CN201412194Y - Engine rotor system installation device - Google Patents
Engine rotor system installation device Download PDFInfo
- Publication number
- CN201412194Y CN201412194Y CN2009203041898U CN200920304189U CN201412194Y CN 201412194 Y CN201412194 Y CN 201412194Y CN 2009203041898 U CN2009203041898 U CN 2009203041898U CN 200920304189 U CN200920304189 U CN 200920304189U CN 201412194 Y CN201412194 Y CN 201412194Y
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- China
- Prior art keywords
- face
- casing
- bearing
- turbine shaft
- ring
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- 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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- 238000009434 installation Methods 0.000 title abstract description 5
- 238000013016 damping Methods 0.000 claims abstract description 23
- 239000000446 fuel Substances 0.000 claims abstract description 10
- 238000000280 densification Methods 0.000 claims description 9
- 125000006850 spacer group Chemical group 0.000 claims description 4
- 238000007789 sealing Methods 0.000 abstract description 11
- 239000000295 fuel oil Substances 0.000 description 9
- 239000003921 oil Substances 0.000 description 4
- 238000012856 packing Methods 0.000 description 3
- 230000015556 catabolic process Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000006731 degradation reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000008676 import Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
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Abstract
The utility model relates to an engine rotor system installation device. An axial-flow impeller, a centrifugal impeller, a fuel jet nozzle and a rubber damping supporting arrangement are fixedly installed on a turbine wheel shaft of the engine. The front end face of the turbine wheel shaft is fixedly connected with a high speed end face sealing device and the rear end face is fixedly connected with a flexible supporting arrangement. The engine rotor system installation device is characterized in that the high speed end face sealing device is composed of a casing, and a sealing ring, an end face sealing ring, a spring and a sealing end cover which are successively installed in the casing along the turbine wheel shaft; the rubber damping supporting arrangement is additionally provided with arubber damping ring between the bearing seat casing and the bearing; the flexible supporting arrangement is provided with a tooth-shaped flexible supporting member between the rear bearing seat casing and the rear bearing. The utility model has novel, compact and practical structural design, less parts, light weight and convenient dismounting and maintaining. The adjustment capability of the damping and rigidity range is increased so as to ensure the connection between the rotor and the stationary member and guarantee the reliability and practicality of the connection and seal between the fuel and gas circuit.
Description
Technical field
The utility model relates to a kind of erecting device, particularly relates to high engine speeds rotor-support-foundation system erecting device.
Background technique
Microminaturization, simplification and cost degradation along with the design of microminiature engine structure, microminiature engine rotor system develops towards directions such as high rotating speed, small-sized simplification and compact structures, single order, second order will be crossed over by work rotor system, even three rank critical speed of rotation, stable operation under supercritical speed.Therefore what the supporting structure of microminiature engine rotor system designed brief microminaturization, big, the overcritical stable operation of critical speed of rotation adjustment range and multiple function system brief integrated etc. has become outstanding problem.The design and installation of traditional engine rotor system, complex structure, number of spare parts is many, and size and weight are big, and critical speed of rotation, supercritical speed are adjusted operational difficulties.
Summary of the invention
The purpose of this utility model is to provide a kind of light-duty, simple in structure, overcritical stable operation and easy installation and reliable engine rotor system erecting device.Be used to solve microminiature engine rotor system complexity is installed, part is many, and critical speed of rotation is adjusted the shortcoming of operational difficulties.
The utility model is to be fixed with axial-flow blower on the turbine shaft of motor successively, spacer sleeve, centrifugal impeller, fuel nozzle and rubber damping bearing device, and press affixed by nut, the front-end face of turbine shaft is connected with high speed end face densification device, ear end face is connected with resilient supporting unit, it is characterized in that: described high speed end face densification device is by casing and the seal ring that is equipped with successively along turbine shaft in casing, the end face ring of obturaging, spring, the end cap of obturaging is formed; Described rubber damping bearing device is to have additional the rubber damping ring between bearing support casing and bearing; Described resilient supporting unit is to be provided with the profile of tooth elastic supporting piece between rear bearing block casing and rear bearing.
In order to realize above-mentioned purpose better, in the described turbine shaft central blind hole cyclone device is housed.
The also coaxial air pipe that is provided with of described turbine shaft front end.The axial position of described resilient supporting unit is provided with the lining back-up ring.
The utility model structural design Nover practical, simple compact, few, in light weight, the dismounting and easy to maintenance of number of spare parts.Adopt rubber damping bearing device and resilient supporting unit, simplified the supporting structure of small rotor system, reduced part number, damping simultaneously and range in stiffness regulating power increase, and can make stable operation under the adjustment of the multistage critical speed of rotation of rotor-support-foundation system and the supercritical speed.Adopt high speed end face densification device, rotor structure is simple, the part amount is few, has solved being connected of rotor and static element, and has guaranteed reliable operation and the practicality that fuel oil, gas circuit connect and seal.
Description of drawings
Fig. 1 is a structural representation of the present utility model.
Fig. 2 is Fig. 1 high speed end face densification device structural representation.
Fig. 3 is the structural representation of Fig. 1 rubber damping bearing device.
Fig. 4 is the structural representation of Fig. 1 resilient supporting unit.
Among the figure 1, nut, 2, axial-flow blower, 3, spacer sleeve, 4, centrifugal impeller, 5, fuel nozzle, 6, turbine shaft, 7, cyclone device, 8, spring, 9, casing, 10, the end face ring of obturaging, 11, seal ring, 12, the end cap of obturaging, 13, air pipe, 14, the oil sealing mouth, 15, the turbine shaft seal ring, 16, fuel inlet, 17, the Continuous pressure-controlled air inflation import, 18, the rubber damping ring, 19, the bearing support casing, 20, bearing, 21, the lining back-up ring, 22, the rear bearing block casing, 23, the profile of tooth elastic supporting piece, 24, rear bearing, 25, high speed end face densification device, 26, the rubber damping bearing device, 27, resilient supporting unit.
Embodiment
By above accompanying drawing as can be seen, turbine shaft 6 links together centrifugal impeller 4, rubber damping bearing device 26, spacer sleeve 3 and axial-flow blower 2, be fixed by nut 1, cyclone device 7 is housed in the central blind hole of turbine shaft 6, the front-end face of turbine shaft 6 is connected with high speed end face densification device 25, and ear end face is connected with resilient supporting unit 27.
High speed end face densification device 25 is made up of the casing 9 and the end cap 12 of obturaging, and obturages and encircles in 10 along turbine shaft 6 ring 11 end face of packing into of will obturaging earlier casing 9 in, and the spring 8 of packing into successively again, end face are obturaged and encircled 10, the end cap 12 of obturaging.Can realize the position adjustment that end face is obturaged ring 10 by the spring 8 and the end cap 12 of obturaging, and realize the motive sealing of fuel oil and Continuous pressure-controlled air inflation.Pass through the gap between control commentaries on classics, the stator during assembling, make the front-end face compression end face of the oil sealing mouth 14 on the turbine shaft 6 ring 10 of obturaging, effect owing to spring 8 during work contacts the ring end face of obturaging all the time well with the front-end face of oil sealing mouth 14, thereby realizes the sealing of fuel oil and Continuous pressure-controlled air inflation.
Rubber damping bearing device 26 is to have additional rubber damping ring 18 between bearing support casing 19 and bearing 20.Cushion rubber damping ring 18 outer shrouds contact with bearing base casing 19, the outer loop contacts of interior ring and bearing 20, and bearing 20 keeps certain clearance with bearing support casing 19.The preceding bearing load of rubber damping ring 18 bear rotor systems and pass to bearing support casing 19 during work.By the structural parameter of adjustment rubber damping ring 18 and the gap between bearing 20 and the bearing support casing 19, can realize the adjustment of rotor bearing rigidity and damping constant.
Resilient supporting unit 27 is to be provided with profile of tooth elastic supporting piece 23 between rear bearing block casing 22 and rear bearing 24.Profile of tooth elastic supporting piece 23 outer shrouds contact with rear bearing block casing 22, interior ring and rear bearing 24 outer loop contacts, and the axial position of profile of tooth elastic supporting piece 23 is provided with spacing lining back-up ring 21.The back bearing load of profile of tooth elastic supporting piece 23 rotor-support-foundation systems passes to rear bearing block casing 22 during work.By adjusting the structural parameter of profile of tooth elastic supporting piece 23, can convenient and swift realization rotor bearing rigidity and the adjustment of critical speed of rotation.
The supporting of rotor-support-foundation system and critical speed of rotation adjustment, supercritical speed stable operation are finished by rubber damping bearing device 26 and resilient supporting unit 27 respectively, have reduced the amplitude of support stiffness and reduction rotor.The fuel oil supply system and the turbine shaft 6 of motor is integrated, the cyclone device 7 of in turbine shaft 6 central blind holes, packing into, the also coaxial air pipe 13 that is provided with of turbine shaft 6 front ends; By turbine shaft 6 rotary driving, give fuel pressurization during work, regulate in order to adapt to fuel oil simultaneously, infeed one Continuous pressure-controlled air inflation with fuel oil at the preceding center of turbine shaft.Fuel oil arrives the fuel nozzle 5 that is contained on the turbine shaft 6 along turbine shaft 6 inner hole walls, and fuel oil is again with the turbine high speed rotating, and fuel nozzle 5 throws away atomizing with the fuel oil rotation.Adopt axial high speed face seals 25, make fuel feed oil circuit and air feed gas circuit UNICOM and sealing, realize the connection of commentaries on classics, stator spare.
Claims (4)
1. engine rotor system erecting device, on the turbine shaft (6) of motor, be fixed with axial-flow blower (2) successively, spacer sleeve (3), centrifugal impeller (4), fuel nozzle (5) and rubber damping bearing device (26), and affixed by nut (1), and the front-end face of turbine shaft (6) is connected with high speed end face densification device (25), ear end face is connected with resilient supporting unit (27), it is characterized in that:
A, described high speed end face densification device (25) be by casing (9) and the seal ring (11) that is equipped with successively along turbine shaft (6) in casing (9), the end face ring (10) of obturaging, and spring (8), the end cap of obturaging (12) is formed;
B, described rubber damping bearing device (26) are to have additional rubber damping ring (18) between bearing support casing (19) and bearing (20);
C, described resilient supporting unit (27) are to be provided with profile of tooth elastic supporting piece (23) between rear bearing block casing (22) and rear bearing (24).
2. according to the described erecting device of claim 1, it is characterized in that: describedly in turbine shaft (6) central blind hole, cyclone device (7) is housed.
3. according to the described erecting device of claim 1, it is characterized in that: the also coaxial air pipe (13) that is provided with of described turbine shaft (6) front end.
4. according to the described erecting device of claim 1, it is characterized in that: the axial position of described resilient supporting unit (27) is provided with lining back-up ring (21).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009203041898U CN201412194Y (en) | 2009-06-10 | 2009-06-10 | Engine rotor system installation device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009203041898U CN201412194Y (en) | 2009-06-10 | 2009-06-10 | Engine rotor system installation device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201412194Y true CN201412194Y (en) | 2010-02-24 |
Family
ID=41714079
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2009203041898U Expired - Lifetime CN201412194Y (en) | 2009-06-10 | 2009-06-10 | Engine rotor system installation device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201412194Y (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106351747A (en) * | 2016-11-21 | 2017-01-25 | 中国航空动力机械研究所 | Fuel supply system and fuel supply method for small-power gas-turbine engine |
| CN110173353A (en) * | 2019-05-31 | 2019-08-27 | 中国航发湖南动力机械研究所 | Engine rotor system |
| CN112197103A (en) * | 2020-09-29 | 2021-01-08 | 中国航发湖南动力机械研究所 | High-speed flywheel shell structure |
| CN113074126A (en) * | 2021-04-18 | 2021-07-06 | 上海尚实能源科技有限公司 | Two-stage axial flow compressor |
| CN114221501A (en) * | 2021-12-15 | 2022-03-22 | 中国航发南方工业有限公司 | Rotor assembly tool and method, centrifugal impeller gap adjusting mechanism and method |
| CN115199343A (en) * | 2022-06-25 | 2022-10-18 | 中科航星科技有限公司 | A contact sealing assembly suitable for axial sealing of rotor and stator |
| CN115355089A (en) * | 2022-07-29 | 2022-11-18 | 中科航星科技有限公司 | Bearing oil mist lubrication cooling structure with axis oil supply |
| CN115978092A (en) * | 2023-03-21 | 2023-04-18 | 中国空气动力研究与发展中心空天技术研究所 | Supporting structure of ultra-high speed miniature rotor and design method of supporting structure |
-
2009
- 2009-06-10 CN CN2009203041898U patent/CN201412194Y/en not_active Expired - Lifetime
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106351747A (en) * | 2016-11-21 | 2017-01-25 | 中国航空动力机械研究所 | Fuel supply system and fuel supply method for small-power gas-turbine engine |
| CN106351747B (en) * | 2016-11-21 | 2018-03-09 | 中国航空动力机械研究所 | A kind of fuel oil supply system and method for small-power gas-turbine unit |
| CN110173353A (en) * | 2019-05-31 | 2019-08-27 | 中国航发湖南动力机械研究所 | Engine rotor system |
| CN112197103A (en) * | 2020-09-29 | 2021-01-08 | 中国航发湖南动力机械研究所 | High-speed flywheel shell structure |
| CN112197103B (en) * | 2020-09-29 | 2022-07-08 | 中国航发湖南动力机械研究所 | High-speed flywheel shell structure |
| CN113074126A (en) * | 2021-04-18 | 2021-07-06 | 上海尚实能源科技有限公司 | Two-stage axial flow compressor |
| CN114221501A (en) * | 2021-12-15 | 2022-03-22 | 中国航发南方工业有限公司 | Rotor assembly tool and method, centrifugal impeller gap adjusting mechanism and method |
| CN114221501B (en) * | 2021-12-15 | 2023-09-08 | 中国航发南方工业有限公司 | Rotor assembly tool and method, centrifugal impeller gap adjusting mechanism and method |
| CN115199343A (en) * | 2022-06-25 | 2022-10-18 | 中科航星科技有限公司 | A contact sealing assembly suitable for axial sealing of rotor and stator |
| CN115355089A (en) * | 2022-07-29 | 2022-11-18 | 中科航星科技有限公司 | Bearing oil mist lubrication cooling structure with axis oil supply |
| CN115978092A (en) * | 2023-03-21 | 2023-04-18 | 中国空气动力研究与发展中心空天技术研究所 | Supporting structure of ultra-high speed miniature rotor and design method of supporting structure |
| CN115978092B (en) * | 2023-03-21 | 2023-06-16 | 中国空气动力研究与发展中心空天技术研究所 | Support structure of ultra-high speed micro rotor and design method of support structure |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term |
Granted publication date: 20100224 |
|
| CX01 | Expiry of patent term |