z.B. Gießen oder Pressen, erzeugt werden.In the illustrated embodiment, the first layer 12 has a profile in which a number of webs 18 are provided over the surface of the first layer 12, between which depressions 20 are formed in the first layer 12. The webs 18 may be applied to the layer 12 or the recesses 20 are introduced into the layer 12. Preferably, depressions 20 and webs 18, respectively, may be formed by non-cutting methods, e.g. Casting or pressing, are generated.

In der dargestellten Ausführungsform umgibt das Profil der ersten Schicht 12 eine zweite Schicht 14, die weitgehend eine einheitliche Schichtdicke aufweist. Durch die Schicht 14 wird somit das Profil der ersten Schicht 12, die den Kern des Einlaufbelags 10 bildet, und insbesondere deren Stege 18 ummantelt. Die den Stegen 18 abgewandte glatte Seite 22 der ersten Schicht 12 wird ebenfalls von der zweiten Schicht 14 abgedeckt. In diesem Bereich der zweiten Schicht 14 ist der Einlaufbelag 10 über eine Fügezone 24 mit dem Grundwerkstoff 16 verbunden. Die Fixierung des Einlaufbelags 10 an dem Grundwerkstoff 16 kann durch herkömmliche Verfahren, wie beispielsweise Schweißen oder Kleben, erfolgen.In the illustrated embodiment, the profile of the first layer 12 surrounds a second layer 14 that has substantially a uniform layer thickness. By the layer 14 thus the profile of the first layer 12, which forms the core of the inlet lining 10, and in particular whose webs 18 are sheathed. The webs 18 facing away from the smooth side 22 of the first layer 12 is also covered by the second layer 14. In this region of the second layer 14, the inlet lining 10 is connected to the base material 16 via a joining zone 24. The fixation of the inlet lining 10 on the base material 16 can be done by conventional methods, such as welding or gluing.

Wie sich aus der Figur 1 entnehmen lässt, ist die Tiefe der Nuten 26, die durch die Vertiefungen 20 und die Ummantelung durch die Schicht 14 gebildet sind, im Verhältnis zu der Breite der Nuten 26 groß. Diese Form kann bei dem erfindungsgemäßen Einlaufbelag 10 aufgrund des formstabilen Kerns realisiert werden.As is clear from the FIG. 1 can be seen, the depth of the grooves 26, which are formed by the recesses 20 and the sheath through the layer 14, in relation to the width of the grooves 26 is large. This shape can be realized in the inlet lining 10 according to the invention due to the dimensionally stable core.

In der Figur 1 ist nur ein Teil des Einlaufbelags 10 dargestellt. Dieser kann erfindungsgemäß einen Ring darstellen, der in das verdichtergehäuse eingebracht werden kann.In the FIG. 1 only a part of the inlet lining 10 is shown. This can represent a ring according to the invention, which can be introduced into the compressor housing.

Claims (6)

  1. A run-in coating (10) for a compressor housing that is applied to the inside of the compressor housing and has at least two layers (12, 14), wherein a first layer (12) is more dimensionally stable than at least one further layer (14), and the at least one further layer (14) has greater run-in capability than the first layer (12), characterised in that the first layer (12) has a profile with a number of webs (18) and with depressions (20) between the webs (18), in that the at least one further layer (14) encases the first, profiled layer (12) in such a way that in the region of each depression (20) there is a groove (26), and in that the run-in coating (10) is connected to the base material (16) of the compressor housing in a joining zone (24) by way of the at least one further layer (14).
  2. A run-in coating according to claim 1, characterised in that the at least one further layer (14) has a uniform thickness at least over the greater part of its surface.
  3. A run-in coating according to claim 1 or 2, characterised in that the ratio of the width of the grooves (26) to their depth amounts to at most 0.5 and preferably to at most 0.3.
  4. A run-in coating according to one of claims 1 to 3, characterised in that the at least one further layer (14) consists of a fibrous or porous material.
  5. A run-in coating according to one of claims 1 to 4, characterised in that the first, profiled layer (12) consists of a fibrous, a porous or a solid material.
  6. A run-in coating according to one of claims 1 to 5, characterised in that the first, profiled layer (12) and/or the at least one further layer (14) are/is provided with reinforcing means.
EP05749930A 2004-06-29 2005-04-29 Run-in coating Expired - Fee Related EP1766193B1 (en)

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DE200410031255 DE102004031255B4 (en) 2004-06-29 2004-06-29 inlet lining
PCT/DE2005/000789 WO2006000174A1 (en) 2004-06-29 2005-04-29 Running-in coating

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DE502005010910D1 (en) 2011-03-10
DE102004031255A1 (en) 2006-01-19
WO2006000174A1 (en) 2006-01-05
US20090214824A1 (en) 2009-08-27
US8895134B2 (en) 2014-11-25
DE102004031255B4 (en) 2014-02-13

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