WO2016135973A1 - 過給機の製造方法 - Google Patents
過給機の製造方法 Download PDFInfo
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- WO2016135973A1 WO2016135973A1 PCT/JP2015/055960 JP2015055960W WO2016135973A1 WO 2016135973 A1 WO2016135973 A1 WO 2016135973A1 JP 2015055960 W JP2015055960 W JP 2015055960W WO 2016135973 A1 WO2016135973 A1 WO 2016135973A1
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- WIPO (PCT)
- Prior art keywords
- housing
- impeller
- abradable
- abradable layer
- layer
- Prior art date
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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
- F04D29/18—Rotors
- F04D29/22—Rotors specially for centrifugal pumps
- F04D29/2205—Conventional flow pattern
- F04D29/2222—Construction and assembly
- F04D29/2227—Construction and assembly for special materials
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C24/00—Coating starting from inorganic powder
- C23C24/02—Coating starting from inorganic powder by application of pressure only
- C23C24/04—Impact or kinetic deposition of particles
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C24/00—Coating starting from inorganic powder
- C23C24/08—Coating starting from inorganic powder by application of heat or pressure and heat
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/02—Pretreatment of the material to be coated, e.g. for coating on selected surface areas
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
- C23C4/10—Oxides, borides, carbides, nitrides or silicides; Mixtures thereof
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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
- F04D13/00—Pumping installations or systems
- F04D13/02—Units comprising pumps and their driving means
- F04D13/021—Units comprising pumps and their driving means containing a coupling
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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
- F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
- F04D17/08—Centrifugal pumps
- F04D17/10—Centrifugal pumps for compressing or evacuating
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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
- F04D25/00—Pumping installations or systems
- F04D25/02—Units comprising pumps and their driving means
- F04D25/024—Units comprising pumps and their driving means the driving means being assisted by a power recovery turbine
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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
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
- F04D27/02—Surge control
- F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
- F04D27/0215—Arrangements therefor, e.g. bleed or by-pass valves
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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
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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
- F04D29/08—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
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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
- F04D29/26—Rotors specially for elastic fluids
- F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
- F04D29/289—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps having provision against erosion or for dust-separation
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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
- F04D29/26—Rotors specially for elastic fluids
- F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
- F04D29/30—Vanes
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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
- F04D29/40—Casings; Connections of working fluid
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
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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
- F04D29/60—Mounting; Assembling; Disassembling
- F04D29/62—Mounting; Assembling; Disassembling of radial or helico-centrifugal pumps
- F04D29/622—Adjusting the clearances between rotary and stationary parts
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- 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
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- 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
- F05D2220/00—Application
- F05D2220/40—Application in turbochargers
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- 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
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D2240/307—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the tip of a rotor blade
Definitions
- the present invention relates to a method of manufacturing a supercharger having a compressor that rotates air by the rotational force of a turbine to compress air.
- a turbine In a turbocharger (supercharger), a turbine is rotationally driven by exhaust gas of an engine, and an impeller of a centrifugal compressor is rotated by rotational power of the turbine. Compressed air compressed by the centrifugal compressor is fed to the engine.
- the centrifugal compressor of the turbocharger has a gap between the housing and the impeller on the inner surface side of the housing. This can prevent contact between the housing and the impeller due to the effects of thermal expansion and vibration during operation and component tolerances.
- Patent Document 1 discloses that an abradable coating layer of a synthetic resin is formed on the inner periphery of a housing facing the impeller.
- the abradable layer narrows the gap between the housing and the impeller, the impeller will not be damaged even when the impeller contacts, and the performance can be improved while maintaining the reliability.
- Patent Document 2 discloses a method in which a synthetic resin sliding member is attached to a housing by adhesion.
- the process of manufacturing a sliding member made of synthetic resin and the bonding process are separately required and the number of parts is increased, the productivity is deteriorated.
- Patent Document 3 discloses a method of bringing a mold into close contact with the inner surface of a housing and injecting a synthetic resin between the housing and the mold. According to this method, the sliding member is formed on the inner surface of the housing by injection molding. However, it is necessary to change the mold according to the shape of the housing or the impeller, and the productivity is poor.
- Patent Document 1 discloses a method of forming an abradable coating layer on the inner periphery of the housing by spraying a synthetic resin on the inner periphery of the housing by thermal spraying.
- thermal spraying or spray it is difficult to limit the application site, and it is also difficult to adjust the film thickness. Therefore, in general, masking around the construction site and post-processing or finishing for adjusting the film thickness are required, and the productivity is poor.
- This invention is made in view of such a situation, Comprising: It aims at providing the manufacturing method of the supercharger which can form an abradable layer rapidly and easily in a supercharger.
- a method of manufacturing a supercharger according to the present invention is a method of manufacturing a supercharger including a turbine which is rotationally driven, and a compressor having an impeller which is rotated by the rotational force of the turbine and a housing which accommodates the impeller. And a step of coating an abradable material, which becomes an abradable layer when solidified, with respect to only one of the surfaces of the impeller and the housing, in which the impeller and the housing face each other, in a predetermined range.
- the abradable material is coated on the surface of the impeller or the surface of the housing, it is not necessary to separately manufacture the abradable material as a part or to perform step replacement according to the shape of the impeller or the housing. Moreover, in coating application, adjustment of a film thickness is generally easy and post-process and finish become unnecessary.
- the abradable material is, for example, the inner peripheral surface of the housing (the surface facing the tip of the impeller blade or the surface facing the outer peripheral surface on the end plate side of the impeller), the tip of the impeller blade, or the impeller It is coated on the outer peripheral surface on the end plate side.
- the abradable material is coated only in a predetermined range without masking.
- the abradable material since the abradable material is coated only in a predetermined range without masking, productivity can be improved.
- the abradable material wets and spreads on the surface of the impeller or the housing because it is coated without masking.
- it is possible to make no level difference at the end of the abradable layer. Therefore, separation of the flow of air on the surface of the impeller or the housing can be suppressed, and a reduction in the efficiency of the turbocharger can also be suppressed.
- the abradable material is coated by a dispensing nozzle, a brush or a pad.
- the abradable layer can be made only in a predetermined range without masking. Easy to form.
- the method before the step of coating the abradable material, the method further includes the step of forming a projection or a recess on the surface of the impeller or the housing at the boundary of the area where the abradable layer is to be formed.
- the abradable material is unlikely to spread excessively, and the abradable layer is reliably applied in a predetermined range.
- a projection or a recess it is desirable that the projection or the recess be at a height or a depth that does not obstruct the air flow, and the abradable layer and the impeller or the housing should have a smoothly continuous shape. .
- the method before the step of coating the abradable material, the method further includes the step of roughening the roughness in the region outside the region in which the abradable layer is to be formed compared with the region in which the abradable layer is formed.
- the abradable material in the area outside the area where the abradable layer is to be formed, the abradable material is unlikely to spread excessively due to the roughness becoming rough, and the abradable layer is reliably applied within the predetermined range.
- the abradable material contains a synthetic resin and fine particles having a self-lubricating property.
- the abradable material when solidified, the abradable material is coated so that the density is lower on the surface side of the abradable layer than on the impeller side or the housing side.
- the strength is reduced on the surface side of the abradable layer, and therefore, when the impeller comes in contact with the impeller, it is easily scraped and breakage of the impeller can be prevented.
- the abradable layer can be formed quickly and easily in the turbocharger.
- the turbocharger 1 includes a turbine 2, a compressor 3, and a rotary shaft 4 connected to the turbine 2 and the compressor 3.
- the exhaust gas from the engine rotationally drives the turbine 2 and the rotational force of the turbine 2 causes the compressor 3 to rotate.
- the impeller 11 rotates.
- the air compressed by the compressor 3 is supplied to the engine.
- the turbine 2 is disposed on one end side of the rotating shaft 4 and includes an impeller 6, a housing 5 and the like.
- the impeller 6 has a blade 7 and is connected to the rotation shaft 4 to rotate about an axis.
- the housing 5 covers the impeller 6 from the outside, and a scroll passage 8 communicating the inside and the outside of the housing 5 is formed.
- the scroll passage 8 extends radially outward from the radially outer end (the front edge 7 a) of the blade 7 and is formed annularly around the axis of the rotation shaft 4. The exhaust gas is introduced into the impeller 6 from the scroll passage 8 to rotate the impeller 6 and the rotating shaft 4.
- the housing 5 is formed with a discharge port 9 opened at one end side of the axis of the rotary shaft 4.
- the exhaust gas having passed through the blade 7 is discharged to the outside of the housing 5 through the discharge port 9.
- the compressor 3 is, for example, a centrifugal compressor, and is disposed on the other end side of the rotation shaft 4 and includes an impeller 11, a housing 10, and the like.
- the impeller 11 has a blade 12 and is connected to the rotation shaft 4 to rotate about an axis.
- the housing 10 covers the impeller 11 from the outside.
- a suction port 13 opened at the other end side of the axis of the rotary shaft 4 is formed. Air is introduced into the impeller 11 from the outside through the suction port 13. The rotational force of the impeller 6 of the turbine 2 is transmitted to the impeller 11 via the rotation shaft 4 to rotate the impeller 11. The air introduced from the outside is compressed by passing through the impeller 11.
- the housing 10 is formed with a compressor passage 14 communicating the inside and the outside of the housing 10, and the compressor passage 14 extends radially outward from the radially outer end portion (rear edge portion 12b) of the blade 12 , And is formed in an annular shape around the axis of the rotation shaft 4.
- the air compressed by the impeller 11 is introduced into the compressor passage 14 and discharged to the outside of the housing 10.
- the bearing housing 15 is disposed between the turbine 2 and the compressor 3 and connects the turbine 2 and the compressor 3.
- the bearing housing 15 covers the rotating shaft 4 from the outside.
- the bearing housing 15 is provided with a bearing 16, and the bearing 16 supports the rotating shaft 4 so as to be rotatable relative to the bearing housing 15.
- the inner circumferential surface of the bearing housing 15 may be disposed to face the impeller 11.
- An abradable layer 20 is formed on the inner peripheral surface of the housing 10 of the compressor 3 and facing the side edge 12a of the blade 12 (see FIG. 2).
- the abradable layer 20 is made of a material (hereinafter referred to as "abradable material") which is easily scraped even when the impeller 11 contacts, and is formed to narrow the gap between the housing 10 and the blade 12 of the impeller 11 .
- abradable material a material
- the abradable material is a material that becomes the abradable layer 20 when solidified, and is, for example, a synthetic resin.
- An epoxy resin, polyamide, a polyimide etc. are applicable as a synthetic resin.
- the abradable material may be made to disperse and contain fine particles having self-lubricity at a content of 5 wt% to 50 wt% in a synthetic resin.
- the fine particles have a particle size of 5 ⁇ m to 50 ⁇ m and are, for example, molybdenum disulfide, PTFE (polytetrafluoroethylene), hBN (hexagonal boron nitride), graphite and the like.
- the abradable layer 20 may have a structure in which the resin density is lower on the surface side of the abradable layer 20 than the contact surface with the housing 10 which is the base material.
- the abradable layer 20 firmly adheres to the housing 10 on the surface in close contact with the housing 10, and the strength of the abradable layer 20 decreases on the surface side of the abradable layer 20. It becomes easy to scrape and breakage of the impeller 11 can be prevented.
- the content of fine particles is increased on the surface side of the abradable layer 20 rather than on the side of the surface in close contact with the housing 10. As a result, more particles are contained on the surface side of the abradable layer 20, and the resin density on the surface side of the abradable layer 20 can be reduced. Specifically, when fine particles having a density lower than that of the base material synthetic resin are dispersed in the abradable material, the fine particles float on the surface side until the abradable material solidifies, and then the abradable material solidifies. So that the microparticles are immobilized on the surface side.
- the fine particles are, for example, molybdenum disulfide, PTFE, hBN, graphite, hollow floating fine particles and the like.
- the methods of (1) to (3) described above may be realized using the same synthetic resin, or different synthetic resins or different formulations may be used. May be realized as a multi-layer structure of two or more layers. For example, a synthetic resin or a compound having high density and high adhesiveness is used on the side in contact with the housing 10, and a synthetic resin or a compound having high abradability is used on the surface side of the abradable layer 20.
- the abradable layer 20 is formed by coating an abradable material only on a predetermined range without masking on the inner circumferential surface of the housing 10. Moreover, since it is coating construction, the film thickness can be adjusted at the time of construction, and post-processing and finish for film thickness adjustment are not performed.
- the abradable material is coated on the surface of the housing 10, it is not necessary to separately manufacture the abradable material as a part or to make a setup change according to the shape of the impeller 11 or the housing 10. In addition, regardless of the shape of the impeller 11 or the housing 10, the coating can be performed with the same production facility, so the productivity is high.
- the coating application can form the abradable layer 20 only in a predetermined range without masking and can improve productivity. Furthermore, in coating application, adjustment of the film thickness is easy, and post-processing and finishing become unnecessary. As a result, mass productivity is high and construction can be done inexpensively.
- the abradable layer 20 in the state as shown in FIG. 3 immediately after the application of the coating wets and spreads the abradable material on the surface of the housing 10 as time passes.
- masking as shown in FIG. 15, after the abradable material is solidified to a certain extent, the masking tape 38 and the like are peeled off, so that a step is formed at the end of the abradable layer 26.
- the end of the abradable layer 20 unlike in the case where the masking is performed, as shown in FIG. 4, it is possible to make the end of the abradable layer 20 have no step. Therefore, the separation of the flow of air on the surface of the housing 10 can be suppressed, and the efficiency reduction of the turbocharger can also be suppressed.
- FIG. 5 As a method of coating the abradable material, as shown in FIG. 5, there is a method of using a constant discharge nozzle 32 position-controlled in the direction of three axes by the three-axis robot 30.
- the housing 10 in which an abradable material is constructed is not shown in figure in FIG.
- the fixed amount discharge nozzle 32 is provided to the three-axis robot 30, and the fixed amount discharge nozzle 32 is supplied with an abradable material from the tank 34.
- the discharge amount of the abradable material from the fixed amount discharge nozzle 32 is adjusted by adjusting the air pressure supplied from the controller 36.
- the abradable material is coated in the vicinity of the surface of the housing 10, so that the abradable layer 20 can be formed only in a predetermined range without masking.
- the position control of the constant discharge nozzle 32 may not be performed by the three-axis robot 30, and another device such as a robot capable of position control only in two axial directions may be used.
- coating application with respect to the surface of the housing 10 is not limited to a fixed quantity discharge nozzle, You may use a brush. Also in this case, position control is performed by the three-axis robot 30 or the like. A brush is replaced with the fixed amount discharge nozzle 32 mentioned above, and is installed. Thus, the abradable material is pressed against the surface of the housing 10 and coated, so that the abradable layer 20 can be formed only in a predetermined range without masking.
- the coating application to the surface of the housing 10 may be performed by pad printing as shown in FIGS. 6 and 7.
- the pad printing can apply the method currently generally performed. Specifically, as shown in FIG. 6, after the abradable material 44 stored in the container 42 is attached to the pad 40 made of silicone, the pad 40 is applied to the housing 10 as shown in FIG. An abradable material 44 is coated on the inner surface of the housing 10. Also in this case, since the abradable material is pressed against the surface of the housing 10 and coated, the abradable layer 20 can be formed only in a predetermined range without masking.
- projections are formed on the surface of the housing 10 at the boundary of the area where the abradable layer 20 is to be formed, as shown in FIG. ) May be formed.
- the convex portion 21 or the concave portion 23 is formed on the surface of the housing 10, the abradable material is unlikely to spread excessively, and the abradable layer 20 is reliably applied in a predetermined range.
- the convex portion 21 or the concave portion 23 has a height or depth such that the air flow is not obstructed and the performance of the turbocharger 1 is not affected. In the case of the convex portion 21, it is desirable that the projection is a minute projection lower than the height of the abradable layer 20.
- the projections 21 may be formed by coating.
- the coating material of the convex portion 21 may use the same material as the abradable material. As a result, it is not necessary to prepare a material different from the formation of the abradable layer 20, and since the abradable layer 20 has high affinity, peeling and the like can be prevented.
- the shape of the convex portion 21 may be a semicircular longitudinal sectional shape, or may be a longitudinal sectional shape having a gentle sloping surface like the convex portion 25 shown in FIG.
- the convex portion 25 can be prevented from obstructing the air flow.
- the area 10B outside the area 10A where the abradable layer 20 is to be formed has a roughness greater than that of the area 10A where the abradable layer 20 is formed. It may be processed to be rough. As a result, in the area 10B outside the area 10A where the abradable layer 20 is formed, the abradable material is unlikely to spread excessively because the roughness becomes rough, and the abradable layer 20 is reliably applied within the predetermined range.
- the abradable layer 20 was formed in the predetermined range of the inner peripheral surface of the housing 10 of the compressor 3 was demonstrated in the above-mentioned 1st Embodiment, this invention is not limited to this example.
- the abradable layer 22 is formed on the side edge 12 a of the blade 12 of the impeller 11 of the compressor 3. In the following, detailed description of the components overlapping with the first embodiment is omitted.
- the abradable layer 22 is formed on the side edge 12 a of the blade 12 at a portion facing the inner circumferential surface of the housing 10 of the compressor 3.
- the abradable layer 22 is made of an abradable material similar to that of the first embodiment, and is formed so as to narrow the gap between the housing 10 and the blade 12 of the impeller 11. By forming the abradable layer 22, the gap between the housing 10 and the impeller 11 is narrowed, the performance of the turbocharger 1 is improved, and the impeller 11 is not damaged even when the impeller 11 contacts. Reliability can be secured.
- the abradable layer 22 is formed by coating an abradable material on the tip of the blade 12 only in a predetermined range. When the coated abradable material solidifies, the abradable layer 22 is formed in a predetermined range. Moreover, since it is coating construction, the film thickness can be adjusted at the time of construction, and post-processing and finish for film thickness adjustment are not performed.
- a method of coating the abradable material there is a method using a fixed quantity discharge nozzle or a brush, which is position-controlled in the three axial directions by the three-axis robot 30, as in the first embodiment, and a method by pad printing.
- a method of giving an abradable material it is not restricted to coating application, You may be by spray coating. However, in this case, masking is performed outside the predetermined range so that the abradable material is applied to the predetermined range.
- the area for applying the abradable material to the side edge 12 a of the blade 12 of the impeller 11 is smaller than the area for applying to the inner peripheral surface of the housing 10. Therefore, by applying the abradable material to the impeller 11 instead of the housing 10, the amount of use of the abradable material can be suppressed to a small amount, which is inexpensive.
- the impeller 11 has a smaller volume than the housing 10. Therefore, when the synthetic resin of abradable material is a thermosetting type and the temperature rises during curing, the impeller 11 has a faster temperature rising rate than the housing 10, so that the construction time can be shortened and the equipment cost can be reduced. Is also possible.
- the abradable layer 20 is formed in the surface facing the blade 12 among the inner peripheral surfaces of the housing 10 of the compressor 3
- the present invention is not limited to this example.
- the abradable layer 24 is formed on the surface of the inner peripheral surface of the housing 10 of the compressor 3 facing the outer peripheral surface 17 a of the end plate 17 of the impeller 11.
- the abradable layer 24 is formed on the inner peripheral surface of the housing 10 of the compressor 3 and on the surface facing the outer peripheral surface 17 a of the end plate 17 of the impeller 11.
- the abradable layer 24 is made of an abradable material similar to that of the first embodiment, and is formed to narrow the gap between the housing 10 and the end plate 17 of the impeller 11. The formation of the abradable layer 24 narrows the gap between the housing 10 and the end plate 17 of the impeller 11, thereby improving the performance of the turbocharger 1 and damaging the impeller 11 even when the impeller 11 contacts. Reliability can be secured without
- the abradable layer 24 is formed by coating an abradable material only in a predetermined range on a surface of the inner peripheral surface of the housing 10 facing the outer peripheral surface 17 a of the end plate 17 of the impeller 11. When the coated abradable material solidifies, the abradable layer 24 is formed in a predetermined range. Moreover, since it is coating construction, the film thickness can be adjusted at the time of construction, and post-processing and finish for film thickness adjustment are not performed.
- a method of coating the abradable material there is a method using a fixed quantity discharge nozzle or a brush, which is position-controlled in the three axial directions by the three-axis robot 30, as in the first embodiment, and a method by pad printing.
- a method of giving an abradable material it is not restricted to coating application, You may be by spray coating. However, in this case, masking is performed outside the predetermined range so that the abradable material is applied to the predetermined range.
- the abradable material is applied to the surface of the inner peripheral surface of the housing 10 facing the outer peripheral surface 17 a of the end plate 17 of the impeller 11 in comparison with the area applied to the surface of the inner peripheral surface of the housing 10 facing the blade 12. small. Therefore, by applying the abradable material to the surface facing the outer peripheral surface 17 a of the end plate 17 of the impeller 11, the amount of use of the abradable material can be suppressed to a small amount, which is inexpensive.
- the present invention is not limited to this example. That is, when the impeller 11 and the bearing housing 15 face each other, the abradable layer is not on the inner circumferential surface of the housing 10 but on the inner circumferential surface of the bearing housing 15 that faces the outer circumferential surface 17 a of the end plate 17 of the impeller 11. May be formed.
- an abradable layer may be formed on the outer peripheral surface 17 a of the end plate 17 of the impeller 11 instead of the inner peripheral surface side of the housing 10 or the bearing housing 15. Also in these cases, the gap between the housing 10 and the end plate 17 of the impeller 11 is narrowed, the performance of the turbocharger 1 is improved, and the impeller 11 is not damaged even when the impeller 11 comes in contact. I can secure the sex.
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Abstract
Description
すなわち、本発明に係る過給機の製造方法は、回転駆動するタービンと、前記タービンの回転力によって回転するインペラ及び前記インペラを収容するハウジングを有する圧縮機とを備える過給機の製造方法であって、前記インペラと前記ハウジングとが対向する、前記インペラ及び前記ハウジングのいずれか一方の面に対し、固化したときにアブレーダブル層となるアブレーダブル材を、所定範囲のみにコーティングする工程を含む。
以下、本発明の第1実施形態に係るターボチャージャ(過給機)について、図1を用いて説明する。
ターボチャージャ1は、タービン2と、圧縮機3と、タービン2及び圧縮機3に連結した回転軸4を備え、エンジンからの排ガスによってタービン2が回転駆動し、タービン2の回転力によって圧縮機3のインペラ11が回転する。圧縮機3によって圧縮された空気はエンジンに供給される。
インペラ6は、ブレード7を有し、回転軸4と連結されて、軸線周りに回転する。
インペラ11は、ブレード12を有し、回転軸4と連結されて、軸線周りに回転する。
なお、ターボチャージャ1の構成によっては、軸受ハウジング15の内周面が、インペラ11と対向するように配置される場合もある。
アブレーダブル層20は、ハウジング10の内周面に対して、アブレーダブル材を、マスキングを施さずに所定範囲のみにコーティングすることで形成される。また、コーティング施工であるため、施工時に膜厚の調整ができ、膜厚調整のための後加工や仕上げを行わない。
次に、本発明の第2実施形態に係るターボチャージャについて説明する。上述の第1実施形態では、圧縮機3のハウジング10の内周面の所定範囲にアブレーダブル層20を形成する場合について説明したが、本発明はこの例に限定されない。本実施形態では、図13に示すように、圧縮機3のインペラ11のブレード12の側縁部12aにアブレーダブル層22を形成する。
以下では、第1実施形態と重複する構成要素については、詳細な説明を省略する。
本実施形態では、ブレード12の側縁部12aであって、圧縮機3のハウジング10の内周面と対向する部分に、アブレーダブル層22が形成される。
次に、本発明の第3実施形態に係るターボチャージャについて説明する。上述の第1実施形態では、圧縮機3のハウジング10の内周面のうち、ブレード12に対向する面にアブレーダブル層20を形成する場合について説明したが、本発明はこの例に限定されない。本実施形態では、図14に示すように、圧縮機3のハウジング10の内周面のうち、インペラ11の端板17の外周面17aに対向する面にアブレーダブル層24を形成する。
以下では、第1実施形態と重複する構成要素については、詳細な説明を省略する。
本実施形態では、圧縮機3のハウジング10の内周面であって、インペラ11の端板17の外周面17aに対向する面に、アブレーダブル層24が形成される。
また、ハウジング10や軸受ハウジング15の内周面側ではなく、インペラ11の端板17の外周面17aにアブレーダブル層を形成してもよい。
これらの場合も、ハウジング10とインペラ11の端板17との間の隙間が狭くなり、ターボチャージャ1の性能が向上するとともに、インペラ11が接触してもインペラ11が破損することがなく、信頼性を確保できる。
2 タービン
3 圧縮機
4 回転軸
5 ハウジング
6 インペラ
7 ブレード
8 スクロール通路
9 排出口
10 ハウジング
11 インペラ
12 ブレード
13 吸込口
14 圧縮機通路
15 軸受ハウジング(ハウジング)
16 軸受
17 端板
20,22,24 アブレーダブル層
Claims (7)
- 回転駆動するタービンと、前記タービンの回転力によって回転するインペラ及び前記インペラを収容するハウジングを有する圧縮機とを備える過給機の製造方法であって、
前記インペラと前記ハウジングとが対向する、前記インペラ及び前記ハウジングのいずれか一方の面に対し、固化したときにアブレーダブル層となるアブレーダブル材を、所定範囲のみにコーティングする工程を含む過給機の製造方法。 - 前記アブレーダブル材を、所定範囲のみにマスキングを施さずにコーティングする請求項1に記載の過給機の製造方法。
- 前記アブレーダブル材は、定量吐出ノズル、刷毛、又は、パッドによってコーティングされる請求項1又は2に記載の過給機の製造方法。
- 前記アブレーダブル材をコーティングする工程の前に、前記アブレーダブル層を形成する領域の境界において、前記インペラ又は前記ハウジングの表面に凸部又は凹部を形成する工程を更に含む請求項1から3のいずれか1項に記載の過給機の製造方法。
- 前記アブレーダブル材をコーティングする工程の前に、前記アブレーダブル層を形成する領域の外部の領域において、前記アブレーダブル層を形成する領域よりも粗度を粗くする工程を更に含む請求項1から3のいずれか1項に記載の過給機の製造方法。
- 前記アブレーダブル材は、合成樹脂と、自己潤滑性を有する微粒子とを含有する請求項1から5のいずれか1項に記載の過給機の製造方法。
- 前記アブレーダブル材は、固化したとき、前記インペラ側又は前記ハウジング側よりも、前記アブレーダブル層の表面側において、密度が低下するようにコーティングされる請求項1から6のいずれか1項に記載の過給機の製造方法。
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US15/551,660 US11028855B2 (en) | 2015-02-27 | 2015-02-27 | Method of manufacturing supercharger |
JP2017501813A JP6607580B2 (ja) | 2015-02-27 | 2015-02-27 | 過給機の製造方法 |
EP15883267.5A EP3263909B1 (en) | 2015-02-27 | 2015-02-27 | Method of manufacturing turbocharger |
PCT/JP2015/055960 WO2016135973A1 (ja) | 2015-02-27 | 2015-02-27 | 過給機の製造方法 |
CN201580076962.8A CN107250552B (zh) | 2015-02-27 | 2015-02-27 | 增压器的制造方法 |
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Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2021505447A (ja) * | 2017-12-06 | 2021-02-18 | サフラン・エアクラフト・エンジンズ | ターボ機械ケーシングのコーティングのその場積層造形方法 |
JP2021505444A (ja) * | 2017-12-06 | 2021-02-18 | サフラン・エアクラフト・エンジンズ | アブレイダブル材料で作られた吸音チャネルの規則正しい網状組織を製造する方法 |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN107327318B (zh) * | 2017-07-25 | 2023-09-22 | 湖南天雁机械有限责任公司 | 采用可磨耗涂层进行叶顶间隙控制的涡轮增压器 |
WO2019157118A1 (en) * | 2018-02-09 | 2019-08-15 | Borgwarner Inc. | Impeller wheel for a turbocharger and method of making the same |
US11441570B2 (en) * | 2019-06-12 | 2022-09-13 | Lg Electronics Inc. | Motor assembly and method for manufacturing the same |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPH03237299A (ja) * | 1990-02-09 | 1991-10-23 | Toyota Motor Corp | 間隙調整皮膜層の製造方法 |
JPH10507245A (ja) * | 1995-10-07 | 1998-07-14 | ホルセット エンジニアリング カンパニー リミテッド | ターボ機構の摩耗シール |
JP2006144790A (ja) * | 2004-11-20 | 2006-06-08 | Borgwarner Inc | 圧縮機ハウジングの製造方法 |
JP2009522430A (ja) * | 2006-01-05 | 2009-06-11 | ゼネラル・エレクトリック・カンパニイ | マイクロカプセルを含む組成物を製造する方法及びそれにより製造される組成物 |
US20090232642A1 (en) * | 2008-03-12 | 2009-09-17 | Atte Anema | Adjustable compressor bleed system and method |
Family Cites Families (48)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3046648A (en) * | 1959-04-13 | 1962-07-31 | Aircraft Prec Products Inc | Method of manufacturing replaceable labyrinth type seal assembly |
US4349313A (en) * | 1979-12-26 | 1982-09-14 | United Technologies Corporation | Abradable rub strip |
US4450184A (en) * | 1982-02-16 | 1984-05-22 | Metco Incorporated | Hollow sphere ceramic particles for abradable coatings |
JPH0396601A (ja) * | 1989-09-08 | 1991-04-22 | Toyota Motor Corp | 相対移動装置 |
DE69010122T2 (de) | 1989-09-08 | 1994-11-17 | Toyota Motor Co Ltd | Abtragbares Material für eine Turbomaschine. |
JPH03156103A (ja) * | 1989-11-10 | 1991-07-04 | Toyota Motor Corp | 相対移動装置 |
JPH0352398U (ja) | 1989-09-29 | 1991-05-21 | ||
JPH0368529U (ja) * | 1989-11-06 | 1991-07-05 | ||
US5435872A (en) * | 1991-11-01 | 1995-07-25 | Decc Technology Partnership | Sized coated pistons |
WO1998048157A1 (fr) | 1997-04-22 | 1998-10-29 | Kyoritsu Corp. | Turbocompresseur equipe d'un element coulissant |
JP2000345984A (ja) * | 1999-06-02 | 2000-12-12 | Matsushita Electric Ind Co Ltd | 圧縮機 |
DE10121019A1 (de) * | 2001-04-28 | 2002-10-31 | Alstom Switzerland Ltd | Gasturbinendichtung |
US6511422B1 (en) * | 2002-04-30 | 2003-01-28 | Karl Storz Imaging, Inc. | Method and apparatus for protection from high intensity light |
JP4305928B2 (ja) * | 2002-10-09 | 2009-07-29 | 株式会社Ihi | 回転体及びそのコーティング方法 |
KR101004236B1 (ko) * | 2002-10-09 | 2010-12-24 | 미츠비시덴키 가부시키가이샤 | 회전체 및 그 코팅방법 |
US20050003172A1 (en) * | 2002-12-17 | 2005-01-06 | General Electric Company | 7FAstage 1 abradable coatings and method for making same |
JP4868037B2 (ja) | 2003-03-20 | 2012-02-01 | 株式会社Ihi | 過給機の製造方法及び過給機 |
JP2006150155A (ja) * | 2004-11-25 | 2006-06-15 | Seiko Epson Corp | 液滴吐出ヘッドおよび液滴吐出ヘッドの製造方法、液滴吐出装置 |
DE102006004769B4 (de) * | 2006-02-02 | 2022-05-25 | Mercedes-Benz Group AG | Oberflächenkonditionierung für thermische Spritzschichten |
PL2078060T3 (pl) * | 2006-10-30 | 2017-09-29 | Andrew W. Suman | Środek smarny ze ścieralnym suchym filmem i sposób jego nakładania oraz wyrób z niego wykonany |
DE102010048147B4 (de) * | 2010-10-11 | 2016-04-21 | MTU Aero Engines AG | Schichtsystem zur Rotor-/Statordichtung einer Strömungsmaschine und Verfahren zum Herstellen eines derartigen Schichtsystems |
US20140199163A1 (en) | 2011-03-09 | 2014-07-17 | Rolls-Royce Corporation- | Abradable layer including a low thermal conductivity composition |
GB201116029D0 (en) * | 2011-09-16 | 2011-10-26 | Rolls Royce Plc | Abradable panel and method of forming the same |
US8685545B2 (en) * | 2012-02-13 | 2014-04-01 | Siemens Aktiengesellschaft | Thermal barrier coating system with porous tungsten bronze structured underlayer |
US10215033B2 (en) * | 2012-04-18 | 2019-02-26 | General Electric Company | Stator seal for turbine rub avoidance |
US20150308276A1 (en) * | 2012-12-17 | 2015-10-29 | General Electric Company | Robust turbine blades |
US10280783B2 (en) * | 2013-11-13 | 2019-05-07 | United Technologies Corporation | Turbomachinery blade outer air seal |
EP2886804B1 (fr) * | 2013-12-20 | 2017-08-16 | Safran Aero Boosters SA | Dispositif d'étanchéité pour un compresseur de turbomachine |
US10539036B2 (en) * | 2014-01-14 | 2020-01-21 | United Technologies Corporation | Abradable seal having nanolayer material |
EP2896796B1 (fr) * | 2014-01-20 | 2019-09-18 | Safran Aero Boosters SA | Stator de turbomachine axiale et turbomachine associée |
US8939707B1 (en) * | 2014-02-25 | 2015-01-27 | Siemens Energy, Inc. | Turbine abradable layer with progressive wear zone terraced ridges |
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 |
WO2015130528A1 (en) * | 2014-02-25 | 2015-09-03 | Siemens Aktiengesellschaft | Turbine component thermal barrier coating with crack isolating engineered surface features |
US10036402B2 (en) * | 2014-05-14 | 2018-07-31 | United Technologies Corporation | Max phase reinforced polymer matrix composite abradables with enhanced thermal conductivity |
US9957826B2 (en) * | 2014-06-09 | 2018-05-01 | United Technologies Corporation | Stiffness controlled abradeable seal system with max phase materials and methods of making same |
US20150354392A1 (en) * | 2014-06-10 | 2015-12-10 | General Electric Company | Abradable coatings |
US20150354393A1 (en) * | 2014-06-10 | 2015-12-10 | General Electric Company | Methods of manufacturing a shroud abradable coating |
US10132185B2 (en) * | 2014-11-07 | 2018-11-20 | Rolls-Royce Corporation | Additive process for an abradable blade track used in a gas turbine engine |
BE1022513B1 (fr) * | 2014-11-18 | 2016-05-19 | Techspace Aero S.A. | Virole interne de compresseur de turbomachine axiale |
JP6210459B2 (ja) | 2014-11-25 | 2017-10-11 | 三菱重工業株式会社 | インペラ、及び回転機械 |
US10533439B2 (en) * | 2014-12-16 | 2020-01-14 | United Technologies Corporation | Gas turbine engine component with abrasive surface formed by electrical discharge machining |
DE102015202070A1 (de) * | 2015-02-05 | 2016-08-25 | MTU Aero Engines AG | Gasturbinenbauteil |
US20170016454A1 (en) * | 2015-02-25 | 2017-01-19 | United Technologies Corporation | Method for coating compressor blade tips |
JP2017082666A (ja) * | 2015-10-27 | 2017-05-18 | 株式会社オティックス | 過給機用のコンプレッサハウジング及びその製造方法 |
US10145252B2 (en) * | 2015-12-09 | 2018-12-04 | General Electric Company | Abradable compositions and methods for CMC shrouds |
FR3044945B1 (fr) * | 2015-12-14 | 2018-01-12 | Centre National De La Recherche Scientifique | Revetement abradable a densite variable |
US20180087387A1 (en) * | 2016-09-28 | 2018-03-29 | General Electric Company | Compositions and methods for coating metal turbine blade tips |
US10329938B2 (en) * | 2017-05-31 | 2019-06-25 | General Electric Company | Aspirating face seal starter tooth abradable pocket |
-
2015
- 2015-02-27 CN CN201580076962.8A patent/CN107250552B/zh active Active
- 2015-02-27 US US15/551,660 patent/US11028855B2/en active Active
- 2015-02-27 EP EP15883267.5A patent/EP3263909B1/en active Active
- 2015-02-27 JP JP2017501813A patent/JP6607580B2/ja active Active
- 2015-02-27 WO PCT/JP2015/055960 patent/WO2016135973A1/ja active Application Filing
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPH03237299A (ja) * | 1990-02-09 | 1991-10-23 | Toyota Motor Corp | 間隙調整皮膜層の製造方法 |
JPH10507245A (ja) * | 1995-10-07 | 1998-07-14 | ホルセット エンジニアリング カンパニー リミテッド | ターボ機構の摩耗シール |
JP2006144790A (ja) * | 2004-11-20 | 2006-06-08 | Borgwarner Inc | 圧縮機ハウジングの製造方法 |
JP2009522430A (ja) * | 2006-01-05 | 2009-06-11 | ゼネラル・エレクトリック・カンパニイ | マイクロカプセルを含む組成物を製造する方法及びそれにより製造される組成物 |
US20090232642A1 (en) * | 2008-03-12 | 2009-09-17 | Atte Anema | Adjustable compressor bleed system and method |
Non-Patent Citations (1)
Title |
---|
See also references of EP3263909A4 * |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2021505447A (ja) * | 2017-12-06 | 2021-02-18 | サフラン・エアクラフト・エンジンズ | ターボ機械ケーシングのコーティングのその場積層造形方法 |
JP2021505444A (ja) * | 2017-12-06 | 2021-02-18 | サフラン・エアクラフト・エンジンズ | アブレイダブル材料で作られた吸音チャネルの規則正しい網状組織を製造する方法 |
JP7250791B2 (ja) | 2017-12-06 | 2023-04-03 | サフラン・エアクラフト・エンジンズ | ターボ機械ケーシングのコーティングのその場積層造形方法 |
JP7304858B2 (ja) | 2017-12-06 | 2023-07-07 | サフラン・エアクラフト・エンジンズ | アブレイダブル材料で作られた吸音チャネルの規則正しい網状組織を製造する方法 |
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US11028855B2 (en) | 2021-06-08 |
EP3263909B1 (en) | 2020-08-19 |
EP3263909A4 (en) | 2018-12-05 |
JPWO2016135973A1 (ja) | 2018-01-18 |
JP6607580B2 (ja) | 2019-11-20 |
EP3263909A1 (en) | 2018-01-03 |
CN107250552A (zh) | 2017-10-13 |
US20180051707A1 (en) | 2018-02-22 |
CN107250552B (zh) | 2020-02-14 |
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