CN102562827A - High-speed bearing cooling system of turbine/compressor for aviation and method and application thereof - Google Patents
High-speed bearing cooling system of turbine/compressor for aviation and method and application thereof Download PDFInfo
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- CN102562827A CN102562827A CN2012100055433A CN201210005543A CN102562827A CN 102562827 A CN102562827 A CN 102562827A CN 2012100055433 A CN2012100055433 A CN 2012100055433A CN 201210005543 A CN201210005543 A CN 201210005543A CN 102562827 A CN102562827 A CN 102562827A
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Abstract
A high-speed bearing cooling system of a turbine/compressor for aviation belongs to the technical field of airplane environment control, and mainly comprises an air supplier (1), a compressor (2), an air radiator (3), a turbine (4), a heat pipe condensation end (5), a heat pipe evaporation end (6), a heat exchanger (7) and an air outlet. The work method of the cooling has the outstanding advantages of high efficiency, simple structure and the like; and according to the work method of the cooling, a heat pipe is introduced into a turbine/compressor two-wheeled system by utilizing the extremely high thermal conductivity of the heat pipe so as to cool a bearing.
Description
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Technical field
The present invention relates to cooling system and method and the application of aviation, belong to aircraft environment control technique field with turbine/gas compressor high-speed bearing.
Background technique
Along with the development of air cycle machine (ACM), in the aircraft industry increasingly high requirement has been proposed bearing.U.S.'s bearing rotating speed generally can reach 1 x 10 by rotating speed
5More than the r/min, but state's inner bearing rotating speed can only reach 3～4 x 10
4About r/min, maybe be lower in production application.Reason is that the bearing lubrication of the U.S. adopts air lubrication more, and China is because technical reason can only adopt grease lubrication.And the air lubrication technology is that the U.S. is exclusive, in a short time, is difficult to break through the technology barriers of air lubrication again.Therefore how seeking breakthrough on the basis of existing grease lubrication further makes improvements, thereby improves lubricating ability, has become the key of the bearing performance that improves.There are positively related relation in the temperature of bearing and the rotating speed of bearing, and the raising of rotating speed can bring the rising of bearing temperature, and the operating temperature of bearing in general can not be above 70 ℃.So how can effectively bearing be cooled is exactly the key issue of research.At present, for ground or the application in enough spaces is arranged, can increase by a cover refrigeration cooling system again, adopt pump or fan to carry liquid or gas that bearing is cooled off.Obviously for the very compact space of air line, can't realize.
Summary of the invention
The purpose of this invention is to provide cooling system and method and the application of high, the simple in structure aviation of a kind of efficient with turbine/gas compressor high-speed bearing.
The cooling system of a kind of turbine/gas compressor high-speed bearing is characterized in that: this system is made up of air feed end, gas compressor, air radiator, turbine, heat pipe, heat exchanger, outlet side; Wherein gas compressor and turbine are positioned at the two ends of rotating shaft; Wherein the air feed end links with gas compressor, air radiator, turbine, heat exchanger, outlet end successively; Wherein the heat pipe condensation end and the heat exchanger of heat pipe join, and heat pipe vaporizing end and bearing outer ring join.Above-mentioned heat pipe can be single tube type heat pipe or loop circuit heat pipe.
Utilize the cooling means of the cooling system of said turbine/gas compressor high-speed bearing, it is characterized in that comprising following process: air feed at first through the compression of gas compressor, further reduces temperature through air radiator then, and this measure can improve cooling effect; Gas connects the heat pipe condensation end as low-temperature receiver after continuing the expansion cooling through turbine; The bearing high-speed rotation produces a large amount of heats, and heat imports the heat pipe vaporizing end into by the bearing outer end, when the heat pipe vaporizing end is heated; Liquid in the heat pipe evaporates rapidly, and steam is at the dirty thermotropism pipework condensation of small pressure difference end, and discharges heat; Regelation becomes liquid; Liquid leans on the effect of capillary force to flow back to the heat pipe vaporizing end along porous material again, and so circulation is more than, and heat reaches the heat pipe condensation end by the heat pipe vaporizing end.Thereby bearing is cooled off, for the further raising of bearing rotating speed provides condition.
The cooling means of described turbine/gas compressor high-speed bearing; It is characterized in that: be applied to the two wheel system that gas compressor/turbine constitutes; Or be applied to three wheel systems that fan/compressor/turbine is formed, or be applied to the four-wheel system that fan/compressor/turbine/turbine is formed.
The aviation upper bearing (metal) adopts rolling bearing more, and its lubricating system adopts grease lubrication, when bearing reaches certain rotating speed, can produce great amount of heat, thereby limit the further raising of bearing rotating speed.
Utilize the high thermal conductivity of heat pipe, heat pipe is introduced in turbine/gas compressor two wheel system, thereby bearing is cooled.
Compare with common cooling unit, heat pipe heat exchanging equipment is safer, reliable than conventional equipment, operation continuously for a long time, and efficient is high, and energy-saving effect is remarkable.Material with thermal conductive resin has aluminium [(λ=202W/m ℃)], bavin copper [λ=385W/ m ℃] and silver: λ=410W/ m ℃)], but its thermal conductivity can only reach 10
2W/m ℃ the order of magnitude far can not satisfy quick heat radiating and heat transfer needs in the aeronautical engineering, and adopts heat pipe just to solve this problem.The suitable thermal conductivity of heat pipe can reach 10
5W/m ℃ the order of magnitude.Be hundreds of times and even thousands of times of common metal material.Therefore heat pipe just can reach the very heavy in section effect of metal with very little sectional area, and it can transmit a large amount of heats at a distance through very little sectional area and need not additionaling power.
Heat pipe is the fabulous artificial member of a kind of heat transfer property; Heat pipe commonly used is made up of three parts: main body is the metal tube (shell) of a sealing; Little work medium (working solution) and capillary structure (tube core) are arranged in the internal cavities, and air and other foreign material in the pipe must foreclose.Utilized three kinds of physics principles during heat pipe work: 1) under low-pressure state, the boiling point of liquid reduces; 2) latent heat of vaporization of material of the same race is than high many of sensible heat; 3) porous capillary structure can make flow of fluid to the suction force of liquid.See that from heat transfer conditions heat pipe can be divided into evaporator section vertically, adiabatic section and condensating section three parts.
General heat pipe is made up of shell, wick and end cap.Inside heat pipe is to be pumped into negative pressure state, charges into suitable liquid, and this boiling point of liquid is low, easily volatilization.Tube wall has wick, and it is made up of the capillary porous material.Heat pipe one end and bearing outer ring join, and this section is as the vaporizing end of heat pipe, and another termination radiator, radiator are used for the air of cooling turbine cooling is dispelled the heat, and this section is as condensation end.
The bearing high-speed rotation produces a large amount of heats, and heat imports the vaporizing end of heat pipe into by the bearing outer end, and the liquid in the capillary tube evaporates rapidly; Steam flows to condensation end under small pressure difference; And discharge heat, regelation becomes liquid, and liquid leans on the effect of capillary force to flow back to evaporator section along porous material again; So circulation is more than, and heat reaches an other end by heat pipe one end.
This circulation is carried out fast, and heat can be come by conduction continuously.Thereby can carry out efficiently radiates heat to bearing, reduce bearing temperature, thereby can arrive the purpose of further raising bearing rotating speed.
Description of drawings
Fig. 1 is the cooling system schematic representation of aviation with turbine/gas compressor high-speed bearing;
Label title among Fig. 1: 1, air feed, 2, gas compressor, 3, air radiator, 4, turbine, 5, heat pipe condensation end, 6, heat pipe vaporizing end, 7, heat exchanger, 8, give vent to anger.
Embodiment
According to shown in Figure 1, aviation of the present invention mainly comprises air feed air feed 1, gas compressor 2, air radiator 3, turbine 4, heat pipe condensation end 5, heat pipe vaporizing end 6, heat exchanger 7, gives vent to anger 8 with the cooling system of turbine/gas compressor high-speed bearing.Gas compressor 2 constitutes two wheel system with turbine 4.
In conjunction with Fig. 1 illustrative system working procedure: air feed 1 at first through the compression of gas compressor 2, further reduces temperature through air radiator 3 then, prevents that gas from absorbing heats at heat pipe condensation end 5 and rising again, and causes the decline of refrigeration performance.Next gas through turbine 4 to its cooling action after as heat pipe condensation end 5.The heat pipe the other end and bearing outer ring join, and this section is as heat pipe vaporizing end 6.The bearing high-speed rotation produces a large amount of heats, and heat imports heat pipe vaporizing end 6 into by the bearing outer end, and the liquid in the heat pipe evaporates rapidly; Steam flows to condensation end 5 under small pressure difference; And discharge heat, regelation becomes liquid, and liquid leans on the effect of capillary force to flow back to evaporator section along porous material again; So circulation is more than, and heat reaches heat pipe condensation end 5 by heat pipe vaporizing end 6.Thereby bearing is cooled off, and the continuation that can be the bearing rotating speed provides condition.
Above-mentioned aviation also can be applicable to aviation or ground surface high speed swivel bearing system with turbine/gas compressor high-speed bearing cooling means.Like motor, generator, motor etc.Its low-temperature receiver can be from other places, like outside air, refrigeration system, fuel oil, PCM (phase-change material) etc.
Claims (4)
1. an aviation is characterized in that with the cooling system of turbine/gas compressor high-speed bearing:
This system is made up of air feed end (1), gas compressor (2), air radiator (3), turbine (4), heat pipe, heat exchanger (7), outlet side (8);
Wherein gas compressor (2) and turbine (4) are positioned at the two ends of rotating shaft;
Wherein air feed end (1) links with gas compressor (2), air radiator (3), turbine (4), heat exchanger (7), outlet end (8) successively;
Wherein the heat pipe condensation end (5) of heat pipe joins with heat exchanger, and heat pipe vaporizing end (6) joins with bearing outer ring.
2. according to the cooling system of claims 1 described aviation with turbine/gas compressor high-speed bearing, it is characterized in that: above-mentioned heat pipe is single tube type heat pipe or loop circuit heat pipe.
3. according to the cooling means of the said aviation of claim 1, it is characterized in that comprising following process with the cooling system of turbine/gas compressor high-speed bearing:
Air feed (1) at first through the compression of gas compressor (2), further reduces temperature through air radiator (3) then, and this measure can improve cooling effect; Gas connects heat pipe condensation end (5) as low-temperature receiver after continuing the expansion cooling through turbine (4);
The bearing high-speed rotation produces a large amount of heats, and heat imports heat pipe vaporizing end (6) into by the bearing outer end, when heat pipe vaporizing end (6) when being heated; Liquid in the heat pipe evaporates rapidly, and steam is at the dirty thermotropism pipework condensation of small pressure difference end (5), and discharges heat; Regelation becomes liquid; Liquid leans on the effect of capillary force to flow back to heat pipe vaporizing end (6) along porous material again, and so circulation is more than, and heat reaches heat pipe condensation end (5) by heat pipe vaporizing end (6); Thereby bearing is cooled off, for the further raising of bearing rotating speed provides condition.
4. aviation according to claim 3 is with the cooling means of turbine/gas compressor high-speed bearing; It is characterized in that: be applied to the two wheel system that gas compressor/turbine constitutes; Or be applied to three wheel systems that fan/compressor/turbine is formed, or be applied to the four-wheel system that fan/compressor/turbine/turbine is formed.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012100055433A CN102562827A (en) | 2012-01-10 | 2012-01-10 | High-speed bearing cooling system of turbine/compressor for aviation and method and application thereof |
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| Application Number | Priority Date | Filing Date | Title |
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| CN2012100055433A CN102562827A (en) | 2012-01-10 | 2012-01-10 | High-speed bearing cooling system of turbine/compressor for aviation and method and application thereof |
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| CN102562827A true CN102562827A (en) | 2012-07-11 |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103630384A (en) * | 2013-12-09 | 2014-03-12 | 沈阳航天新光集团有限公司 | System and method for testing cooling turbine |
| CN103770946A (en) * | 2012-09-28 | 2014-05-07 | 奥格斯塔韦斯兰股份公司 | System and method for cooling a hover-capable aircraft transmission |
| CN103925233A (en) * | 2013-01-16 | 2014-07-16 | 宝山钢铁股份有限公司 | Method and device for self-circulation cooling of mechanical seal of emulsified liquid lift pump |
| CN107076158A (en) * | 2014-07-08 | 2017-08-18 | 琳德股份有限公司 | For the method for the rotating speed for adjusting the cryogenic compressor being connected in series |
| CN109073068A (en) * | 2015-12-23 | 2018-12-21 | 阿拉泽-阿瑞玛公司 | Cooling device for wind turbine components |
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| CN1081757A (en) * | 1992-07-31 | 1994-02-09 | 李华聪 | A kind of open-type compression refrigerating apparatus |
| CN1865692A (en) * | 2006-06-19 | 2006-11-22 | 孙景 | Automatic cycle cooling device for hydropower station unit |
| US20100111740A1 (en) * | 2008-10-30 | 2010-05-06 | Scroll Laboratories, Inc. | Scroll-type fluid displacement apparatus with improved cooling system |
| CN102120266A (en) * | 2010-12-27 | 2011-07-13 | 东莞理工学院 | High-speed precise electric spindle cooling system |
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2012
- 2012-01-10 CN CN2012100055433A patent/CN102562827A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1081757A (en) * | 1992-07-31 | 1994-02-09 | 李华聪 | A kind of open-type compression refrigerating apparatus |
| CN1865692A (en) * | 2006-06-19 | 2006-11-22 | 孙景 | Automatic cycle cooling device for hydropower station unit |
| US20100111740A1 (en) * | 2008-10-30 | 2010-05-06 | Scroll Laboratories, Inc. | Scroll-type fluid displacement apparatus with improved cooling system |
| CN102120266A (en) * | 2010-12-27 | 2011-07-13 | 东莞理工学院 | High-speed precise electric spindle cooling system |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103770946A (en) * | 2012-09-28 | 2014-05-07 | 奥格斯塔韦斯兰股份公司 | System and method for cooling a hover-capable aircraft transmission |
| CN103925233A (en) * | 2013-01-16 | 2014-07-16 | 宝山钢铁股份有限公司 | Method and device for self-circulation cooling of mechanical seal of emulsified liquid lift pump |
| CN103630384A (en) * | 2013-12-09 | 2014-03-12 | 沈阳航天新光集团有限公司 | System and method for testing cooling turbine |
| CN107076158A (en) * | 2014-07-08 | 2017-08-18 | 琳德股份有限公司 | For the method for the rotating speed for adjusting the cryogenic compressor being connected in series |
| CN107076158B (en) * | 2014-07-08 | 2019-06-04 | 琳德股份有限公司 | Method for adjusting the revolving speed for the cryogenic compressor being connected in series |
| CN109073068A (en) * | 2015-12-23 | 2018-12-21 | 阿拉泽-阿瑞玛公司 | Cooling device for wind turbine components |
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Application publication date: 20120711 |