WO2018041938A1 - Modular turbo compressor shaft - Google Patents

Modular turbo compressor shaft Download PDF

Info

Publication number
WO2018041938A1
WO2018041938A1 PCT/EP2017/071849 EP2017071849W WO2018041938A1 WO 2018041938 A1 WO2018041938 A1 WO 2018041938A1 EP 2017071849 W EP2017071849 W EP 2017071849W WO 2018041938 A1 WO2018041938 A1 WO 2018041938A1
Authority
WO
WIPO (PCT)
Prior art keywords
turbo compressor
impeller
tubular bearing
compressor shaft
tubular
Prior art date
Application number
PCT/EP2017/071849
Other languages
French (fr)
Inventor
Patrice Bonnefoi
Arnaud DAUSSIN
Yves Rosson
Original Assignee
Danfoss Silicon Power Gmbh
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Danfoss Silicon Power Gmbh filed Critical Danfoss Silicon Power Gmbh
Priority to DE112017004422.7T priority Critical patent/DE112017004422B4/en
Priority to CN201780060808.0A priority patent/CN109790847B/en
Priority to US16/329,332 priority patent/US10794390B2/en
Publication of WO2018041938A1 publication Critical patent/WO2018041938A1/en

Links

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
    • F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
    • F04D29/053—Shafts
    • F04D29/054—Arrangements for joining or assembling shafts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/26—Starting; Ignition
    • F02C7/268—Starting drives for the rotor, acting directly on the rotor of the gas turbine to be started
    • F02C7/275—Mechanical drives
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
    • 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
    • F04D25/06—Units comprising pumps and their driving means the pump being electrically driven
    • 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
    • F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
    • F04D29/051—Axial thrust balancing
    • F04D29/0513—Axial thrust balancing hydrostatic; hydrodynamic thrust bearings
    • 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
    • F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
    • F04D29/053—Shafts
    • 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
    • F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
    • F04D29/056—Bearings
    • F04D29/057—Bearings hydrostatic; hydrodynamic
    • 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
    • F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C3/00—Shafts; Axles; Cranks; Eccentrics
    • F16C3/02—Shafts; Axles
    • F16C3/023—Shafts; Axles made of several parts, e.g. by welding
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02K—DYNAMO-ELECTRIC MACHINES
    • H02K1/00—Details of the magnetic circuit
    • H02K1/06—Details of the magnetic circuit characterised by the shape, form or construction
    • H02K1/22—Rotating parts of the magnetic circuit
    • H02K1/27—Rotor cores with permanent magnets
    • H02K1/2706—Inner rotors
    • H02K1/272—Inner rotors the magnetisation axis of the magnets being perpendicular to the rotor axis
    • H02K1/2726—Inner rotors the magnetisation axis of the magnets being perpendicular to the rotor axis the rotor consisting of a single magnet or two or more axially juxtaposed single magnets
    • H02K1/2733—Annular magnets
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02K—DYNAMO-ELECTRIC MACHINES
    • H02K7/00—Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
    • H02K7/003—Couplings; Details of shafts
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02K—DYNAMO-ELECTRIC MACHINES
    • H02K7/00—Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
    • H02K7/14—Structural association with mechanical loads, e.g. with hand-held machine tools or fans
    • 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
    • F05D2250/30—Arrangement of components
    • F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
    • F05D2250/311—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being in line
    • 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
    • F05D2250/30—Arrangement of components
    • F05D2250/36—Arrangement of components in inner-outer relationship, e.g. shaft-bearing arrangements
    • 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/37—Retaining components in desired mutual position by a press fit connection
    • 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
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/506—Hardness

Definitions

  • the present invention relates to a rotor shaft for a turbo compressor, and in particular for a high speed turbo compressor.
  • US4063850 discloses a gas turbine motor with a turbo compressor comprising notably:
  • turbo compressor shaft also named rotor shaft, including:
  • tubular bearing portion having a first axial end portion and a second axial end portion opposite to the first axial end portion
  • At least one compression stage configured to compress a refrigerant, the at least one compression stage including at least one impeller connected to the impeller portion of the turbo compressor shaft,
  • an axial bearing arrangement configured to limit an axial movement of the turbo compressor shaft during operation.
  • the tubular bearing portion and the driving portion are formed as an integral part, and are connected to the impeller portion by an annular fusing joint.
  • turbo compressor shaft is less costly to manufacture compared to monolithic turbo compressor shafts
  • the manufacturing of such a turbo compressor shaft is still expensive and time consuming due to the hard material used to make the driving portion. Indeed, such a hard material is difficult to machine, due to its high surface hardness.
  • connection between the tubular bearing portion and the impeller portion may lead to a breaking of said connection, and thus may harm the reliability of such a turbo compressor shaft, particularly when the turbo compressor shaft is driven at very high speeds.
  • fused joints may also be expensive to make, due to addition of special materials and necessary precise control of the temperature profiles during joining process.
  • Another object of the present invention is to provide a modular turbo compressor shaft which is reliable, and easier and less costly to manufacture.
  • such a modular turbo compressor shaft comprises:
  • tubular bearing portion having a first axial end portion and a second axial end portion opposite to the first axial end portion
  • tubular bearing portion is made of a hard material
  • the impeller portion and/or the driving portion are made of relatively soft material compared to the hard material of the tubular bearing portion
  • impeller portion and/or the driving portion is at least partially extending into the tubular bearing portion and are firmly connected to the tubular bearing portion
  • tubular bearing portion, the impeller portion and the driving portion are configured such that radial deformations, occurring during assembly of the impeller portion and/or the driving portion to the tubular bearing portion, are substantially limited to the driving portion and/or the impeller portion.
  • Such a configuration of the modular turbo compressor shaft reduces machining costs, as only the tubular bearing portion, which has to fulfil small tolerances and increased wear resistance, is made of hard material.
  • the other shaft portions made of softer (and less stiff) materials are easier to machine, and absorb the major part of radial deformations, which occur during the assembly (e.g. heat shrinking) process of the modular turbo compressor shaft.
  • tolerances of the outer surfaces of the impeller portion and/or the driving portion can be increased without any risk of over constraint on the tubular bearing portion.
  • the softer shaft portions take up the deformations occurring during compressor operation, caused by different coefficients of thermal expansion of hard and soft materials.
  • the modular turbo compressor shaft according to the present invention is more reliable, lighter, and easier and less costly to manufacture than conventional turbo compressor shafts.
  • the turbo compressor shaft may also include one or more of the following features, taken alone or in combination.
  • the impeller portion and the driving portion are at least partially extending into the tubular bearing portion and are firmly connected to the tubular bearing portion, the tubular bearing portion, the impeller portion and the driving portion being configured such that radial deformations, occurring during assembly of the impeller portion and the driving portion to the tubular bearing portion, are substantially limited to the driving portion and the impeller portion.
  • the impeller portion and/or the driving portion are connected to the tubular bearing portion by press-fit or shrink-fit, the tubular bearing portion, the impeller portion and the driving portion being configured such that radial deformations, occurring during shrink-fit or press-fit assembly of the impeller portion and/or the driving portion to the tubular bearing portion, are substantially limited to the driving portion and/or the impeller portion.
  • the impeller portion and/or the driving portion are connected to the tubular bearing portion by heat shrink-fit.
  • the impeller portion and/or the driving portion are radially deformable during assembly of the impeller portion and/or the driving portion to the tubular bearing portion.
  • the ratio between the Vickers hardness of the hard material of the tubular bearing portion and the Vickers hardness of the relatively soft material of the impeller portion is higher than 3.
  • the ratio between the Vickers hardness of the hard material of the tubular bearing portion and the Vickers hardness of the relatively soft material of the driving portion is higher than 3.
  • the tubular bearing portion includes:
  • a flat disc shaped part having an outer diameter larger than the outer diameter of the tubular cylindrical part, the flat disc shaped part having a first axial end face and a second axial end face opposite to the first axial end face, the first and second axial end faces being configured to cooperate with an axial bearing arrangement.
  • the driving portion is firmly connected to the tubular cylindrical part.
  • the impeller portion is firmly connected to the tubular cylindrical part and to the flat disc shaped part.
  • the flat disc shaped part includes a central opening having a diameter substantially corresponding to the inner diameter of the tubular cylindrical part.
  • the tubular cylindrical part and the flat disc shaped part are formed as an integral part or as two separate parts.
  • the tubular bearing portion is made of a high strength material having a high surface hardness.
  • the tubular bearing portion is made of tungsten carbide or ceramic materials.
  • the hard material of the tubular bearing portion has a Vickers hardness of more than 1500HV.
  • the relatively soft material of the impeller portion has a Vickers hardness of less than 500HV.
  • the impeller portion is made of titanium alloys or aluminum alloys.
  • the driving portion comprises:
  • the mounting part of the driving portion is arranged inside the tubular cylindrical part.
  • the mounting part of the driving portion is arranged inside the tubular bearing portion by shrink-fit or press-fit.
  • the mounting part of the driving portion includes a cylindrical outer surface.
  • the rotor attachment part includes an axial bore extending along at least a portion of the length of the rotor attachment part, the axial bore being configured to receive the rotor.
  • the rotor may comprise permanent magnets and may be firmly fitted, for example press fitted or shrink fitted, within the axial bore of the rotor attachment part.
  • the rotor attachment part is tubular.
  • the mounting part of the driving portion includes an axial hole extending along at least a portion of the length of the mounting part of the driving portion.
  • the axial hole provided on the driving portion extends at least partially into the tubular bearing portion.
  • Such a configuration of the driving portion increases the flexibility of the mounting part of the driving portion, and thus allows to further limit radial deformations of the tubular bearing portion occurring during the assembly of the turbo compressor shaft.
  • the driving portion is made of a titanium alloy or other non-magnetic material.
  • the relatively soft material of the driving portion has a Vickers hardness of less than 500HV.
  • the impeller portion comprises:
  • the mounting part of the impeller portion is at least partially arranged inside the tubular cylindrical part.
  • the mounting part of the impeller portion is connected to the tubular bearing portion by shrink-fit or press-fit.
  • the mounting part of the impeller portion includes an outer surface substantially cylindrical.
  • the mounting part of the impeller portion includes an axial hole extending along at least a portion of the length of said mounting part.
  • the axial hole provided on the impeller portion extends at least partially into the tubular bearing portion.
  • Such a configuration of the impeller portion increases the flexibility of the mounting part of the impeller portion, and thus allows to further limit radial deformations of the tubular bearing portion occurring during the assembly of the turbo compressor shaft.
  • the flat disc shaped part is connected to the mounting part of the impeller portion, and is arranged around said mounting part.
  • the flat disc shaped part is adjacent to an axial end of the tubular cylindrical part.
  • the flat disc shaped part extends radially outwardly with respect to the mounting part of the impeller portion.
  • the tubular bearing portion, the impeller portion and the driving portion extends along a same longitudinal axis.
  • the turbo compressor shaft is configured to be axially and radially supported by gas bearing arrangements formed at outer surfaces of the tubular bearing portion.
  • the present invention also relates to a centrifugal turbo compressor including a modular turbo compressor shaft according to the present invention.
  • the centrifugal turbo compressor further includes:
  • At least one compression stage configured to compress a refrigerant, the at least one compression stage including at least one impeller connected to the impeller portion of the turbo compressor shaft,
  • the centrifugal turbo compressor further includes a radial bearing arrangement configured for rotatably supporting the tubular bearing portion.
  • the radial bearing arrangement is a gas bearing arrangement.
  • the radial bearing arrangement is configured to cooperate with an outer surface of the tubular cylindrical part.
  • the radial bearing arrangement includes a radial bearing extending along at least a part of the length of the tubular cylindrical part.
  • the centrifugal turbo compressor further includes a thrust bearing arrangement configured to limit an axial movement of the turbo compressor shaft during operation.
  • the thrust bearing arrangement is located between the electric motor and the first compression stage.
  • the thrust bearing arrangement is configured to cooperate with the first and second axial end faces of the flat disc shaped part.
  • the thrust bearing arrangement is a gas bearing arrangement.
  • the thrust bearing arrangement includes a first annular thrust bearing element having a first thrust bearing surface, and a second annular thrust bearing element having a second thrust bearing surface, the first and second thrust bearing surfaces being configured to respectively cooperate with the first and second axial end faces of the flat disc shaped part.
  • Figure 1 is a longitudinal section view of a centrifugal turbo compressor including a turbo compressor shaft according to the invention.
  • Figure 2 is a longitudinal section view of the turbo compressor shaft of figure 1.
  • FIG. 3 is an exploded perspective view of the turbo compressor shaft of figure 1. Detailed description of the invention
  • FIG. 1 represents a centrifugal turbo compressor 2, and particularly a two-stage centrifugal turbo compressor.
  • the centrifugal turbo compressor 2 includes a hermetic housing 3, and a turbo compressor shaft 4 rotatably arranged within the hermetic housing 3 and extending along a longitudinal axis A.
  • the turbo compressor shaft 4 includes a tubular bearing portion 5, an impeller portion 6 arranged at a first axial end portion 5a of the tubular bearing portion 5, and a driving portion 7 arranged at a second axial end portion 5b of the tubular bearing portion 5.
  • the impeller portion 6 and the driving portion 7 are partially extending into the tubular bearing portion 5 and are firmly connected to the tubular bearing portion 5, by press-fit or shrink-fit.
  • the tubular bearing portion 5, the impeller portion 6 and the driving portion 7 are defined such that radial deformations, occurring during shrink-fit or press-fit assembly of the impeller portion 6 and the driving portion 7 to the tubular bearing portion 5, are substantially limited to the driving portion 7 and the impeller portion 6.
  • the tubular bearing portion 5 includes a tubular cylindrical part 8 having an outer surface 9 configured to cooperate with a radial bearing arrangement configured for rotatably and radially supporting the turbo compressor shaft 4.
  • the radial bearing arrangement includes at least one radial bearing 11, such as a radial sleeve bearing, located within the hermetic housing 3 and having an inner surface 12 configured to cooperate with the outer surface 9 of the tubular cylindrical part 8.
  • the or each radial bearing 11 may be a fluid radial bearing, and for example a gas radial bearing.
  • the radial bearing arrangement includes a plurality of radial bearings 11, for example two, distributed along the axial length of the tubular cylindrical part 8. However the radial bearing arrangement may include only one radial bearing 11 extending along the tubular cylindrical part 8.
  • the tubular bearing portion 5 further includes a flat disc shaped part 13 which extends coaxially with the tubular cylindrical part 8.
  • the flat disc shaped part 13 has an outer diameter larger than the outer diameter of the tubular cylindrical part 8, and includes a first axial end face 13a and a second axial end face 13b opposite to the first axial end face 13a.
  • the first and second axial end faces 13a, 13b are configured to cooperate with an axial bearing arrangement, also named thrust bearing arrangement, configured to limit an axial movement of the turbo compressor shaft 4 during operation.
  • the axial bearing arrangement includes a first annular thrust bearing element 14 and a second annular thrust bearing element 15 located within the hermetic housing 3.
  • the first annular thrust bearing element 14 has a first thrust bearing surface 16 configured to cooperate with the first axial end face 13a of the flat disc shaped part 13, and the second annular thrust bearing element 15 has a second thrust bearing surface 17 configured to cooperate with the second axial end face 13b of the flat disc shaped part 13.
  • the flat disc shaped part 13 is adjacent to an axial end of the tubular cylindrical part 8 which is opposite to the driving portion 7, and includes a central opening 18 having a diameter substantially corresponding to the inner diameter of the tubular cylindrical part 8.
  • the tubular cylindrical part 8 and the flat disc shaped part 13 are formed as two separate parts.
  • the tubular cylindrical part 8 and the flat disc shaped part 13 could be formed as an integral part.
  • the tubular bearing portion 5 (i.e. the tubular cylindrical part 8 and the flat disc shaped part 13) is made of a hard material having a Vickers hardness of more than 1500HV.
  • the tubular bearing portion 5 is made of a high strength material having a high surface hardness.
  • the tubular bearing portion 5 may be made of tungsten carbide or ceramic materials. Tungsten carbide is especially preferred, due to its relatively low thermal expansion coefficient combined with relatively high thermal conductivity, which is advantageous to control the clearance in the gas bearings and to remove heat during compressor operation. Hereby, the risk of bearing seizures is further reduced.
  • the driving portion 7 comprises a mounting part 19 and a tubular rotor attachment part 20 each extending along the longitudinal axis A of the turbo compressor shaft 4.
  • the mounting part 19 is arranged inside the tubular cylindrical part 8 of the tubular bearing portion 5, and has a cylindrical outer surface configured to cooperate with the inner surface of the tubular bearing portion 5.
  • the mounting part 19 of the driving portion 7 includes an axial hole 21 extending along at least a portion of the length of the mounting part 19 and emerging in a end face of the mounting part 19 opposite to the rotor attachment part 20.
  • the axial hole 21 extends into the tubular cylindrical part 8.
  • the tubular rotor attachment part 20 includes an axial bore 22 emerging in an end face of the tubular rotor attachment part 20 opposite to the impeller portion 6.
  • the axial bore 22 may also emerge into the axial hole 21.
  • the driving portion 7 is in one piece.
  • the mounting part 19 and the tubular rotor attachment part 20 could be formed as two separate parts connected together.
  • the driving portion 7 is made of relatively soft material compared to the hard material of the tubular bearing portion 5.
  • the relatively soft material of the driving portion 7 has a Vickers hardness of less than 500HV.
  • the driving portion 7 is made of a titanium alloy or other non-magnetic material.
  • the impeller portion 6 comprises a mounting part 23 and an impeller attachment part 24 each extending along the longitudinal axis A of the turbo compressor shaft 4.
  • the mounting part 23 is partially arranged inside the tubular cylindrical part 8, and includes an outer surface substantially cylindrical and configured to cooperate with the inner surface of the tubular cylindrical part 8.
  • the mounting part 23 of the impeller portion 6 includes an axial hole 25 extending along at least a portion of the length of the mounting part 23 and emerging in a end face of the mounting part 23 opposite to the impeller attachment part 24.
  • the axial hole 25 extends partially into the tubular cylindrical part 8.
  • the flat disc shaped part 13 is firmly connected to the mounting part 23 of the impeller portion 6 by press-fit or shrink-fit, and extends radially outwardly with respect to the mounting part 23 of the impeller portion 6.
  • the impeller portion 6 is in one piece.
  • the mounting part 23 and the impeller attachment part 24 could be formed as two separate parts connected together.
  • the impeller portion 6 is made of relatively soft material compared to the hard material of the tubular bearing portion 5.
  • the relatively soft material of the impeller portion 6 has a Vickers hardness of less than 500HV.
  • the impeller portion 6 is made of titanium alloys or aluminum alloys.
  • the centrifugal refrigeration compressor 2 further includes a first compression stage 26 and a second compression stage 27 configured to compress a refrigerant.
  • the first compression stage 26 includes a fluid inlet 28 and a fluid outlet 29, while the second compression stage 27 includes a fluid inlet 31 and a fluid outlet 32, the fluid outlet 29 of the first compression stage 26 being fluidly connected to the fluid inlet 31 of the second compression stage 27.
  • the hermetic housing 3 includes therefore a low pressure chamber located upstream the first compression stage 26, a high pressure chamber located downstream the second compression stage 27, and an intermediate pressure chamber provided between the fluid outlet 29 of the first compression stage 26 and the fluid inlet 31 of the second compression stage 27.
  • the first and second compression stages 26, 27 respectively include a first impeller 33 and a second impeller 34.
  • the first and second impellers 33, 34 are connected to the impeller attachment part 24.
  • the first and second impellers 33, 34 are provided on an impeller member 35 secured to the impeller attachment part 24, and are arranged in a back- to-back configuration, so that the directions of fluid flow at the fluid inlet 28, 31 of the first and second compression stages 26, 27 are opposite to each other.
  • Each of the first and second impellers 33, 34 includes a front side equipped with a plurality of blades configured to accelerate, during rotation of the turbo compressor shaft 4, the refrigerant entering the respective one of the first and second compression stages 26, 27, and to deliver the accelerated refrigerant to a diffuser arranged at the radial outside edge of the respective one of the first and second impellers 33, 34.
  • the centrifugal turbo compressor 2 is configured so that a part of the refrigerant compressed by the first and second compression stages 26, 27 is used as lubricating fluid in the gas radial bearing arrangement and the gas thrust bearing arrangement.
  • the centrifugal refrigeration compressor 2 further includes an electric motor 36 configured for driving in rotation the turbo compressor shaft 4 about its longitudinal axis A.
  • the electric motor 36 is arranged in the low pressure chamber defined by the hermetic housing 3.
  • the electric motor 36 includes a stator 37 and a rotor 38.
  • the rotor 38 comprises permanent magnets, and is firmly fitted, for example press fitted or shrink fitted, within the axial bore 22 of the rotor attachment part 20.
  • the thrust bearing arrangement is located between the electric motor 36 and the first compression stage 26.
  • Bearing portion Light weight, high strength, small dimensional tolerances and high hardness on outer surface for gas bearings, low thermal expansion coefficient, good thermal conductivity for heat removal,
  • Driving portion high strength to accommodate a high speed rotor, nonmagnetic, good thermal conductivity for heat removal, easy to machine due to larger tolerances, relatively soft to limit stress during connection with rotor and bearing portion,
  • Impeller portion high strength to accommodate at least one high speed impeller, easy to machine due to larger tolerances, relatively soft to limit stress during connection with impeller and bearing portions.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Power Engineering (AREA)
  • Ocean & Marine Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Supercharger (AREA)

Abstract

The Modular turbo compressor shaft (4) comprise a tubular bearing portion (5) having a first axial end portion and a second axial end portion; an impeller portion (6) arranged at the first axial end portion of the tubular bearing portion (5); and a driving portion (7) arranged at the second axial end portion of the tubular bearing portion (5). The tubular bearing portion (5) is made of a hard material, and the impeller portion (6) and/or the driving portion (7) are made of relatively soft material compared to the hard material of the tubular bearing portion (5). The impeller portion (6) and/or the driving portion (7) are at least partially extending into the tubular bearing portion (5) and are firmly connected to the tubular bearing portion (5). The tubular bearing portion (5), the impeller portion (6) and the driving portion (7) are configured such that radial deformations, occurring during assembly of the impeller portion (6) and/or the driving portion (7) to the tubular bearing portion (5), are substantially limited to the driving portion (7) and/or the impeller portion (6).

Description

MODULAR TURBO COMPRESSOR SHAFT
Field of the invention
The present invention relates to a rotor shaft for a turbo compressor, and in particular for a high speed turbo compressor.
Background of the invention
US4063850 discloses a gas turbine motor with a turbo compressor comprising notably:
- a turbo compressor shaft, also named rotor shaft, including:
- a tubular bearing portion having a first axial end portion and a second axial end portion opposite to the first axial end portion,
- an impeller portion arranged at the first axial end portion of the tubular bearing portion, and
- a driving portion arranged at the second axial end portion of the tubular bearing portion,
- at least one compression stage configured to compress a refrigerant, the at least one compression stage including at least one impeller connected to the impeller portion of the turbo compressor shaft,
- a radial bearing arrangement configured for rotatably supporting the tubular bearing portion, and
- an axial bearing arrangement configured to limit an axial movement of the turbo compressor shaft during operation.
Accoding to US4063850, the tubular bearing portion and the driving portion are formed as an integral part, and are connected to the impeller portion by an annular fusing joint.
Despite such a turbo compressor shaft is less costly to manufacture compared to monolithic turbo compressor shafts, the manufacturing of such a turbo compressor shaft is still expensive and time consuming due to the hard material used to make the driving portion. Indeed, such a hard material is difficult to machine, due to its high surface hardness.
Further, the disclosed fusing joint configuration of the connection between the tubular bearing portion and the impeller portion may lead to a breaking of said connection, and thus may harm the reliability of such a turbo compressor shaft, particularly when the turbo compressor shaft is driven at very high speeds. Such fused joints may also be expensive to make, due to addition of special materials and necessary precise control of the temperature profiles during joining process.
Summary of the invention
It is an object of the present invention to provide an improved turbo compressor shaft which can overcome the drawbacks encountered in conventional turbo compressor shafts.
Another object of the present invention is to provide a modular turbo compressor shaft which is reliable, and easier and less costly to manufacture.
According to the invention such a modular turbo compressor shaft comprises:
- a tubular bearing portion having a first axial end portion and a second axial end portion opposite to the first axial end portion,
- an impeller portion arranged at the first axial end portion of the tubular bearing portion, and
- a driving portion arranged at the second axial end portion of the tubular bearing portion,
wherein the tubular bearing portion is made of a hard material, and the impeller portion and/or the driving portion are made of relatively soft material compared to the hard material of the tubular bearing portion,
wherein the impeller portion and/or the driving portion is at least partially extending into the tubular bearing portion and are firmly connected to the tubular bearing portion, and
wherein the tubular bearing portion, the impeller portion and the driving portion are configured such that radial deformations, occurring during assembly of the impeller portion and/or the driving portion to the tubular bearing portion, are substantially limited to the driving portion and/or the impeller portion.
Such a configuration of the modular turbo compressor shaft reduces machining costs, as only the tubular bearing portion, which has to fulfil small tolerances and increased wear resistance, is made of hard material. The other shaft portions made of softer (and less stiff) materials are easier to machine, and absorb the major part of radial deformations, which occur during the assembly (e.g. heat shrinking) process of the modular turbo compressor shaft. Thus, tolerances of the outer surfaces of the impeller portion and/or the driving portion can be increased without any risk of over constraint on the tubular bearing portion. Further the softer shaft portions take up the deformations occurring during compressor operation, caused by different coefficients of thermal expansion of hard and soft materials.
Therefore the deformations of the tubular bearing portion occurring during the assembly of the modular turbo compressor shaft and occurring in operation are limited. This results in an improvement of the reliability of the radial and axial bearings supporting the modular turbo compressor shaft, particularly when gas bearings are used as they require very small clearance to be stable while requiring enough clearance to avoid bearing seizure.
Consequently, the modular turbo compressor shaft according to the present invention is more reliable, lighter, and easier and less costly to manufacture than conventional turbo compressor shafts.
The turbo compressor shaft may also include one or more of the following features, taken alone or in combination.
According to an embodiment of the invention, the impeller portion and the driving portion are at least partially extending into the tubular bearing portion and are firmly connected to the tubular bearing portion, the tubular bearing portion, the impeller portion and the driving portion being configured such that radial deformations, occurring during assembly of the impeller portion and the driving portion to the tubular bearing portion, are substantially limited to the driving portion and the impeller portion.
According to an embodiment of the invention, the impeller portion and/or the driving portion are connected to the tubular bearing portion by press-fit or shrink-fit, the tubular bearing portion, the impeller portion and the driving portion being configured such that radial deformations, occurring during shrink-fit or press-fit assembly of the impeller portion and/or the driving portion to the tubular bearing portion, are substantially limited to the driving portion and/or the impeller portion.
According to an embodiment of the invention, the impeller portion and/or the driving portion are connected to the tubular bearing portion by heat shrink-fit.
According to an embodiment of the invention, the impeller portion and/or the driving portion are radially deformable during assembly of the impeller portion and/or the driving portion to the tubular bearing portion.
According to an embodiment of the invention, the ratio between the Vickers hardness of the hard material of the tubular bearing portion and the Vickers hardness of the relatively soft material of the impeller portion is higher than 3. According to an embodiment of the invention, the ratio between the Vickers hardness of the hard material of the tubular bearing portion and the Vickers hardness of the relatively soft material of the driving portion is higher than 3.
According to an embodiment of the invention, the tubular bearing portion includes:
- a tubular cylindrical part having an outer surface configured to cooperate with a radial bearing arrangement of a turbo compressor, and
- a flat disc shaped part having an outer diameter larger than the outer diameter of the tubular cylindrical part, the flat disc shaped part having a first axial end face and a second axial end face opposite to the first axial end face, the first and second axial end faces being configured to cooperate with an axial bearing arrangement.
According to an embodiment of the invention, the driving portion is firmly connected to the tubular cylindrical part.
According to an embodiment of the invention, the impeller portion is firmly connected to the tubular cylindrical part and to the flat disc shaped part.
According to an embodiment of the invention, the flat disc shaped part includes a central opening having a diameter substantially corresponding to the inner diameter of the tubular cylindrical part.
According to an embodiment of the invention, the tubular cylindrical part and the flat disc shaped part are formed as an integral part or as two separate parts.
According to an embodiment of the invention, the tubular bearing portion is made of a high strength material having a high surface hardness.
According to an embodiment of the invention, the tubular bearing portion is made of tungsten carbide or ceramic materials.
According to an embodiment of the invention, the hard material of the tubular bearing portion has a Vickers hardness of more than 1500HV.
According to an embodiment of the invention, the relatively soft material of the impeller portion has a Vickers hardness of less than 500HV.
According to an embodiment of the invention, the impeller portion is made of titanium alloys or aluminum alloys.
According to an embodiment of the invention, the driving portion comprises:
- a mounting part arranged inside the tubular bearing portion, and - a rotor attachment part for the attachment of a rotor of the turbo compressor. According to an embodiment of the invention, the mounting part of the driving portion is arranged inside the tubular cylindrical part.
According to an embodiment of the invention, the mounting part of the driving portion is arranged inside the tubular bearing portion by shrink-fit or press-fit.
According to an embodiment of the invention, the mounting part of the driving portion includes a cylindrical outer surface.
According to an embodiment of the invention, the rotor attachment part includes an axial bore extending along at least a portion of the length of the rotor attachment part, the axial bore being configured to receive the rotor.
According to an embodiment of the invention, the rotor may comprise permanent magnets and may be firmly fitted, for example press fitted or shrink fitted, within the axial bore of the rotor attachment part.
According to an embodiment of the invention, the rotor attachment part is tubular.
According to an embodiment of the invention, the mounting part of the driving portion includes an axial hole extending along at least a portion of the length of the mounting part of the driving portion. Such a configuration of the driving portion reduces the weight of the latter, and thus of the turbo compressor shaft.
According to an embodiment of the invention, the axial hole provided on the driving portion extends at least partially into the tubular bearing portion. Such a configuration of the driving portion increases the flexibility of the mounting part of the driving portion, and thus allows to further limit radial deformations of the tubular bearing portion occurring during the assembly of the turbo compressor shaft.
According to an embodiment of the invention, the driving portion is made of a titanium alloy or other non-magnetic material.
According to an embodiment of the invention, the relatively soft material of the driving portion has a Vickers hardness of less than 500HV.
According to an embodiment of the invention, the impeller portion comprises:
- a mounting part at least partially arranged inside the tubular bearing portion, and
- an impeller attachment part for the attachment of at least one impeller. According to an embodiment of the invention, the mounting part of the impeller portion is at least partially arranged inside the tubular cylindrical part.
According to an embodiment of the invention, the mounting part of the impeller portion is connected to the tubular bearing portion by shrink-fit or press-fit. According to an embodiment of the invention, the mounting part of the impeller portion includes an outer surface substantially cylindrical.
According to an embodiment of the invention, the mounting part of the impeller portion includes an axial hole extending along at least a portion of the length of said mounting part. Such a configuration of the impeller portion reduces the weight of the latter, and thus of the turbo compressor shaft.
According to an embodiment of the invention, the axial hole provided on the impeller portion extends at least partially into the tubular bearing portion. Such a configuration of the impeller portion increases the flexibility of the mounting part of the impeller portion, and thus allows to further limit radial deformations of the tubular bearing portion occurring during the assembly of the turbo compressor shaft.
According to an embodiment of the invention, the flat disc shaped part is connected to the mounting part of the impeller portion, and is arranged around said mounting part.
According to an embodiment of the invention, the flat disc shaped part is adjacent to an axial end of the tubular cylindrical part.
According to an embodiment of the invention, the flat disc shaped part extends radially outwardly with respect to the mounting part of the impeller portion.
According to an embodiment of the invention, the tubular bearing portion, the impeller portion and the driving portion extends along a same longitudinal axis.
According to an embodiment of the invention, the turbo compressor shaft is configured to be axially and radially supported by gas bearing arrangements formed at outer surfaces of the tubular bearing portion.
The present invention also relates to a centrifugal turbo compressor including a modular turbo compressor shaft according to the present invention.
According to an embodiment of the invention, the centrifugal turbo compressor further includes:
- at least one compression stage configured to compress a refrigerant, the at least one compression stage including at least one impeller connected to the impeller portion of the turbo compressor shaft,
- an electric motor configured for driving in rotation the turbo compressor shaft about a rotation axis, the electric motor including a stator and a rotor, the rotor being connected to the driving portion of the turbo compressor shaft. According to an embodiment of the invention, the centrifugal turbo compressor further includes a radial bearing arrangement configured for rotatably supporting the tubular bearing portion.
According to an embodiment of the invention, the radial bearing arrangement is a gas bearing arrangement.
According to an embodiment of the invention, the radial bearing arrangement is configured to cooperate with an outer surface of the tubular cylindrical part.
According to an embodiment of the invention, the radial bearing arrangement includes a radial bearing extending along at least a part of the length of the tubular cylindrical part.
According to an embodiment of the invention, the centrifugal turbo compressor further includes a thrust bearing arrangement configured to limit an axial movement of the turbo compressor shaft during operation.
According to an embodiment of the invention, the thrust bearing arrangement is located between the electric motor and the first compression stage.
According to an embodiment of the invention, the thrust bearing arrangement is configured to cooperate with the first and second axial end faces of the flat disc shaped part.
According to an embodiment of the invention, the thrust bearing arrangement is a gas bearing arrangement.
According to an embodiment of the invention, the thrust bearing arrangement includes a first annular thrust bearing element having a first thrust bearing surface, and a second annular thrust bearing element having a second thrust bearing surface, the first and second thrust bearing surfaces being configured to respectively cooperate with the first and second axial end faces of the flat disc shaped part.
These and other advantages will become apparent upon reading the following description in view of the drawing attached hereto representing, as a non- limiting example, one embodiment of a turbo compressor shaft according to the invention.
Brief description of the drawings The following detailed description of one embodiment of the invention is better understood when read in conjunction with the appended drawings being understood, however, that the invention is not limited to the specific embodiment disclosed.
Figure 1 is a longitudinal section view of a centrifugal turbo compressor including a turbo compressor shaft according to the invention.
Figure 2 is a longitudinal section view of the turbo compressor shaft of figure 1.
Figure 3 is an exploded perspective view of the turbo compressor shaft of figure 1. Detailed description of the invention
Figure 1 represents a centrifugal turbo compressor 2, and particularly a two-stage centrifugal turbo compressor. The centrifugal turbo compressor 2 includes a hermetic housing 3, and a turbo compressor shaft 4 rotatably arranged within the hermetic housing 3 and extending along a longitudinal axis A.
As better shown on figures 2 and 3, the turbo compressor shaft 4 includes a tubular bearing portion 5, an impeller portion 6 arranged at a first axial end portion 5a of the tubular bearing portion 5, and a driving portion 7 arranged at a second axial end portion 5b of the tubular bearing portion 5. The impeller portion 6 and the driving portion 7 are partially extending into the tubular bearing portion 5 and are firmly connected to the tubular bearing portion 5, by press-fit or shrink-fit. Particularly, the tubular bearing portion 5, the impeller portion 6 and the driving portion 7 are defined such that radial deformations, occurring during shrink-fit or press-fit assembly of the impeller portion 6 and the driving portion 7 to the tubular bearing portion 5, are substantially limited to the driving portion 7 and the impeller portion 6.
The tubular bearing portion 5 includes a tubular cylindrical part 8 having an outer surface 9 configured to cooperate with a radial bearing arrangement configured for rotatably and radially supporting the turbo compressor shaft 4.
According to the embodiment shown on the figures, the radial bearing arrangement includes at least one radial bearing 11, such as a radial sleeve bearing, located within the hermetic housing 3 and having an inner surface 12 configured to cooperate with the outer surface 9 of the tubular cylindrical part 8. The or each radial bearing 11 may be a fluid radial bearing, and for example a gas radial bearing. According to the embodiment shown on the figures, the radial bearing arrangement includes a plurality of radial bearings 11, for example two, distributed along the axial length of the tubular cylindrical part 8. However the radial bearing arrangement may include only one radial bearing 11 extending along the tubular cylindrical part 8.
The tubular bearing portion 5 further includes a flat disc shaped part 13 which extends coaxially with the tubular cylindrical part 8. The flat disc shaped part 13 has an outer diameter larger than the outer diameter of the tubular cylindrical part 8, and includes a first axial end face 13a and a second axial end face 13b opposite to the first axial end face 13a. The first and second axial end faces 13a, 13b are configured to cooperate with an axial bearing arrangement, also named thrust bearing arrangement, configured to limit an axial movement of the turbo compressor shaft 4 during operation. According to the embodiment shown on the figures, the axial bearing arrangement includes a first annular thrust bearing element 14 and a second annular thrust bearing element 15 located within the hermetic housing 3. The first annular thrust bearing element 14 has a first thrust bearing surface 16 configured to cooperate with the first axial end face 13a of the flat disc shaped part 13, and the second annular thrust bearing element 15 has a second thrust bearing surface 17 configured to cooperate with the second axial end face 13b of the flat disc shaped part 13.
According to the embodiment shown on the figures, the flat disc shaped part 13 is adjacent to an axial end of the tubular cylindrical part 8 which is opposite to the driving portion 7, and includes a central opening 18 having a diameter substantially corresponding to the inner diameter of the tubular cylindrical part 8. Further, according to the embodiment shown on the figures, the tubular cylindrical part 8 and the flat disc shaped part 13 are formed as two separate parts. However, according to another embodiment of the invention, the tubular cylindrical part 8 and the flat disc shaped part 13 could be formed as an integral part.
Advantageously, the tubular bearing portion 5 (i.e. the tubular cylindrical part 8 and the flat disc shaped part 13) is made of a hard material having a Vickers hardness of more than 1500HV. According to an embodiment of the invention, the tubular bearing portion 5 is made of a high strength material having a high surface hardness. For example, the tubular bearing portion 5 may be made of tungsten carbide or ceramic materials. Tungsten carbide is especially preferred, due to its relatively low thermal expansion coefficient combined with relatively high thermal conductivity, which is advantageous to control the clearance in the gas bearings and to remove heat during compressor operation. Hereby, the risk of bearing seizures is further reduced. As better shown on figure 2, the driving portion 7 comprises a mounting part 19 and a tubular rotor attachment part 20 each extending along the longitudinal axis A of the turbo compressor shaft 4. The mounting part 19 is arranged inside the tubular cylindrical part 8 of the tubular bearing portion 5, and has a cylindrical outer surface configured to cooperate with the inner surface of the tubular bearing portion 5. Further, the mounting part 19 of the driving portion 7 includes an axial hole 21 extending along at least a portion of the length of the mounting part 19 and emerging in a end face of the mounting part 19 opposite to the rotor attachment part 20. Advantageously, the axial hole 21 extends into the tubular cylindrical part 8.
The tubular rotor attachment part 20 includes an axial bore 22 emerging in an end face of the tubular rotor attachment part 20 opposite to the impeller portion 6. The axial bore 22 may also emerge into the axial hole 21.
According to the embodiment shown on the figures, the driving portion 7 is in one piece. However, according to another embodiment of the invention, the mounting part 19 and the tubular rotor attachment part 20 could be formed as two separate parts connected together.
Advantageously, the driving portion 7 is made of relatively soft material compared to the hard material of the tubular bearing portion 5. According to an embodiment of the invention, the relatively soft material of the driving portion 7 has a Vickers hardness of less than 500HV. For example, the driving portion 7 is made of a titanium alloy or other non-magnetic material.
The impeller portion 6 comprises a mounting part 23 and an impeller attachment part 24 each extending along the longitudinal axis A of the turbo compressor shaft 4. The mounting part 23 is partially arranged inside the tubular cylindrical part 8, and includes an outer surface substantially cylindrical and configured to cooperate with the inner surface of the tubular cylindrical part 8. Further, the mounting part 23 of the impeller portion 6 includes an axial hole 25 extending along at least a portion of the length of the mounting part 23 and emerging in a end face of the mounting part 23 opposite to the impeller attachment part 24. Advantageously, the axial hole 25 extends partially into the tubular cylindrical part 8.
It should be noted that the flat disc shaped part 13 is firmly connected to the mounting part 23 of the impeller portion 6 by press-fit or shrink-fit, and extends radially outwardly with respect to the mounting part 23 of the impeller portion 6.
According to the embodiment shown on the figures, the impeller portion 6 is in one piece. However, according to another embodiment of the invention, the mounting part 23 and the impeller attachment part 24 could be formed as two separate parts connected together.
Advantageously, the impeller portion 6 is made of relatively soft material compared to the hard material of the tubular bearing portion 5. According to an embodiment of the invention, the relatively soft material of the impeller portion 6 has a Vickers hardness of less than 500HV. For example, the impeller portion 6 is made of titanium alloys or aluminum alloys.
The centrifugal refrigeration compressor 2 further includes a first compression stage 26 and a second compression stage 27 configured to compress a refrigerant. The first compression stage 26 includes a fluid inlet 28 and a fluid outlet 29, while the second compression stage 27 includes a fluid inlet 31 and a fluid outlet 32, the fluid outlet 29 of the first compression stage 26 being fluidly connected to the fluid inlet 31 of the second compression stage 27.
The hermetic housing 3 includes therefore a low pressure chamber located upstream the first compression stage 26, a high pressure chamber located downstream the second compression stage 27, and an intermediate pressure chamber provided between the fluid outlet 29 of the first compression stage 26 and the fluid inlet 31 of the second compression stage 27.
The first and second compression stages 26, 27 respectively include a first impeller 33 and a second impeller 34. The first and second impellers 33, 34 are connected to the impeller attachment part 24. According to the embodiment shown on the figures, the first and second impellers 33, 34 are provided on an impeller member 35 secured to the impeller attachment part 24, and are arranged in a back- to-back configuration, so that the directions of fluid flow at the fluid inlet 28, 31 of the first and second compression stages 26, 27 are opposite to each other.
Each of the first and second impellers 33, 34 includes a front side equipped with a plurality of blades configured to accelerate, during rotation of the turbo compressor shaft 4, the refrigerant entering the respective one of the first and second compression stages 26, 27, and to deliver the accelerated refrigerant to a diffuser arranged at the radial outside edge of the respective one of the first and second impellers 33, 34.
According to an embodiment of the invention, the centrifugal turbo compressor 2 is configured so that a part of the refrigerant compressed by the first and second compression stages 26, 27 is used as lubricating fluid in the gas radial bearing arrangement and the gas thrust bearing arrangement. The centrifugal refrigeration compressor 2 further includes an electric motor 36 configured for driving in rotation the turbo compressor shaft 4 about its longitudinal axis A. According to the embodiment shown on the figures, the electric motor 36 is arranged in the low pressure chamber defined by the hermetic housing 3.
The electric motor 36 includes a stator 37 and a rotor 38.
Advantageously, the rotor 38 comprises permanent magnets, and is firmly fitted, for example press fitted or shrink fitted, within the axial bore 22 of the rotor attachment part 20. According to the embodiment shown on the figures, the thrust bearing arrangement is located between the electric motor 36 and the first compression stage 26.
The different portions of a rotor shaft according to the invention are optimized in relation to their function, manufacturability and costs:
Bearing portion: Light weight, high strength, small dimensional tolerances and high hardness on outer surface for gas bearings, low thermal expansion coefficient, good thermal conductivity for heat removal,
Driving portion: high strength to accommodate a high speed rotor, nonmagnetic, good thermal conductivity for heat removal, easy to machine due to larger tolerances, relatively soft to limit stress during connection with rotor and bearing portion,
Impeller portion: high strength to accommodate at least one high speed impeller, easy to machine due to larger tolerances, relatively soft to limit stress during connection with impeller and bearing portions.
Of course, the invention is not restricted to the embodiment described above by way of non-limiting example, but on the contrary it encompasses all embodiments thereof.

Claims

1. Modular turbo compressor shaft (4) comprising:
- a tubular bearing portion (5) having a first axial end portion (5a) and a second axial end portion (5b) opposite to the first axial end portion (5a),
- an impeller portion (6) arranged at the first axial end portion (5a) of the tubular bearing portion (5), and
- a driving portion (7) arranged at the second axial end portion (5b) of the tubular bearing portion (5),
wherein the tubular bearing portion (5) is made of a hard material, and the impeller portion (6) and/or the driving portion (7) are made of relatively soft material compared to the hard material of the tubular bearing portion (5),
characterized in that the impeller portion (6) and/or the driving portion (7) are at least partially extending into the tubular bearing portion (5) and are firmly connected to the tubular bearing portion (5), and in that the tubular bearing portion
(5) , the impeller portion (6) and the driving portion (7) are configured such that radial deformations, occurring during assembly of the impeller portion (6) and/or the driving portion (7) to the tubular bearing portion (5), are substantially limited to the driving portion (7) a nd/or the impeller portion (6).
2. The modular turbo compressor shaft (4) according to claim 1, wherein the impeller portion (6) and/or the driving portion (7) are connected to the tubular bearing portion (5) by press-fit or shrink-fit, the tubular bearing portion (5), the impeller portion (6) and the driving portion (7) being configured such that radial deformations, occurring during shrink-fit or press-fit assembly of the im peller portion
(6) and/or the driving portion (7) to the tubular bearing portion (5), are substantially limited to the driving portion (7) and/or the impeller portion (6).
3. The modular turbo compressor shaft (4) according to claim 1 or 2, wherein:
- the ratio between the Vickers hardness of the hard material of the tubular bearing portion (5) and the Vickers hardness of the relatively soft material of the impeller portion (6) is higher than 3, and/or
- the ratio between the Vickers hardness of the hard material of the tubular bearing portion (5) and the Vickers hardness of the relatively soft material of the driving portion (7) is higher than 3.
4. The modular turbo compressor shaft (4) according to any one of claims 1 to 3, wherein the tubular bearing portion (5) includes:
- a tubular cylindrical part (8) having an outer surface (9) configured to cooperate with a radial bearing arrangement of a turbo compressor (2), and
- a flat disc shaped part (13) having an outer diameter larger than the outer diameter of the tubular cylindrical part (8), the flat disc shaped part (13) having a first axial end face (13a) and a second axial end face (13b) opposite to the first axial end face (13a), the first and second axial end faces (13a, 13b) being configured to cooperate with an axial bearing arrangement.
5. The modular turbo compressor shaft (4) according to claim 4, wherein the flat disc shaped part (13) includes a central opening (18) having a diameter substantially corresponding to the inner diameter of the tubular cylindrical part (8).
6. The modular turbo compressor shaft (4) according to claim 4 or 5, wherein the tubular cylindrical part (8) and the flat disc shaped part (13) are formed as an integral part or as two separate parts.
7. The modular turbo compressor shaft (4) according to any one of claims
1 to 6, wherein the hard material of the tubular bearing portion (5) has a Vickers hardness of more than 1500HV.
8. The modular turbo compressor shaft (4) according to any one of claims 1 to 7, wherein:
- the relatively soft material of the impeller portion (6) has a Vickers hardness of less than 500HV, and/or
- the relatively soft material of the driving portion (7) has a Vickers hardness of less than 500HV.
10. The modular turbo compressor shaft (4) according to claim 9, wherein the rotor attachment part (20) includes an axial bore (22) configured to receive the rotor (38).
11. The modular turbo compressor shaft (4) according to claim 9 or 10, wherein the mounting part (19) of the driving portion (7) includes an axial hole (21) extending along at least a portion of the length of the mounting part (19) of the driving portion (7).
12. The modular turbo compressor shaft (4) according to any one of claims 1 to 11, wherein the impeller portion (6) comprises:
- a mounting part (23) at least partially arranged inside the tubular bearing portion (5), and
- an impeller attachment part (24) for the attachment of at least one impeller.
13. The modular turbo compressor shaft (4) according to claim 12, wherein the mounting part (23) of the impeller portion (6) includes an axial hole (25) extending along at least a portion of the length of the mounting part (23) of the impeller portion (6).
14. A centrifugal turbo compressor (2) including a modular turbo compressor shaft (4) according to any one of claims 1 to 13.
15. The centrifugal turbo compressor (2) according to claim 14, further including:
- at least one compression stage (26, 27) configured to compress a refrigerant, the at least one compression stage (26, 27) including at least one impeller (33, 34) connected to the impeller portion (6) of the turbo compressor shaft (4),
- an electric motor (36) configured for driving in rotation the turbo compressor shaft (4) about a rotation axis, the electric motor (36) including a stator (37) and a rotor (38), the rotor (38) being connected to the driving portion (7) of the turbo compressor shaft (4).
16. The centrifugal turbo compressor (2) according to claim 14 or 15, further including:
- a radial bearing arrangement configured for rotatably supporting the tubular bearing portion (5), and
- a thrust bearing arrangement configured to limit an axial movement of the turbo compressor shaft (4) during operation.
PCT/EP2017/071849 2016-09-02 2017-08-31 Modular turbo compressor shaft WO2018041938A1 (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
DE112017004422.7T DE112017004422B4 (en) 2016-09-02 2017-08-31 Modular turbo compressor shaft
CN201780060808.0A CN109790847B (en) 2016-09-02 2017-08-31 Modular turbo-compressor shaft
US16/329,332 US10794390B2 (en) 2016-09-02 2017-08-31 Modular turbo compressor shaft

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1658169A FR3055677B1 (en) 2016-09-02 2016-09-02 MODULAR TURBOCHARGER SHAFT
FR1658169 2016-09-02

Publications (1)

Publication Number Publication Date
WO2018041938A1 true WO2018041938A1 (en) 2018-03-08

Family

ID=57539390

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2017/071849 WO2018041938A1 (en) 2016-09-02 2017-08-31 Modular turbo compressor shaft

Country Status (5)

Country Link
US (1) US10794390B2 (en)
CN (1) CN109790847B (en)
DE (1) DE112017004422B4 (en)
FR (1) FR3055677B1 (en)
WO (1) WO2018041938A1 (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3613993A1 (en) * 2018-08-22 2020-02-26 Danfoss A/S A turbo compressor provided with an axial bearing cooling arrangement
EP4117145A1 (en) 2021-07-07 2023-01-11 Celeroton AG Rotor for a high-speed electrical machine
EP4117146A1 (en) 2021-07-07 2023-01-11 Celeroton AG Rotor for a high-speed electrical machine

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3063778A1 (en) * 2017-03-08 2018-09-14 BD Kompressor GmbH CENTRIFUGAL TURBOCHARGER
US11434918B2 (en) * 2019-06-21 2022-09-06 Danfoss A/S Partially hollow shaft for HVAC compressor
FR3101208B1 (en) * 2019-09-23 2023-06-30 Ifp Energies Now Hybrid transient magnet rotor
US11560900B2 (en) 2020-06-09 2023-01-24 Emerson Climate Technologies, Inc. Compressor driveshaft assembly and compressor including same
KR102660781B1 (en) 2021-12-21 2024-04-26 엘지전자 주식회사 Turbo compressor

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4063850A (en) 1975-12-03 1977-12-20 Motoren- Und Turbinen-Union Munchen Gmbh Gas turbine engine having a ceramic turbine wheel
WO1998034324A1 (en) * 1997-01-29 1998-08-06 Turbocorp Limited Improvements in high speed rotor shafts
DE102008056061A1 (en) * 2008-08-04 2010-02-11 Mtu Friedrichshafen Gmbh Turbosupercharger for internal-combustion engine, has sleeve provided in radial bearing, and axial-thrust bearing disk frictionally clamped with sleeve through screwing shaft stubs by set of threading parts

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
AUPO478297A0 (en) * 1997-01-24 1997-02-20 Commonwealth Scientific And Industrial Research Organisation Improvements in high speed electric motors
JP2002213385A (en) * 2001-01-19 2002-07-31 Ebara Corp Canned motor and canned motor pump
US6866478B2 (en) 2002-05-14 2005-03-15 The Board Of Trustees Of The Leland Stanford Junior University Miniature gas turbine engine with unitary rotor shaft for power generation
JP2007092646A (en) * 2005-09-29 2007-04-12 Jtekt Corp Supercharger for fuel cell
JP4961485B2 (en) * 2010-03-30 2012-06-27 本田技研工業株式会社 Dynamic pressure type foil type gas bearing
CN102322448B (en) * 2011-09-02 2013-02-27 西安交通大学 Cooling structure of motor-driven high-speed centrifugal air compressor
US9028220B2 (en) * 2011-10-24 2015-05-12 Hamilton Sundstrand Corporation Tie rod
FR3034460B1 (en) * 2015-04-01 2019-07-19 Liebherr-Aerospace Toulouse Sas ROTOR AND ROTOR TURBOMACHINE ASSEMBLY AT VERY HIGH SPEEDS INCLUDING SUCH A ROTOR ASSEMBLY
CN105889096B (en) * 2016-05-06 2019-10-18 同济大学 The two-stage series connection pressurization of fuel battery engines is straight to drive centrifugal air compressor

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4063850A (en) 1975-12-03 1977-12-20 Motoren- Und Turbinen-Union Munchen Gmbh Gas turbine engine having a ceramic turbine wheel
WO1998034324A1 (en) * 1997-01-29 1998-08-06 Turbocorp Limited Improvements in high speed rotor shafts
DE102008056061A1 (en) * 2008-08-04 2010-02-11 Mtu Friedrichshafen Gmbh Turbosupercharger for internal-combustion engine, has sleeve provided in radial bearing, and axial-thrust bearing disk frictionally clamped with sleeve through screwing shaft stubs by set of threading parts

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3613993A1 (en) * 2018-08-22 2020-02-26 Danfoss A/S A turbo compressor provided with an axial bearing cooling arrangement
FR3085188A1 (en) * 2018-08-22 2020-02-28 Danfoss A/S A TURBOCHARGER WITH AN AXIAL BEARING COOLING ARRANGEMENT
EP4117145A1 (en) 2021-07-07 2023-01-11 Celeroton AG Rotor for a high-speed electrical machine
EP4117146A1 (en) 2021-07-07 2023-01-11 Celeroton AG Rotor for a high-speed electrical machine
WO2023280894A1 (en) 2021-07-07 2023-01-12 Celeroton Ag Rotor for a high-speed electrical machine
WO2023280893A1 (en) 2021-07-07 2023-01-12 Celeroton Ag Rotor for a high-speed electrical machine

Also Published As

Publication number Publication date
CN109790847B (en) 2021-02-05
DE112017004422T5 (en) 2019-07-25
FR3055677B1 (en) 2020-05-29
US10794390B2 (en) 2020-10-06
FR3055677A1 (en) 2018-03-09
DE112017004422B4 (en) 2023-12-28
CN109790847A (en) 2019-05-21
US20190249682A1 (en) 2019-08-15

Similar Documents

Publication Publication Date Title
US10794390B2 (en) Modular turbo compressor shaft
CN110431310B (en) Support structure for a drive shaft of a turbomachine and turbomachine comprising such a support structure
WO2016193002A1 (en) A centrifugal refrigeration compressor
US11480194B2 (en) Turbo compressor
US10619645B2 (en) Centrifugal compressor having an inter-stage sealing arrangement
WO2002027190A1 (en) Multi-stage impeller
US10494937B2 (en) Inner ring for an annular guide vane assembly of a turbomachine
WO2015076217A1 (en) Impeller, rotary machine, and impeller manufacturing method
WO2018162660A1 (en) A double-stage impeller arrangement for a double-stage centrifugal turbo-compressor
US11530706B2 (en) Rotating body, turbocharger, and rotating body manufacturing method
CN101131092A (en) Methods and apparatus for fabricating a rotor for a steam turbine
CN108350798B (en) Mounting structure and supercharger
JP3144272U (en) Turbo molecular pump
KR20230014711A (en) Compressor drive shaft assembly and compressor including the same
JP6403020B2 (en) Touchdown bearing and rotating machine
EP4117145A1 (en) Rotor for a high-speed electrical machine
EP4117146A1 (en) Rotor for a high-speed electrical machine
US20240093701A1 (en) Rotor assembly for a turbomolecular pump
EP0806571A2 (en) A rotatable assembly for supporting the rotor of a vacuum pump
JPH09144691A (en) Turbo-compressor
CN111371213A (en) Compressor rotor, compressor and refrigerant circulation system

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 17765114

Country of ref document: EP

Kind code of ref document: A1

122 Ep: pct application non-entry in european phase

Ref document number: 17765114

Country of ref document: EP

Kind code of ref document: A1