EP1766193A1 - Revetement de retrecissement - Google Patents

Revetement de retrecissement

Info

Publication number
EP1766193A1
EP1766193A1 EP05749930A EP05749930A EP1766193A1 EP 1766193 A1 EP1766193 A1 EP 1766193A1 EP 05749930 A EP05749930 A EP 05749930A EP 05749930 A EP05749930 A EP 05749930A EP 1766193 A1 EP1766193 A1 EP 1766193A1
Authority
EP
European Patent Office
Prior art keywords
layer
inlet lining
dimensionally stable
einlauffähige
inlet
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.)
Granted
Application number
EP05749930A
Other languages
German (de)
English (en)
Other versions
EP1766193B1 (fr
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
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by MTU Aero Engines GmbH filed Critical MTU Aero Engines GmbH
Publication of EP1766193A1 publication Critical patent/EP1766193A1/fr
Application granted granted Critical
Publication of EP1766193B1 publication Critical patent/EP1766193B1/fr
Ceased legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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 Oberbe ⁇ handle of claim 1.
  • Deterioration i. an increase in the gap between the rotor and the compressor housing influences both the efficiency and the surge limit of the compressor as the operating time increases.
  • the compressor must be designed for all operating times and be able to generate sufficient efficiency without damaging individual components in all operating ranges.
  • the blade tips are usually provided with a hard abrasive coating.
  • the housing may be coated with so-called inlet blades. Inlet linings have the particular advantage that, in the event of material removal due to contact with the blade tips, these do not lead to a gap enlargement over the entire circumference and thus only to a lower power loss of the engine.
  • a compressor must therefore be designed so that a good butter ⁇ distance between the so-called surge limit, that is, the state where it comes at the prevailing Vietnamese Gutier- and pressure ratio values pumping vibrations, and the working line, that is the Vietnamese Gut ⁇ set and Pressure ratio values at which 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 a low efficiency loss, and the distance to the surge line can be maintained.
  • a so-called "Casing Treatment" can be used.
  • the compressor housing is provided with slots which are generally inclined in relation 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 object of the present invention is to create an inlet lining which allows a flexible design of the compressor housing, in particular a targeted casing treatment.
  • This object is achieved according to the invention by an inlet lining for a compressor housing, which has at least two layers, wherein a first layer is dimensionally stable and at least one further layer is capable of running.
  • the coating in particular a gasket, is referred to as an abradable coating, which is preferably applied to the inside of the compressor housing.
  • This inlet lining may be limited to the area of the individual rotors, but may also be in the axial direction extend beyond this area, in particular covering or lining the entire compressor housing. According to the invention, 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 first dimensionally stable layer is preferably made of a material with high dimensional stability.
  • 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 an ein ⁇ executable material.
  • This further layer preferably represents the second layer, which adjoins the first layer.
  • At least one of the layers of the inlet lining can be profiled.
  • profiling both a fluidically advantageous geometry can be generated and the thermal properties of the inlet lining can be positively influenced.
  • the first dimensionally stable layer is profiled.
  • a profile of the entire inlet lining can be predetermined.
  • the first layer preferably has a smooth side, wherein a side is referred to as smooth, in which neither Wells still surveys are provided. This smooth side faces the inside of the compressor housing and may be indirectly or indirectly attached thereto.
  • At least one further enterable layer is provided which has a uniform thickness.
  • This is preferably applied directly to the first profiled layer.
  • This second layer thus represents a sheathing of the profile formed by the first layer.
  • the second layer is provided on the side of the first layer, on which these elevations and / or recesses, that is on the side facing away from the compressor housing inner wall.
  • the advantage of applying a uniform layer lies 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.
  • At the positions of the recesses of the profile of the first layer may optionally be completely dispensed with a second layer. In this case, the second layer is not continuous.
  • the profile formed by the first layer can be zu ⁇ reliably maintained even under mechanical stress.
  • the inlet lining according to the invention is so madest ⁇ taltet that it has on one side at least partially grooves, 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 essentially determined by the shape or by the profile of the first layer.
  • 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 in the inlet lining according to the invention for influencing the flow behavior and for setting different pressure conditions.
  • the grooves can thus be used as a means of 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 such 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 abrasion of a certain amount of the einlauffähi ⁇ gene material can.
  • the abraded material can be taken up in the grooves and nevertheless a sufficient groove depth can be ensured.
  • 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 preferably continuous, i. also covers the ends of the core.
  • the embodiments in which the first dimensionally stable layer of the inlet lining is profiled are also referred to below as macro-profiled inlet coverings. These can be used especially in the low-pressure Compressor of a compressor, in particular a compressor of a Flug ⁇ engine or a gas turbine can be used.
  • the inlet linings according to the invention can have, according to a further embodiment, a structure in which the at least one further infillable layer is profiled.
  • the first dimensionally stable layer may have a uniform thickness, i. have no profiling.
  • the at least one further infusible layer may have microprofiling on at least the side facing away from the first layer.
  • This is the side of the inlet lining to which the inlet lining is exposed to mechanical and thermal stresses.
  • the microprofiling can be produced, for example, by a film having an uneven, in particular brittle or flaky surface, for example a flaky surface.
  • the flakes are preferably aligned, the orientation being optimized according to flow engineering aspects.
  • the film is preferably applied to another infillable layer, which consists of einlaufmillem material.
  • An inlet lining with a micro-profiling can be used at higher temperatures compared to a macro-profiled inlet lining.
  • the micro-profiled inlet lining offers, for example, for the high-pressure compressor, while the inlet lining with macroprofiling can be used for the housing of the low-pressure compressor.
  • the shrinkable layer which may be coated with an insertable film, may consist of a fibrous material with oriented fibers, wherein the orientation of the fibers is preferably also selected to be flow-optimized.
  • the einlaufmede layer may consist of a shrinkable material or be coated with an enterable material.
  • fibrous or porous material may be used as the material for the shrinkable layer.
  • a material for the first dimensionally stable layer according to the invention for example, fibrous, porous or full material into consideration.
  • the first dimensionally stable and / or the at least one further einlaufsome layer provided with reinforcing means in particular be penetrated. These can represent, for example, kisses.
  • spheres of brittle material which can be accommodated, for example, in a layer of straightened fibers, are suitable for the shrinkable layer.
  • FIG. 1 shows a perspective sectional view of astrasbei ⁇ game of the inlet lining according to the invention with macro-profile shows
  • FIG. 2 shows a perspective sectional view of an embodiment of the micro-profile inlet lining according to the invention
  • FIG. 3 shows a further perspective sectional view of the exemplary embodiment of the inlet lining according to the invention with micro-profile according to FIG. 2.
  • FIG. 1 shows an inlet lining 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 can be applied to the layer 12 or the depressions 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 having a uniform layer thickness.
  • the layer 14 thus surrounds the profile of the first layer 12, which forms the core of the inlet lining 10, and in particular its webs 18 umman ⁇ .
  • the webs 18 facing away from the smooth side 22 of the first layer 12 is also covered by the second layer 14.
  • the second layer 14 of the inlet lining 10 is connected via a joining zone 24 with the base material 16.
  • the fixation of the inlet lining 10 on the base material 16 can be carried out by conventional methods, such as welding or gluing, for example.
  • the depth of the grooves 26, which are formed by the depressions 20 and the sheath through the layer 14, is large in relation to the width of the grooves 26.
  • This shape can be realized in the inlet lining 10 according to the invention due to the dimensionally stable core.
  • FIG. 2 shows a microprofiled inlet lining consisting of a first dimensionally stable layer 28, which has a constant thickness, and an insertable layer 30. On this main inlet layer 30, a profile 32 is applied.
  • the profile 32 has a scaly structure, wherein the profile 32 is designed to optimize flow.
  • the dimensionally stable first layer 28 in this embodiment is a felt, i. a fiber layer with undirected fibers, formed and may be interspersed with balls 34.
  • FIG. 3 again shows the inlet lining of FIG. 2, but without the profile 32.
  • the structure of the main inlet layer 30 can be seen.
  • this consists of directed fibers with brittle balls 36 received in a distributed fashion.

Landscapes

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

Abstract

Revêtement de rétrécissement (10) pour un carter de compresseur, qui comporte au moins deux couches (12, 14, 28, 30, 32). Ledit revêtement est caractérisé en ce que la première couche (12, 28) possède une forme stable et en ce qu'au moins une autre couche (14, 30, 32) est capable de rétrécir un espace.
EP05749930A 2004-06-29 2005-04-29 Garniture de rodage Ceased EP1766193B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE200410031255 DE102004031255B4 (de) 2004-06-29 2004-06-29 Einlaufbelag
PCT/DE2005/000789 WO2006000174A1 (fr) 2004-06-29 2005-04-29 Revetement de retrecissement

Publications (2)

Publication Number Publication Date
EP1766193A1 true EP1766193A1 (fr) 2007-03-28
EP1766193B1 EP1766193B1 (fr) 2011-01-26

Family

ID=34969633

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05749930A Ceased EP1766193B1 (fr) 2004-06-29 2005-04-29 Garniture de rodage

Country Status (4)

Country Link
US (1) US8895134B2 (fr)
EP (1) EP1766193B1 (fr)
DE (2) DE102004031255B4 (fr)
WO (1) WO2006000174A1 (fr)

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DE102009034025A1 (de) * 2009-07-21 2011-01-27 Mtu Aero Engines Gmbh Einlaufbelag zur Anordnung an einem Gasturbinenbauteil
FR2991374B1 (fr) * 2012-06-04 2016-04-08 Snecma Paroi stator de turbomachine recouverte d'un revetement abradable
US9598969B2 (en) * 2012-07-20 2017-03-21 Kabushiki Kaisha Toshiba Turbine, manufacturing method thereof, and power generating system
US20140096509A1 (en) * 2012-10-05 2014-04-10 United Technologies Corporation Geared Turbofan Engine With Increased Bypass Ratio and Compressor Ratio ...
EP2951241A4 (fr) * 2013-01-29 2016-08-24 United Technologies Corp Matériau de frottement de lame
DE102013201761A1 (de) * 2013-02-04 2014-08-07 Bosch Mahle Turbo Systems Gmbh & Co. Kg Gehäusebauteil
US20170211404A1 (en) * 2016-01-25 2017-07-27 United Technologies Corporation Blade outer air seal having surface layer with pockets
US20180016678A1 (en) * 2016-07-15 2018-01-18 Applied Materials, Inc. Multi-layer coating with diffusion barrier layer and erosion resistant layer

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Also Published As

Publication number Publication date
US20090214824A1 (en) 2009-08-27
DE502005010910D1 (de) 2011-03-10
DE102004031255B4 (de) 2014-02-13
EP1766193B1 (fr) 2011-01-26
WO2006000174A1 (fr) 2006-01-05
US8895134B2 (en) 2014-11-25
DE102004031255A1 (de) 2006-01-19

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