WO2022127054A1 - 具有平衡轴向力结构的微型燃气轮机 - Google Patents

具有平衡轴向力结构的微型燃气轮机 Download PDF

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Publication number
WO2022127054A1
WO2022127054A1 PCT/CN2021/099974 CN2021099974W WO2022127054A1 WO 2022127054 A1 WO2022127054 A1 WO 2022127054A1 CN 2021099974 W CN2021099974 W CN 2021099974W WO 2022127054 A1 WO2022127054 A1 WO 2022127054A1
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Prior art keywords
bearing
air
nut
gas turbine
rotating shaft
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PCT/CN2021/099974
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English (en)
French (fr)
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靳普
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至玥腾风科技集团有限公司
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Publication of WO2022127054A1 publication Critical patent/WO2022127054A1/zh

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    • 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
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • 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
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
    • 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
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • 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
    • 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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/266—Rotors specially for elastic fluids mounting compressor rotors on shafts
    • 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
    • F16C32/04—Bearings not otherwise provided for using magnetic or electric supporting means
    • F16C32/0402—Bearings not otherwise provided for using magnetic or electric supporting means combined with other supporting means, e.g. hybrid bearings with both magnetic and fluid supporting means
    • 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
    • F16C32/0614—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 the gas being supplied under pressure, e.g. aerostatic bearings
    • F16C32/0625—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 the gas being supplied under pressure, e.g. aerostatic bearings via supply slits
    • 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 a micro gas turbine with a balanced axial force structure, belonging to the technical field of micro gas turbines.
  • the micro gas turbine mainly includes three parts: compressor, combustion chamber and turbine. After the air enters the compressor, it is compressed into high temperature and high pressure air, and then supplied to the combustion chamber to mix and burn with fuel. . During the operation of the gas turbine, the airflow will generate an axial force on the rotor blades and the disk, thereby generating an axial force. In order to prevent the rotor from moving in the axial direction, the thrust bearing will bear the axial force from the gas turbine rotor. It can be known from aerodynamics that the axial force on the gas turbine compressor rotor is forward, while the axial force on the turbine rotor is backward.
  • the turbine rotor on the gas turbine generator needs to bear a backward axial force, but the compressor rotor needs to bear a larger forward axial force, even if the compressor rotor and the turbine rotor are integrated into one body.
  • the two opposite axial forces cancel each other out in part, and it is still a considerable forward axial force. Therefore, a load relief device must be provided to reduce the axial load of the rotor acting on the thrust bearing.
  • the present invention provides a micro gas turbine with a balanced axial force structure.
  • a micro gas turbine with a balanced axial force structure includes a rotating shaft, a compressor, a turbine and a combustion chamber, wherein the compressor and the turbine are mounted on the rotating shaft, the compressor communicates with a combustion chamber through a high-pressure air chamber, and an exhaust port of the combustion chamber Directly facing the turbine; a thrust disc is set on the rotating shaft, a thrust bearing is sleeved on the thrust disc, and a radial bearing is also set on the rotating shaft;
  • the thrust bearing includes a first bearing body and a second bearing body that are symmetrically arranged, the first bearing body and the second bearing body and the thrust plate are symmetrically installed in the axial direction and have a predetermined first axial gap; the first bearing body
  • the outer end wall of the main body is provided with a first air groove
  • the outer end wall of the second bearing body is provided with a second air groove
  • the bottoms of the first air groove and the second air groove are both provided with air holes that communicate with the corresponding air grooves and the air holes.
  • the corresponding first axial gap; the third radial gap is preset between the inner ring of the first bearing body and the second bearing body and the rotating shaft; the side wall of the thrust plate accommodating groove enclosed by the first bearing body and the second bearing body A fourth radial gap is set between the thrust plate and the side wall of the thrust plate;
  • the outer wall of the radial bearing is provided with a third air groove, and the bottom of the third air groove is provided with a transparent air hole, and the air hole communicates with the third air groove and the third air groove.
  • It also includes several air intake pipes, the first air groove, the second air groove and the third air groove are respectively connected with one air intake pipe, and the air intake pipe supplies air to each air groove;
  • the compressor is fixed on the intake end of the rotating shaft through the nut at its end; the end face of the nut is flat, and the outer end of the end face of the nut is provided with a bearing stator, and there is a bearing gap between the bearing stator and the end face of the nut; the high pressure
  • the air cavity communicates with the bearing clearance through a supplementary air intake pipe.
  • an air groove is provided on the end face of the nut and/or the side of the bearing stator against the nut; when the nut rotates, the flowing gas existing in the bearing gap is pressed into the air groove, thereby generating pressure to realize the axial direction of the nut. Hold non-contact.
  • the bearing gap is maintained between the nut and the bearing stator by means of magnetic force (a magnetic component is added).
  • a magnetic component is added.
  • the end face of the nut is provided with a first magnetic component
  • the side of the bearing stator against the nut is provided with a plurality of second magnetic components that can generate magnetic force with the first magnetic component in the circumferential direction, and the nut can be connected between the first magnetic component and the multiple magnetic components.
  • the rotating shaft is driven to move in the axial direction under the action of the magnetic force between the second magnetic components.
  • the first magnetic component includes a plurality of magnetic materials uniformly distributed in the circumferential direction on the end face of the nut;
  • the second magnetic component includes a plurality of permanent magnets, which are evenly distributed in the circumferential direction on the end surface of the bearing stator. ; or: the second magnetic component includes a plurality of electromagnets, the plurality of electromagnets are evenly distributed in the circumferential direction on the end face of the bearing stator, and each electromagnet in the plurality of electromagnets includes a magnetic magnet arranged on the end face of the bearing stator The core and the coil wound on the core.
  • bearing stator may be supported in a casing provided on the front side of the compressor by means of connecting rods or the like.
  • a pressure valve is set on the supplementary air inlet pipe to control the pressure of the supplementary gas.
  • both the thrust bearing and the radial bearing are air bearings.
  • the thrust plate and the thrust bearing are arranged in the middle of the rotating shaft; the radial bearing For two, set at both ends of the shaft.
  • the thrust bearing further includes a first bearing housing and a second bearing housing;
  • the first bearing housing includes an end portion and a circumferential portion, the end portion is mounted on the outer end of the first bearing body, and the circumferential portion is sealed Covered on the outer circumference of a radial bearing;
  • the second bearing housing includes a cylindrical first circumferential portion and a second circumferential portion arranged in steps, and the first circumferential portion is covered on the first bearing body and the second circumferential portion.
  • the outer circumference of the bearing body, the second circumferential portion sealing cover is provided on the outer circumference of the other radial bearing; the first circumferential portion of the second bearing housing is axially fixed with the end of the first bearing housing; the first bearing housing And/or the second bearing housing is a stationary part.
  • decompression holes are provided on the first bearing housing or/and the second bearing housing.
  • the gas when working, the gas first enters the compressor, is pressurized by the compressor, flows through the high-pressure gas chamber and then enters the combustion chamber for combustion, and the hot combustion product, that is, the high-temperature gas, exits the combustion chamber. It sprays out, pushes the turbine to rotate, and drives the compressor coaxially connected to it through the rotating shaft to rotate.
  • the compressor no longer needs to be driven by other devices, which can effectively reduce the operating cost of the equipment; the high-temperature gas after the turbine is rotated can be used for waste heat. recycled, or used to generate electricity.
  • the turbine of the generator can be placed at the end of the combustion chamber, so that its rim is located at the end of the exhaust port of the combustion chamber. thereby generating electricity.
  • the principle of balancing the axial force is: when starting the micro gas turbine, first close the supplementary intake pipe, open the other intake pipes, supply air to each air slot and enter the first axial gap and the second radial gap along the intake holes respectively. A gas film is formed; when the gas turbine rotor is in normal operation, the front and rear forces on the rotor are offset and the forward force remains. At this time, the remaining intake pipes are closed to maintain the static pressure of each bearing, and the supplementary intake pipe is opened.
  • the micro gas turbine with balanced axial force structure of the present invention sends the gas in the high-pressure gas chamber to the force-bearing surface of the air inlet end of the compressor, so that the gas in the high-pressure air chamber continuously presses the end face of the air inlet end of the compressor, So as to achieve the purpose of balancing the axial force.
  • the present invention makes the thrust bearing form a gas-magnetic hybrid thrust bearing by arranging a bearing gap and a magnetic bearing in the thrust bearing. In this way, since the gas bearing and the magnetic bearing can work together, the dynamic performance and stability of the thrust bearing (especially in the high-speed operation state) can be improved, and the anti-disturbance ability is strong, thereby improving the bearing capacity of the thrust bearing.
  • the micro gas turbine with the balanced axial force structure of the present invention can effectively reduce the axial force, increase the stability of the unit, reduce power consumption, improve the efficiency, and has no wearing parts, and can prolong the life of the unit.
  • Figure 1 Schematic diagram of the structure of a micro gas turbine (the arrows in the figure indicate the flow direction of the gas).
  • Figure 2 Schematic diagram of the structure of the air groove on the end face of the nut.
  • Example 1 A micro gas turbine with a balanced axial force structure
  • It includes a rotating shaft 24, a compressor 20, a turbine 21 and a combustion chamber 231, as shown in FIG. 1, wherein the compressor 20 and the turbine 21 are installed on the rotating shaft 24, and the compressor 20 communicates with the combustion chamber 231 through the high-pressure gas chamber 234, and the combustion chamber
  • the exhaust port of 231 is facing the turbine 21;
  • a thrust plate is arranged in the middle of the rotating shaft 24, a thrust bearing 241 is sleeved on the thrust plate, and a radial bearing 242 is arranged at each end of the rotating shaft 24; the thrust bearing 241 and the radial bearing 242 are both Air bearing.
  • the thrust bearing 241 includes a first bearing body 2411 and a second bearing body 2412 arranged symmetrically.
  • the first bearing body 2411 and the second bearing body 2412 are symmetrically installed with the thrust plate in the axial direction and have a predetermined first axial direction.
  • the outer end wall of the first bearing body 2411 is provided with a first air groove 2401
  • the outer end wall of the second bearing body 2412 is provided with a second air groove 2402
  • the bottoms of the first air groove 2401 and the second air groove 2402 are both provided with A permeable air hole, the air hole communicates with the corresponding air groove and the corresponding first axial gap S1
  • a third radial gap S3 is preset between the inner rings of the first bearing body 2411 and the second bearing body 2412 and the rotating shaft 24
  • the first A fourth radial gap S4 is provided between the side wall of the thrust disc accommodating groove 244 and the side wall of the thrust disc enclosed by the bearing body 2411 and the second bearing body 2412 .
  • the outer wall of the radial bearing 242 is provided with a third air groove 2403, and the bottom of the third air groove 2403 is provided with a transparent air hole, the air hole
  • the third air groove 2403 is communicated with the second radial gap S2.
  • the first air groove 2401, the second air groove 2402 and the third air groove 2403 are respectively communicated with one air intake pipe 243, and the air intake pipe 243 supplies air to each air groove.
  • the compressor 20 is fixed on the intake end of the rotating shaft 21 through the nut at its end; the end face of the nut 3 is flat, and the outer end of the end face of the nut 3 is provided with a bearing stator 4, and there is a bearing stator 4 and the end face of the nut 3.
  • a pressure valve may be set on the supplementary air inlet pipe to control the pressure of supplementary gas.
  • An air groove 301 is provided on the end face of the nut 3, as shown in FIG. 2; when the nut 3 rotates, the flowing gas existing in the bearing gap S5 is pressed into the air groove 301, thereby generating pressure to realize the axial direction of the nut 3. Hold non-contact.
  • the bearing stator 4 may be supported in a casing provided on the front side of the compressor 20 by means of connecting rods or the like.
  • the above-mentioned micro gas turbine with a balanced axial force structure when working, the gas first enters the compressor 20, is pressurized by the compressor 20, flows through the high-pressure gas chamber 234, and then enters the combustion chamber 231 for combustion, and the hot combustion product, that is, the high-temperature gas flows from the gas.
  • the outlet of the combustion chamber 231 is ejected, which drives the turbine 21 to rotate, and drives the compressor 20 that is coaxially connected to it through the rotating shaft 24 to rotate.
  • the high-temperature gas after 21 rotation can be used for waste heat recovery, or for power generation.
  • the turbine of the generator can be placed at the end of the combustion chamber, so that its rim is located at the end of the exhaust port of the combustion chamber. turn to generate electricity.
  • the principle of balancing the axial force is: when starting the micro gas turbine, first close the supplementary intake pipe 2431, open the other intake pipes, supply air to each air slot and enter the first axial gap S1 and the second radial gap along the intake holes respectively. A gas film is formed in the gap S2; when the gas turbine rotor is in normal operation, the front and rear forces on the rotor are offset and the forward force remains.
  • Example 2 A micro gas turbine with a balanced axial force structure
  • the bearing gap S5 is also maintained between the nut 3 and the bearing stator 4 by magnetic force: the end face of the nut 3 is provided with a first magnetic component, and the side of the bearing stator 4 against the nut 3 is circumferentially arranged with the first magnetic component.
  • the plurality of second magnetic components of magnetic force, the nut 3 can drive the rotating shaft 24 to move in the axial direction under the action of the magnetic force between the first magnetic component and the plurality of second magnetic components.
  • the first magnetic component includes a plurality of magnetic materials uniformly distributed in the circumferential direction on the end face of the nut 3 ; the second magnetic component includes a plurality of permanent magnets, which are evenly distributed in the circumferential direction on the end surface of the bearing stator 4 .
  • Example 3 A micro gas turbine with balanced axial force structure
  • the bearing gap S5 is also maintained between the nut 3 and the bearing stator 4 by magnetic force: the end face of the nut 3 is provided with a first magnetic component, and the side of the bearing stator 4 against the nut 3 is circumferentially arranged with the first magnetic component.
  • the plurality of second magnetic components of magnetic force, the nut 3 can drive the rotating shaft 24 to move in the axial direction under the action of the magnetic force between the first magnetic component and the plurality of second magnetic components.
  • the first magnetic component includes a plurality of magnetic materials uniformly distributed in the circumferential direction on the end face of the nut 3; the second magnetic component includes a plurality of electromagnets, and the plurality of electromagnets are radially distributed along the circumferential direction on the end face of the bearing stator 4. Evenly distributed, each electromagnet in the plurality of electromagnets includes a magnetic core disposed on the end face of the bearing stator 4 and a coil wound on the magnetic core.
  • Example 4 A micro gas turbine with balanced axial force structure
  • the thrust bearing 241 further includes a first bearing housing 281 and a second bearing housing 282, as shown in FIG. 1;
  • the first bearing housing 281 includes an end portion and a circumferential portion, the end portion of which is mounted on the first bearing body At the outer end of 2411, its circumferential portion sealing cover is provided on the outer circumference of a radial bearing 242;
  • the second bearing housing 282 includes a cylindrical first circumferential portion and a second circumferential portion arranged in steps, the first circumferential portion Covered on the outer circumference of the first bearing body 2411 and the second bearing body 2412, the second circumferential portion sealing cover is provided on the outer circumference of the other radial bearing 242;
  • the first circumferential portion of the second bearing housing 282 is axially and
  • the end of the first bearing housing 281 is fixed;
  • the first bearing housing 281 and/or the second bearing housing 282 are stationary components.
  • the first bearing housing 281 or/and the second bearing housing 282 may be provided with de

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  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
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  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Magnetic Bearings And Hydrostatic Bearings (AREA)

Abstract

一种具有平衡轴向力结构的微型燃气轮机，包括转轴（24）、压气机（20）、涡轮（21）和燃烧室（231），其中，压气机（20）和涡轮（21）安装在转轴（24）上，压气机（20）通过高压气腔（234）连通燃烧室（231），燃烧室（231）的排气口正对涡轮（21）；推力轴承（241）及径向轴承（242）通过进气管（243）供气；高压气腔（234）通过一补充进气管（2431）连通轴承间隙（S5），螺母（3）与轴承定子（4）之间依靠空气推力和磁力保持轴承间隙（S5）。

Description

具有平衡轴向力结构的微型燃气轮机 技术领域
本发明涉及一种具有平衡轴向力结构的微型燃气轮机，属于微型燃气轮机技术领域。
背景技术
微型燃气轮机主要包括压气机、燃烧室及透平三大部件，空气进入压气机后被压缩成高温高压的空气，然后供给燃烧室与燃料混合燃烧，其产生的高温高压燃气在透平中膨胀做功。燃气轮机在运行过程中，气流会对转子叶片及轮盘产生轴向力作用，从而产生轴向上的力。而为了防止转子发生轴向上的移动，推力轴承会承受来自燃气轮机转子的轴向力。由气体动力学可知：燃气轮机压气机转子上的轴向力是向前的，而涡轮转子上的轴向力是向后的。在最大工况下，燃气轮机发生器上涡轮转子需要承受向后的轴向力，然而压气机转子需要承受更大的向前的轴向力，即便压气机转子和涡轮转子连成一体后转子上的两个方向相反的轴向力相互抵消了一部分，仍是一个数值相当大的向前的轴向力。因此，必须设置减荷装置，以减少转子作用在止推轴承上的轴向负荷。
发明内容
针对上述现有技术，本发明提供了一种具有平衡轴向力结构的微型燃气轮机。
本发明是通过以下技术方案实现的：
一种具有平衡轴向力结构的微型燃气轮机，包括转轴、压气机、涡轮和燃烧室，其中，压气机和涡轮安装在转轴上，压气机通过高压气腔连通燃烧室，燃烧室的排气口正对涡轮；转轴上设置推力盘，推力盘上套设推力轴承，转轴上还设置有径向轴承；
所述推力轴承，包括对称设置的第一轴承本体和第二轴承本体，第一轴承本体和第二轴承本体与推力盘在轴向上对称安装且具有预定的第一轴向间隙；第一轴承本体的外端壁设置第一空气槽，第二轴承本体的外端壁设置第二空气槽，第一空气槽和第二空气槽底部均设置通透的气孔，该气孔连通对应的空气槽和对应的第一轴向间隙；第一轴承本体和第二轴承本体内圈与转轴之间预设第三径向间隙；第一轴承本体和第二轴承本体围成的推力盘容置槽侧壁与推力盘侧壁之间设置第四径向间隙；
所述径向轴承的内壁和转轴之间具有预定的第二径向间隙；径向轴承的外壁设置第三空气槽，第三空气槽底部设置通透的气孔，该气孔连通第三空气槽和第二径向间隙；
还包括若干条进气管，第一空气槽、第二空气槽和第三空气槽分别与一条进气管连通，由进气管向各空气槽供气；
所述压气机通过其端部的螺母固定在转轴的进气端；所述螺母的端面为平面，且螺母端面外端设置轴承定子，轴承定子与螺母端面之间存在一轴承间隙；所述高压气腔通过一补充进气管连通轴承间隙。
进一步地，所述螺母端面和/或轴承定子靠螺母的一面设置空气槽；当螺母旋转时，存在于轴承间隙的流动气体被压入空气槽内，从而产生压力，以实现螺母沿轴向方向非接触地保持。
进一步地，所述螺母与轴承定子之间还依靠磁力保持轴承间隙(增设磁性部件)。具体地，螺母端面设置有第一磁性部件，轴承定子靠螺母的一面沿周向设置有能够与第一磁性部件之间产生磁力的多个第二磁性部件，螺母能够在第一磁性部件和多个第二磁性部件之间的磁力作用下带动转轴在轴向方向上移动。
再进一步地，第一磁性部件包括多个在螺母端面上沿周向呈辐状均匀分布的磁性材料；第二磁性部件包括多个永磁体，在轴承定子端面上沿周向呈辐状均匀分布；或：第二磁性部件包括多个电磁铁，多个电磁铁在轴承定子端面上沿周向呈辐状均匀分布，多个电磁铁中的每个电磁铁包括设置于轴承定子端面上的磁芯及缠绕于磁芯上的线圈。
进一步地，所述轴承定子可通过连杆等方式支撑于压气机前侧罩设的壳体内。
进一步地，所述补充进气管上设置压力阀，用于控制补充气体的压力大小。
进一步地，所述推力轴承和径向轴承均为空气轴承。
进一步地，轴承数量及位置变化可以根据本发明的技术构思做出各种相应的改变和变形，优选的一种方式是：所述推力盘及推力轴承设置在转轴的中部；所述径向轴承为两个，设置在转轴的两端。
进一步地，所述推力轴承还包括第一轴承壳体以及第二轴承壳体；所述第一轴承壳体包括端部和周向部，其端部安装于第一轴承本体的外端，其周向部密封罩设于一径向轴承的外周；所述第二轴承壳体包括阶梯布置的圆筒状的第一周向部和第二周向部，第一周向部罩设于第一轴承本体和第二轴承本体的外周，第二周向部密封罩设于另一径向轴承的外周；第二轴承壳体的第一周向部在轴向上与第一轴承壳体端部固定；第一轴承壳体和/或第二轴承壳体为静止部件。
进一步地，所述第一轴承壳体或/和第二轴承壳体上开设减压孔。
本发明的具有平衡轴向力结构的微型燃气轮机，工作时，气体首先进入压气机，经压气机增压、流经高压气腔后进入燃烧室内燃烧，热的燃烧产物即高温气从燃烧室出口喷出，推动涡轮旋转，并带动与其通过转轴同轴连接的压气机旋转，如此，压气机运转就不再需要其 他装置驱动，可有效降低设备运行成本；推动涡轮旋转后的高温气可用于余热回收，或者用于发电。用于发电时，可将发电机的涡轮置于燃烧室末端，使其轮缘位于燃烧室的排气口末端，高温气依次推动涡轮转动和发电机的涡轮转动，进而带动发电机的转轴转动从而发电。
平衡轴向力的原理是：启动微型燃气轮机时，先关闭补充进气管，开启其余各进气管，向各空气槽供气并沿进气孔分别进入第一轴向间隙、第二径向间隙内形成气膜；当燃气轮机转子正常运行后，转子所受的前后两个方向作用力抵消后还剩余向前的作用力，此时关闭其余各进气管，使各个轴承维持静压，打开补充进气管，使高压气腔内的部分气体进入轴承间隙S5，从前侧形成气推力轴承(螺母3与轴承定子4之间增加磁力保持轴承间隙S5时，形成气、磁混合推力轴承)，进而减小或抵消作用力(可通过压力阀控制补充气体的压力大小)。
本发明的具有平衡轴向力结构的微型燃气轮机，是将高压气腔内气体送至压气机进气端的受力面内，使高压气腔内的气体持续对压气机进气端的端面施压，从而达到平衡轴向力的目的。更进一步地，本发明通过在推力轴承中设置轴承间隙和磁轴承，从而使该推力轴承形成气、磁混合推力轴承。如此，由于气体轴承与磁轴承能够协同工作，能够改善推力轴承(尤其在高速运转状态下)的动态性能和稳定性，抗受扰动能力强，进而提高了推力轴承的承载能力。本发明的具有平衡轴向力结构的微型燃气轮机，可有效降低轴向力，增加机组稳定性，降低功耗，提升效率，且没有易损件，可延长机组寿命。
本发明使用的各种术语和短语具有本领域技术人员公知的一般含义。提及的术语和短语如有与公知含义不一致的，以本发明所表述的含义为准。
附图说明
图1：微型燃气轮机的结构示意图(图中箭头所示为气体的流动方向)。
图2：螺母端面设置空气槽的结构示意图。
其中，20-压气机；21-涡轮；231-燃烧室；234-高压气腔；24-转轴；241-推力轴承；2411-第一轴承本体；2412-第二轴承本体；242-径向轴承；243-进气管；2431-补充进气管；281-第一轴承壳体；282-第二轴承壳体；S1-第一径向间隙；S2-第二轴向间隙；S3-第三轴向间隙；S4-第四轴向间隙；3-螺母；301-空气槽；4-轴承定子；S5-轴承间隙；2401-第一空气槽；2402-第二空气槽；2403-第三空气槽；244-推力盘容置槽。
具体实施方式
下面结合实施例对本发明作进一步的说明。然而，本发明的范围并不限于下述实施例。本领域的专业人员能够理解，在不背离本发明的精神和范围的前提下，可以对本发明进行各种变化和修饰。
实施例1 一种具有平衡轴向力结构的微型燃气轮机
包括转轴24、压气机20、涡轮21和燃烧室231，如图1所示，其中，压气机20和涡轮21安装在转轴24上，压气机20通过高压气腔234连通燃烧室231，燃烧室231的排气口正对涡轮21；转轴24中部设置推力盘，推力盘上套设推力轴承241，转轴24两端各设置一个径向轴承242；所述推力轴承241和径向轴承242均为空气轴承。
所述推力轴承241，包括对称设置的第一轴承本体2411和第二轴承本体2412，第一轴承本体2411和第二轴承本体2412与推力盘在轴向上对称安装且具有预定的第一轴向间隙S1；第一轴承本体2411的外端壁设置第一空气槽2401，第二轴承本体2412的外端壁设置第二空气槽2402，第一空气槽2401和第二空气槽2402底部均设置通透的气孔，该气孔连通对应的空气槽和对应的第一轴向间隙S1；第一轴承本体2411和第二轴承本体2412内圈与转轴24之间预设第三径向间隙S3；第一轴承本体2411和第二轴承本体2412围成的推力盘容置槽244侧壁与推力盘侧壁之间设置第四径向间隙S4。
所述径向轴承242的内壁和转轴24之间具有预定的第二径向间隙S2；径向轴承242的外壁设置第三空气槽2403，第三空气槽2403底部设置通透的气孔，该气孔连通第三空气槽2403和第二径向间隙S2。
还包括4条进气管243，第一空气槽2401、第二空气槽2402和第三空气槽2403(两个)分别与一条进气管243连通，由进气管243向各空气槽供气。
所述压气机20通过其端部的螺母固定在转轴21的进气端；所述螺母3的端面为平面，且螺母3端面外端设置轴承定子4，轴承定子4与螺母3端面之间存在一轴承间隙S5；所述高压气腔234通过一补充进气管2431连通轴承间隙S5。所述补充进气管上可以设置压力阀，用于控制补充气体的压力大小。
所述螺母3端面设置空气槽301，如图2所示；当螺母3旋转时，存在于轴承间隙S5的流动气体被压入空气槽301内，从而产生压力，以实现螺母3沿轴向方向非接触地保持。
所述轴承定子4可通过连杆等方式支撑于压气机20前侧罩设的壳体内。
上述具有平衡轴向力结构的微型燃气轮机，工作时，气体首先进入压气机20，经压气机20增压、流经高压气腔234后进入燃烧室231内燃烧，热的燃烧产物即高温气从燃烧室231出口喷出，推动涡轮21旋转，并带动与其通过转轴24同轴连接的压气机20旋转，如此，压气机20运转就不再需要其他装置驱动，可有效降低设备运行成本；推动涡轮21旋转后的高温气可用于余热回收，或者用于发电。用于发电时，可将发电机的涡轮置于燃烧室末端，使其轮缘位于燃烧室的排气口末端，高温气依次推动涡轮21转动和发电机的涡轮转动，进而带 动发电机的转轴转动从而发电。
平衡轴向力的原理是：启动微型燃气轮机时，先关闭补充进气管2431，开启其余各进气管，向各空气槽供气并沿进气孔分别进入第一轴向间隙S1、第二径向间隙S2内形成气膜；当燃气轮机转子正常运行后，转子所受的前后两个方向作用力抵消后还剩余向前的作用力，此时关闭其余各进气管，使各个轴承维持静压，打开补充进气管2431，使高压气腔内的部分气体进入轴承间隙S5，从前侧形成气推力轴承(螺母3与轴承定子4之间增加磁力保持轴承间隙S5时，形成气、磁混合推力轴承)，进而减小或抵消作用力(可通过压力阀控制补充气体的压力大小)。
实施例2 一种具有平衡轴向力结构的微型燃气轮机
结构同实施例1，不同之处在于：
所述螺母3与轴承定子4之间还依靠磁力保持轴承间隙S5：螺母3端面设置有第一磁性部件，轴承定子4靠螺母3的一面沿周向设置有能够与第一磁性部件之间产生磁力的多个第二磁性部件，螺母3能够在第一磁性部件和多个第二磁性部件之间的磁力作用下带动转轴24在轴向方向上移动。
第一磁性部件包括多个在螺母3端面上沿周向呈辐状均匀分布的磁性材料；第二磁性部件包括多个永磁体，在轴承定子4端面上沿周向呈辐状均匀分布。
实施例3 一种具有平衡轴向力结构的微型燃气轮机
结构同实施例1，不同之处在于：
所述螺母3与轴承定子4之间还依靠磁力保持轴承间隙S5：螺母3端面设置有第一磁性部件，轴承定子4靠螺母3的一面沿周向设置有能够与第一磁性部件之间产生磁力的多个第二磁性部件，螺母3能够在第一磁性部件和多个第二磁性部件之间的磁力作用下带动转轴24在轴向方向上移动。
第一磁性部件包括多个在螺母3端面上沿周向呈辐状均匀分布的磁性材料；第二磁性部件包括多个电磁铁，多个电磁铁在轴承定子4端面上沿周向呈辐状均匀分布，多个电磁铁中的每个电磁铁包括设置于轴承定子4端面上的磁芯及缠绕于磁芯上的线圈。
实施例4 一种具有平衡轴向力结构的微型燃气轮机
结构同实施例1、2或3，不同之处在于：
所述推力轴承241还包括第一轴承壳体281以及第二轴承壳体282，如图1所示；所述第一轴承壳体281包括端部和周向部，其端部安装于第一轴承本体2411的外端，其周向部密封罩设于一径向轴承242的外周；所述第二轴承壳体282包括阶梯布置的圆筒状的第一周向 部和第二周向部，第一周向部罩设于第一轴承本体2411和第二轴承本体2412的外周，第二周向部密封罩设于另一径向轴承242的外周；第二轴承壳体282的第一周向部在轴向上与第一轴承壳体281端部固定；第一轴承壳体281和/或第二轴承壳体282为静止部件。所述第一轴承壳体281或/和第二轴承壳体282上可以开设减压孔。
给本领域技术人员提供上述实施例，以完全公开和描述如何实施和使用所主张的实施方案，而不是用于限制本文公开的范围。对于本领域技术人员而言显而易见的修饰将在所附权利要求的范围内。

Claims (10)

  1. 一种具有平衡轴向力结构的微型燃气轮机，其特征在于：包括转轴、压气机、涡轮和燃烧室，其中，压气机和涡轮安装在转轴上，压气机通过高压气腔连通燃烧室，燃烧室的排气口正对涡轮；转轴上设置推力盘，推力盘上套设推力轴承，转轴上还设置有径向轴承；
    所述推力轴承，包括对称设置的第一轴承本体和第二轴承本体，第一轴承本体和第二轴承本体与推力盘在轴向上对称安装且具有预定的第一轴向间隙；第一轴承本体的外端壁设置第一空气槽，第二轴承本体的外端壁设置第二空气槽，第一空气槽和第二空气槽底部均设置通透的气孔，该气孔连通对应的空气槽和对应的第一轴向间隙；第一轴承本体和第二轴承本体内圈与转轴之间预设第三径向间隙；第一轴承本体和第二轴承本体围成的推力盘容置槽侧壁与推力盘侧壁之间设置第四径向间隙；
    所述径向轴承的内壁和转轴之间具有预定的第二径向间隙；径向轴承的外壁设置第三空气槽，第三空气槽底部设置通透的气孔，该气孔连通第三空气槽和第二径向间隙；
    还包括若干条进气管，第一空气槽、第二空气槽和第三空气槽分别与一条进气管连通，由进气管向各空气槽供气；
    所述压气机通过其端部的螺母固定在转轴的进气端；所述螺母的端面为平面，且螺母端面外端设置轴承定子，轴承定子与螺母端面之间存在一轴承间隙；所述高压气腔通过一补充进气管连通轴承间隙。
  2. 根据权利要求1所述的具有平衡轴向力结构的微型燃气轮机，其特征在于：所述螺母端面和/或轴承定子靠螺母的一面设置空气槽。
  3. 根据权利要求1所述的具有平衡轴向力结构的微型燃气轮机，其特征在于：所述螺母与轴承定子之间增设磁性部件，使二者之间还依靠磁力保持轴承间隙。
  4. 根据权利要求3所述的具有平衡轴向力结构的微型燃气轮机，其特征在于：所述螺母端面设置有第一磁性部件，轴承定子靠螺母的一面沿周向设置有能够与第一磁性部件之间产生磁力的多个第二磁性部件，螺母能够在第一磁性部件和多个第二磁性部件之间的磁力作用下带动转轴在轴向方向上移动。
  5. 根据权利要求4所述的具有平衡轴向力结构的微型燃气轮机，其特征在于：所述第一磁性部件包括多个在螺母端面上沿周向呈辐状均匀分布的磁性材料；第二磁性部件包括多个永磁体，在轴承定子端面上沿周向呈辐状均匀分布；或：第二磁性部件包括多个电磁铁，多个电磁铁在轴承定子端面上沿周向呈辐状均匀分布，多个电磁铁中的每个电磁铁包括设置于轴承定子端面上的磁芯及缠绕于磁芯上的线圈。
  6. 根据权利要求1所述的具有平衡轴向力结构的微型燃气轮机，其特征在于：所述轴承 定子通过连杆支撑于压气机前侧罩设的壳体内。
  7. 根据权利要求1所述的具有平衡轴向力结构的微型燃气轮机，其特征在于：所述补充进气管上设置压力阀。
  8. 根据权利要求1所述的具有平衡轴向力结构的微型燃气轮机，其特征在于：所述推力盘及推力轴承设置在转轴的中部；所述径向轴承为两个，设置在转轴24的两端。
  9. 根据权利要求1或8所述的具有平衡轴向力结构的微型燃气轮机，其特征在于：所述推力轴承还包括第一轴承壳体以及第二轴承壳体；所述第一轴承壳体包括端部和周向部，其端部安装于第一轴承本体的外端，其周向部密封罩设于一径向轴承的外周；所述第二轴承壳体包括阶梯布置的圆筒状的第一周向部和第二周向部，第一周向部罩设于第一轴承本体和第二轴承本体的外周，第二周向部密封罩设于另一径向轴承的外周；第二轴承壳体的第一周向部在轴向上与第一轴承壳体端部固定；第一轴承壳体和/或第二轴承壳体为静止部件。
  10. 根据权利要求9所述的具有平衡轴向力结构的微型燃气轮机，其特征在于：所述第一轴承壳体或/和第二轴承壳体上开设减压孔。
PCT/CN2021/099974 2020-12-14 2021-06-15 具有平衡轴向力结构的微型燃气轮机 WO2022127054A1 (zh)

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