CN102094712A - Micro gas turbine system with gas bearing-rotor structure - Google Patents
Micro gas turbine system with gas bearing-rotor structure Download PDFInfo
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- CN102094712A CN102094712A CN2009102507236A CN200910250723A CN102094712A CN 102094712 A CN102094712 A CN 102094712A CN 2009102507236 A CN2009102507236 A CN 2009102507236A CN 200910250723 A CN200910250723 A CN 200910250723A CN 102094712 A CN102094712 A CN 102094712A
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- 230000003068 static effect Effects 0.000 claims abstract description 19
- 238000013461 design Methods 0.000 claims abstract description 14
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims abstract description 10
- 239000000463 material Substances 0.000 claims abstract description 9
- 229920001967 Metal rubber Polymers 0.000 claims abstract description 7
- 238000000034 method Methods 0.000 claims abstract description 6
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 claims abstract description 5
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims abstract description 5
- 238000009413 insulation Methods 0.000 claims abstract description 5
- 229910052750 molybdenum Inorganic materials 0.000 claims abstract description 5
- 239000011733 molybdenum Substances 0.000 claims abstract description 5
- 229910052759 nickel Inorganic materials 0.000 claims abstract description 5
- 239000010936 titanium Substances 0.000 claims abstract description 5
- 229910052719 titanium Inorganic materials 0.000 claims abstract description 5
- 230000001050 lubricating effect Effects 0.000 claims description 12
- 238000002485 combustion reaction Methods 0.000 claims description 11
- 238000013016 damping Methods 0.000 claims description 5
- 230000008878 coupling Effects 0.000 claims description 2
- 238000010168 coupling process Methods 0.000 claims description 2
- 238000005859 coupling reaction Methods 0.000 claims description 2
- 230000002706 hydrostatic effect Effects 0.000 claims description 2
- 238000012545 processing Methods 0.000 claims description 2
- 238000010276 construction Methods 0.000 claims 1
- 238000005461 lubrication Methods 0.000 abstract description 10
- 239000004519 grease Substances 0.000 abstract description 5
- 238000004519 manufacturing process Methods 0.000 abstract description 5
- 238000012423 maintenance Methods 0.000 abstract description 2
- 239000007789 gas Substances 0.000 description 64
- 238000005516 engineering process Methods 0.000 description 6
- 238000010304 firing Methods 0.000 description 6
- 238000005096 rolling process Methods 0.000 description 4
- 238000010438 heat treatment Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 230000033001 locomotion Effects 0.000 description 2
- 239000000725 suspension Substances 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 240000002853 Nelumbo nucifera Species 0.000 description 1
- 235000006508 Nelumbo nucifera Nutrition 0.000 description 1
- 235000006510 Nelumbo pentapetala Nutrition 0.000 description 1
- 238000005299 abrasion Methods 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 239000000306 component Substances 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000007667 floating Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 229910002804 graphite Inorganic materials 0.000 description 1
- 239000010439 graphite Substances 0.000 description 1
- 239000000314 lubricant Substances 0.000 description 1
- 230000035800 maturation Effects 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 239000008041 oiling agent Substances 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
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Abstract
气浮轴承-转子结构的微型燃气轮机系统是一种新结构形式的旋转机械系统。这种系统的结构特征是使用气体润滑轴承作为微型燃气轮机转子系统的支撑轴承，气体轴承采用动压、静压和动静压混合的三种润滑方式；轴承体采用耐磨、耐高温的镍、钼、钛等特殊自润滑材料，并采用金属橡胶等作为减振隔热的结构设计措施。这种气体轴承支撑的微型燃气轮机转子结构系统，极大地简化了燃气轮机的结构设计，降低了制造和维护成本，大大提高了工作转速，磨损更小，效率更高。这种结构设计可以广泛应用于各种微型涡轮喷气发动机，以及微型燃气轮机-发电机系统，与燃机连接的发电机和电动机也可使用气体润滑轴承。气体轴承支撑结构具有结构简单、运行稳定、清洁环保、轻便耐用的特点，相比于传统的油脂润滑轴承系统具有更长久的使用寿命，进一步拓宽了气体轴承产品在能源动力和航空航天领域工程应用的范围。
The micro gas turbine system with air bearing-rotor structure is a new type of rotating machinery system. The structural feature of this system is to use gas lubricated bearings as the supporting bearings of the micro gas turbine rotor system. The gas bearings adopt three lubrication methods of dynamic pressure, static pressure and dynamic and static pressure; the bearing body is made of wear-resistant and high-temperature resistant nickel and molybdenum. , titanium and other special self-lubricating materials, and use metal rubber as structural design measures for vibration reduction and heat insulation. The micro gas turbine rotor structure system supported by gas bearings greatly simplifies the structural design of the gas turbine, reduces manufacturing and maintenance costs, greatly increases the working speed, has less wear and tear, and has higher efficiency. This structural design can be widely applied to various microturbine jet engines and micro gas turbine-generator systems, and the generator and electric motor connected to the gas turbine can also use gas lubricated bearings. The gas bearing support structure has the characteristics of simple structure, stable operation, clean and environmentally friendly, light and durable. Compared with the traditional grease lubricated bearing system, it has a longer service life, which further broadens the engineering application of gas bearing products in the fields of energy, power and aerospace range.
Description
Technical field: the present invention relates to gas bearing design and manufacturing technology, micro-gas-turbine machine technology, and the rotating machinery structural system of using gases bearings.Can be widely used in fields such as Aero-Space, energy source and power and defence and military.
Background technique: the bearing rotor structure is the common structure form in the rotating machinery.This structure can together be used with structures such as gas compressor, turbine, firing chamber, regenerators, and becomes the core component of miniature gas turbine system.Therefore, high-efficiency reliable is lubricated to be supported for the miniature gas turbine system provides, and is the major issue that bearing is used.
At present, conventional fat lubricating bearings (rolling bearing or grease sliding bearing) is the main support form of miniature gas turbine system.The advantage of this supporting form is a technology maturation, is simple and easy to use.But; continuous rising along with rotating speed; frictional heating is very serious; the high temperature that while turbine heat end piece stands when work can be delivered to bearing by main shaft; lubricant grease causes bearing fault through regular meeting owing to rotten when high-temperature severe environment is worked, greatly influenced system works efficient and life-span.Simultaneously, because oily lubricating bearings needs corresponding fuel feeding lubrication system, make structure relative complex also increase manufacturing maintenance cost and system weight with safeguarding.
Gas bearing is a new high-tech product that develops rapidly mid-term in 20th century, its principle is the viscosity that relies on gas, improve the pressure of gas in the gap, thereby axle suspension is floated next bearing, using gases is lubricated, just there is not the problem of oiling agent pyrometamorphism, also can realizes the function of cooling off simultaneously.It does not have the restriction of general rolling bearing to ultrahigh rotating speed, makes the miniature gas turbine system can obtain higher rotating speed and performance.Owing to cancelled complicated heavy fuel feeding lubrication system, make simple in structure, safeguard use convenient.Therefore, gas bearing as supporting form, is used for the miniature gas turbine system, has outstanding usability and development prospect.
Two kinds of principal modes of miniature gas turbine are that miniature turbine jet or turbofan engine and ground are used to generate electricity and the miniature gas turbine-generator system of distributed energy.Gas bearing goes for the miniature gas turbine of above two kinds of forms owing to its unique good performance.
Series of advantages such as the application of gas bearing does not at present more and more widely have the machinery contact because of it has, and frictional loss is little, vibration is little, noise is low, fundamentally overcome traditional supporting form intrinsic shortcoming.Owing to adopted technology such as gas lubrication, graphite alloy and metal-rubber sealing, when being used for turbojet or turbofan engine, can solve effectively that metal rolling bearing weight is big, poor lubrication, problem that heat resistance is low, effectively improved motor thrust weight ratio, reliability and shelf life; When being applied to miniature gas turbine-generator system, not only, the gas turbine core engine supports for providing lubricated effectively reliably, also solved the support lubrication problem of high-speed engine rotor, shortcomings such as the weight of having avoided using electromagnetic bearing and rolling bearing to bring in the conventional generator is big, complex structure, power consumption height.
Therefore, what patent application of the present invention proposed is a kind of brand-new design and application thinking for gas turbine engine systems rotor supports and lubricated form, realizes the feasible evolution of the conventional grease lubricating bearings of miniature and small-sized gas turbine to gas bearing.
Summary of the invention: the technical disadvantages that the objective of the invention is to overcome the miniature gas turbine system that has the grease lubrication bearings now, a kind of new structure form is proposed, the miniature gas turbine structural system that the using gases lubricating bearings supports, its rotor-impeller-bearing structure such as Fig. 1.This bearings form has not only greatly improved gas turbine bearing-rotor surface of contact wear-resisting property, and has improved system's rotating speed, performance and reliability greatly, reduces design and manufacture cost, and environmental protection and energy saving more.
Core technology of the present invention is to use gas bearing to provide lubricated for the miniature gas turbine structure and supports.Use the gas bearing of static pressure, dynamic pressure and active and static pressure mixed form, its principle is the structural feature according to gas bearing and axle journal sound parts, at dynamic and static gaps runner place, the power that utilizes the axle journal rotation to drive fluid pressurized and outside supply gas pressure coupling generation makes its axle suspension float.Bearing inner surface is offered runner-type line, then is to utilize the take offence effect of body supercharging of axle journal rotating band, for rotor provides dynamic pressure carrying effect, as Fig. 2; Offer many row pressures power air vent at the floating ring body, provide static pressure carrying and damping function to rotor, as Fig. 3; Application conditions at gas bearing, adopt special self lubricating materials such as wear-resisting, high temperature resistant, high-intensity nickel, molybdenum, titanium as gas bearing body material, solved the abrasion of supercharging flow path groove sound parts short-time contact, and the heating of gas turbine hot-end component is to the problem that influences of bearing lubrication; Adopt metal rubber material heat insulation and damping technology measure, can effectively reduce the heat transfer of turbine hot junction, also improved the stability of high speed rotor carrying operation simultaneously bearing as bearing.
Technological scheme of the present invention mainly realizes as follows:
1. the selection of gas bearing body material, promptly according to the conditions such as temperature, pressure and working medium of gas bearing application, special self lubricating materials such as wear-resisting, the resistant to elevated temperatures nickel of choose reasonable, molybdenum, titanium are as gas bearing body material;
2. gas turbine, the electric machine structure design supported of gas bearing promptly according to axle journal rotation, whirling motion rotating speed and bear load character, rationally determined gas compressor-impeller working speed, pressure ratio and flow, determines physical dimension, geometric form line.The maximum static lotus of bearing according to gas bearing is that 10kg, rotor maximum functional rotating speed are 50000～80000rpm, determines rotor physical dimension, architecture quality and bearings layout.
3. the body structure of gas bearing design, i.e. conditions such as the load character of bearing according to gas bearing, stability and working medium, conduit molded lines in determining adopts measures such as metal-rubber, finishes the design of impeller of rotor system architecture, intensity and the stability of motions of gas bearing support;
4. the processing of gas bearing and gas turbine and manufacturing, promptly according to the technological requirement of structural designs such as gas bearing and impeller, volute, rotor, selection can be satisfied the equipment of required precision and make, processes and assemble.
Embodiments of the invention are as follows:
As shown in Figure 4, a kind of miniature gas turbine-generator system comprises: 1, motor stator 2, motor bearings 3, shaft joint 4, gas compressor volute 5, compressor impeller 6, combustion machine main shaft 7, intermediate 8, firing chamber 9, turbine volute 10, turbine wheel 11, regenerator 12, combustion machine bearing 13, the outside air vent of bearing.
As shown in Figure 5, a kind of miniature turbine jet engines system comprises 1, suction port 2, preceding spindle nut 3, compressor casing 4, compressor impeller 5, blower outlet Diffuser 6, cannular combustion chamber 7, bearing positioning ring 8, main shaft 9, H type joint bearing 10, bearing thrust dish 11, axle sleeve 12, turbine air inlet guide vane 13, turbine 14, jet pipe.
The rotor of gas turbine uses the gas bearing of dynamic pressure, static pressure and dynamic and static pressure lubricating form, and in the present embodiment, the H type joint bearing of the dynamic pressure selflubricating form that the combustion machine bearing adopts adopts metal-rubber as bearing vibration damping and heat insulation measures simultaneously.
Description of drawings
Fig. 1 is the impeller of rotor structure that gas bearing supports.Among Fig. 1,1 is rotor, and 2 is gas bearing, and 3 is compressor impeller, and 4 is turbine wheel.
Fig. 2 is an active and static pressure mixed gas lubricating bearings structural drawing.
Fig. 3 is the nozzle throttling gas-supplying structure of gas bearing hydrostatic lubrication.
Fig. 4 is miniature gas turbine-generator system that gas bearing supports.
Fig. 5 is the miniature turbine jet engines system that gas bearing supports.
Claims (5)
1. the miniature gas turbine system of air-bearing-rotor structure is characterized in that:
(1) rotor structure of miniature gas turbine adopts gas bearing as lubricated supporting form., can be arranged between two impellers of gas compressor-turbine (as shown in Figure 1) according to design objective and processing use condition in turbojet miniature gas bearings position, also can be arranged on a side of two impellers;
(2) gas bearing can adopt three kinds of forms of static pressure, dynamic pressure and active and static pressure mixed construction.For the hydrostatic gas-lubricated bearing of outside air feed, adopt nozzle throttling gas-supplying structure; For hydrodynamic gas-lubricated bearing, take to offer the form of supercharging flow path groove structure at the gas bearing internal surface; For hybrid bearing, take to offer the form of supercharging flow path groove structure and the structural type of air vent at the gas bearing internal surface
(3) bearing adopts special self lubricating materials such as wear-resisting, resistant to elevated temperatures nickel, molybdenum, titanium;
(4) adopt metal-rubber as gas turbine bearing vibration damping and heat insulation structural design.
2. according to right 1 described structure and method, it is characterized in that the motor of miniature gas turbine and connection thereof, adopt static pressure, dynamic pressure or dynamical and static pressure gas lubricating bearings as supporting and lubricated form.Combustion machine main shaft is connected by shaft joint with machine shaft, also can be by major axis directly as the main shaft of combustion machine and motor.
3. according to right 1 described structure and method, it is characterized in that bearing inner surface adopts special self lubricating material design such as wear-resisting, resistant to elevated temperatures nickel, molybdenum, titanium and the active and static pressure coupling gas bearing of making.
4. according to right 1 described structure and method, it is characterized in that, on the gas bearing of gas turbine, adopt the structural design of metal-rubber as vibration damping and heat insulation measures.
5. the miniature gas turbine system of air-bearing-rotor structure, it is characterized in that: be applicable to miniature gas turbine (turbojet engine) system of working speed at 5000～8000rpm, corresponding turbojet engine system thrust is at 5～150kg, and gas turbine-generator system power is at 5～150kw.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009102507236A CN102094712A (en) | 2009-12-09 | 2009-12-09 | Micro gas turbine system with gas bearing-rotor structure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009102507236A CN102094712A (en) | 2009-12-09 | 2009-12-09 | Micro gas turbine system with gas bearing-rotor structure |
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| Publication Number | Publication Date |
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| CN102094712A true CN102094712A (en) | 2011-06-15 |
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| CN2009102507236A Pending CN102094712A (en) | 2009-12-09 | 2009-12-09 | Micro gas turbine system with gas bearing-rotor structure |
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103089451A (en) * | 2013-01-18 | 2013-05-08 | 中国科学院工程热物理研究所 | a heat shield |
| CN104196632A (en) * | 2014-08-20 | 2014-12-10 | 中国科学院工程热物理研究所 | Device for lubricating and cooling bearing of miniature aircraft engine by virtue of multi-point oil mist spraying |
| CN105370410A (en) * | 2014-08-15 | 2016-03-02 | 通用电气公司 | Power train architectures with hybrid-type low-loss bearings and low-density materials |
| CN106996870A (en) * | 2017-06-02 | 2017-08-01 | 中国科学院工程热物理研究所 | Multi- scenarios method acts on lower rotor part nonlinear dynamic characteristic analogue experiment installation |
| CN108223135A (en) * | 2017-12-06 | 2018-06-29 | 中国科学院工程热物理研究所 | A kind of small-size turbojet engine and rotor support structure using self-acting air bearing |
| CN108608015A (en) * | 2018-04-23 | 2018-10-02 | 北京航空航天大学 | A kind of gas eddy wheel drive high speed water lubrication dynamic and static pressure bearing rotor system |
| CN108952964A (en) * | 2018-07-13 | 2018-12-07 | 南昌航空大学 | A gas turbine engine with a single compound impeller |
| WO2020082965A1 (en) * | 2018-10-25 | 2020-04-30 | 至玥腾风科技集团有限公司 | Gas turbine generator and control method |
| CN112049687A (en) * | 2020-07-28 | 2020-12-08 | 北京控制工程研究所 | High temperature resistant turbine generator rotor for space thermoelectric conversion and its assembly method |
| CN113959731A (en) * | 2021-11-16 | 2022-01-21 | 盛能工业科技(廊坊)有限公司 | Rotor testing system of air-flotation dynamic pressure bearing micro gas turbine |
| CN114939679A (en) * | 2022-01-28 | 2022-08-26 | 深圳富联智能制造产业创新中心有限公司 | High-speed precise pneumatic main shaft |
| WO2023051157A1 (en) * | 2021-09-28 | 2023-04-06 | 永旭腾风新能源动力科技（北京）有限公司 | Gas path system for rotor system of micro fuel-gas turbine, and micro fuel-gas turbine |
-
2009
- 2009-12-09 CN CN2009102507236A patent/CN102094712A/en active Pending
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103089451A (en) * | 2013-01-18 | 2013-05-08 | 中国科学院工程热物理研究所 | a heat shield |
| CN105370410A (en) * | 2014-08-15 | 2016-03-02 | 通用电气公司 | Power train architectures with hybrid-type low-loss bearings and low-density materials |
| CN104196632A (en) * | 2014-08-20 | 2014-12-10 | 中国科学院工程热物理研究所 | Device for lubricating and cooling bearing of miniature aircraft engine by virtue of multi-point oil mist spraying |
| CN106996870A (en) * | 2017-06-02 | 2017-08-01 | 中国科学院工程热物理研究所 | Multi- scenarios method acts on lower rotor part nonlinear dynamic characteristic analogue experiment installation |
| CN108223135B (en) * | 2017-12-06 | 2019-09-24 | 中国科学院工程热物理研究所 | A kind of small-size turbojet engine and rotor support structure using self-acting air bearing |
| CN108223135A (en) * | 2017-12-06 | 2018-06-29 | 中国科学院工程热物理研究所 | A kind of small-size turbojet engine and rotor support structure using self-acting air bearing |
| CN108608015A (en) * | 2018-04-23 | 2018-10-02 | 北京航空航天大学 | A kind of gas eddy wheel drive high speed water lubrication dynamic and static pressure bearing rotor system |
| CN108952964A (en) * | 2018-07-13 | 2018-12-07 | 南昌航空大学 | A gas turbine engine with a single compound impeller |
| WO2020082965A1 (en) * | 2018-10-25 | 2020-04-30 | 至玥腾风科技集团有限公司 | Gas turbine generator and control method |
| CN112049687A (en) * | 2020-07-28 | 2020-12-08 | 北京控制工程研究所 | High temperature resistant turbine generator rotor for space thermoelectric conversion and its assembly method |
| CN112049687B (en) * | 2020-07-28 | 2023-02-03 | 北京控制工程研究所 | High temperature resistant turbine generator rotor for space thermoelectric conversion and method of assembling same |
| WO2023051157A1 (en) * | 2021-09-28 | 2023-04-06 | 永旭腾风新能源动力科技（北京）有限公司 | Gas path system for rotor system of micro fuel-gas turbine, and micro fuel-gas turbine |
| CN113959731A (en) * | 2021-11-16 | 2022-01-21 | 盛能工业科技(廊坊)有限公司 | Rotor testing system of air-flotation dynamic pressure bearing micro gas turbine |
| CN114939679A (en) * | 2022-01-28 | 2022-08-26 | 深圳富联智能制造产业创新中心有限公司 | High-speed precise pneumatic main shaft |
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Application publication date: 20110615 |