US20130004305A1 - Machine with Abradable Ridges and Method - Google Patents

Machine with Abradable Ridges and Method Download PDF

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Publication number
US20130004305A1
US20130004305A1 US13/505,086 US201013505086A US2013004305A1 US 20130004305 A1 US20130004305 A1 US 20130004305A1 US 201013505086 A US201013505086 A US 201013505086A US 2013004305 A1 US2013004305 A1 US 2013004305A1
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United States
Prior art keywords
machine
abradable
abradable material
ridges
diaphragm
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Abandoned
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US13/505,086
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English (en)
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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Assigned to NUOVO PIGNONE S.P.A. reassignment NUOVO PIGNONE S.P.A. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: MICHELASSI, VITTORIO, GHASRIPOOR, FARSHAD, SHENG, NUO, GIANNOZZI, MASSIMO, GRAY, DENNIS M., GIOVANNETTI, IACOPO
Publication of US20130004305A1 publication Critical patent/US20130004305A1/en
Abandoned legal-status Critical Current

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    • 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.
  • the abradable material includes a ceramic
  • 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.
  • U.S. Pat. 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.
  • 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 . As shown in FIG.
  • 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 about 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 about 1000° C., and at least one ridge of the plural ridges is continuously curved.
  • a method of depositing an abradable material on a diaphragm of a machine 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 about 1000° C.; and machining plural ridges in the abradable layer such that at least one ridge of the plural ridges is curved.
  • FIG. 1 is a schematic diagram of a portion of a conventional gas turbine with an abradable material deposited on a grid formed in the casing of the gas turbine;
  • FIG. 2 is a schematic diagram of a conventional pattern of the abradable material of FIG. 1 ;
  • FIG. 3 is a schematic diagram of a compressor
  • FIG. 4 is a schematic diagram of an impeller of the compressor of FIG. 3 ;
  • FIG. 5 is a schematic diagram of a portion of a diaphragm of a compressor according to an exemplary embodiment of the present invention
  • FIG. 6 is a schematic diagram of an abradable material deposited on a diaphragm of a compressor according to an exemplary embodiment of the present invention
  • FIG. 7 is a schematic diagram of a pattern of plural ridges formed in an abradable material according to an exemplary embodiment of the present invention.
  • FIG. 8 is a schematic diagram of various ridge shapes that can be formed according to an exemplary embodiment of the present invention.
  • FIG. 9 is a schematic diagram of an interaction between ridges and an impeller of a compressor according to an exemplary embodiment of the present invention.
  • FIG. 10 is a schematic diagram of various layers that may be formed on a diaphragm of a compressor according to an exemplary embodiment of the present invention.
  • FIG. 11 is a graph showing advantages of curved patterns for the ridges formed on a diaphragm according to an exemplary embodiment of the present invention.
  • FIG. 12 is a flow chart illustrating steps for forming the plural ridges on the diaphragm of a machine according to an exemplary embodiment of the present invention.
  • 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 FIG. 4 .
  • Other structures for the impeller 32 may be used.
  • the specific shape of impeller 32 shown in FIG. 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 FIG. 5 as element 60 .
  • portion 60 may be smaller than shown in FIG.
  • 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 FIG. 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. Further, even if small unevennesses are present in the surface 62 of portion 60 , if these are not intentionally made, it is considered that the surface 62 is smooth. This is different from some gas turbine shrouds that have ridges or grids 11 intentionally formed in the casing 10 of the gas turbine prior to depositing the abradable material 16 , as shown in FIG. 1 .
  • 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 about 1000° C., while a compressor operates at lower temperatures, in the range from about 100 to about 400° C., and about 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 about 200° C. In another embodiment, depending on the type of compressor, the abradable materials may operate at temperatures up to about 400° C.
  • Metallic abradable materials may include one or more of AlSi, AlSi and Polyester, NiCrFeBNAl, 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 FIG. 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 FIG. 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 FIG. 8 .
  • a shape of ridge 72 as shown in the cross sectional view in FIG. 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 FIG. 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 h 1 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 h 2 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 h 3 of about 1.3 mm. Deviations from these exemplary numbers in the range of 5% to 50% are also possible.
  • FIG. 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.
  • FIG. 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 18 mils clearance reduction over the plural ridges with the straight line pattern.
  • the curved pattern may provide approximately 40 mils clearance reduction over a compressor with no abradable layer versus approximately 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 FIG. 2 , ridges 22 ) and curve 124 corresponds to plural ridges having curved patterns (see for example FIG. 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 FIG. 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 about 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 spirit and scope of 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)
US13/505,086 2009-10-30 2010-10-12 Machine with Abradable Ridges and Method Abandoned US20130004305A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
ITCO2009A000045A IT1396362B1 (it) 2009-10-30 2009-10-30 Macchina con righe in rilievo che possono essere abrase e metodo.
ITCO2009A000045 2009-10-30
PCT/US2010/052232 WO2011053448A1 (fr) 2009-10-30 2010-10-12 Machine comportant des crêtes susceptibles d'érosion et procédé associé

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US20130004305A1 true US20130004305A1 (en) 2013-01-03

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US (1) US20130004305A1 (fr)
EP (1) EP2494210B1 (fr)
JP (1) JP5728017B2 (fr)
KR (1) KR20120095407A (fr)
CN (1) CN102753833B (fr)
BR (1) BR112012009977A2 (fr)
CA (1) CA2779380A1 (fr)
IT (1) IT1396362B1 (fr)
MX (1) MX2012005085A (fr)
RU (1) RU2556092C2 (fr)
WO (1) WO2011053448A1 (fr)

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8939716B1 (en) 2014-02-25 2015-01-27 Siemens Aktiengesellschaft Turbine abradable layer with nested loop groove pattern
US8939706B1 (en) 2014-02-25 2015-01-27 Siemens Energy, Inc. Turbine abradable layer with progressive wear zone having a frangible or pixelated nib surface
US8939705B1 (en) 2014-02-25 2015-01-27 Siemens Energy, Inc. Turbine abradable layer with progressive wear zone multi depth grooves
US8939707B1 (en) 2014-02-25 2015-01-27 Siemens Energy, Inc. Turbine abradable layer with progressive wear zone terraced ridges
US9151175B2 (en) 2014-02-25 2015-10-06 Siemens Aktiengesellschaft Turbine abradable layer with progressive wear zone multi level ridge arrays
US9243511B2 (en) 2014-02-25 2016-01-26 Siemens Aktiengesellschaft Turbine abradable layer with zig zag groove pattern
US9249680B2 (en) 2014-02-25 2016-02-02 Siemens Energy, Inc. Turbine abradable layer with asymmetric ridges or grooves
US20170089214A1 (en) * 2014-05-15 2017-03-30 Nuovo Pignone Srl Method of manufacturing a component of a turbomachine, component of a turbomachine and turbomachine
US20170276142A1 (en) * 2016-03-24 2017-09-28 Gregory Graham Clearance reducing system, appratus and method
US10174481B2 (en) 2014-08-26 2019-01-08 Cnh Industrial America Llc Shroud wear ring for a work vehicle
US10189082B2 (en) 2014-02-25 2019-01-29 Siemens Aktiengesellschaft Turbine shroud with abradable layer having dimpled forward zone
US10190435B2 (en) 2015-02-18 2019-01-29 Siemens Aktiengesellschaft Turbine shroud with abradable layer having ridges with holes
US10408079B2 (en) 2015-02-18 2019-09-10 Siemens Aktiengesellschaft Forming cooling passages in thermal barrier coated, combustion turbine superalloy components
EP3618240A4 (fr) * 2017-04-24 2021-01-13 LG Electronics Inc. Moteur de ventilateur et son procédé de fabrication
US11187245B2 (en) 2018-08-22 2021-11-30 LG Electionics Inc. Fan motor and manufacturing method of the same
US20220381188A1 (en) * 2021-05-26 2022-12-01 Doosan Heavy Industries & Construction Co., Ltd. Gas turbine inner shroud with abradable surface feature

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102012106090A1 (de) * 2012-07-06 2014-01-09 Ihi Charging Systems International Gmbh Turbine und Turbine für einen Abgasturbolader
US9598973B2 (en) 2012-11-28 2017-03-21 General Electric Company Seal systems for use in turbomachines and methods of fabricating the same
US20160281727A1 (en) * 2015-03-27 2016-09-29 Dresser-Rand Company Apparatus, system, and method for compressing a process fluid
US9951642B2 (en) * 2015-05-08 2018-04-24 United Technologies Corporation Intermittent grooved soft abradable material to reduce blade tip temperature
KR20180061507A (ko) 2016-11-29 2018-06-08 순천향대학교 산학협력단 방염 및 항균용 도료 조성물
KR102400236B1 (ko) * 2018-08-22 2022-05-23 엘지전자 주식회사 팬 모터 및 그 제조방법

Citations (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1528421A (en) * 1975-09-22 1978-10-11 Nissan Motor Shroud for rotor or impeller of a turbine or compressor with abradable seal layer on inside to establish minimized running clearance
US4329308A (en) * 1976-01-30 1982-05-11 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Method of making an abradable stator joint for an axial turbomachine
US5476704A (en) * 1992-07-01 1995-12-19 Hoac-Austria Flugzeugwerk Wr.Neustadt Gesellschaft M.B.H. Plastic-composite profiled girder, in particular a wing spar for aircraft and for wind-turbine rotors
US5975845A (en) * 1995-10-07 1999-11-02 Holset Engineering Company, Ltd. Turbomachinery abradable seal
US6234749B1 (en) * 1998-08-21 2001-05-22 Ishikawajima-Harima Heavy Industries Co., Ltd. Centrifugal compressor
US6547522B2 (en) * 2001-06-18 2003-04-15 General Electric Company Spring-backed abradable seal for turbomachinery
US6830428B2 (en) * 2001-11-14 2004-12-14 Snecma Moteurs Abradable coating for gas turbine walls
US6899339B2 (en) * 2001-08-30 2005-05-31 United Technologies Corporation Abradable seal having improved durability
DE102004011818A1 (de) * 2004-03-11 2005-09-29 Daimlerchrysler Ag Gehäuse für ein Turbinenrad
US7160352B2 (en) * 2002-12-13 2007-01-09 Snecma Moteurs Powder material for an abradable seal
US20090097970A1 (en) * 2007-10-16 2009-04-16 United Technologies Corp. Systems and Methods Involving Abradable Air Seals
US7600968B2 (en) * 2004-11-24 2009-10-13 General Electric Company Pattern for the surface of a turbine shroud
US20120107103A1 (en) * 2010-09-28 2012-05-03 Yoshitaka Kojima Gas turbine shroud with ceramic abradable layer
US8454300B2 (en) * 2008-04-15 2013-06-04 Borgwarner Inc. Open-blade engine-cooling fan shroud guide vanes
US8622784B2 (en) * 2008-07-02 2014-01-07 Huffman Corporation Method for selectively removing portions of an abradable coating using a water jet
US9151175B2 (en) * 2014-02-25 2015-10-06 Siemens Aktiengesellschaft Turbine abradable layer with progressive wear zone multi level ridge arrays

Family Cites Families (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS6251798A (ja) * 1985-08-30 1987-03-06 Akio Kawatani 粉塵耐摩耗プレ−ト
JPS6285198A (ja) * 1985-10-11 1987-04-18 Mitsubishi Heavy Ind Ltd コンプレツサ
US5489186A (en) * 1991-08-30 1996-02-06 Airflow Research And Manufacturing Corp. Housing with recirculation control for use with banded axial-flow fans
JPH05106594A (ja) * 1991-10-21 1993-04-27 Nissan Motor Co Ltd コンプレツサハウジング
US5599026A (en) * 1995-09-06 1997-02-04 Innovative Technology, L.L.C. Turbine seal with sealing strip and rubbing strip
JP3294491B2 (ja) * 1995-12-20 2002-06-24 株式会社日立製作所 内燃機関の過給機
US5980203A (en) * 1996-06-05 1999-11-09 Atlas Compco Comptec Spark-prevention coating for oxygen compressor shroud
JP4028923B2 (ja) * 1997-12-10 2008-01-09 株式会社協立 滑り部材付きターボチャージャ
EP0935009B1 (fr) 1998-02-05 2002-04-10 Sulzer Markets and Technology AG Corps moulé revêtu d'une couche
ATE420272T1 (de) * 1999-12-20 2009-01-15 Sulzer Metco Ag Profilierte, als anstreifschicht verwendete oberfläche in strömungsmaschinen
JP3930734B2 (ja) * 2001-12-28 2007-06-13 株式会社荏原製作所 立軸ポンプ
DE50303306D1 (de) * 2002-08-23 2006-06-14 Mtu Aero Engines Gmbh Rezirkulationsstruktur für turboverdichter
US20050003172A1 (en) 2002-12-17 2005-01-06 General Electric Company 7FAstage 1 abradable coatings and method for making same
US6887528B2 (en) * 2002-12-17 2005-05-03 General Electric Company High temperature abradable coatings
JP2005090383A (ja) * 2003-09-18 2005-04-07 Ishikawajima Harima Heavy Ind Co Ltd 回転機械の回転部のラビリンス構造
US20090129093A1 (en) * 2007-11-19 2009-05-21 Spi Lighting, Inc. Shadow-free cove light

Patent Citations (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1528421A (en) * 1975-09-22 1978-10-11 Nissan Motor Shroud for rotor or impeller of a turbine or compressor with abradable seal layer on inside to establish minimized running clearance
US4329308A (en) * 1976-01-30 1982-05-11 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Method of making an abradable stator joint for an axial turbomachine
US5476704A (en) * 1992-07-01 1995-12-19 Hoac-Austria Flugzeugwerk Wr.Neustadt Gesellschaft M.B.H. Plastic-composite profiled girder, in particular a wing spar for aircraft and for wind-turbine rotors
US5975845A (en) * 1995-10-07 1999-11-02 Holset Engineering Company, Ltd. Turbomachinery abradable seal
US6234749B1 (en) * 1998-08-21 2001-05-22 Ishikawajima-Harima Heavy Industries Co., Ltd. Centrifugal compressor
US6547522B2 (en) * 2001-06-18 2003-04-15 General Electric Company Spring-backed abradable seal for turbomachinery
US6899339B2 (en) * 2001-08-30 2005-05-31 United Technologies Corporation Abradable seal having improved durability
US6830428B2 (en) * 2001-11-14 2004-12-14 Snecma Moteurs Abradable coating for gas turbine walls
US7160352B2 (en) * 2002-12-13 2007-01-09 Snecma Moteurs Powder material for an abradable seal
DE102004011818A1 (de) * 2004-03-11 2005-09-29 Daimlerchrysler Ag Gehäuse für ein Turbinenrad
US7600968B2 (en) * 2004-11-24 2009-10-13 General Electric Company Pattern for the surface of a turbine shroud
US20090097970A1 (en) * 2007-10-16 2009-04-16 United Technologies Corp. Systems and Methods Involving Abradable Air Seals
US8061978B2 (en) * 2007-10-16 2011-11-22 United Technologies Corp. Systems and methods involving abradable air seals
US8454300B2 (en) * 2008-04-15 2013-06-04 Borgwarner Inc. Open-blade engine-cooling fan shroud guide vanes
US8622784B2 (en) * 2008-07-02 2014-01-07 Huffman Corporation Method for selectively removing portions of an abradable coating using a water jet
US20120107103A1 (en) * 2010-09-28 2012-05-03 Yoshitaka Kojima Gas turbine shroud with ceramic abradable layer
US9151175B2 (en) * 2014-02-25 2015-10-06 Siemens Aktiengesellschaft Turbine abradable layer with progressive wear zone multi level ridge arrays

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
Metco 601NS Aluminum-Polyester Powder: Technical Bulletin #10-141, Sulzer-Metco, October 2000 *

Cited By (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10189082B2 (en) 2014-02-25 2019-01-29 Siemens Aktiengesellschaft Turbine shroud with abradable layer having dimpled forward zone
US9249680B2 (en) 2014-02-25 2016-02-02 Siemens Energy, Inc. Turbine abradable layer with asymmetric ridges or grooves
US8939716B1 (en) 2014-02-25 2015-01-27 Siemens Aktiengesellschaft Turbine abradable layer with nested loop groove pattern
US8939707B1 (en) 2014-02-25 2015-01-27 Siemens Energy, Inc. Turbine abradable layer with progressive wear zone terraced ridges
WO2015130328A1 (fr) * 2014-02-25 2015-09-03 Siemens Aktiengesellschaft Rainures composites en « bâtons de hockey » sur une surface d'un segment de virole de turbine
US9151175B2 (en) 2014-02-25 2015-10-06 Siemens Aktiengesellschaft Turbine abradable layer with progressive wear zone multi level ridge arrays
US9243511B2 (en) 2014-02-25 2016-01-26 Siemens Aktiengesellschaft Turbine abradable layer with zig zag groove pattern
US10323533B2 (en) 2014-02-25 2019-06-18 Siemens Aktiengesellschaft Turbine component thermal barrier coating with depth-varying material properties
US10221716B2 (en) 2014-02-25 2019-03-05 Siemens Aktiengesellschaft Turbine abradable layer with inclined angle surface ridge or groove pattern
US10196920B2 (en) 2014-02-25 2019-02-05 Siemens Aktiengesellschaft Turbine component thermal barrier coating with crack isolating engineered groove features
US9920646B2 (en) 2014-02-25 2018-03-20 Siemens Aktiengesellschaft Turbine abradable layer with compound angle, asymmetric surface area ridge and groove pattern
US8939706B1 (en) 2014-02-25 2015-01-27 Siemens Energy, Inc. Turbine abradable layer with progressive wear zone having a frangible or pixelated nib surface
US8939705B1 (en) 2014-02-25 2015-01-27 Siemens Energy, Inc. Turbine abradable layer with progressive wear zone multi depth grooves
US11105216B2 (en) * 2014-05-15 2021-08-31 Nuovo Pignone Srl Method of manufacturing a component of a turbomachine, component of a turbomachine and turbomachine
US20170089214A1 (en) * 2014-05-15 2017-03-30 Nuovo Pignone Srl Method of manufacturing a component of a turbomachine, component of a turbomachine and turbomachine
US10174481B2 (en) 2014-08-26 2019-01-08 Cnh Industrial America Llc Shroud wear ring for a work vehicle
US10190435B2 (en) 2015-02-18 2019-01-29 Siemens Aktiengesellschaft Turbine shroud with abradable layer having ridges with holes
US10408079B2 (en) 2015-02-18 2019-09-10 Siemens Aktiengesellschaft Forming cooling passages in thermal barrier coated, combustion turbine superalloy components
US20170276142A1 (en) * 2016-03-24 2017-09-28 Gregory Graham Clearance reducing system, appratus and method
AU2018260360B2 (en) * 2017-04-24 2021-07-15 Lg Electronics Inc. Fan motor and manufacturing method therefor
EP3618240A4 (fr) * 2017-04-24 2021-01-13 LG Electronics Inc. Moteur de ventilateur et son procédé de fabrication
US11306730B2 (en) 2017-04-24 2022-04-19 Lg Electronics Inc. Fan motor and method of manufacturing the same
AU2021204043B2 (en) * 2017-04-24 2023-06-22 Lg Electronics Inc. Fan motor and method of manufacturing the same
US11187245B2 (en) 2018-08-22 2021-11-30 LG Electionics Inc. Fan motor and manufacturing method of the same
US11859639B2 (en) 2018-08-22 2024-01-02 Lg Electronics Inc. Fan motor and manufacturing method of the same
US20220381188A1 (en) * 2021-05-26 2022-12-01 Doosan Heavy Industries & Construction Co., Ltd. Gas turbine inner shroud with abradable surface feature
US11692490B2 (en) * 2021-05-26 2023-07-04 Doosan Heavy Industries & Construction Co., Ltd. Gas turbine inner shroud with abradable surface feature

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ITCO20090045A1 (it) 2011-04-30
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CN102753833B (zh) 2016-02-10
CN102753833A (zh) 2012-10-24
JP2013509533A (ja) 2013-03-14
RU2012119299A (ru) 2013-12-10
EP2494210A1 (fr) 2012-09-05
JP5728017B2 (ja) 2015-06-03
CA2779380A1 (fr) 2011-05-05
RU2556092C2 (ru) 2015-07-10
MX2012005085A (es) 2012-10-01
EP2494210B1 (fr) 2018-09-26
KR20120095407A (ko) 2012-08-28
WO2011053448A8 (fr) 2012-06-14

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