CN104500268A - Micro turbine jet engine with two-sided centrifugal pressure roller - Google Patents
Micro turbine jet engine with two-sided centrifugal pressure roller Download PDFInfo
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- CN104500268A CN104500268A CN201410766868.2A CN201410766868A CN104500268A CN 104500268 A CN104500268 A CN 104500268A CN 201410766868 A CN201410766868 A CN 201410766868A CN 104500268 A CN104500268 A CN 104500268A
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Abstract
The invention belongs to the technical field of micro turbine jet engines and particularly relates to a micro turbine jet engine with a two-sided centrifugal pressure roller. The micro turbine jet engine comprises a starting motor, a double-sided centrifugal compressor, a three-dimensional streamline diffuser, an intermediate casing, a turbine guider, an axial flow turbine, an exhaust tailcone, a tail jet pipe, an outer housing, a combustion chamber, a front-end casing, a rotor shaft, an air inlet rectifier, an auxiliary support, a first main support and a second main support, wherein the axial flow turbine and the rotor shaft are connected together by electron beam welding; the three-dimensional streamline diffuser is arranged on the outlet end of the double-sided centrifugal compressor. The micro turbine jet engine disclosed by the invention has the advantages that the reliability of the engine is improved, the life of the engine is prolonged, the rotor supporting rigidity is improved, the flexible deformation and vibration of a shaft are reduced and the efficiency of the diffuser is improved.
Description
Technical field
The invention belongs to miniature turbine jet engines technical field, specifically a kind of miniature turbine jet engines with two-sided centrifugal pinch roller.
Background technique
Miniature turbine jet engines (abbreviation microvovtex) is a kind of aviation power developed rapidly in recent years, and this thermo-mechanical machine uses the macro being characterised in that power and geometric scale, makes it have a wide range of applications in a lot of fields.Its working principle is same as conventional turbine air breathing engine.Turbine drives gas compressor pressurized air, and high-pressure air flows through firing chamber oil jetting combustion heating and becomes high-temperature high-pressure fuel gas, drives turbine work done, then produces thrust by jet pipe high velocity jet.The gas compressor of microvovtex adopts micro centrifugal compressor usually, its feature is that single-stage pressure ratio is high, efficiency higher than same minute sized axial flow compressor, good operating stability, the simple low cost of manufacture of structure, but under identical wind-exposuring area, its air mass flow is significantly less than axial flow compressor.
Due to size and weight limits, microvovtex adopts first-stage centrifugal gas compressor to add the structural type of first turbine usually, and this makes to increase air mass flow and is subject to larger restriction, and the raising of engine thrust-weight ratio is also very limited.This patent project adopts two-sided centrifugal pinch roller, which overcomes the deficiency of traditional microvovtex, engine air capacity and thrust weight ratio are greatly improved.In theory, adopt two-sided centrifugal pinch roller that air mass flow can correspondingly be doubled, but due to the resistance of runner, the impacts such as the mixed interference of ginseng of boundary layer thickness and two strands of air-flows make the actual increment of air mass flow probably can reach about 60 percent.This will make engine performance significantly be improved.
In addition, adopt the mutual counteract of axial force that two-sided centrifugal pinch roller makes impeller produce, decrease the axial force suffered by rotor bearing.And the design of nozzle ring makes combustion gas stagnation pressure major part be converted into dynamic pressure, turbine rotor blade mainly draws combustion gas kinetic energy work done (impulse wheel), static pressure change little (being less than 20 percent) on blade.Therefore, to be applied to the axial force of rotor bearing less for pinch roller, turbine on the whole, improves the mechanical efficiency of motor, add microvovtex reliability and life-span.
Summary of the invention
The problem to be solved in the present invention increases the axial force on engine air capacity and balance elimination rotor, provides a kind of miniature turbine jet engines with two-sided centrifugal pinch roller.
Present invention employs following technological scheme:
There is the miniature turbine jet engines of two-sided centrifugal pinch roller, it comprises starting electrical machinery, two-sided centrifugal compressor, three dimensional streamline Diffuser, middle casing, nozzle ring, axial flow turbine, tail cone of giving vent to anger, jet pipe, outer casing, firing chamber, preposition casing, rotor shaft, air inlet rectifier, aiding support, the first main supporting and the second main supporting, described axial flow turbine and rotor shaft electron beam welding one, three dimensional streamline Diffuser is located at two-sided centrifugal press outlet end.
Described first main supporting and the second main supporting are flexible damping support.
Advantage of the present invention improves the reliability and the life-span that add motor, improves rotor bearing rigidity, reduces flexible deformation and the vibration of axle, improve the efficiency of Diffuser.
Accompanying drawing explanation
Fig. 1 is structural representation of the present invention.
Embodiment
As shown in Figure 1, there is the miniature turbine jet engines of two-sided centrifugal pinch roller, it comprises starting electrical machinery 1, two-sided centrifugal compressor 2, three dimensional streamline Diffuser 3, middle casing 4, nozzle ring 5, axial flow turbine 6, to give vent to anger tail cone 7, jet pipe 8, outer casing 9, firing chamber 10, preposition casing 11, rotor shaft 12, air inlet rectifier 13, aiding support 14, first main supporting 15 and the second main supporting 16, described axial flow turbine 6 and rotor shaft 12 electron beam welding one, three dimensional streamline Diffuser 3 is located at two-sided centrifugal press 2 outlet end, first main supporting 15 and the second main supporting 16 are flexible damping support.
This miniature turbine jet engines rotor has two-sided centrifugal pinch roller and one-level axial flow impact wheel.Its role is to improve air mass flow and eliminate rotor axial power, it is made up of two-sided centrifugal pinch roller 1, axial flow turbine 6 and rotor shaft 12.
Whole rotor is made up of three supporting systems, two main supportings, an auxiliary floating support.This supporting system can improve rotor bearing rigidity, reduce flexible deformation and vibration, it is made up of the first main bearing 15 and the second main bearing 16 and auxiliary floating bearing 14, first main supporting 15 and the second main supporting 16 are flexible damping support, to reduce shafting vibration and noise, between first main supporting 15 and the second main supporting 16, rotating shaft is directly through reducing 0.6mm, becomes a shallow slot.Fine finishing amount can be reduced, be convenient to bearing and install, reduce rotor oscillation.
Axial flow turbine 6 adopts electron beam welding to be connected with rotor shaft 13, is connected as a single entity, and has simplified processing, assembling and structure, has added reliability, has no employing in miniature turbine jet engines field.
Three dimensional streamline Diffuser 3 is equipped with in the outlet of two-sided centrifugal press 2, and can reduce flow losses, improve extension pressur efficiency, the exit flow of preposition casing 11 pairs of Diffusers 3 carries out rectification, and provides radial air inlet passage for the centrifugal pinch roller of right flank.
Pinch roller, turbine, guider all adopt accurate without surplus integral casting process, when can save material, minimizing merit, improve the fatigue resistance of workpiece.
Ambient air enters two-sided centrifugal compressor 2 by import a, b of preposition casing 11, become high-pressure air after being compressed and flow into three dimensional streamline Diffuser 2, through the rectification of preposition casing 11 after air-flow diffusion, and flow through middle casing 4 and enter firing chamber 10, in firing chamber oil spout, burning, heating, high-temperature high-pressure fuel gas expands acceleration in nozzle ring 5, air-flow impulsion turbine 6 work done after accelerating, gas flow with dump energy continues to expand and accelerates in jet pipe 8, finally to spray jet pipe at a high speed, produce propelling force.Due to centrifugal compressor double-entry, air mass flow can be made in theory to double.
Three fulcrums are had with the engine rotor axle 12 of High Rotation Speed, first main bearing 15 and the second main bearing 16, a floating aiding support 14, this supporting means can improve the supporting rigidity of rotor, reduce flexible deformation and the vibration of axle, first main bearing 15 and the second main bearing 16 adopt flexible damping support, to reduce shafting vibration; Main bearing lubrication system adopts open type lubricating system, and fuel oil, as lubricant medium, is dumped into firing chamber and burns after lubricating bearings.This lubricating system structure, simply without the need to traditional oil system, also can not waste lubricating fuel.
Claims (2)
1. there is the miniature turbine jet engines of two-sided centrifugal pinch roller, it comprises starting electrical machinery, two-sided centrifugal compressor, three dimensional streamline Diffuser, middle casing, nozzle ring, axial flow turbine, tail cone of giving vent to anger, jet pipe, outer casing, firing chamber, preposition casing, rotor shaft, air inlet rectifier, aiding support, the first main supporting and the second main supporting, it is characterized in that: described axial flow turbine and rotor shaft electron beam welding one, three dimensional streamline Diffuser is located at two-sided centrifugal press outlet end.
2. the miniature turbine jet engines with two-sided centrifugal pinch roller according to claim 1, is characterized in that: the described first main supporting and the second main supporting are flexible damping support.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410766868.2A CN104500268A (en) | 2014-12-12 | 2014-12-12 | Micro turbine jet engine with two-sided centrifugal pressure roller |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410766868.2A CN104500268A (en) | 2014-12-12 | 2014-12-12 | Micro turbine jet engine with two-sided centrifugal pressure roller |
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| CN104500268A true CN104500268A (en) | 2015-04-08 |
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| CN201410766868.2A Pending CN104500268A (en) | 2014-12-12 | 2014-12-12 | Micro turbine jet engine with two-sided centrifugal pressure roller |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104847695A (en) * | 2015-05-13 | 2015-08-19 | 张澄宇 | Stage-middle air bleeding type air compressor based on micro-turbine jet engine |
| CN105156216A (en) * | 2015-08-20 | 2015-12-16 | 深圳智慧能源技术有限公司 | Gas turbine and starting device thereof |
| CN105422313A (en) * | 2015-12-09 | 2016-03-23 | 南京航空航天大学 | Miniature turbofan engine separate exhausting device with rectifier |
| CN105927559A (en) * | 2015-04-22 | 2016-09-07 | 张澄宇 | Micro-miniature split turbojet driven compressor |
| CN105952539A (en) * | 2016-04-22 | 2016-09-21 | 山东元动力科技有限公司 | Micro turbojet engine |
| CN105952537A (en) * | 2016-04-22 | 2016-09-21 | 山东元动力科技有限公司 | Micro turbojet engine |
| CN105952538A (en) * | 2016-04-22 | 2016-09-21 | 山东元动力科技有限公司 | Micro turbojet engine |
| CN108590862A (en) * | 2018-05-29 | 2018-09-28 | 张敏 | Diameter formula turbojet power plant after a kind of microminiature |
| CN108590859A (en) * | 2018-04-24 | 2018-09-28 | 南方科技大学 | Additive manufacturing's miniature turbojet engine |
| CN110273782A (en) * | 2019-07-12 | 2019-09-24 | 南昌航空大学 | A kind of Micro Turbine Jet Engine of two-sided NEW TYPE OF COMPOSITE impeller |
| CN110617115A (en) * | 2019-10-29 | 2019-12-27 | 北京动力机械研究所 | Turbine engine guide ring assembly produced by additive manufacturing mode |
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| CN86105185A (en) * | 1986-08-04 | 1988-02-17 | 孔斯堡兵器制造公司 | Dual entry radial turbine gas generator |
| CN1490514A (en) * | 2002-09-23 | 2004-04-21 | 北京航空航天大学 | Miniature turbine jet engines |
| CN101542088A (en) * | 2006-12-11 | 2009-09-23 | 博格华纳公司 | Turbocharger |
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Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105927559A (en) * | 2015-04-22 | 2016-09-07 | 张澄宇 | Micro-miniature split turbojet driven compressor |
| CN104847695A (en) * | 2015-05-13 | 2015-08-19 | 张澄宇 | Stage-middle air bleeding type air compressor based on micro-turbine jet engine |
| CN105156216A (en) * | 2015-08-20 | 2015-12-16 | 深圳智慧能源技术有限公司 | Gas turbine and starting device thereof |
| CN105422313A (en) * | 2015-12-09 | 2016-03-23 | 南京航空航天大学 | Miniature turbofan engine separate exhausting device with rectifier |
| CN105952538A (en) * | 2016-04-22 | 2016-09-21 | 山东元动力科技有限公司 | Micro turbojet engine |
| CN105952537A (en) * | 2016-04-22 | 2016-09-21 | 山东元动力科技有限公司 | Micro turbojet engine |
| CN105952539A (en) * | 2016-04-22 | 2016-09-21 | 山东元动力科技有限公司 | Micro turbojet engine |
| CN108590859A (en) * | 2018-04-24 | 2018-09-28 | 南方科技大学 | Additive manufacturing's miniature turbojet engine |
| CN108590859B (en) * | 2018-04-24 | 2021-03-09 | 深圳意动航空科技有限公司 | Additive manufacturing's miniature turbojet engine |
| CN108590862A (en) * | 2018-05-29 | 2018-09-28 | 张敏 | Diameter formula turbojet power plant after a kind of microminiature |
| CN110273782A (en) * | 2019-07-12 | 2019-09-24 | 南昌航空大学 | A kind of Micro Turbine Jet Engine of two-sided NEW TYPE OF COMPOSITE impeller |
| CN110617115A (en) * | 2019-10-29 | 2019-12-27 | 北京动力机械研究所 | Turbine engine guide ring assembly produced by additive manufacturing mode |
| CN110617115B (en) * | 2019-10-29 | 2021-11-02 | 北京动力机械研究所 | Turbine engine guide ring assembly produced by additive manufacturing mode |
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Application publication date: 20150408 |
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