CN104791132A - Automatic lubrication and cooling type turbojet engine - Google Patents
Automatic lubrication and cooling type turbojet engine Download PDFInfo
- Publication number
- CN104791132A CN104791132A CN201510150052.1A CN201510150052A CN104791132A CN 104791132 A CN104791132 A CN 104791132A CN 201510150052 A CN201510150052 A CN 201510150052A CN 104791132 A CN104791132 A CN 104791132A
- Authority
- CN
- China
- Prior art keywords
- oil
- bearings
- axis
- communicated
- storage tank
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000001816 cooling Methods 0.000 title abstract description 13
- 238000005461 lubrication Methods 0.000 title abstract description 9
- 239000003921 oil Substances 0.000 claims description 45
- 230000029058 respiratory gaseous exchange Effects 0.000 claims description 8
- 239000010687 lubricating oil Substances 0.000 claims description 5
- 230000003292 diminished effect Effects 0.000 claims description 2
- 239000002828 fuel tank Substances 0.000 claims description 2
- 230000007704 transition Effects 0.000 claims description 2
- 238000000034 method Methods 0.000 abstract description 4
- 230000001050 lubricating effect Effects 0.000 description 6
- 239000012530 fluid Substances 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 238000010304 firing Methods 0.000 description 2
- 238000000889 atomisation Methods 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000003595 mist Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
Landscapes
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention belongs to the technical field of engine lubrication and cooling and particularly relates to a small automatic lubrication and cooling type turbojet engine. The automatic lubrication and cooling type turbojet engine comprises an air compressor and turbine blades, wherein the air compressor and the turbine blades are fixedly arranged on a middle shaft, bearings are respectively arranged on the middle shaft where the air compressor and the inner sides of the turbine blades are located, inner rings of the two bearings are fixed to the middle shaft, and outer rings of the two bearings are fixed to an engine housing. The engine further comprises two oil pipes for delivering lubrication oil, and oil outlets of the two oil pipes are located between the two bearings and are respectively pointed to the end faces of the two bearings. In the high-speed running process of the turbine blades and the air compressor, a certain amount of negative pressures is produced by the outer end faces of the two bearings, the pressure in a cavity between the middle shaft where the two bearings are located and the housing is greater than the pressures of the outer end faces of the two bearings, accordingly oil flows out of the oil outlets of the oil pipes and is jet onto the end faces of the bearings, and the bearings rotating at high speed are automatically cooled and lubricated.
Description
Technical field
The invention belongs to the lubrication and cooling technology field that relate to motor, be specially a kind of small-sized self oiling cooled turbine air breathing engine.
Background technique
Turbine jet engine principle utilizes gas compressor that air is gone from suction port inspiration, and by air compressing in firing chamber, oil nozzle is to the oil plant of firing chamber ejection atomization, high-pressure air after compression and mist of oil mixed gas are lighted by ignition mechanism, mixed gas burning expansion, promotes turbine and rotates, after the turbine of rotation drives gas compressor (this is a feedback) mixture combustion to expand through turbine, gas after burning sprays from puff prot, thus produces thrust.Wherein gas compressor and turbine blade are fixedly installed on axis, the assembly rotary type that gas compressor, turbine blade, axis are formed is arranged in engine casing, for realizing the rotational support to gas compressor, turbine blade, axis formation assembly, described axis is provided with bearing, inner ring and the axis of described bearing are fixed, the outer ring of bearing is fixed by support and engine casing, and the gap between engine casing and axis forms the duct entering air, oil gas.
For small sized turbine jet engine, described motor generally operates under the high speed of 4 ten thousand to 10 ten thousand turns, and the cooling and lubricating of the front and back bearings on axis is quite important.But be difficult to maintain longer time by general high-quality lubrication, be limited to structure and the heavily quantitative limitation of small sized turbine jet engine, set up larger volume in addition, the cooling and lubricating system of weight is unpractical for motor itself.
Summary of the invention
The object of the invention is to: a kind of self oiling cooled turbine jet engine is provided, when without the need to set up larger volume, weight cooling and lubricating device, the cooling of turbine jet engine bearing itself can self oiling cooling.
For achieving the above object, the technical solution used in the present invention is: a kind of self oiling cooled turbine air breathing engine, comprise and be fixedly installed on gas compressor on axis and turbine blade, the axis closing on place inside gas compressor and turbine blade is respectively arranged with bearing, inner ring and the axis of described two bearings are fixed, outer ring and engine casing are fixed, described motor also comprises two oil pipes be communicated with lubricating oil, and described two oil pipe oil outlets are between two bearings and point to the end face of two bearings respectively.
Compared with prior art, the technique effect that the present invention exists is: in the process that the turbine blade in motor and gas compressor run up, the exterior edge face of two bearings is made to produce a certain amount of negative pressure, pressure in chamber between two bearings between the axis at place and casing is greater than the pressure of two bearings exterior edge face, make the oil outlet of oil pipe fuel-displaced, and be injected on the end face of bearing, thus make the automatic cooling and lubricating of the bearing of High Rotation Speed.
Accompanying drawing explanation
Fig. 1 is structural representation of the present invention.
Embodiment
By reference to the accompanying drawings, the present invention will be further described in detail:
A kind of self oiling cooled turbine air breathing engine, comprise and be fixedly installed on gas compressor 20 on axis 10 and turbine blade 30, the axis 10 closing on place inside gas compressor 20 and turbine blade 30 is respectively arranged with bearing 40, the inner ring of described two bearings 40 and axis 10 is fixing, outer ring is fixing with engine casing 50, described motor also comprises two oil pipes 60 be communicated with lubricating oil, and described two oil pipe 60 oil outlets point between two bearings 40 and respectively the end face of two bearings 40.
By reference to the accompanying drawings 1, gas compressor 20 and the turbine blade 30 of rotation at a high speed make the person's of closing on two bearing 40 endface position places produce great negative pressure, the air pressure of the chamber between two bearings 40 between the axis 10 at place and casing 50 is obviously greater than the air pressure of the exterior edge face of two bearings 40, therefore under the effect of the pressure, lubricating oil is flowed out along the ball between bearing 40 inner ring and outer ring, and then the bearing 40 of High Rotation Speed is carried out cooling and lubricating, gas compressor 20 and turbine blade 30 are healed High Rotation Speed, the wearing and tearing of the generation of bearing 40 and heat are larger, the negative pressure of bearing 40 both ends of the surface is larger, and then make the lubricating oil jet velocity of oil pipe 60 larger, and then the lubrication of complete matched bearings 40, this self-lubricated turbine jet engine can realize self-lubricating function, without the need to arranging independent lubrication system, greatly reduce the structure of motor.
For guaranteeing in the ball that fluid can enter between the inner ring of bearing 40 and outer ring smoothly, described axis 10 entirety is in ladder shaft-like, comprise the ladder shaft part 12 at middle shaft part 11 and two ends, described bearing 40 to be arranged on ladder shaft part 12 and inner ring end face and middle shaft part 11 end face against, described middle shaft part 11 to be diminished to two ends setting gradually by centre, the negative pressure of the exterior edge face generation of bearing 40, the fluid of oil pipe 60 is flowed out, if the little situation of suction strength exists, the slope of middle shaft part 11, fluid can be made to flow on the inner face of bearing 40 inner ring smoothly, and then the cooling and lubricating guaranteeing bearing 40.
For guaranteeing the suction strength of bearing 40 both ends of the surface, the both ends of the surface of casing 50 are stretched out at the two ends of described axis 10 respectively, described gas compressor 20 and turbine blade 30 are separately positioned on the external part of axis 10, gas compressor 20 and turbine blade 30 close on casing 50 both ends of the surface and gap is arranged, this gap forms negative pressure gap, bearing 40 can select ball bearing, there is the air gap that gas passes through between the inner ring of bearing 40 and outer ring.
Further, described oil pipe 60 is communicated with oil storage tank 70, and oil storage tank 70 is fixedly installed on the outer wall of casing 50, and wherein, described oil storage tank 70 is in threeway tubulose, and one entrance point is communicated with oil inlet pipe 80, and other two oil outlets of oil storage tank 70 are communicated with oil pipe 60.
Described oil pipe 60 level is drawn from oil storage tank 70, and oil pipe 60 is oblique points to the end face of bearing 40 through casing 50, and described oil inlet pipe 80 pipe shaft is parallel with axis 10, and one end of oil inlet pipe 80 is communicated with fuel tank, the other end curve transition is extremely communicated with oil storage tank 70.
Claims (7)
1. a self oiling cooled turbine air breathing engine, comprise and be fixedly installed on gas compressor (20) on axis (10) and turbine blade (30), close on gas compressor (20) and turbine blade (30) inner side place axis (10) on be respectively arranged with bearing (40), the inner ring of described two bearings (40) and axis (10) are fixed, outer ring and engine casing (50) are fixed, it is characterized in that: described motor also comprises two oil pipes (60) be communicated with lubricating oil, described two oil pipes (60) oil outlet to be positioned between two bearings (40) and to point to the end face of two bearings (40) respectively.
2. self oiling cooled turbine air breathing engine according to claim 1, it is characterized in that: described axis (10) entirety is in ladder shaft-like, comprise the ladder shaft part (12) at middle shaft part (11) and two ends, described bearing (40) is arranged on the upper and inner ring end face of ladder shaft part (12) and middle shaft part (11) end face and is diminished gradually to two ends setting by centre against, described middle shaft part (11).
3. the self oiling cooled turbine air breathing engine according to claims 2, it is characterized in that: the both ends of the surface of casing (50) are stretched out at the two ends of described axis (10) respectively, described gas compressor (20) and turbine blade (30) are separately positioned on the external part of axis (10), and gas compressor (20) and turbine blade (30) close on casing (50) both ends of the surface and gap is arranged.
4. self oiling cooled turbine air breathing engine according to claim 1, it is characterized in that: described oil pipe (60) is communicated with oil storage tank (70), oil storage tank (70) is fixedly installed on the outer wall of casing (50).
5. self oiling cooled turbine jet engine according to claim 4, it is characterized in that: described oil storage tank (70) is in threeway tubulose, one entrance point is communicated with oil inlet pipe (80), and other two oil outlets of oil storage tank (70) are communicated with oil pipe (60).
6. self oiling cooled turbine jet engine according to claim 5, it is characterized in that: described oil pipe (60) level is drawn from oil storage tank (70), oil pipe (60) is oblique points to the end face of bearing (40) through casing (50).
7. self oiling cooled turbine jet engine according to claim 5, it is characterized in that: described oil inlet pipe (80) pipe shaft is parallel with axis (10), one end of oil inlet pipe (80) is communicated with fuel tank, and the other end curve transition is to being communicated with oil storage tank (70).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510150052.1A CN104791132A (en) | 2015-03-31 | 2015-03-31 | Automatic lubrication and cooling type turbojet engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510150052.1A CN104791132A (en) | 2015-03-31 | 2015-03-31 | Automatic lubrication and cooling type turbojet engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104791132A true CN104791132A (en) | 2015-07-22 |
Family
ID=53556229
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510150052.1A Pending CN104791132A (en) | 2015-03-31 | 2015-03-31 | Automatic lubrication and cooling type turbojet engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104791132A (en) |
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 |
| RU2685154C1 (en) * | 2018-06-07 | 2019-04-16 | Публичное акционерное общество "ОДК - Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") | Two-shaft gas turbine engine support |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5526640A (en) * | 1994-05-16 | 1996-06-18 | Technical Directions, Inc. | Gas turbine engine including a bearing support tube cantilevered from a turbine nozzle wall |
| CN1399706A (en) * | 1999-10-12 | 2003-02-26 | Alm开发公司 | Bearing housing for turbomachine |
| CN101473124A (en) * | 2006-06-21 | 2009-07-01 | 株式会社Ihi | Bearings conformation of rotating machinery, rotating machinery, method for manufacturing bearings conformation and rotating machinery |
| 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 |
-
2015
- 2015-03-31 CN CN201510150052.1A patent/CN104791132A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5526640A (en) * | 1994-05-16 | 1996-06-18 | Technical Directions, Inc. | Gas turbine engine including a bearing support tube cantilevered from a turbine nozzle wall |
| CN1399706A (en) * | 1999-10-12 | 2003-02-26 | Alm开发公司 | Bearing housing for turbomachine |
| CN101473124A (en) * | 2006-06-21 | 2009-07-01 | 株式会社Ihi | Bearings conformation of rotating machinery, rotating machinery, method for manufacturing bearings conformation and rotating machinery |
| 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 |
Cited By (3)
| 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 |
| RU2685154C1 (en) * | 2018-06-07 | 2019-04-16 | Публичное акционерное общество "ОДК - Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") | Two-shaft gas turbine engine support |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103375267B (en) | Oil scoop manifold | |
| US7748209B1 (en) | Small single use gas turbine engine with oil-less bearing arrangement | |
| JP4841222B2 (en) | Reverse rotating turbine engine and method of assembling it | |
| US20070234733A1 (en) | Small gas turbine engine with multiple burn zones | |
| US10267214B2 (en) | Compressor inlet recirculation system for a turbocharger | |
| CN105221295A (en) | A kind of punching press-turbojet compound aeroengine | |
| US10612436B2 (en) | Deoiler for a gas turbine engine | |
| CN106460726A (en) | Fan rotor for a turbo machine such as a multiple flow turbojet engine driven by a reduction gear | |
| CA2888673A1 (en) | External cooling fluid injection system in a gas turbine engine | |
| US5568984A (en) | Fuel lubricated bearing | |
| RU2016100346A (en) | Device for cooling oil in a gas turbine engine | |
| CN111503063B (en) | Generator with jet pump | |
| CN104975941A (en) | Turbocharger bearing housing oil groove | |
| US20190101081A1 (en) | Turbofan comprising a simplified bearing lubrication assembly | |
| CN104791132A (en) | Automatic lubrication and cooling type turbojet engine | |
| CA2551904C (en) | Scavenge pump system and method | |
| JP2015506434A (en) | Adaptive eductor system | |
| CN208040567U (en) | A kind of boosting impacting fanjet | |
| CN107916994B (en) | Gas turbine engine and method for operating a sump pressurization assembly thereof | |
| US10670077B2 (en) | Sealed bearing assembly and method of forming same | |
| US10443443B2 (en) | Non-contacting seals for geared gas turbine engine bearing compartments | |
| US20150337731A1 (en) | Oil pump transfer plate | |
| CN109707515A (en) | A kind of vane type wheeling disk structure for gas turbine lubricant passage way system | |
| EP3789597A1 (en) | Aircraft engine having a common-rail fuel system with ejector pump and method of operating an aircraft engine | |
| CN107842423A (en) | The pushing system of water spray or methanol suitable for small-size turbojet engine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| EXSB | Decision made by sipo to initiate substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20150722 |