CN206636653U - A kind of Micro Turbine Jet Engine vertically borrows gas high pressure cooling and lubricating bearing arrangement - Google Patents
A kind of Micro Turbine Jet Engine vertically borrows gas high pressure cooling and lubricating bearing arrangement Download PDFInfo
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- CN206636653U CN206636653U CN201720198696.2U CN201720198696U CN206636653U CN 206636653 U CN206636653 U CN 206636653U CN 201720198696 U CN201720198696 U CN 201720198696U CN 206636653 U CN206636653 U CN 206636653U
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Abstract
The utility model discloses a kind of Micro Turbine Jet Engine and vertically borrows gas high pressure cooling and lubricating bearing arrangement, includes, and axle, pressure impeller, turbine, Bearing Casing, pressure side bearing, whirlpool end bearing, pressure side covers surely, whirlpool end covers surely and diffuser.The pressure side covers surely covers outer peripheral face and pressure side covers end face surely surely with pressure side, the pressure side covers the inner peripheral surface that outer peripheral face system is pointed to the Bearing Casing surely, the inner peripheral surface that the pressure side covers outer peripheral face and the Bearing Casing surely mutually seals, the pressure side covers end face system and is pointed to the pressure side bearing surely, the pressure side covers the globoidal structure that end face system is oriented to baffling surely, has on the diffuser to borrow air drain road by means of gas.The utility model has the advantage of：（1）Pressure side bearing and the lubricant effect of whirlpool end bearing are good, reduce addition machine oil 60%.（2）Good cooling results, prolong bearing service life.
Description
Technical field
Turbojet engine is the utility model is related to, vertically borrows gas high pressure to cool down more particularly to a kind of Micro Turbine Jet Engine
Lubricate bearing arrangement.
Background technology
Fig. 1 is referred to, shown in figure is that a kind of traditional Micro Turbine Jet Engine vertically borrows gas high pressure cooling and lubricating axle
Bearing structure, include, axle 1, pressure impeller 2, turbine 8, Bearing Casing 4, pressure side bearing 5, whirlpool end bearing 6, pressure side cover 3, whirlpool end surely
Surely set 7 and diffuser 9.Specifically, beaten behind to pressure impeller behind from diffuser by means of stomata 10, this mode is to carry on the back diffuser
Between high pressure draught afterwards is first introduced into before the pressure impeller wheel back of the body and diffuser, then it is folded to Bearing Casing.When the air-flow borrowed exists
When between pressing before the impeller wheel back of the body and diffuser, high pressure gas can flow to turbine end into Bearing Casing, can also flow to pressure leaf
Take turns at air passage outlet 11；Enough pressure has not yet been formed in engine because rotating speed is low in engine startup, does not rise
To the effect that lubricating oil is blowed to turbine end and cooling and lubricating bearing by means of gas；In the operation of engine high rotating speed, due to thus borrow into
Stream pressure it is high, and press low with pressure in Bearing Casing at the pressure impeller wheel back of the body, so a part of air-flow is by bearing by lubricating oil
Band is served to bearing cooling, the effect of lubrication to turbine end, but because borrowing tolerance deficiency so that the less effective of cooling bearing；
And another part borrows gas to flow at pressure impeller air passage outlet and diffuser tracheal entrance, by the high velocity air of new air inlet again
Bring diffuser into flow into engine body, thus reduce engine efficiency.
Utility model content
The purpose of the utility model is to overcome the problems of the prior art, there is provided a kind of new Micro Turbine Jet Engine is vertical
By means of gas high pressure cooling and lubricating bearing arrangement.
In order to realize this purpose, the technical solution of the utility model is as follows：A kind of Micro Turbine Jet Engine vertically borrows gas
High pressure cooling and lubricating bearing arrangement, includes, and axle, pressure impeller, turbine, Bearing Casing, pressure side bearing, whirlpool end bearing, pressure side are fixed
Set, whirlpool end covers surely and diffuser, wherein, the axle has the pressure impeller end and turbine end along its axially opposing setting, the axle
Pressure impeller end on there is the pressure impeller, there is the turbine in the turbine end of the axle, the Bearing Casing system is surrounded on
The outside of the axle and it is placed between the pressure impeller and the turbine, the Bearing Casing and the between centers have distance so that
Both define bearing house cavity, the bearing house cavity in have in it is described pressure impeller side the pressure side bearing and
The turbine bearing in the turbo-side, there is the pressure side between the pressure side bearing and the pressure impeller on the axle
It is fixed to cover, between the whirlpool end bearing and the turbine there is whirlpool end to cover surely on the axle, the diffuser system is surrounded on the pressure
There is air-flow conduit at impeller outlet and between pressure impeller and pressure side Bearing Casing.
The preferred scheme of gas high pressure cooling and lubricating bearing arrangement, the pressure side are vertically borrowed as a kind of Micro Turbine Jet Engine
Fixed set covers outer peripheral face surely with pressure side and pressure side covers end face surely, and the pressure side covers outer peripheral face system and is pointed to the Bearing Casing surely
Inner peripheral surface, the inner peripheral surface that the pressure side covers outer peripheral face and the Bearing Casing surely mutually seal, and the pressure side covers the contraposition of end face system surely
In the pressure side bearing, the pressure side covers the globoidal structure that end face system is oriented to baffling surely, have on the diffuser to
Air drain road is borrowed by means of gas, described to borrow air drain road to have conduit air inlet and conduit gas outlet, the conduit air inlet system is pointed to
Engine inner chamber, the conduit gas outlet system are pointed to the pressure side and cover end face surely so that the air of engine inner chamber is from described
By means of air drain road, end face is covered surely through the pressure side, is housed into the bearing in cavity.
The preferred scheme of gas high pressure cooling and lubricating bearing arrangement, the whirlpool end are vertically borrowed as a kind of Micro Turbine Jet Engine
Fixed set has whirlpool Duan Dingtao end faces, and the whirlpool Duan Dingtao end faces system is pointed to the whirlpool end bearing, the whirlpool Duan Dingtao end faces system
The globoidal structure being oriented to baffling.
The preferred scheme of gas high pressure cooling and lubricating bearing arrangement is vertically borrowed as a kind of Micro Turbine Jet Engine, it is described to borrow gas
Circumferencial direction of the conduit system along the diffuser is uniformly distributed.
The preferred scheme of gas high pressure cooling and lubricating bearing arrangement is vertically borrowed as a kind of Micro Turbine Jet Engine, it is described to borrow gas
The quantity of conduit is 6.
Compared with prior art, the advantages of the utility model at least that：（1）The lubrication of pressure side bearing and whirlpool end bearing is imitated
Fruit is good, reduces addition machine oil 60%：Lubrication either in the high rotating speed of engine still in the slow-speed of revolution when can fully enter bearing
Casing is lubricated to bearing.The vertical directive pressure side of a large amount of high pressure cold streams through being borrowed by means of air drain road is covered on end face surely, and is slided
Oil is also that the vertical directive of high pressure this pressure side is covered on end face surely through oil pipe, and lubricating oil hits pressure side because of wound and covers baffling surely in this process
Spigot surface is simultaneously centrifuged that oil column is become into tiny oil droplet, and high pressure draught therewith mix, atomization forms oil by force by ginseng
Mist, lubricating oil are lubricated in the form of mist of oil into Bearing Casing to bearing, and fog lubrication bearing effect is optimal, non-this patent
Micro Turbine Jet Engine 5% machine oil is added in fuel oil, and do not add or at most add using structure of the present utility model
2% machine oil.（2）Good cooling results, prolong bearing service life：Using the utility model because there is substantial amounts of high pressure cold stream
（Than it is non-it is of the present utility model tradition borrow tolerance more than 2-3 times）Through six air intake ducts vertically into fixed by pressure impeller, diffuser, pressure side
Set and Bearing Casing composition cavity in, and covered surely through pressure side baffling spigot surface baffling, be oriented at a high speed enter Bearing Casing, it is right
Pressure side bearing and whirlpool end bearing carry out air-cooled, high temperature and fixed turbine particularly to being conducted to whirlpool end bearing from turbine
The axle journal at place has strong wind cooling, achieves extraordinary effect.The temperature at the end bearing of whirlpool can be made to reduce by 34% after measured, greatly
The big service life for extending bearing.Just because of this, after engine misses without or use machine oil less.（3）Starting rank
Section due in engine air pressure it is relatively low in the case of, it is ensured that lubricating oil must all flow into Bearing Casing and to bearing lubrication, change
The phenomenon of conventional engines pressure impeller end oil leak is become.
Brief description of the drawings
Fig. 1 is the structural representation of prior art.
Fig. 2 is the structural representation of the embodiment of the utility model one.
Embodiment
The utility model is described in further detail below by specific embodiment combination accompanying drawing.
Fig. 2 is referred to, shown in figure is that a kind of Micro Turbine Jet Engine vertically borrows gas high pressure cooling and lubricating bearing arrangement,
Include, axle 1, pressure impeller 2, turbine 8, Bearing Casing 4, pressure side bearing 5, whirlpool end bearing 6, pressure side cover surely 3, whirlpool end cover surely 7 and
Diffuser 9, wherein, the axle 1 has along the end of pressure impeller 2 of its axially opposing setting and the end of turbine 8, the pressure impeller 2 of the axle 1
There is the pressure impeller 2 on end, there is the turbine 8 on the end of turbine 8 of the axle 1, the system of Bearing Casing 4 is surrounded on described
The outside of axle 1 and be placed in it is described pressure impeller 2 and the turbine 8 between, distance be present between the Bearing Casing 4 and the axle 1 so that
Both define bearing and house cavity, and the bearing, which houses, has the pressure side bearing 5 in pressure impeller 2 side in cavity
And the bearing of the turbine 8 in the side of turbine 8, have between the pressure side bearing 5 and the pressure impeller 2 on the axle 1
The pressure side covers 3 surely, between the whirlpool end bearing 6 and the turbine 8 there is whirlpool end to cover 7 surely on the axle 1, the diffuser 9
System, which is surrounded on pressure impeller 2 exit, has air-flow conduit and between pressure impeller and pressure side Bearing Casing.The pressure side is determined
Set 3 covers 3 outer peripheral faces and pressure side with pressure side and covers 3 end faces surely surely, and the pressure side covers 3 outer peripheral face systems and is pointed to the Bearing Casing surely
4 inner peripheral surface, the inner peripheral surface that the pressure side covers 3 outer peripheral faces and the Bearing Casing 4 surely mutually seal, and the pressure side covers 3 end faces surely
System is pointed to the pressure side bearing 5, and the pressure side covers the globoidal structure that 3 end face systems are oriented to baffling surely, on the diffuser 9
With to borrow air drain road 10 by means of gas, described to borrow air drain road 10 to have conduit air inlet and conduit gas outlet, the conduit enters
Gas port system is pointed to engine inner chamber, and the conduit gas outlet system is pointed to the pressure side and covers 3 end faces surely so that engine inner chamber
Air borrow air drain road 10 from described, cover 3 end faces surely through the pressure side, into the bearing house cavity in.
When lubricating oil is vertically ejected into the pressure side through oil inlet pipe covers 3 end face surely, due to the pressure side cover surely 3 end faces from
The heart acts on, and can only get rid of to the inwall of Bearing Casing 4, and can only determine by the pressure impeller 2, the diffuser 9, the pressure side
Set 3 and the Bearing Casing 4 form cavity it is atomization, due to the pressure side cover surely formd between 3 and the Bearing Casing 4 it is close
Envelope, but because it is opening that this cavity, which only has the direction of Bearing Casing 4, pressure is also minimum herein, so no matter sending out
Motivation rotating speed is high with low, and lubricating oil all can only flow into the Bearing Casing 4 and pass through the pressure side bearing 5 and the whirlpool end bearing 6, from
And reach cooling, lubricate the purpose of bearing, and compressor oil leak when will not cause low engine speeds.
Same a large amount of high pressure cold streams when after the diffuser 9 supercharging（Tolerance is borrowed than non-tradition of the present utility model
More 2-3 times）From by means of air drain road 10（Totally 6）When pressure side described in vertical directive covers 3 end face surely, it is forced to be folded to the Bearing Casing 4.
Sealing is formd between 3 and the Bearing Casing 4 because the pressure side covers surely（See at sealing）, by the pressure impeller 2, the expansion
Depressor 9, the pressure side cover surely 3 and the Bearing Casing 4 form cavity in only the direction of Bearing Casing 4 be opening,
Air pressure herein is also minimum, so the high pressure cold stream introduced brings lubricating oil into Bearing Casing 4 in the lump, through the pressure side bearing
5 and the whirlpool end bearing 6 after discharged by the turbine 8, so as to reached cooling, lubrication bearing purpose.
Only express embodiment of the present utility model above, its describe it is more specific and in detail, but and can not therefore and
It is interpreted as the limitation to utility model patent scope.It should be pointed out that for the person of ordinary skill of the art, not
On the premise of departing from the utility model design, various modifications and improvements can be made, these belong to guarantor of the present utility model
Protect scope.Therefore, the protection domain of the utility model patent should be determined by the appended claims.
Claims (4)
1. a kind of Micro Turbine Jet Engine vertically borrows gas high pressure cooling and lubricating bearing arrangement, include, axle, pressure impeller, turbine, axle
Hold that casing, pressure side bearing, whirlpool end bearing, pressure side cover surely, whirlpool end covers surely and diffuser, wherein, the axle has along its axial phase
To the pressure impeller end and turbine end of setting, there is the pressure impeller on the pressure impeller end of the axle, have in the turbine end of the axle
There is the turbine, the Bearing Casing system is surrounded on the outside of the axle and is placed between the pressure impeller and the turbine, described
There is distance in Bearing Casing so that both define bearing and house cavity, and the bearing houses to be had in cavity with the between centers
The pressure side bearing in the pressure impeller side and the turbine bearing in the turbo-side, in the pressure on the axle
Between end bearing and the pressure impeller there is the pressure side to cover surely, there is whirlpool on the axle between the whirlpool end bearing and the turbine
The fixed set in end, the diffuser system, which is surrounded at the pressure impeller outlet, has air-flow conduit and in pressure impeller and pressure side Bearing Casing
Between, it is characterised in that the pressure side covers surely covers outer peripheral face with pressure side and pressure side covers end face surely surely, and the pressure side covers periphery surely
Face system is pointed to the inner peripheral surface of the Bearing Casing, and the inner peripheral surface that the pressure side covers outer peripheral face and the Bearing Casing surely is mutually close
Envelope, the pressure side cover end face system and are pointed to the pressure side bearing surely, and the pressure side covers the cambered surface that end face system is oriented to baffling surely
Structure, have on the diffuser to borrow air drain road by means of gas, it is described that there is conduit air inlet and conduit outlet by means of air drain road
Mouthful, the conduit air inlet system is pointed to engine inner chamber, and the conduit gas outlet system is pointed to the pressure side and covers end face surely, makes
The air for obtaining engine inner chamber borrows air drain road from described, covers end face surely through the pressure side, is housed into the bearing in cavity.
2. a kind of Micro Turbine Jet Engine according to claim 1 vertically borrows gas high pressure cooling and lubricating bearing arrangement, it is special
Sign is that the whirlpool end covers with whirlpool Duan Dingtao end faces surely, and the whirlpool Duan Dingtao end faces system is pointed to the whirlpool end bearing, described
The globoidal structure that whirlpool Duan Dingtao end faces system is oriented to baffling.
3. a kind of Micro Turbine Jet Engine according to claim 1 or 2 vertically borrows gas high pressure cooling and lubricating bearing arrangement, its
It is characterised by, it is described to be uniformly distributed by means of circumferencial direction of the air drain road system along the diffuser.
4. a kind of Micro Turbine Jet Engine according to claim 3 vertically borrows gas high pressure cooling and lubricating bearing arrangement, it is special
Sign is that the quantity by means of air drain road is 6.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720198696.2U CN206636653U (en) | 2017-03-02 | 2017-03-02 | A kind of Micro Turbine Jet Engine vertically borrows gas high pressure cooling and lubricating bearing arrangement |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720198696.2U CN206636653U (en) | 2017-03-02 | 2017-03-02 | A kind of Micro Turbine Jet Engine vertically borrows gas high pressure cooling and lubricating bearing arrangement |
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| Publication Number | Publication Date |
|---|---|
| CN206636653U true CN206636653U (en) | 2017-11-14 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720198696.2U Expired - Fee Related CN206636653U (en) | 2017-03-02 | 2017-03-02 | A kind of Micro Turbine Jet Engine vertically borrows gas high pressure cooling and lubricating bearing arrangement |
Country Status (1)
| Country | Link |
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| CN (1) | CN206636653U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107246324A (en) * | 2017-03-02 | 2017-10-13 | 蔡肃民 | A kind of Micro Turbine Jet Engine vertically borrows gas high pressure cooling and lubricating bearing arrangement |
-
2017
- 2017-03-02 CN CN201720198696.2U patent/CN206636653U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107246324A (en) * | 2017-03-02 | 2017-10-13 | 蔡肃民 | A kind of Micro Turbine Jet Engine vertically borrows gas high pressure cooling and lubricating bearing arrangement |
| CN107246324B (en) * | 2017-03-02 | 2024-01-05 | 蔡肃民 | Vertical air-borrowing high-pressure cooling lubrication bearing structure of miniature turbojet engine |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20171114 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |