WO2016184412A1 - 一种超高速燃气轮发电机 - Google Patents

一种超高速燃气轮发电机 Download PDF

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Publication number
WO2016184412A1
WO2016184412A1 PCT/CN2016/082709 CN2016082709W WO2016184412A1 WO 2016184412 A1 WO2016184412 A1 WO 2016184412A1 CN 2016082709 W CN2016082709 W CN 2016082709W WO 2016184412 A1 WO2016184412 A1 WO 2016184412A1
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WIPO (PCT)
Prior art keywords
high speed
gas turbine
groove pattern
turbine generator
speed gas
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PCT/CN2016/082709
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English (en)
French (fr)
Inventor
罗立峰
Original Assignee
罗立峰
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Publication date
Priority claimed from PCT/CN2015/079234 external-priority patent/WO2016183788A1/zh
Priority claimed from PCT/CN2015/079233 external-priority patent/WO2016183787A1/zh
Application filed by 罗立峰 filed Critical 罗立峰
Publication of WO2016184412A1 publication Critical patent/WO2016184412A1/zh

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    • 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
    • H02K7/18—Structural association of electric generators with mechanical driving motors, e.g. with turbines
    • H02K7/1807—Rotary generators
    • H02K7/1823—Rotary generators structurally associated with turbines or similar engines
    • H02K7/183—Rotary generators structurally associated with turbines or similar engines wherein the turbine is a wind turbine
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • F02B37/04—Engines with exhaust drive and other drive of pumps, e.g. with exhaust-driven pump and mechanically-driven second pump
    • F02B37/10—Engines with exhaust drive and other drive of pumps, e.g. with exhaust-driven pump and mechanically-driven second pump at least one pump being alternatively or simultaneously driven by exhaust and other drive, e.g. by pressurised fluid from a reservoir or an engine-driven pump
    • 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
    • F16C17/00—Sliding-contact bearings for exclusively rotary movement
    • F16C17/02—Sliding-contact bearings for exclusively rotary movement for radial load only
    • 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
    • F04D25/08—Units comprising pumps and their driving means the working fluid being air, e.g. for ventilation
    • 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
    • F16C17/00—Sliding-contact bearings for exclusively rotary movement
    • F16C17/04—Sliding-contact bearings for exclusively rotary movement for axial load only
    • F16C17/042—Sliding-contact bearings for exclusively rotary movement for axial load only with flexible leaves to create hydrodynamic wedge, e.g. axial foil bearings
    • 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
    • F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
    • F01D15/10—Adaptations for driving, or combinations with, electric generators
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B41/00—Engines characterised by special means for improving conversion of heat or pressure energy into mechanical power
    • F02B41/02—Engines with prolonged expansion
    • F02B41/10—Engines with prolonged expansion in exhaust turbines
    • 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
    • F02C7/06—Arrangements of bearings; Lubricating
    • 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
    • F02C7/12—Cooling of plants
    • 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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
    • 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
    • F04D29/58—Cooling; Heating; Diminishing heat transfer
    • F04D29/582—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps
    • 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
    • F16C17/00—Sliding-contact bearings for exclusively rotary movement
    • F16C17/02—Sliding-contact bearings for exclusively rotary movement for radial load only
    • F16C17/026—Sliding-contact bearings for exclusively rotary movement for radial load only with helical grooves in the bearing surface to generate hydrodynamic pressure, e.g. herringbone grooves
    • 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
    • F16C17/00—Sliding-contact bearings for exclusively rotary movement
    • F16C17/04—Sliding-contact bearings for exclusively rotary movement for axial load only
    • F16C17/08—Sliding-contact bearings for exclusively rotary movement for axial load only for supporting the end face of a shaft or other member, e.g. footstep bearings
    • 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
    • F16C17/00—Sliding-contact bearings for exclusively rotary movement
    • F16C17/10—Sliding-contact bearings for exclusively rotary movement for both radial and axial load
    • F16C17/102—Sliding-contact bearings for exclusively rotary movement for both radial and axial load with grooves in the bearing surface to generate hydrodynamic pressure
    • F16C17/107—Sliding-contact bearings for exclusively rotary movement for both radial and axial load with grooves in the bearing surface to generate hydrodynamic pressure with at least one surface for radial load and at least one surface for axial load
    • 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
    • F16C17/00—Sliding-contact bearings for exclusively rotary movement
    • F16C17/26—Systems consisting of a plurality of sliding-contact bearings
    • 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
    • F16C32/00—Bearings not otherwise provided for
    • F16C32/06—Bearings not otherwise provided for with moving member supported by a fluid cushion formed, at least to a large extent, otherwise than by movement of the shaft, e.g. hydrostatic air-cushion bearings
    • F16C32/0603—Bearings not otherwise provided for with moving member supported by a fluid cushion formed, at least to a large extent, otherwise than by movement of the shaft, e.g. hydrostatic air-cushion bearings supported by a gas cushion, e.g. an air cushion
    • 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
    • F16C33/00—Parts of bearings; Special methods for making bearings or parts thereof
    • F16C33/02—Parts of sliding-contact bearings
    • 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
    • F16C33/00—Parts of bearings; Special methods for making bearings or parts thereof
    • F16C33/02—Parts of sliding-contact bearings
    • F16C33/04—Brasses; Bushes; Linings
    • 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
    • F16C33/00—Parts of bearings; Special methods for making bearings or parts thereof
    • F16C33/02—Parts of sliding-contact bearings
    • F16C33/04—Brasses; Bushes; Linings
    • F16C33/06—Sliding surface mainly made of metal
    • F16C33/10—Construction relative to lubrication
    • F16C33/1005—Construction relative to lubrication with gas, e.g. air, as lubricant
    • 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
    • F16C37/00—Cooling of bearings
    • F16C37/002—Cooling of bearings of fluid bearings
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02K—DYNAMO-ELECTRIC MACHINES
    • H02K5/00—Casings; Enclosures; Supports
    • H02K5/04—Casings or enclosures characterised by the shape, form or construction thereof
    • H02K5/16—Means for supporting bearings, e.g. insulating supports or means for fitting bearings in the bearing-shields
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02K—DYNAMO-ELECTRIC MACHINES
    • H02K5/00—Casings; Enclosures; Supports
    • H02K5/04—Casings or enclosures characterised by the shape, form or construction thereof
    • H02K5/16—Means for supporting bearings, e.g. insulating supports or means for fitting bearings in the bearing-shields
    • H02K5/161—Means for supporting bearings, e.g. insulating supports or means for fitting bearings in the bearing-shields radially supporting the rotary shaft at both ends of the rotor
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02K—DYNAMO-ELECTRIC MACHINES
    • H02K5/00—Casings; Enclosures; Supports
    • H02K5/04—Casings or enclosures characterised by the shape, form or construction thereof
    • H02K5/16—Means for supporting bearings, e.g. insulating supports or means for fitting bearings in the bearing-shields
    • H02K5/163—Means for supporting bearings, e.g. insulating supports or means for fitting bearings in the bearing-shields radially supporting the rotary shaft at only one end of the rotor
    • 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
    • H02K7/18—Structural association of electric generators with mechanical driving motors, e.g. with turbines
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02K—DYNAMO-ELECTRIC MACHINES
    • H02K9/00—Arrangements for cooling or ventilating
    • H02K9/02—Arrangements for cooling or ventilating by ambient air flowing through the machine
    • H02K9/04—Arrangements for cooling or ventilating by ambient air flowing through the machine having means for generating a flow of cooling medium
    • H02K9/06—Arrangements for cooling or ventilating by ambient air flowing through the machine having means for generating a flow of cooling medium with fans or impellers driven by the machine shaft
    • 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
    • F16C17/00—Sliding-contact bearings for exclusively rotary movement
    • F16C17/02—Sliding-contact bearings for exclusively rotary movement for radial load only
    • F16C17/028—Sliding-contact bearings for exclusively rotary movement for radial load only with fixed wedges to generate hydrodynamic pressure, e.g. multi-lobe bearings
    • 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
    • F16C2360/00—Engines or pumps
    • F16C2360/23—Gas turbine engines

Definitions

  • the invention relates to an ultra-high speed gas turbine generator, belonging to the technical field of high precision machinery.
  • the gas turbine generator is an internal combustion type power machine that uses a continuous flow of gas as a working medium to drive the impeller to rotate at a high speed and convert the energy of the fuel into useful work. It is a rotary impeller type heat engine composed of a gas turbine and a generator.
  • the necessary backup power supply for important places such as oil fields, power plants, telecommunications buildings, high-rise buildings, hotels, living quarters, shopping malls, hospitals, military, conference centers, remote areas, islands, etc., and necessary mobile power sources for emergencies, field operations, etc. It can also be used as ship power and power peaking.
  • micro-turbine generators with air bearings have small size, light weight, strong fuel adaptability, low fuel consumption, low noise, low vibration, low pollution emissions, and maintenance costs.
  • a series of advanced technical features such as low cost and no need for water cooling have begun to be applied in military and civilian transportation (hybrid vehicles) and land and coastal defense, and have been highly valued and paid attention by the United States and Russia.
  • the structure is complicated, and it is not suitable for industrialization; the reliability is poor, and it is easy to be unstable or even stuck during high-speed operation; the heat generated by high-speed operation cannot be effectively exported, and can not be continuously operated for a long time; It is bulky and cannot meet the requirements of today's miniaturization.
  • An ultra-high speed gas turbine generator comprising a turbine, a compressor, a motor, two radial bearings, a thrust bearing and a combustion chamber, the turbine comprising a turbine, a turbine deflector and a turbine deflector housing,
  • the compressor comprises a pressure wheel, a compressor housing and a compressor diffuser, the motor comprising a rotor, a stator, an inner shaft, an outer shaft and a motor housing; wherein the radial bearing is a trough a hydrodynamic gas radial bearing comprising a bearing sleeve and a bearing inner sleeve;
  • the thrust bearing is a hybrid dynamic pressure gas thrust bearing comprising two side discs and a middle disc sandwiched between the two side discs,
  • a foil-type elastic member is disposed between each of the side plates and the middle plate; the rotor is sleeved in the middle of the inner shaft, and two radial bearings are respectively sleeved on the outer shafts at the left and
  • the turbine and the compressor are respectively disposed at both ends of the inner shaft, and the combustion chamber is disposed at the turbine end.
  • combustion chamber is disposed in the middle of the inner shaft, and the turbine and the compressor are respectively disposed at two ends of the inner shaft or back to back at one end of the inner shaft.
  • the ultra-high speed gas turbine generator further includes a left radial bearing sleeve and a left bearing chamber end cover, the turbine deflector housing is fixedly connected with the left bearing chamber end cover, and the left bearing chamber end cover and the left
  • the radial bearing sleeve is fixedly connected
  • the housing of the combustion chamber is fixedly connected with the left radial bearing sleeve
  • the left radial bearing sleeve is fixedly connected with the motor housing.
  • the ultra high speed gas turbine generator further includes a right radial bearing sleeve and a right bearing chamber end cover, the compressor housing is fixedly connected with the right bearing chamber end cover, and the right bearing chamber end cover and the right radial direction
  • the bearing sleeve is fixedly connected, and the right radial bearing sleeve is fixedly connected to the motor housing.
  • the surface of the inner shaft is provided with a heat dissipation spiral groove to facilitate heat dissipation of the rotating shaft and the bearing chamber.
  • a plurality of open slots are defined in a peripheral side of the inner wall of the motor housing, and a plurality of vent holes are formed in an end surface of the motor housing, and the open slots communicate with the vent holes to facilitate gas introduction and derivation.
  • the open slots communicate with the vent holes to facilitate gas introduction and derivation.
  • the outer circumferential surface and the both end surfaces of the bearing inner sleeve have a regular pattern of grooves.
  • the groove pattern of one end surface of the bearing inner sleeve is mirror-symmetrical with the groove pattern of the other end surface, and the axial contour line of the groove pattern of the outer circumferential surface and the groove pattern of the both end surfaces
  • the radial contour lines form a one-to-one correspondence and intersect each other.
  • the axial high line in the groove pattern of the outer circumferential surface of the bearing inner sleeve corresponds to the radial high line in the groove pattern on both end faces, and is mutually overlapped before the end face is chamfered.
  • the axial median line in the groove pattern of the outer circumferential surface corresponds to the radial median line in the groove pattern on both end faces, and is mutually overlapped before the end face is chamfered;
  • the axial lower line in the middle corresponds to the radially lower line in the groove pattern on both end faces, and is mutually overlapped before the end face is chamfered.
  • the matching gap between the bearing inner sleeve and the bearing outer sleeve is 0.003 to 0.008 mm.
  • a stop ring is provided at both ends of the bearing housing.
  • both end faces of the middle plate are provided with a regular pattern of groove patterns, and the groove pattern of one end face is mirror-symmetrical with the groove pattern of the other end face.
  • the outer circumferential surface of the intermediate disk is also provided with a groove pattern, and the shape of the groove pattern of the outer circumferential surface is the same as the shape of the groove pattern on both end faces, and the groove pattern of the outer circumferential surface
  • the axial contour line forms a one-to-one correspondence with the radial contour lines of the groove patterns on both end faces and intersects each other.
  • the axial high line in the groove pattern of the outer circumferential surface of the middle disk corresponds to the radial high line in the groove pattern on both end faces, and is mutually overlapped before the end face is chamfered; the outer circumference In the axial direction of the groove pattern
  • the bit line corresponds to the radial median line in the groove pattern on both end faces, and crosses each other before the end face is chamfered; the axial low line and the groove pattern on both end faces in the groove pattern of the outer circumferential surface
  • the radial lower bit lines in the middle correspond to each other and overlap each other before the end face is chamfered.
  • a wear-resistant coating is provided on the mating surface of the foil-type elastic member that is fitted to the intermediate disk.
  • the fitting gap between the foil-type elastic member and the middle plate is 0.003 to 0.008 mm.
  • At least one end of the foil-type elastic member is fixed to an inner end surface of the corresponding side disk.
  • the foil-type elastic members on each of the side plates are plural and evenly distributed along the inner end faces of the side plates.
  • the foil-type elastic member fixed to one side disk is mirror-symmetrical to the foil-shaped elastic member fixed to the other side disk.
  • a card slot for fixing the foil-type elastic member is provided on the inner end surface of the side disk.
  • the foil-type elastic member is composed of a wave foil and a flat foil, and the curved convex top end of the wave foil is attached to the flat foil.
  • the foil-type elastic member is composed of a wave foil and a flat foil, and the inter-wave arch transition bottom edge of the wave foil is in contact with the flat foil.
  • the foil-type elastic member is composed of two flat foils.
  • the above-mentioned groove patterns are all impeller shapes.
  • the above-mentioned foil-type elastic member is preferably subjected to surface heat treatment.
  • the rotor comprises a rotor base, a magnetic steel and a magnetic steel protective sleeve, the rotor base is sleeved on the inner shaft, the magnetic steel sleeve is disposed at a central portion of the rotor base, and the magnetic steel protective sleeve is sleeved On the magnetic steel.
  • the stator comprises a core and a winding, the core being fixed on an inner wall of a motor housing located above the rotor, the winding being disposed on the core.
  • the core comprises a stator lamination formed by stacking a plurality of punching sheets and an end platen fixed to both sides of the stator lamination.
  • the punching piece has a circular shape, and a plurality of cup-shaped perforations are arranged at intervals in the annular portion, the mouth of the perforated cup is closed, and the bottom of the cup is open.
  • the winding is a three-phase star connection
  • the center line is not led out, and only three ends of A, B, and C are drawn.
  • each phase winding is 2 coils, and each coil is continuously wound from an enamelled copper wire.
  • the present invention has the following beneficial effects:
  • the gas turbine generator provided by the present invention uses gas as a lubricant of the bearing, so that it has not only pollution-free, low friction loss, long use time, wide application range, energy saving and environmental protection, but also adopts the above structure.
  • Heat dissipation If it is good, it can guarantee stable operation for a long time; in particular, because the air bearing of the structure can achieve ultra-high-speed stable operation under air-floating state (tested, the limit speed can reach 100,000 to 450,000 rpm), so the same
  • the invention can significantly reduce the volume of the gas turbine generator to achieve miniaturization, has the advantages of small occupied space and convenient use, and has important value for promoting the development of miniaturization high-tech, and is significant compared with the prior art. progress.
  • Embodiment 1 is a schematic cross-sectional structural view of an ultra high speed gas turbine generator provided in Embodiment 1;
  • Embodiment 2 is a partially divided left perspective structural view of a trough type dynamic pressure gas radial bearing provided in Embodiment 1;
  • Figure 3 is a partial enlarged view of A in Figure 2;
  • Embodiment 4 is a schematic partial right side perspective view showing the slot type dynamic pressure gas radial bearing provided in Embodiment 1;
  • Figure 5 is a partial enlarged view of B in Figure 4.
  • FIG. 6 is a schematic cross-sectional structural view of a hybrid dynamic pressure gas thrust bearing provided in Embodiment 1;
  • Figure 7a is a left side view of the center disk described in Embodiment 1;
  • Figure 7b is a right side view of the center disk described in Embodiment 1;
  • Figure 8a is a right side view of the left side disk to which the foil-type elastic member is fixed as described in Embodiment 1;
  • Figure 8b is a left side view of the right side disk with the foil-type elastic member fixed in Embodiment 1;
  • FIG. 9 is a schematic cross-sectional structural view of a foil-type elastic member provided in Embodiment 1;
  • Figure 10 is a perspective view showing the structure of the foil-type elastic member provided in Embodiment 1;
  • Figure 11a is a left side perspective structural view of a hybrid dynamic pressure gas thrust bearing provided in Embodiment 2;
  • Figure 11b is a right perspective view showing the hybrid dynamic pressure gas thrust bearing of the second embodiment
  • Figure 12 is a partially sectional perspective structural view of the hybrid dynamic pressure gas thrust bearing provided in the second embodiment
  • Figure 13 is a left perspective view showing the middle plate of the second embodiment
  • Figure 14 is a partial enlarged view of C in Figure 13;
  • Figure 15 is a right perspective view showing the center disk of the second embodiment
  • Figure 16 is a partial enlarged view of D in Figure 15;
  • Figure 17 is a schematic view showing the structure of a rotor provided in Embodiment 3.
  • FIG. 18 is a schematic structural view of a core provided in Embodiment 4.
  • Figure 19 is a schematic structural view of a punching piece according to Embodiment 4.
  • FIG. 20 is a schematic structural view of a winding provided in Embodiment 4.
  • Figure 21 is a schematic view showing the structure of the inner shaft provided in the fifth embodiment.
  • Figure 22 is a partial enlarged view of E in Figure 21;
  • FIG. 23 is a schematic perspective structural view of a motor housing provided in Embodiment 6;
  • Figure 24 is a partial enlarged view of F in Figure 23 .
  • an ultra-high speed gas turbine generator provided by the embodiment includes a turbine 1, a compressor 2, a motor 3, two radial bearings 4, a thrust bearing 5 and a combustion chamber 6.
  • the turbine 1 comprises a turbine 11, a turbine deflector 12 and a turbine deflector housing 13, the compressor 2 comprising a pressure wheel 21, a compressor housing 22 and a compressor diffuser 23, the motor 3 comprising a rotor 31, a stator 32, an inner shaft 33, an outer shaft 34 and a motor housing 35;
  • the radial bearing 4 is a slot type dynamic pressure gas radial bearing, including a bearing outer casing 41 and a bearing inner sleeve 42;
  • the thrust bearing 5 is a hybrid dynamic pressure gas thrust bearing comprising two side discs 51 and a middle disc 52 interposed between the two side discs, at each of the side discs 51 and the middle disc 52 Each of the two is provided with a foil-shaped elastic member 53; the rotor 31 is sleeved in the middle of the inner shaft 33, and
  • the turbine 1 and the compressor 2 are respectively disposed at both ends of the inner shaft 33, and the combustion chamber 6 is disposed at the end of the turbine 1 (as shown in Fig. 1); however, the following structure may also be employed:
  • the combustion chamber 6 is disposed in the middle of the inner shaft 33, and the turbine 1 and the compressor 2 are respectively disposed at both ends of the inner shaft 33 or are provided back to back at one end of the inner shaft 33.
  • the ultra high speed gas turbine generator further includes a left radial bearing sleeve 7a, a left bearing chamber end cover 8a, a right radial bearing sleeve 7b and a right bearing chamber end cover 8b, a turbine deflector housing 13 and a left bearing chamber.
  • the end cover 8a is fixedly connected, the left bearing chamber end cover 8a is fixedly connected with the left radial bearing sleeve 7a, the housing 61 of the combustion chamber 6 is fixedly connected with the left radial bearing sleeve 7a, and the left radial bearing sleeve 7a and the motor housing 35 is fixedly connected, the compressor housing 22 is fixedly connected to the right bearing chamber end cover 8b, the right bearing chamber end cover 8b is fixedly connected to the right radial bearing sleeve 7b, and the right radial bearing sleeve 7b is fixedly coupled to the motor housing 35.
  • the outer circumferential surface and the left and right end surfaces of the bearing inner sleeve 42 each have a regular shape of the groove pattern 43 (431, 432 and 433 in the figure, the groove in this embodiment).
  • the pattern is an impeller shape), and the groove pattern 432 of the left end surface is mirror-symmetrical with the groove pattern 433 of the right end surface.
  • the axial contour line of the groove pattern 431 located on the outer circumferential surface of the bearing inner sleeve 42 forms a one-to-one correspondence with the radial contour lines of the groove patterns (432 and 433) of the left and right end surfaces, and is mutually overlapped, that is, external
  • the axially high bit line 4311 in the circumferential groove pattern 431 corresponds to the radial high bit lines (4321 and 4331) in the groove patterns (432 and 433) of the left and right end faces, and is chamfered before the end face is chamfered Interacting with each other;
  • the axial center line 4312 in the groove pattern 431 of the outer circumferential surface corresponds to the radial center line (4322 and 4332) in the groove patterns (432 and 433) of the left and right end faces, and
  • the front end is circumferentially chamfered to each other;
  • the groove pattern 432 of the left end surface and the groove pattern 433 of the right end surface are mirror-symmetrical and outer circumference.
  • the axial contour line of the groove pattern 431 forms a one-to-one correspondence with the radial contour lines of the groove patterns (432 and 433) of the left and right end faces, and mutually intersects each other, thereby ensuring the groove pattern of the impeller shape at both end faces.
  • the pressurized gas generated by (432 and 433) is transported from the axial direction of the shaft to the groove passage formed by the groove pattern 431 of the outer circumferential surface, so as to form a gas film required for supporting the high-speed running bearing more strongly, and
  • the gas film is used as a lubricant for the dynamic pressure gas radial bearing, and thus is advantageous for achieving high-speed stable operation of the trough type dynamic pressure gas radial bearing 4 in an air floating state.
  • the retaining ring 44 when the retaining ring 44 is respectively disposed at both ends of the bearing outer casing 41, it can be realized by the high-speed rotary shaft.
  • the two end faces of the bearing inner sleeve 42 and the retaining ring 44 are self-sealing, so that the dynamic pressure gas continuously generated by the groove pattern can be tightly sealed and stored in the entire fitting clearance of the bearing, and the dynamic pressure gas radial bearing that fully operates at a high speed is fully ensured. Lubrication is required.
  • the fitting clearance between the bearing outer casing 41 and the bearing inner sleeve 42 is preferably 0.003 to 0.008 mm to further ensure the reliability and stability of the bearing at high speed.
  • a hybrid dynamic pressure gas thrust bearing 5 provided in this embodiment includes: two side discs 51 with a middle disc 52 interposed between the two side discs 51 on each side.
  • a foil-shaped elastic member 53 is disposed between the disk 51 and the intermediate plate 52; the left end surface of the intermediate plate 52 is provided with a groove pattern 521 having a regular shape, and the right end surface is provided with a groove pattern 522 having a regular shape.
  • the groove pattern 521 of the left end surface of the middle plate 52 and the groove pattern 522 of the right end surface form a mirror symmetry, and the radial contour line and the right end surface of the groove pattern 521 of the left end surface are formed.
  • the radial contours of the troughs 522 form a one-to-one correspondence.
  • the troughs 521 and 522 have the same shape, and are in the shape of an impeller in this embodiment.
  • the foil-type elastic member 53 is fixed to the inner end surface of the corresponding side disk 51 (for example, the left side disk 511 to which the foil-type elastic member 53a is fixed as shown in Fig. 8a and the left side disk 511 shown in Fig. 8b
  • the right side disc 512) to which the foil type elastic member 53b is fixed, and the foil type elastic member 53a fixed to the left side disc 511 is mirror-symmetrical with the foil type elastic member 53b fixed to the right side disc 512.
  • the foil-type elastic member 53 By providing the foil-type elastic member 53 between the side disk 51 and the intermediate disk 52, regular groove patterns (521 and 522) are provided on the left and right end faces of the middle plate 52, and the groove pattern 521 of the left end face is The groove pattern 522 of the right end surface is mirror-symmetrical, thereby obtaining a rigid characteristic of a high limit rotation speed of the groove type dynamic pressure gas thrust bearing, and a high impact resistance and load of the foil type dynamic pressure gas thrust bearing.
  • the hybrid dynamic pressure gas thrust bearing of the flexible nature of the capability because the foil-shaped elastic member 53 forms a wedge-shaped space with the intermediate disk 52, when the disk 52 rotates, the gas is driven by its own viscous action and is compressed to the wedge shape.
  • the axial dynamic pressure can be significantly enhanced, compared with the existing simple foil dynamic pressure gas thrust bearing, which can have a limit rotation speed which is multiplied under the same load; meanwhile, due to the increased foil type
  • the elastic member 53 can also significantly improve the bearing capacity, the impact resistance and the ability to suppress the whirl of the bearing under the elastic action, and can have the same in comparison with the existing simple groove type dynamic pressure gas thrust bearing. Doubling the speed of impact resistance and load capacity.
  • the foil-shaped elastic member 53 is composed of a wave foil 531 and a flat foil 532, and a top end of the curved protrusion 5311 of the wave foil 531 is attached to the flat foil 532.
  • the inter-wave transition bottom edge 5312 of the wave foil 531 is in contact with the inner end surface of the corresponding side disk 51.
  • a wear-resistant coating (not shown) is provided on the mating surface of the foil-type elastic member 53 that cooperates with the intermediate plate 52.
  • a hybrid dynamic pressure gas thrust bearing provided by the present embodiment differs from Embodiment 1 only in that:
  • a groove pattern 523 is also provided on the outer circumferential surface of the intermediate disk 52, and the shape of the groove pattern 523 of the outer circumferential surface is the same as that of the groove patterns (521 and 522) of the left and right end faces (this embodiment)
  • the axial contour of the groove pattern 523 of the outer circumferential surface and the radial contour lines of the groove patterns (521 and 522) of the left and right end faces are in one-to-one correspondence with each other and intersect with each other; :
  • the axially high bit line 5231 in the groove pattern 523 of the outer circumferential surface corresponds to the radial high line line 5211 in the groove pattern 521 of the left end surface, and is mutually overlapped before the end face is chamfered;
  • the groove of the outer circumferential surface The axial center line 5232 in the pattern 523 corresponds to the radial center line 5212 in the groove pattern 521 of the left end surface, and is mutually overlapped before the end surface is chamfered;
  • the axially lower bit line 5233 corresponds to the radially lower bit line 5213 in the groove pattern 521 of the left end face, and is mutually overlapped before the end face is chamfered (as shown in FIG. 14);
  • the axially high bit line 5231 in the groove pattern 523 of the outer circumferential surface corresponds to the radial high line 5221 in the groove pattern 522 of the right end face, and is mutually overlapped before the end face is chamfered;
  • the groove of the outer circumferential surface The axial center line 5232 in the pattern 523 corresponds to the radial center line 5222 in the groove pattern 522 of the right end surface, and is mutually overlapped before the end surface is chamfered;
  • the axially lower bit line 5233 corresponds to the radially lower bit line 5223 in the groove pattern 522 of the right end face, and is mutually overlapped before the end face is chamfered (as shown in FIG. 16).
  • a groove pattern is also provided on the outer circumferential surface of the intermediate disk 52, and the shape of the groove pattern 523 of the outer circumferential surface is the same as that of the groove patterns (521 and 522) of the left and right end faces, and When the axial contour line of the groove pattern 523 of the circumferential surface forms a one-to-one correspondence with the radial contour lines of the groove patterns (521 and 522) of the left and right end faces, the groove pattern of both end faces of the inner disk can be obtained.
  • the pressurized gas generated by (521 and 522) is transported from the axial direction of the shaft to the groove passage formed by the groove pattern 523 of the outer circumferential surface so as to form a gas film which is stronger for supporting the high speed running bearing, and
  • the gas film is used as a lubricant for the dynamic pressure gas thrust bearing, so that the high-speed stable operation of the hybrid dynamic pressure gas thrust bearing in the air-floating state can be further ensured, and further guarantee for realizing the high limit rotation speed of the motor.
  • a card slot 513 (shown in Fig. 12) for fixing the foil-type elastic member 53 is provided on the inner end surface of the side disk 51.
  • the fitting clearance of the foil-type elastic member 53 and the intermediate disk 52 is preferably 0.003 to 0.008 mm to further ensure the reliability and stability of the high-speed operation of the bearing.
  • the foil-type elastic member 53 is preferably subjected to surface heat treatment.
  • composition of the foil-type elastic member 53 of the present invention is not limited to that described in the above embodiments. It is also possible to use a wave foil and a flat foil composition, but the transition edge between the wave arches of the wave foil is bonded to the flat foil, or directly composed of two flat foils, or other existing structures.
  • the rotor 31 includes a rotor base 311, a magnetic steel 312, and a magnetic steel sleeve 313.
  • the rotor base 311 is sleeved on the inner shaft 33, and the magnetic steel 312 is sleeved on the rotor.
  • the magnetic steel protective sleeve 313 is sleeved on the magnetic steel 312 to better satisfy the ultra-high speed rotation.
  • the stator 32 includes a core 321 and a winding 322 fixed to an inner wall of the motor housing 35 above the rotor 31, the winding 322 being disposed on the core
  • the core 321 includes a stator lamination 3212 formed by stacking a plurality of punching pieces 3211 and an end platen 3213 fixed to both sides of the stator lamination 3212.
  • the punching piece 3211 has a circular ring shape, and a plurality of cup-shaped through holes 32111 are formed at intervals in the annular portion.
  • the cup mouth portion 32111a of the through hole 32111 is closed, and the bottom of the cup foot 32111b is open.
  • the winding 322 is connected by a three-phase star type, the center line is not led out, and only three ends of A, B, and C are taken out; each phase winding is two coils, and each coil is made of an enamelled copper wire. Continuously wound.
  • a heat dissipating spiral groove 331 is formed in the surface of the inner shaft 33 to facilitate heat dissipation of the rotating shaft and the bearing chamber.
  • a plurality of opening slots 351 are defined in the inner wall of the motor housing 35, and a plurality of vent holes 352 are formed in the end surface of the motor housing.
  • the opening slots 351 are connected to the vent holes 352.
  • the bearing provided by the invention can reach the limit rotation speed of 100,000-450,000 rpm in the air floating state, so the invention can significantly reduce the volume of the gas turbine generator to achieve miniaturization for the same power requirement, and promote miniaturization.
  • the development of high technology has important value.

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Abstract

一种超高速燃气轮发电机，其包括涡轮机（1）、压气机（2）、电机（3）、2个径向轴承（4a、4b）、1个止推轴承（5）及燃烧室（6），所述径向轴承（4a、4b）为槽式动压气体径向轴承，所述止推轴承（5）为混合式动压气体止推轴承，转子（31）套设在內轴（33）的中部，2个径向轴承（4a、4b）分别套设在位于转子（31）左、右端的外轴（34）上，所述止推轴承（5）套设在右端的外轴（34）上、并位于右端径向轴承（4b）的外端侧。这种结构可实现在气浮状态下的超高速稳定运转，针对相同功率要求，可使燃气轮发电机的体积显著减小实现微型化。

Description

一种超高速燃气轮发电机 技术领域
本发明是涉及一种超高速燃气轮发电机，属于高精密机械技术领域。
背景技术
燃气轮发电机是以连续流动的气体为工质带动叶轮高速旋转，将燃料的能量转变为有用功的内燃式动力机械，是一种旋转叶轮式热力发动机，由燃气轮机与发电机组成，主要用于油田、发电厂、电信大楼、高层建筑、酒店、生活小区、商场、医院、军队、会议中心、偏远地区、海岛等重要场所必需的备用电源及作为紧急事件、野外作业等必需的移动电源，也可作为船舶动力、电力调峰。
随着全球范围内的能源与动力需求，采用空气轴承的微型燃气轮发电机因具有尺寸小、重量轻、燃料适应性强、低燃料消耗率、噪音低、振动小、污染排放低、维护费用低廉、不需用水冷却等一系列先进技术特征在军民用交通运输(混合动力汽车)以及陆海边防方面开始应用，受到美、俄等国家的高度重视和关注。但由于现有的空气轴承主要存在如下问题：结构复杂，不适合工业化；可靠性较差，在高速运转时容易失稳甚至卡死；高速运转产生的热量不能有效导出，不能长时间连续工作；体积较大，不能满足当今微型化发展要求。
发明内容
针对现有技术存在的上述问题，本发明的目的是提供一种可稳定运行的超高速燃气轮发电机。
为实现上述目的，本发明采用的技术方案如下：
一种超高速燃气轮发电机，包括涡轮机、压气机、电机、2个径向轴承、1个止推轴承及燃烧室，所述涡轮机包括涡轮、涡轮机导流器及涡轮机导流器壳体，所述压气机包括压轮、压气机壳体及压气机扩压器，所述电机包括转子、定子、內轴、外轴及电机壳体；其特征在于：所述径向轴承为槽式动压气体径向轴承，包括轴承外套和轴承内套；所述止推轴承为混合式动压气体止推轴承，包括两个侧盘以及夹设在两个侧盘之间的中盘，在每个侧盘与中盘之间均设有箔型弹性件；所述转子套设在內轴的中部，2个径向轴承分别套设在位于转子左、右端的外轴上，所述止推轴承套设在右端的外轴上、并位于右端径向轴承的外端侧。
一种实施方案，所述涡轮机和压气机分别设置在內轴的两端，所述燃烧室设置在涡轮机端。
另一种实施方案，所述燃烧室设置在内轴的中部，所述涡轮机和压气机分别设置在內轴的两端或者背靠背设置在內轴的一端。
作为进一步实施方案，所述的超高速燃气轮发电机还包括左径向轴承套和左轴承室端盖，涡轮机导流器壳体与左轴承室端盖固定连接，左轴承室端盖与左径向轴承套固定连接，燃烧室的壳体与左径向轴承套固定连接，左径向轴承套与电机壳体固定连接。
作为进一步实施方案，所述的超高速燃气轮发电机还包括右径向轴承套和右轴承室端盖，压气机壳体与右轴承室端盖固定连接，右轴承室端盖与右径向轴承套固定连接，右径向轴承套与电机壳体固定连接。
作为优选方案，所述内轴的表面开设有散热螺旋槽，以利于转轴和轴承室的散热。
作为优选方案，在电机壳体的内壁周侧开设有若干开口槽，在电机壳体的端面开设有若干通气孔，所述开口槽与通气孔相连通，以利于气体的导入和导出，一方面实现快速散热排气，另一面实现对轴承室内进行空气补给。
作为优选方案，所述轴承内套的外圆周面和两端面均具有规则形状的槽式花纹。
作为进一步优选方案，所述轴承内套的一端面的槽式花纹与另一端面的槽式花纹形成镜像对称，以及外圆周面的槽式花纹的轴向轮廓线与两端面的槽式花纹的径向轮廓线均形成一一对应并相互交接。
作为进一步优选方案，所述轴承内套的外圆周面的槽式花纹中的轴向高位线与两端面的槽式花纹中的径向高位线均相对应、并在端面圆周倒角前相互交接；外圆周面的槽式花纹中的轴向中位线与两端面的槽式花纹中的径向中位线均相对应、并在端面圆周倒角前相互交接；外圆周面的槽式花纹中的轴向低位线与两端面的槽式花纹中的径向低位线均相对应、并在端面圆周倒角前相互交接。
作为优选方案，所述轴承内套与轴承外套间的配合间隙为0.003～0.008mm。
作为优选方案，在所述轴承外套的两端设有止环。
作为优选方案，所述中盘的两端面均设有规则形状的槽式花纹，且一端面的槽式花纹与另一端面的槽式花纹形成镜像对称。
作为优选方案，在所述中盘的外圆周面也设有槽式花纹，且外圆周面的槽式花纹的形状与两端面的槽式花纹的形状相同，以及外圆周面的槽式花纹的轴向轮廓线与两端面的槽式花纹的径向轮廓线均形成一一对应并相互交接。
作为进一步优选方案，中盘的外圆周面的槽式花纹中的轴向高位线与两端面的槽式花纹中的径向高位线均相对应、并在端面圆周倒角前相互交接；外圆周面的槽式花纹中的轴向中 位线与两端面的槽式花纹中的径向中位线均相对应、并在端面圆周倒角前相互交接；外圆周面的槽式花纹中的轴向低位线与两端面的槽式花纹中的径向低位线均相对应、并在端面圆周倒角前相互交接。
作为进一步优选方案，在与中盘相配合的箔型弹性件的配合面上设有耐磨涂层。
作为进一步优选方案，所述箔型弹性件与中盘的配合间隙为0.003～0.008mm。
作为进一步优选方案，所述箔型弹性件的至少一端固定在对应侧盘的内端面上。
作为进一步优选方案，每个侧盘上的箔型弹性件为多个，且沿侧盘的内端面均匀分布。
作为进一步优选方案，固定在一个侧盘上的箔型弹性件与固定在另一个侧盘上的箔型弹性件形成镜像对称。
作为进一步优选方案，在侧盘的内端面设有用于固定箔型弹性件的卡槽。
作为一种实施方案，所述的箔型弹性件由波箔和平箔组成，所述波箔的弧形凸起顶端与平箔相贴合。
作为另一种实施方案，所述的箔型弹性件由波箔和平箔组成，所述波箔的波拱间过渡底边与平箔相贴合。
作为又一种实施方案，所述的箔型弹性件由两个平箔组成。
上述的槽式花纹均为叶轮形状。
上述的箔型弹性件优选经过表面热处理。
作为优选方案，所述转子包括转子底座、磁钢和磁钢保护套，所述转子底座套设在內轴上，所述磁钢套设在转子底座的中心部，所述磁钢保护套套设在磁钢上。
作为优选方案，所述定子包括铁芯和绕组，所述铁芯固定在位于转子上方的电机壳体的内壁上，所述绕组设置在铁芯上。
作为优选方案，所述铁芯包括由若干冲片上下叠置形成的定子叠片和固定在定子叠片两侧的端压板。
作为进一步优选方案，所述冲片呈圆环形，在环形部间隔设有多个杯状穿孔，所述穿孔的杯口部封闭，杯脚的底部开口。
作为优选方案，所述绕组为三相星型连接，中心线不引出，只引出A、B、C三个端头。
作为进一步优选方案，每相绕组为2个线圈，每个线圈由漆包铜线连续绕制而成。
与现有技术相比，本发明具有如下有益效果：
因本发明所提供的燃气轮发电机，是以气体作为轴承的润滑剂，因此不仅具有无污染、摩擦损失低、使用时间长、适用范围广、节能环保等诸多优点，而且采用所述结构，散热效 果好，可保证长时间稳定运行；尤其是，因所述结构的空气轴承能实现在气浮状态下的超高速稳定运转(经测试，可达100,000～450,000rpm的极限转速)，因此针对相同功率要求，本发明可使燃气轮发电机的体积显著减小实现微型化，具有占用空间小、使用便捷等优点，对促进微型化高新技术的发展具有重要价值，相对于现有技术具有显著性进步。
附图说明
图1是实施例1提供的一种超高速燃气轮发电机的剖面结构示意图；
图2是实施例1提供的槽式动压气体径向轴承的局部分割的左视立体结构示意图；
图3是图2中的A局部放大图；
图4是实施例1提供的槽式动压气体径向轴承的局部分割的右视立体结构示意图；
图5是图4中的B局部放大图；
图6是实施例1提供的混合式动压气体止推轴承的剖面结构示意图；
图7a是实施例1中所述中盘的左视图；
图7b是实施例1中所述中盘的右视图；
图8a是实施例1中所述的固定有箔型弹性件的左侧盘的右视图；
图8b是实施例1中所述的固定有箔型弹性件的右侧盘的左视图；
图9是实施例1提供的箔型弹性件的截面结构示意图；
图10是实施例1提供的箔型弹性件的立体结构示意图；
图11a是实施例2提供的一种混合式动压气体止推轴承的左视立体结构示意图；
图11b是实施例2提供的混合式动压气体止推轴承的右视立体结构示意图；
图12是实施例2提供的混合式动压气体止推轴承的局部分割立体结构示意图；
图13是实施例2中所述中盘的左视立体结构示意图；
图14是图13中的C局部放大图；
图15是实施例2中所述中盘的右视立体结构示意图；
图16是图15中的D局部放大图；
图17是实施例3所提供的转子结构示意图；
图18是实施例4所提供的铁芯结构示意图；
图19是实施例4所述冲片的结构示意图；
图20是实施例4所提供的绕组结构示意图；
图21是实施例5所提供的内轴结构示意图；
图22是图21中的E局部放大图；
图23是实施例6所提供的电机壳体的立体结构示意图；
图24是图23中的F局部放大图。
图中标号示意如下：
1、涡轮机；11、涡轮；12、涡轮机导流器；13、涡轮机导流器壳体；2、压气机；21、压轮；22、压气机壳体；23、压气机扩压器；3、电机；31、转子；311、转子底座；312、磁钢；313、磁钢保护套；32、定子；321、铁芯；3211、冲片；32111、杯状穿孔；32111a、杯口部；32111b、杯脚；3212、定子叠片；3213、端压板；322、绕组；33、內轴；331、散热螺旋槽；34、外轴；35、电机壳体；351、开口槽；352、通气孔；4、槽式动压气体径向轴承；4a、左端径向轴承；4b、右端径向轴承；41、轴承外套；42、轴承内套；43、槽式花纹；431、外圆周面的槽式花纹；4311、轴向高位线；4312、轴向中位线；4313、轴向低位线；432、左端面的槽式花纹；4321、径向高位线；4322、径向中位线；4323、径向低位线；433、右端面的槽式花纹；4331、径向高位线；4332、径向中位线；4333、径向低位线；44、止环；5、混合式动压气体止推轴承；51、侧盘；511、左侧盘；512、右侧盘；513、卡槽；52、中盘；521、左端面的槽式花纹；5211、径向高位线；5212、径向中位线；5213、径向低位线；522、右端面的槽式花纹；5221、径向高位线；5222、径向中位线；5223、径向低位线；523、外圆周面的槽式花纹；5231、轴向高位线；5232、轴向中位线；5233、轴向低位线；53、箔型弹性件；53a、固定在左侧盘上的箔型弹性件；53b、固定在右侧盘上的箔型弹性件；531、波箔；5311、弧形凸起；5312、波拱间过渡底边；532、平箔；6、燃烧室；61、燃烧室的壳体；7a、左径向轴承套；7b、右径向轴承套；8a、左轴承室端盖；8b、右轴承室端盖。
具体实施方式
下面结合附图及实施例对本发明的技术方案做进一步详细地说明。
实施例1
如图1所示：本实施例提供的一种超高速燃气轮发电机，包括涡轮机1、压气机2、电机3、2个径向轴承4、1个止推轴承5及燃烧室6，所述涡轮机1包括涡轮11、涡轮机导流器12及涡轮机导流器壳体13，所述压气机2包括压轮21、压气机壳体22及压气机扩压器23，所述电机3包括转子31、定子32、內轴33、外轴34及电机壳体35；所述径向轴承4为槽式动压气体径向轴承，包括轴承外套41和轴承内套42；所述止推轴承5为混合式动压气体止推轴承，包括两个侧盘51以及夹设在两个侧盘之间的中盘52，在每个侧盘51与中盘52之 间均设有箔型弹性件53；所述转子31套设在內轴33的中部，2个径向轴承4分别套设在位于转子31左、右端的外轴34上，所述止推轴承5套设在右端的外轴34上、并位于右端径向轴承4b的外端侧。
一种实施方案，所述涡轮机1和压气机2分别设置在內轴33的两端，所述燃烧室6设置在涡轮机1端(如图1中所示)；但也可以采用如下结构：
所述燃烧室6设置在内轴33的中部，所述涡轮机1和压气机2分别设置在內轴33的两端或者背靠背设置在內轴33的一端。
所述的超高速燃气轮发电机还包括左径向轴承套7a、左轴承室端盖8a、右径向轴承套7b和右轴承室端盖8b，涡轮机导流器壳体13与左轴承室端盖8a固定连接，左轴承室端盖8a与左径向轴承套7a固定连接，燃烧室6的壳体61与左径向轴承套7a固定连接，左径向轴承套7a与电机壳体35固定连接，压气机壳体22与右轴承室端盖8b固定连接，右轴承室端盖8b与右径向轴承套7b固定连接，右径向轴承套7b与电机壳体35固定连接。
结合图2至图5所示：所述轴承内套42的外圆周面和左、右端面均具有规则形状的槽式花纹43(如图中的431、432和433，本实施例中的槽式花纹均为叶轮形状)，且左端面的槽式花纹432与右端面的槽式花纹433形成镜像对称。位于轴承内套42的外圆周面的槽式花纹431的轴向轮廓线与左、右端面的槽式花纹(432和433)的径向轮廓线均形成一一对应并相互交接，即：外圆周面的槽式花纹431中的轴向高位线4311与左、右端面的槽式花纹(432和433)中的径向高位线(4321和4331)均相对应、并在端面圆周倒角前相互交接；外圆周面的槽式花纹431中的轴向中位线4312与左、右端面的槽式花纹(432和433)中的径向中位线(4322和4332)均相对应、并在端面圆周倒角前相互交接；外圆周面的槽式花纹431中的轴向低位线4313与左、右端面的槽式花纹(432和433)中的径向低位线(4323和4333)均相对应、并在端面圆周倒角前相互交接。
通过使轴承内套42的外圆周面和两端面均具有规则形状的槽式花纹(431、432和433)，左端面的槽式花纹432与右端面的槽式花纹433形成镜像对称及外圆周面的槽式花纹431的轴向轮廓线与左、右端面的槽式花纹(432和433)的径向轮廓线均形成一一对应并相互交接，可保证两端面的叶轮形状的槽式花纹(432和433)所产生的增压气体从轴心沿径向不断地往外圆周面的槽式花纹431形成的凹槽通道里输送，以致形成更强支撑高速运转轴承所需的气膜，而气膜即作为动压气体径向轴承的润滑剂，因此有利于实现所述槽式动压气体径向轴承4在气浮状态下的高速稳定运转。
另外，当在轴承外套41的两端分别设置止环44时，可实现在高速回转轴的带动下，使 轴承内套42的两端面与止环44间产生自密封作用，使槽式花纹连续产生的动压气体能完好地密闭保存在轴承的整个配合间隙中，充分保证高速运转的动压气体径向轴承的润滑需要。
所述轴承外套41与轴承内套42间的配合间隙优选为0.003～0.008mm，以进一步确保轴承高速运转的可靠性和稳定性。
如图6所示：本实施例提供的一种混合式动压气体止推轴承5，包括：两个侧盘51，在两个侧盘51之间夹设有中盘52，在每个侧盘51与中盘52之间设有箔型弹性件53；所述中盘52的左端面设有规则形状的槽式花纹521，右端面设有规则形状的槽式花纹522。
结合图7a和图7b可见：所述中盘52的左端面的槽式花纹521与右端面的槽式花纹522之间形成镜像对称，左端面的槽式花纹521的径向轮廓线与右端面的槽式花纹522的径向轮廓线形成一一对应。
所述的槽式花纹521与522的形状相同，本实施例中均为叶轮形状。
进一步结合图8a和图8b可见：所述箔型弹性件53固定在对应侧盘51的内端面上(例如图8a所示的固定有箔型弹性件53a的左侧盘511和图8b所示的固定有箔型弹性件53b的右侧盘512)，且固定在左侧盘511上的箔型弹性件53a与固定在右侧盘512上的箔型弹性件53b形成镜像对称。在每个侧盘上的箔型弹性件可为多个(图中示出的是4个)，且沿侧盘的内端面均匀分布。
通过在侧盘51与中盘52之间设置箔型弹性件53，在中盘52的左、右端面设置规则形状的槽式花纹(521和522)，且使左端面的槽式花纹521与右端面的槽式花纹522形成镜像对称，从而得到了既具有槽式动压气体止推轴承的高极限转速的刚性特征、又具有箔片式动压气体止推轴承的高抗冲击能力和载荷能力的柔性特征的混合式动压气体止推轴承；因为箔型弹性件53与中盘52间形成了楔形空间，当中盘52转动时，气体因其自身的粘性作用被带动并被压缩到楔形空间内，从而可使轴向动压力得到显著增强，相对于现有的单纯箔片式动压气体止推轴承，可具有在相同载荷下成倍增加的极限转速；同时，由于增加了箔型弹性件53，在其弹性作用下，还可使轴承的载荷能力、抗冲击能力和抑制轴涡动的能力显著提高，相对于现有的单纯槽式动压气体止推轴承，可具有在相同转速下成倍增加的抗冲击能力和载荷能力。
结合图6和图9、图10所示：所述的箔型弹性件53由波箔531和平箔532组成，所述波箔531的弧形凸起5311的顶端与平箔532相贴合，所述波箔531的波拱间过渡底边5312与对应侧盘51的内端面相贴合。
为进一步降低高速运转的中盘52对箔型弹性件53的磨损，以延长轴承的使用寿命，最 好在与中盘52相配合的箔型弹性件53的配合面上设置耐磨涂层(图中未示出)。
实施例2
结合图11a、11b、12至16所示可见，本实施例提供的一种混合式动压气体止推轴承与实施例1的区别仅在于：
在所述中盘52的外圆周面也设有槽式花纹523，且外圆周面的槽式花纹523的形状与左、右端面的槽式花纹(521和522)的形状相同(本实施例中均为叶轮形状)，以及外圆周面的槽式花纹523的轴向轮廓线与左、右端面的槽式花纹(521和522)的径向轮廓线均形成一一对应并相互交接；即：
外圆周面的槽式花纹523中的轴向高位线5231与左端面的槽式花纹521中的径向高位线5211均相对应、并在端面圆周倒角前相互交接；外圆周面的槽式花纹523中的轴向中位线5232与左端面的槽式花纹521中的径向中位线5212均相对应、并在端面圆周倒角前相互交接；外圆周面的槽式花纹523中的轴向低位线5233与左端面的槽式花纹521中的径向低位线5213均相对应、并在端面圆周倒角前相互交接(如图14所示)；
外圆周面的槽式花纹523中的轴向高位线5231与右端面的槽式花纹522中的径向高位线5221均相对应、并在端面圆周倒角前相互交接；外圆周面的槽式花纹523中的轴向中位线5232与右端面的槽式花纹522中的径向中位线5222均相对应、并在端面圆周倒角前相互交接；外圆周面的槽式花纹523中的轴向低位线5233与右端面的槽式花纹522中的径向低位线5223均相对应、并在端面圆周倒角前相互交接(如图16所示)。
当在所述中盘52的外圆周面也设有槽式花纹，且使外圆周面的槽式花纹523的形状与左、右端面的槽式花纹(521和522)的形状相同，以及外圆周面的槽式花纹523的轴向轮廓线与左、右端面的槽式花纹(521和522)的径向轮廓线均形成一一对应并相互交接时，可使内盘两端面的槽式花纹(521和522)所产生的增压气体从轴心沿径向不断地往外圆周面的槽式花纹523形成的凹槽通道里输送，以致形成更强支撑高速运转轴承所需的气膜，而气膜即作为动压气体止推轴承的润滑剂，因而可进一步确保所述的混合式动压气体止推轴承在气浮状态下的高速稳定运转，为实现电机的高极限转速提供进一步保证。
在侧盘51的内端面上设有用于固定箔型弹性件53的卡槽513(如图12所示)。
所述的箔型弹性件53与中盘52的配合间隙优选为0.003～0.008mm，以进一步确保轴承高速运转的可靠性和稳定性。
为了更好地满足高速运转的性能要求，所述的箔型弹性件53优选经过表面热处理。
另外需要说明的是：本发明所述的箔型弹性件53的组成结构不限于上述实施例中所述， 还可以采用波箔和平箔组成，但所述波箔的波拱间过渡底边与平箔相贴合，或者，直接采用两个平箔组成，或采用其它的现有结构。
实施例3
结合图1和图17所示：所述转子31包括转子底座311、磁钢312和磁钢保护套313，所述转子底座311套设在內轴33上，所述磁钢312套设在转子底座311的中心部，所述磁钢保护套313套设在磁钢312上，以更好满足超高速转动。
实施例4
结合图1和图18所示：所述定子32包括铁芯321和绕组322，所述铁芯321固定在位于转子31上方的电机壳体35的内壁上，所述绕组322设置在铁芯321上；所述铁芯321包括由若干冲片3211上下叠置形成的定子叠片3212和固定在定子叠片3212两侧的端压板3213。
如图19所示：所述冲片3211呈圆环形，在环形部间隔设有多个杯状穿孔32111，所述穿孔32111的杯口部32111a封闭，杯脚32111b的底部开口。
如图20所示：所述绕组322采用三相星型连接，中心线不引出，只引出A、B、C三个端头；每相绕组为2个线圈，每个线圈由漆包铜线连续绕制而成。
实施例5
结合图21和图22所示：在内轴33的表面开设有散热螺旋槽331，以利于转轴和轴承室的散热。
实施例6
结合图23和图24所示：在电机壳体35的内壁周侧开设有若干开口槽351，在电机壳体的端面开设有若干通气孔352，所述开口槽351与通气孔352相连通，以利于气体的导入和导出，一方面实现快速散热排气，另一面实现对轴承室内进行空气补给。
经测试，本发明提供的轴承在气浮状态下能达到100,000～450,000rpm的极限转速，因此针对相同功率要求，本发明可使燃气轮发电机的体积显著减小实现微型化，对促进微型化高新技术的发展具有重要价值。
最后有必要在此指出的是：以上内容只用于对本发明所述技术方案做进一步详细说明，不能理解为对本发明保护范围的限制，本领域的技术人员根据本发明的上述内容作出的一些非本质的改进和调整均属于本发明的保护范围。

Claims (22)

  1. 一种超高速燃气轮发电机，包括涡轮机、压气机、电机、2个径向轴承、1个止推轴承及燃烧室，所述涡轮机包括涡轮、涡轮机导流器及涡轮机导流器壳体，所述压气机包括压轮、压气机壳体及压气机扩压器，所述电机包括转子、定子、內轴、外轴及电机壳体；其特征在于：所述径向轴承为槽式动压气体径向轴承，包括轴承外套和轴承内套；所述止推轴承为混合式动压气体止推轴承，包括两个侧盘以及夹设在两个侧盘之间的中盘，在每个侧盘与中盘之间均设有箔型弹性件；所述转子套设在內轴的中部，2个径向轴承分别套设在位于转子左、右端的外轴上，所述止推轴承套设在右端的外轴上、并位于右端径向轴承的外端侧。
  2. 根据权利要求1所述的超高速燃气轮发电机，其特征在于：所述涡轮机和压气机分别设置在內轴的两端，所述燃烧室设置在涡轮机端。
  3. 根据权利要求1所述的超高速燃气轮发电机，其特征在于：所述燃烧室设置在内轴的中部，所述涡轮机和压气机分别设置在內轴的两端或者背靠背设置在內轴的一端。
  4. 根据权利要求1至3中任一项所述的超高速燃气轮发电机，其特征在于：所述的超高速燃气轮发电机还包括左径向轴承套和左轴承室端盖，涡轮机导流器壳体与左轴承室端盖固定连接，左轴承室端盖与左径向轴承套固定连接，燃烧室的壳体与左径向轴承套固定连接，左径向轴承套与电机壳体固定连接。
  5. 根据权利要求4所述的超高速燃气轮发电机，其特征在于：所述的超高速燃气轮发电机还包括右径向轴承套和右轴承室端盖，压气机壳体与右轴承室端盖固定连接，右轴承室端盖与右径向轴承套固定连接，右径向轴承套与电机壳体固定连接。
  6. 根据权利要求1所述的超高速燃气轮发电机，其特征在于：所述内轴的表面开设有散热螺旋槽。
  7. 根据权利要求1所述的超高速燃气轮发电机，其特征在于：在电机壳体的内壁周侧开设有若干开口槽，在电机壳体的端面开设有若干通气孔，所述开口槽与通气孔相连通。
  8. 根据权利要求1所述的超高速燃气轮发电机，其特征在于：所述轴承内套的外圆周面和两端面均具有规则形状的槽式花纹。
  9. 根据权利要求8所述的超高速燃气轮发电机，其特征在于：所述轴承内套的一端面的槽式花纹与另一端面的槽式花纹形成镜像对称，以及外圆周面的槽式花纹的轴向轮廓线与两端面的槽式花纹的径向轮廓线均形成一一对应并相互交接。
  10. 根据权利要求9所述的超高速燃气轮发电机，其特征在于：所述轴承内套的外圆周面的槽式花纹中的轴向高位线与两端面的槽式花纹中的径向高位线均相对应、并在端面圆周倒角前相互交接；外圆周面的槽式花纹中的轴向中位线与两端面的槽式花纹中的径向中位线 均相对应、并在端面圆周倒角前相互交接；外圆周面的槽式花纹中的轴向低位线与两端面的槽式花纹中的径向低位线均相对应、并在端面圆周倒角前相互交接。
  11. 根据权利要求1所述的超高速燃气轮发电机，其特征在于：所述中盘的两端面均设有规则形状的槽式花纹，且一端面的槽式花纹与另一端面的槽式花纹形成镜像对称。
  12. 根据权利要求11所述的超高速燃气轮发电机，其特征在于：在所述中盘的外圆周面也设有槽式花纹，且外圆周面的槽式花纹的形状与两端面的槽式花纹的形状相同，以及外圆周面的槽式花纹的轴向轮廓线与两端面的槽式花纹的径向轮廓线均形成一一对应并相互交接。
  13. 根据权利要求12所述的超高速燃气轮发电机，其特征在于：中盘的外圆周面的槽式花纹中的轴向高位线与两端面的槽式花纹中的径向高位线均相对应、并在端面圆周倒角前相互交接；外圆周面的槽式花纹中的轴向中位线与两端面的槽式花纹中的径向中位线均相对应、并在端面圆周倒角前相互交接；外圆周面的槽式花纹中的轴向低位线与两端面的槽式花纹中的径向低位线均相对应、并在端面圆周倒角前相互交接。
  14. 根据权利要求1所述的超高速燃气轮发电机，其特征在于：固定在一个侧盘上的箔型弹性件与固定在另一个侧盘上的箔型弹性件形成镜像对称。
  15. 根据权利要求1或14所述的超高速燃气轮发电机，其特征在于：所述的箔型弹性件由波箔和平箔组成，所述波箔的弧形凸起顶端与平箔相贴合。
  16. 根据权利要求1或14所述的超高速燃气轮发电机，其特征在于：所述的箔型弹性件由波箔和平箔组成，所述波箔的波拱间过渡底边与平箔相贴合。
  17. 根据权利要求1或14所述的超高速燃气轮发电机，其特征在于：所述的箔型弹性件由两个平箔组成。
  18. 根据权利要求1所述的超高速燃气轮发电机，其特征在于：所述转子包括转子底座、磁钢和磁钢保护套，所述转子底座套设在內轴上，所述磁钢套设在转子底座的中心部，所述磁钢保护套套设在磁钢上。
  19. 根据权利要求1所述的超高速燃气轮发电机，其特征在于：所述定子包括铁芯和绕组，所述铁芯固定在位于转子上方的电机壳体的内壁上，所述绕组设置在铁芯上。
  20. 根据权利要求19所述的超高速燃气轮发电机，其特征在于：所述铁芯包括由若干冲片上下叠置形成的定子叠片和固定在定子叠片两侧的端压板；所述冲片呈圆环形，在环形部间隔设有多个杯状穿孔，所述穿孔的杯口部封闭，杯脚的底部开口。
  21. 根据权利要求19所述的超高速燃气轮发电机，其特征在于：所述绕组为三相星型连 接，中心线不引出，只引出A、B、C三个端头。
  22. 根据权利要求21所述的超高速燃气轮发电机，其特征在于：每相绕组为2个线圈，每个线圈由漆包铜线连续绕制而成。
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