EP2494210B1 - Maschine mit schleifbaren leisten und verfahren - Google Patents

Maschine mit schleifbaren leisten und verfahren Download PDF

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Publication number
EP2494210B1
EP2494210B1 EP10771600.3A EP10771600A EP2494210B1 EP 2494210 B1 EP2494210 B1 EP 2494210B1 EP 10771600 A EP10771600 A EP 10771600A EP 2494210 B1 EP2494210 B1 EP 2494210B1
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EP
European Patent Office
Prior art keywords
machine
ridges
abradable
rotating part
diaphragm
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Not-in-force
Application number
EP10771600.3A
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English (en)
French (fr)
Other versions
EP2494210A1 (de
Inventor
Lacopo Giovannetti
Vittorio Michelassi
Massimo Giannozzi
Farshad Ghasripoor
Dennis M. Gray
Nuo Sheng
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Nuovo Pignone SpA
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Nuovo Pignone SpA
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Publication of EP2494210A1 publication Critical patent/EP2494210A1/de
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/02—Selection of particular materials
    • F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
    • 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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/08—Sealings
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F04D29/162—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of a centrifugal flow wheel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44—Fluid-guiding means, e.g. diffusers
    • F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
    • 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
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/181—Two-dimensional patterned ridged
    • 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
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/182—Two-dimensional patterned crenellated, notched
    • 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
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/183—Two-dimensional patterned zigzag
    • 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
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/184—Two-dimensional patterned sinusoidal
    • 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
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/17—Alloys
    • 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
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/17—Alloys
    • F05D2300/173—Aluminium alloys, e.g. AlCuMgPb
    • 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
    • F05D2300/40—Organic materials
    • F05D2300/43—Synthetic polymers, e.g. plastics; Rubber
    • 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
    • F05D2300/40—Organic materials
    • F05D2300/43—Synthetic polymers, e.g. plastics; Rubber
    • F05D2300/432—PTFE [PolyTetraFluorEthylene]
    • 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
    • F05D2300/40—Organic materials
    • F05D2300/43—Synthetic polymers, e.g. plastics; Rubber
    • F05D2300/434—Polyimides, e.g. AURUM

Definitions

  • Embodiments of the subject matter disclosed herein generally relate to methods and systems and, more particularly, to mechanisms and techniques for producing abradable ridges in a machine having a rotating part and a fixed part.
  • Rotating machines for example, gas turbines, used today in various technical fields (power systems, petrochemical plants, etc.) have at least a rotating part (rotor with blades) that rotates with respect to a fixed part (shroud).
  • a fluid is typically injected at an input of the rotating machine to be accelerated/pressurized and the fluid is then ejected at an outlet of the rotating machine.
  • a fluid flow is generated by the rotating blades.
  • a seal between the rotating part and the fixed part is desired to be achieved so that most of the fluid flow is engaged by the blades of the rotating part and does not leak over the tips of the blades, which is unwanted leakage.
  • One way to provide the seal between the rotating part and the fixed part of the rotating machine is to deposit an abradable material on the fixed part so that the tips of the blades together with the abradable material form a seal. If the abradable material includes a ceramic, then an abrasive material may be provided on tips of the blades of the rotating part to protect the tips when contacting the abradable material to form the seal. Such a method is described in U.S. Patent No. 6,457,939 . U.S. Pat. No.
  • 6,251,526 describes profiled abradable ceramic coating systems, in which a porous ceramic coating is deposited onto a substrate with a profiled surface, e.g., a metal grid brazed onto the substrate surface (casing of the gas turbine) to form an abradable profiled surface.
  • a profiled surface e.g., a metal grid brazed onto the substrate surface (casing of the gas turbine) to form an abradable profiled surface.
  • the blades of the rotor of the turbine may increase their size due to thermal expansion during the normal operation of the turbine and/or due to centrifugal effects produced by the high rotational speeds of the rotating part of the turbine during operation, the blades may move towards the casing and may remove part of the abradable material to achieve a smaller clearance.
  • U.S. Patent No. 6,887,528 and U.S. Patent Application Publication No. 2005/0003172 disclose a method for producing a profiled abradable coating on a casing of a gas turbine without providing a grid on the casing of the turbine.
  • the abradable material includes a porous ceramic material that is able to withstand temperatures as high as 1500 °C.
  • the abradable layer is formed on the casing by using direct-write technology or plasma sprayed onto the substrate through a mask or a plasma gun.
  • this method uses expensive materials for the plural ridges in order to withstand the high temperatures inside the gas turbines.
  • EP 1270876 A2 discloses an abradable seal for turbomachinery.
  • FIG. 1 traditional methods for improving a clearance between the tips of the blades and the fixed part of the turbine is to machine in the casing 10 of the turbine a grid 11 by removing part of the original material of the casing 10. Then, a thermal barrier coating (TBC) layer 12 (i.e., a high temperature resistant layer for protecting the casing from heat damage) is formed to not be in direct contact with a surface 14 of the casing 10. An abradable layer 16 is deposited on layer 12. A blade 18 of the rotating part faces the abradable layer 16 and may scrape this layer 16.
  • TBC thermal barrier coating
  • the abradable layer 16 and the TBC layer 12 may be shaped as a ridge 20 having a straight-line shape or ridge 22 having a zigzag shape.
  • these traditional methods for providing a high temperature resistant seal in the turbines may be disadvantageous if used in other machines that do not experience a high temperature because casing 10 may be damaged when machining the grid 11 and/or may be expensive as the ceramic abradable material requires exotic components, as for example, yttria-stabilized zirconia.
  • a machine that includes a fixed part having a portion with a smooth surface; a rotating part configured to rotate relative to the fixed part, the rotating part directly facing the portion of the fixed part; and plural ridges formed on the portion of the fixed part directly facing the rotating part, the plural ridges being made of an abradable material that is configured to be inoperable at temperatures above 1000 °C. At least one ridge of the plural ridges is curved.
  • a diaphragm of a compressor that includes a fixed part configured to accommodate at least an impeller of the compressor and having a portion with a smooth surface; and an abradable layer formed on the portion with the smooth surface of the fixed part.
  • the abradable layer is machined to form plural ridges directly facing the impeller, the plural ridges being made of an abradable material that is configured to be inoperable at temperatures above 1000 °C, and at least one ridge of the plural ridges is continuously curved.
  • the method includes identifying in the diaphragm a portion with a smooth surface that directly faces a rotating part of the machine; depositing an abradable layer on the portion directly facing the rotating part, the abradable layer including an abradable material that is configured to be inoperable at temperatures above 1000 °C; and machining plural ridges in the abradable layer such that at least one ridge of the plural ridges is curved.
  • FIG 3 illustrates an open impeller centrifugal compressor 30.
  • the open impeller centrifugal compressor 30 has an impeller 32 connected to a shaft 34. Shaft 34 may be supported by bearings 36 and 38.
  • the impeller 32 has a hub portion 40 and a blade portion 42.
  • a fluid enters the centrifugal compressor 30 at an inlet 44, along an incoming direction A. The fluid reaches the impeller 32, where it is accelerated based on the centrifugal force while changing the fluid direction prior to being discharged at outlet 46 along direction B.
  • a diaphragm 48 which faces the impeller 32, is part of the fixed part of the compressor 30. The diaphragm may be attached to a casing 49 of the compressor 30.
  • FIG. 4 A detailed view of the impeller 32 is shown in Figure 4 .
  • Other structures for the impeller 32 may be used.
  • the specific shape of impeller 32 shown in Figure 4 corresponds to an open impeller (no element is covering blade portion 42).
  • a centrifugal compressor having this impeller is called an open impeller centrifugal compressor.
  • the blade portion 42 may have multiple blades 50 having various contours, depending on the application/operation of the compressor. These multiple blades 50 rotate inside the diaphragm 48 such that tips 52 of the blades 50 may move closer or even touch the diaphragm 48 due to an elongation of the blades 50 because of thermal transients, and/or the high rotational speed of the blades 50 relative to the diaphragm 48, and/or critical vibrations.
  • an abrasive material may be coated on tips 52.
  • no such abrasive material is used in this exemplary embodiment.
  • tips 52 of the blades 50 are vulnerable to damage if they contact the strong material that the diaphragm 48 is made.
  • a continuous layer of abradable material is deposited on a portion of the diaphragm 48 that directly faces blades 50. This portion is shown in Figure 5 as element 60.
  • portion 60 may be smaller than shown in Figure 5 , i.e., may not extend the entire axial span of the blade portion 42.
  • portion 60 may be one third of the axial span of the blade portion 42.
  • the axial span of the blade portion 42 is between C and F.
  • the axial span of portion 60, which has the abradable material thereon, may be between C and F or smaller, with the smallest axial span being between E and F.
  • the diaphragm 48 and more specifically, a surface 62 (see Figure 5 ) of the diaphragm 48 that receives the abradable material is smooth, i.e., has no ridges, grids, or other formations intentionally formed in the metal of the diaphragm 48.
  • the surface 62 of the portion 60 of the diaphragm 48 if represented in a XY plane, with a longitudinal axis of the diaphragm 48 along axis X, has a same sign of a partial derivative of a Y position with respect to X along the longitudinal axis of the diaphragm 48 ignoring normal tolerances accepted in the industry for making such large pieces of equipment.
  • the temperature range Another difference between the traditional gas turbines and the novel embodiments is the temperature range. More specifically, the gas turbines are known to operate at high temperatures, e.g., higher than 1000 °C, while a compressor operates at lower temperatures, in the range of 100 to 400 °C, and around 200 °C for a centrifugal compressor diaphragm. This large difference in the operation temperature of a gas turbine and a compressor makes the ceramic based abradable coatings of the traditional turbines not suitable/unnecessary for compressors. Thus, other materials, as will be discussed later, are used for coating the diaphragm of the compressors.
  • the surface 62 of the diaphragm 48 may be directly covered with a smooth layer 70 of an abradable material.
  • the layer 70 of abradable material may be directly deposited on the surface 62 of the diaphragm 48, which is different from the gas turbine case in which the TBC layer is formed on the casing prior to depositing the abradable material.
  • the direct formation of the abradable material 70 on the surface 62 of diaphragm 48 is possible because of the lower temperature environment in which compressors operate.
  • Abradable materials to be used for compressors may be divided into metallic-based abradable materials and plastic-based abradable materials. These materials have a common property that they are not designed to withstand high temperatures, as those materials used in a gas turbine. In other words, the abradable materials to be used in the compressors may become inoperable (melt, peel, etc.) if used in the turbine of a gas turbine. In this regard, the abradable materials to be used, for example, in centrifugal compressors, are selected to operate at temperatures up to 200 °C. In another embodiment, depending on the type of compressor, the abradable materials may operate at temperatures up to 400 °C.
  • Metallic abradable materials may include one or more of AISi, AISi and Polyester, NiCrFeBNAI, etc.
  • Plastic abradable materials may include one or more of polytetrafluoroethylene (PTFE), Polyester, polyimide, etc.
  • the metallic and/or plastic abradable material may be formed directly on the surface of the diaphragm 48, without any protection layers (for example, TBC layers) as is customary in the gas turbines.
  • a known ceramic abradable material is not directly deposited on the substrate but rather on a thermally resistant coating (layer 12 in Figure 1 ), for protecting the substrate (the casing) from the high temperatures generated during the operation of the gas turbines.
  • thermally protective coatings may be deposited on the diaphragm 48 prior to depositing the abradable material 70.
  • the abradable material 70 may be machined to form ridges 72 having peaks 74 and valleys 76 as shown in Figure 7 .
  • the shape of the ridges 72 may be diamond shape, straight lines, constantly curved, continuously curved, etc.
  • a cross sectional view of ridges 72 is shown in Figure 8 .
  • a shape of ridge 72, as shown in the cross sectional view in Figure 8 may have a smooth shape as indicated by 80, or may have a triangular cross section as indicated by 82, or may have a rectangular cross section as indicated by 84, or other shapes.
  • the diaphragm 48 may be provided with a combination of one or more of the above discussed shapes 80, 82, and 84.
  • a dimension "d" of the ridges 72 may be between about 0.0025 and about 0.102 mm for the rectangular shape and between about 0 and about 0.102 mm for the triangular shape, and a height "h" of the ridges 72 may be between about 0.1 and about 0.5 mm.
  • blades 50 Once blades 50 are rotating with shaft 34 inside diaphragm 48, due to centrifugal effects and/or rotor unbalance and/or thermal transients, the blades may move radially or axially towards the diaphragm 48 to contact ridges 72. Depending on the degree of expansion of the blades 50, tips 52 of the blades 50 may touch and even break (remove) top parts of ridges 72 to form groove regions 90 as shown in Figure 9 . This close contact between ridges 72 and blades 50 may achieve the desired sealing between the rotating part and the fixed part of the compressor.
  • the close contact of the tips 52 of the blades 50 with ridges 72 which are abradable and also have a soft structure due to their small physical dimensions, prevents the tips 52 of the blades 50 to suffer damages, given the fact that tips 52 have no protective abrasive materials.
  • the material used to form the ridge may be dense.
  • the entire diaphragm 48 may be made of the abradable material so that the ridges 72 may be formed by machining the diaphragm 48 and not by depositing abradable material.
  • a bond coat layer 100 (for example, the bond coat can be NiAl or NiCrAlY) having a height h1 of around 0.125 mm optionally may be deposited on the diaphragm 48 by, for example, plasma spray process.
  • a layer 102 of DVC-TBC (Dense Vertically Cracked Thermal Barrier Coating) having a height h2 of about 1.00 mm may be deposited over layer 100.
  • the abradable layer 70 is formed over layer 102 or directly on layer 100 or directly on diaphragm 48 and may have a height h3 of about 1.3 mm. Deviations from these exemplary numbers in the range of 5% to 50% are also possible.
  • Figure 11 shows the variation of a total clearance reduction as a function of hot running rubbed clearance for various abradable ridge shapes having the same height.
  • the hot running rubbed clearance is the actual clearance between the impeller and the diaphragm when the impeller rotates and the total clearance is the effective clearance due to the shape of the ridges and other parameters.
  • Figure 11 illustrates the relative effect of (i) abradable ridges with a curved pattern (curve 124), (ii) abradable ridges with 45 degrees straight line pattern (curve 122), and (iii) a smooth abradable layer with no ridges and no pattern (curve 120).
  • the abradable ridges with curved pattern provide an advantage of approximately 0.46 mm (18 mils) clearance reduction over the plural ridges with the straight line pattern.
  • the curved pattern may provide approximately 1 mm (40 mils) clearance reduction over a compressor with no abradable layer versus approximately 0.68 mm (27 mils) clearance for the straight line pattern over the no abradable layer compressor.
  • Curve 122 corresponds to plural ridges having a straight pattern inclined at 45 degrees relative to the axial direction of the compressor (see for example Figure 2 , ridges 22) and curve 124 corresponds to plural ridges having curved patterns (see for example Figure 7 , ridges 72).
  • the curved patterns curve 124 provides a higher clearance reduction (approximately 40 mils or 1 mm) than the straight pattern curve 122 (clearance reduction approximately 27 mils or 0.68 mm) and the smooth abradable layer curve 120 (approximately 23 mils or 0.58 mm) for the same hot running rubbed clearance 126.
  • the total clearance reduction shown on the Y axis of Figure 11 indicates that for a same height of the ridges 72 of the three curves 120, 122, and 124, the amount of fluid leaked between the moving part and the fixed part of the compressor is smaller for ridges 72 of curve 124 than for ridges 72 of curve 122.
  • the shape of the ridges (straight versus curved) generate this effect of reduced clearance.
  • the method includes a step 130 of identifying in the diaphragm a portion with a smooth surface that directly faces a rotating part of the machine; a step 132 of depositing an abradable layer on the portion directly facing the rotating part, the abradable layer including an abradable material that is configured to be inoperable at temperatures above 1000 °C; and a step 134 of machining plural ridges in the abradable layer such that at least one ridge of the plural ridges is curved.
  • the disclosed exemplary embodiments provide a system and a method for depositing an abradable material on a fixed part of a machine having a moving part.
  • the exemplary embodiments are intended to cover alternatives, modifications and equivalents, which are included in the invention as defined by the appended claims.
  • numerous specific details are set forth in order to provide a comprehensive understanding of the claimed invention. However, one skilled in the art would understand that various embodiments may be practiced without such specific details.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Crushing And Grinding (AREA)
  • Electrical Discharge Machining, Electrochemical Machining, And Combined Machining (AREA)
  • Other Air-Conditioning Systems (AREA)

Claims (13)

  1. Maschine (30), wobei die Maschine ein Kreiselverdichter mit offenem Gehäuse ist, wobei die Maschine umfasst:
    einen fixen Teil (48), welcher einen Abschnitt (62) mit einer glatten Oberfläche aufweist;
    einen rotierenden Teil (32), welcher konfiguriert ist, relativ zu dem fixen Teil zu rotieren, wobei der rotierende Teil direkt dem Abschnitt des fixen Teils zugewandt ist; dadurch gekennzeichnet, dass
    mehrere Stege (72) auf dem direkt dem rotierenden Teil (32) zugewandten Abschnitt (62) des fixen Teils gebildet sind, wobei die mehreren Stege aus einem abschleifbaren Material (70) hergestellt sind, welches konfiguriert ist, bei Temperaturen über 1000 °C unbrauchbar zu sein,
    wobei zumindest ein Steg der mehreren Stege (72) gewölbt ist,
    wobei der rotierende Teil (32) weiter mehrere Klingen (50) umfasst, welche auf dem rotierenden Teil (32) angeordnet sind, die Spitzen (52) der mehreren Klingen (50) konfiguriert sind, einen oder mehrere der mehreren Stege (72) zu berühren, wenn der rotierende Teil (32) rotiert und die Spitzen (52) der mehreren Klingen (50) nicht behandelt sind, um schleifbares Material zu beinhalten.
  2. Maschine nach Anspruch 1, wobei der gesamte zumindest eine Steg (72) kontinuierlich gewölbt ist.
  3. Maschine nach Anspruch 1, wobei alle mehreren Stege (72) kontinuierlich gewölbt sind.
  4. Maschine nach Anspruch 1, wobei die mehreren Stege (72) konfiguriert sind, bei Temperaturen über 400 °C unbrauchbar zu sein.
  5. Maschine nach Anspruch 1, wobei das abschleifbare Material (70) kunststoff- oder metallbasiert ist.
  6. Maschine nach Anspruch 5, wobei das abschleifbare Kunststoffmaterial (70) eines oder mehrere aus Polytetrafluorethylen, Polyimid oder Polyester beinhaltet.
  7. Maschine nach Anspruch 5, wobei das abschleifbare Metallmaterial (70) eines oder mehrere aus AISi, AISi und Polyester oder NiCrFeBNAI beinhaltet.
  8. Maschine nach Anspruch 1, wobei das abschleifbare Material (70) einen Bereich des Abschnitts bedeckt, welcher ein Drittel oder weniger einer axialen Ausdehnung des rotierenden Teils (32) umspannt.
  9. Maschine nach Anspruch 1, weiter umfassend:
    eine Membran (48), welche konfiguriert ist, den rotierenden Teil (32) zu umschließen, wobei die gesamte Membran (48) aus dem abschleifbaren Material (70) hergestellt ist.
  10. Maschine nach Anspruch 1, wobei ein Querschnitt von Stegen (72) der mehreren Stege ein Rechteck (84) oder ein Dreieck (82) ist.
  11. Maschine nach Anspruch 10, wobei eine Höhe (h) der rechteckigen oder dreieckigen Stege zwischen 0,1 und ungefähr 0,5 mm beträgt.
  12. Maschine nach Anspruch 1, wobei eine Betriebstemperatur des Kreiselverdichters weniger als 200 °C beträgt.
  13. Verfahren zum Aufbringen eines abschleifbaren Materials auf einem fixen Teil der Maschine nach einem der Ansprüche 1 bis 12, in welchem der fixe Teil eine Membran (48) ist, wobei das Verfahren umfasst:
    Identifizieren eines Abschnitts (62) mit einer glatten Oberfläche, welche einem rotierenden Teil (32) der Maschine direkt zugewandt ist, in der Membran (48);
    Aufbringen einer abschleifbaren Schicht (70) auf dem Abschnitt (62), welcher dem rotierenden Teil direkt zugewandt ist, wobei die abschleifbare Schicht (70) ein abschleifbares Material beinhaltet, welches konfiguriert ist, bei Temperaturen über 1000 °C unbrauchbar zu sein; und
    maschinelles Herstellen mehrerer Stege (72) in der abschleifbaren Schicht (70), sodass zumindest ein Steg der mehreren Stege (72) gewölbt ist.
EP10771600.3A 2009-10-30 2010-10-12 Maschine mit schleifbaren leisten und verfahren Not-in-force EP2494210B1 (de)

Applications Claiming Priority (2)

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ITCO2009A000045A IT1396362B1 (it) 2009-10-30 2009-10-30 Macchina con righe in rilievo che possono essere abrase e metodo.
PCT/US2010/052232 WO2011053448A1 (en) 2009-10-30 2010-10-12 Machine with abradable ridges and method

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EP2494210B1 true EP2494210B1 (de) 2018-09-26

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KR20120095407A (ko) 2012-08-28
BR112012009977A2 (pt) 2016-03-01
ITCO20090045A1 (it) 2011-04-30
MX2012005085A (es) 2012-10-01
CN102753833B (zh) 2016-02-10
WO2011053448A1 (en) 2011-05-05
CN102753833A (zh) 2012-10-24
RU2556092C2 (ru) 2015-07-10
JP5728017B2 (ja) 2015-06-03
WO2011053448A8 (en) 2012-06-14
CA2779380A1 (en) 2011-05-05
IT1396362B1 (it) 2012-11-19
EP2494210A1 (de) 2012-09-05
RU2012119299A (ru) 2013-12-10
US20130004305A1 (en) 2013-01-03
JP2013509533A (ja) 2013-03-14

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