CN201025157Y - Micro turbine jet engine - Google Patents
Micro turbine jet engine Download PDFInfo
- Publication number
- CN201025157Y CN201025157Y CNU2007201184987U CN200720118498U CN201025157Y CN 201025157 Y CN201025157 Y CN 201025157Y CN U2007201184987 U CNU2007201184987 U CN U2007201184987U CN 200720118498 U CN200720118498 U CN 200720118498U CN 201025157 Y CN201025157 Y CN 201025157Y
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- China
- Prior art keywords
- diffuser
- pipe
- inclined flow
- air compressor
- flow air
- 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.)
- Expired - Lifetime
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Abstract
The utility model relates to a mini turbine jet engine which comprises a gas machine valve, an inclined flow machine, an expansion pipe, a burning room, an outer machine valve, a vortex, a tail spraying pipe, an axis and an axis sleeve; the axis comprises a front nut, a rotor of the inclined flow machine, an axis sleeve, a rotor of the vortex and a back nut; the axis sleeve comprises a pair of bearings, a stressing spring and a supporting pipe; and the burning room is an evaporating tube type ring burning room. Therefore the utility model can enhance the pressure ratio, reduce the oil consumption and enhance the pushing force.
Description
Affiliated technical field
The utility model relates to a kind of air breathing engine, especially refers to a kind of miniature turbine jet engines.
Background technique
From present miniature turbine jet engines, its gas compressor mainly is a centrifugal compressor, and air-flow passes through radial and axial Diffuser, turns to turn 90 degrees, and loss is serious.
Adopt inclined flow air compressor can effectively suppress airflow breakaway, increase pressure ratio, increase flow, and then reduce oil consumption rate, increase thrust.
Summary of the invention
The purpose of this utility model provides a kind of miniature turbine jet engines, increases pressure ratio, increases flow and thrust.
The utility model relates to a kind of miniature turbine jet engines, it comprises inlet casing, inclined flow air compressor, diffuser pipe, the firing chamber, outer casing, turbine, jet pipe, axle, axle sleeve, it is characterized in that: preceding nut (4) is installed on axle (18) foremost, inclined flow air compressor rotor (6) is installed in preceding nut (4) back, inclined flow air compressor rotor (6) outlet installation shaft is to Diffuser (7), axially Diffuser (7) outlet is installed by interior, the diffuser pipe (8) that outer shroud is formed, axle envelope (22) is installed in axial Diffuser (7) groove and with axle sleeve (11) and even is fixed in axial Diffuser (7), axle sleeve (11) front end and back end inlet is installed bearing, fore bearing (21) and rear bearing (17) are by loaded spring (20) and support tube (19) supporting, ring is fixed in axial Diffuser (7) ear end face in firing chamber (9) and the diffuser pipe (8), nozzle ring (12) is installed on axle sleeve (11) rear end step, nozzle ring (12) outer ring flange is by screw and outer casing (16), jet pipe (14) is fastening, outer casing (16) front end and inlet casing (5) rear end are anchored on diffuser pipe (8) outer shroud by screw, nozzle ring (12) rear end groove is installed turbine rotor (13), turbine rotor (13) rear end is fastening by back nut (15), direct current generator (1) output shaft is equipped with oblique ascension clutch (3), and direct current generator (1) is fixed in electric machine support (2).
Described miniature turbine jet engines, its gas compressor are inclined flow air compressor, increase pressure ratio and flow.
Described miniature turbine jet engines has increased diffuser pipe (8), and diffuser pipe is made up of interior ring (Fig. 2) and outer shroud (Fig. 3).
The beneficial effects of the utility model are, adopt inclined flow air compressor, can effectively reduce airflow breakaway, increase flow, have only axial Diffuser simultaneously, simplify the structure, increasing diffuser pipe can be further to the air-flow diffusion, smooth combustion chamber flame, finally reaching increases pressure ratio and flow, increases the purpose of thrust.
Description of drawings
Fig. 1 is a structural representation of the present utility model.
Fig. 2 is a ring schematic representation in the diffuser pipe of the present utility model.
Fig. 3 is a diffuser pipe outer shroud schematic representation of the present utility model.
Among the figure: 1. 22. envelopes of nut 5. inlet casing 6. inclined flow air compressor rotors, 7. axial Diffuser 8. diffuser pipe 9. firing chambers, 10. glow plug 11. axle sleeves, 12. nozzle ring 13. turbine rotors, 14. jet pipe 15. back nuts, 16. outer casing 17. rear bearings 18. 19. support tubes, 20. loaded springs, 21. fore bearings before the direct current generator 2. electric machine supports 3. oblique ascension clutches 4.
Embodiment
Below in conjunction with accompanying drawing the utility model is further described.
Please referring to shown in the accompanying drawing, in the drawings, preceding nut (4) is installed on axle (18) foremost, inclined flow air compressor rotor (6) is installed in preceding nut (4) back, inclined flow air compressor rotor (6) outlet installation shaft is to Diffuser (7), axially Diffuser (7) outlet is installed by interior, the diffuser pipe (8) that outer shroud is formed, axle envelope (22) is installed in axial Diffuser (7) groove and with axle sleeve (11) and even is fixed in axial Diffuser (7), axle sleeve (11) front end and back end inlet is installed bearing, fore bearing (21) and rear bearing (17) are by loaded spring (20) and support tube (19) supporting, ring is fixed in axial Diffuser (7) ear end face in firing chamber (9) and the diffuser pipe (8), nozzle ring (12) is installed on axle sleeve (11) rear end step, nozzle ring (12) outer ring flange is by screw and outer casing (16), jet pipe (14) is fastening, outer casing (16) front end and inlet casing (5) rear end are anchored on diffuser pipe (8) outer shroud by screw, nozzle ring (12) rear end groove is installed turbine rotor (13), turbine rotor (13) rear end is fastening by back nut (15), direct current generator (1) output shaft is equipped with oblique ascension clutch (3), and direct current generator (1) is fixed in electric machine support (2).
During engine operation, direct current generator (1) rotates, oblique ascension clutch (3) is to the preceding nut (4) of anteroclusion inclined flow air compressor front, the rotation of drive rotor, reach certain rotating speed, glow plug (10) is lighted combustion gas, and firing chamber (9) are carried out preheating, reaches uniform temperature, oil pump begins fuel feeding, (9) rear end arrives firing chamber (9) front bulkhead burning through the baffling of waveform evaporating pipe from the firing chamber, after rotor reaches the rotation rotating speed, stops direct current generator (1) is powered, oblique ascension clutch (3) withdrawal original position, air constantly is sucked into gas compressor, through inclined flow air compressor compression, the further diffusion of diffuser pipe, enter the firing chamber, with the combustion gas that fuel oil mixed combustion produces High Temperature High Pressure, further expand to entering jet pipe after the turbine acting, produce thrust.
Claims (3)
1. miniature turbine jet engines, it comprises inlet casing, inclined flow air compressor, diffuser pipe, the firing chamber, outer casing, turbine, jet pipe, axle, axle sleeve, it is characterized in that: preceding nut (4) is installed on axle (18) foremost, inclined flow air compressor rotor (6) is installed in preceding nut (4) back, inclined flow air compressor rotor (6) outlet installation shaft is to Diffuser (7), axially Diffuser (7) outlet is installed by interior, the diffuser pipe (8) that outer shroud is formed, axle envelope (22) is installed in axial Diffuser (7) groove and with axle sleeve (11) and even is fixed in axial Diffuser (7), axle sleeve (11) front end and back end inlet is installed bearing, fore bearing (21) and rear bearing (17) are by loaded spring (20) and support tube (19) supporting, ring is fixed in axial Diffuser (7) ear end face in firing chamber (9) and the diffuser pipe (8), nozzle ring (12) is installed on axle sleeve (11) rear end step, nozzle ring (12) outer ring flange is by screw and outer casing (16), jet pipe (14) is fastening, outer casing (16) front end and inlet casing (5) rear end are anchored on diffuser pipe (8) outer shroud by screw, nozzle ring (12) rear end groove is installed turbine rotor (13), turbine rotor (13) rear end is fastening by back nut (15), direct current generator (1) output shaft is equipped with oblique ascension clutch (3), and direct current generator (1) is fixed in electric machine support (2).
2. miniature turbine jet engines according to claim 1 is characterized in that: gas compressor is an inclined flow air compressor.
3. miniature turbine jet engines according to claim 1 is characterized in that: the inclined flow air compressor back increases diffuser pipe (8), and diffuser pipe is made up of interior ring (Fig. 2) and outer shroud (Fig. 3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2007201184987U CN201025157Y (en) | 2007-02-12 | 2007-02-12 | Micro turbine jet engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2007201184987U CN201025157Y (en) | 2007-02-12 | 2007-02-12 | Micro turbine jet engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201025157Y true CN201025157Y (en) | 2008-02-20 |
Family
ID=39099018
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNU2007201184987U Expired - Lifetime CN201025157Y (en) | 2007-02-12 | 2007-02-12 | Micro turbine jet engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201025157Y (en) |
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101571056B (en) * | 2009-06-09 | 2011-05-18 | 北京航空航天大学 | Miniature rotor dynamic mechanical damping structure |
| CN102261996A (en) * | 2011-04-27 | 2011-11-30 | 北京航空航天大学 | Micro jet engine test bench |
| CN104500268A (en) * | 2014-12-12 | 2015-04-08 | 常州环能涡轮动力股份有限公司 | Micro turbine jet engine with two-sided centrifugal pressure roller |
| CN104806310A (en) * | 2015-04-15 | 2015-07-29 | 武汉理工大学 | Steam-powered engine for small aircraft |
| 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 |
| CN105422285A (en) * | 2015-11-27 | 2016-03-23 | 西北工业大学 | Micro-engine wave-type fuel-oil evaporating tube |
| CN105588145A (en) * | 2016-01-25 | 2016-05-18 | 西北工业大学 | Micro-engine combustion chamber spiral evaporating pipe with fins arranged inside |
| CN106948877A (en) * | 2017-04-15 | 2017-07-14 | 罗显平 | Aircraft gas screwed pipe rotary engine |
| CN108035805A (en) * | 2017-12-28 | 2018-05-15 | 深圳市华阳新材料科技有限公司 | One kind uses the molding aero-engine of 3D printing |
| CN108266272A (en) * | 2018-03-12 | 2018-07-10 | 西北工业大学 | A kind of microminiature turbine engine axle sleeve |
| CN108590862A (en) * | 2018-05-29 | 2018-09-28 | 张敏 | Diameter formula turbojet power plant after a kind of microminiature |
| CN110953026A (en) * | 2018-11-22 | 2020-04-03 | 李华玉 | Combined cycle power plant |
| CN110985148A (en) * | 2018-11-18 | 2020-04-10 | 李华玉 | Combined cycle power plant |
| CN112334664A (en) * | 2019-05-23 | 2021-02-05 | 开利公司 | Mixed flow compressor of refrigeration system |
| CN112449670A (en) * | 2019-06-28 | 2021-03-05 | 开利公司 | Vaneless supersonic diffuser for a compressor |
-
2007
- 2007-02-12 CN CNU2007201184987U patent/CN201025157Y/en not_active Expired - Lifetime
Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101571056B (en) * | 2009-06-09 | 2011-05-18 | 北京航空航天大学 | Miniature rotor dynamic mechanical damping structure |
| CN102261996A (en) * | 2011-04-27 | 2011-11-30 | 北京航空航天大学 | Micro jet engine test bench |
| CN104500268A (en) * | 2014-12-12 | 2015-04-08 | 常州环能涡轮动力股份有限公司 | Micro turbine jet engine with two-sided centrifugal pressure roller |
| CN104806310A (en) * | 2015-04-15 | 2015-07-29 | 武汉理工大学 | Steam-powered engine for small aircraft |
| 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 |
| CN105422285A (en) * | 2015-11-27 | 2016-03-23 | 西北工业大学 | Micro-engine wave-type fuel-oil evaporating tube |
| CN105588145A (en) * | 2016-01-25 | 2016-05-18 | 西北工业大学 | Micro-engine combustion chamber spiral evaporating pipe with fins arranged inside |
| CN106948877A (en) * | 2017-04-15 | 2017-07-14 | 罗显平 | Aircraft gas screwed pipe rotary engine |
| CN106948877B (en) * | 2017-04-15 | 2018-06-05 | 罗显平 | Aircraft gas screwed pipe rotary engine |
| CN108035805A (en) * | 2017-12-28 | 2018-05-15 | 深圳市华阳新材料科技有限公司 | One kind uses the molding aero-engine of 3D printing |
| CN108266272A (en) * | 2018-03-12 | 2018-07-10 | 西北工业大学 | A kind of microminiature turbine engine axle sleeve |
| CN108590862A (en) * | 2018-05-29 | 2018-09-28 | 张敏 | Diameter formula turbojet power plant after a kind of microminiature |
| CN110985148A (en) * | 2018-11-18 | 2020-04-10 | 李华玉 | Combined cycle power plant |
| CN110953026A (en) * | 2018-11-22 | 2020-04-03 | 李华玉 | Combined cycle power plant |
| CN112334664A (en) * | 2019-05-23 | 2021-02-05 | 开利公司 | Mixed flow compressor of refrigeration system |
| CN112449670A (en) * | 2019-06-28 | 2021-03-05 | 开利公司 | Vaneless supersonic diffuser for a compressor |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C56 | Change in the name or address of the patentee | ||
| CP02 | Change in the address of a patent holder |
Address after: Guangdong province Shenzhen City Guangming Street with rich industrial park 0301 block 7 Building 8 building, zip code: 518107 Patentee after: Shenzhen Kangcheng Machine Equipment Co., Ltd. Address before: Guangdong Province, Shenzhen city Nanshan District street Taoyuan Changyuan River Source Industrial Park 24, zip code: 518055 Patentee before: Shenzhen Kangcheng Machine Equipment Co., Ltd. |
|
| C56 | Change in the name or address of the patentee |
Owner name: KANGCHENG MACHINERY EQUIPMENTS CO., LTD., SHENZHEN Free format text: NEW ADDRESS: BUILDING 8, NO.12, QIANGSHI FIRST INDUSTRY DISTRICT, DAOBANQIANGSHI COMMUNITY, GONGMING STREET, GUANGMING NEW DISTRICT, SHENZHEN CITY, GUANGDONG PROVINCE, ZIP CODE:518106 |
|
| CP02 | Change in the address of a patent holder |
Address after: Guangdong province Shenzhen Guangming New District Gongming Subdistrict Office will stone community will stone first Industrial Zone No. 8, building 12, zip code: 518106 Patentee after: Shenzhen Kangcheng Machine Equipment Co., Ltd. Address before: Guangdong province Shenzhen City Guangming Street with rich industrial park 0301 block 7 Building 8 building, zip code: 518107 Patentee before: Shenzhen Kangcheng Machine Equipment Co., Ltd. |
|
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20080220 |