CN204922126U - Aeroengine bearing bore pressure adjustment assembly and governing valve thereof - Google Patents
Aeroengine bearing bore pressure adjustment assembly and governing valve thereof Download PDFInfo
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- CN204922126U CN204922126U CN201520217117.5U CN201520217117U CN204922126U CN 204922126 U CN204922126 U CN 204922126U CN 201520217117 U CN201520217117 U CN 201520217117U CN 204922126 U CN204922126 U CN 204922126U
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- axle center
- guide rod
- flexible thin
- bearing bore
- slider
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Abstract
The utility model provides a change and can not appear changing by a wide margin that aeroengine bearing bore pressure adjustment assembly, can so that the pressure differential of seal structure border department along with the engine speed. Bearing bore wherein holds there is the bearing, the bearing is used for supporting a rotatable parts on fixed part, sealed and enclose into the bearing bore by the labyrinth seals subassembly between rotatable parts and the fixed part, this pressure adjustment assembly includes the axle center vent of bearing bore, communicating with the axle center vent and lie in the wind channel of rotatable parts's pivot and set up in wind channel pressure regulating valve, a serial communication port, pressure regulating valve includes flexible thin type thing, flexible thin type thing sets up in the axle center in wind channel and is in the contraction state, and the rotational speed rising that can follow the pivot is opened until opening completely from the contraction state under the centrifugal force effect gradually, so that the latus rectum in wind channel reduces gradually, and then the pressure that makes the bearing bore remains stable.
Description
Technical field
The utility model relates to the bearing bore pressure regulator of aeroengine, particularly relates to pressure regulator and the modulating valve thereof of the bearing bore sealed by castor tooth of aeroengine.
Background technique
In turbojet engine, between rotary component and fixed component, include rolling bearing.In order to use lubricating oil, circulating cooling is carried out to this bearing and must design bearing bore around bearing, to guarantee that lubricating oil remains in bearing bore before recirculation before being recovered and in pipeline.In order to prevent other chambers of slippery oil pollution motor, described bearing bore sealing needs pressure reduction of obturaging.Introduce high pressure air to bearing bore from gas compressor, and axle center ventilated port is set on the axle of rotary component, for stuffing box bearing chamber, prevent lubricating oil from flowing out cavity.Air pressure in bearing bore changes with the difference of engine speed.When low engine speed is rotated, the atmospheric pressure of obturaging introduced by gas compressor is less, and introduce atmospheric pressure of obturaging when high engine speeds is run higher, bearing bore inlet and outlet pressure difference is larger.Because air is significantly compressed when running up, the air mass flow of result conveying is very high, and the pressure at bearing bore ventilated port place is approximately barometric pressure.Therefore Sealing can bear very large pressure difference, and this causes its wearing and tearing very fast, and it meets with the risk damaged and increases.
Model utility content
The purpose of this utility model is to provide a kind of Aero-engine Bearing cavity pressure controlling device, the pressure difference of sealing configuration boundary can be made to there will not be along with the change of engine speed and significantly change.
Another object of the present utility model is to provide a kind of modulating valve, and it can reduce the flow in runner gradually with rotation speed change.
For realizing described object Aero-engine Bearing cavity pressure controlling device, for regulating the pressure in bearing bore, described bearing bore accommodates bearing, described bearing is used for rotatable parts to be supported on fixed component, sealed by labyrinth seal assemblies between described rotatable parts and described fixed component and surround described bearing bore, this pressure regulator comprises the axle center ventilated port of described bearing bore, that communicate with described axle center ventilated port and be positioned at the air channel of the rotating shaft of described rotatable parts and be arranged on the pressure regulator valve in described air channel, be characterized in, described pressure regulator valve comprises flexible thin object, flexible thin object is arranged at the axle center in described air channel and is in contraction state, and can open gradually from described contraction state until open completely under centrifugal action with the rotating speed rising of described rotating shaft, reduce gradually to make the latus rectum in described air channel, and then make the pressure remained steady of described bearing bore.
Described Aero-engine Bearing cavity pressure controlling device, its further feature is, described pressure regulator valve also comprises support and elastic connecting device, described support has multiple guide rod and axle center supporting element, described axle center supporting element is arranged at axle center, described air channel, described multiple guide rod outwards distributes radially centered by the supporting element of described axle center, each described guide rod configures described elastic connecting device, described elastic connecting device comprises slider and elastic component, described elastic component one end is fixedly installed and the other end connects described slider, the peripheral edge of described flexible thin object connects described slider and inner periphery is fixed on the supporting element of described axle center, described flexible thin object can raise with the rotating speed of described rotating shaft and outwards be guided by described slider and expand, and the elastic force that described elastic component provides the described flexible thin object making expansion to shrink.
Described Aero-engine Bearing cavity pressure controlling device, its further feature is, described slider is run through by described guide rod and can be free to slide on described guide rod.
Described Aero-engine Bearing cavity pressure controlling device, its further feature is that described elastic component is the spring being sheathed on described guide rod, and one end described in it is fixed on the supporting element of described axle center.
Described Aero-engine Bearing cavity pressure controlling device, its further feature is, the radial outer end of described guide rod connects the inwall of described rotating shaft.
For realizing the modulating valve of described object, for being arranged in the runner of the rotor that can rotate, be characterized in, described modulating valve comprises flexible thin object, flexible thin object is arranged at the axle center of described runner and is in contraction state, and can open gradually from described contraction state until open completely under centrifugal action with the rotating speed rising of described rotor, reduce gradually to make the latus rectum of described runner.
Described modulating valve, its further feature is, described modulating valve also comprises support and elastic connecting device, described support has multiple guide rod and axle center supporting element, described multiple guide rod outwards distributes radially centered by the supporting element of described axle center, each described guide rod configures described elastic connecting device, described elastic connecting device comprises slider and elastic component, described elastic component one end is fixedly installed and the other end connects described slider, the peripheral edge of described flexible thin object connects described slider and inner periphery is fixed on the supporting element of described axle center, described flexible thin object can raise with the rotating speed of described rotor and outwards be guided by described slider and expand, and the elastic force that described elastic component provides the described flexible thin object making expansion to shrink.
Described modulating valve, its further feature is, described slider is run through by described guide rod and can be free to slide on described guide rod.
Described modulating valve, its further feature is that described elastic component is the spring being sheathed on described guide rod, and one end described in it is fixed on the supporting element of described axle center.
Described modulating valve, its further feature is, the radial outer end of described guide rod connects the inwall of described rotor.
The utility model beneficial effect is compared with prior art:
According to Aero-engine Bearing cavity pressure controlling device of the present utility model, even if after engine speed raises, ventilated port place, axle center air pressure flow also can not obviously raise, and therefore can not damage labyrinth seal assemblies, and reduce and expend high pressure and to obturage gas; Along with engine speed raise time, modulating valve controls back pressure after bearing bore automatically, this makes the flow flowing through bearing bore keep within the specific limits, the pressure difference of sealing configuration boundary there will not be along with the change of engine speed and significantly changes, namely can not there is larger change at all engine condition points, the life-span of labyrinth seal assemblies is significantly increased.
According to modulating valve of the present utility model, flexible thin object is arranged at the axle center of described runner and is in contraction state, and can open gradually from described contraction state until open completely under centrifugal action with the rotating speed rising of described rotor, to make the latus rectum of described runner reduce gradually, thus the flow in runner is reduced gradually.
Accompanying drawing explanation
The above and other feature of the present utility model, character and advantage become more obvious by passing through below in conjunction with the description of drawings and Examples, wherein:
Fig. 1 is the schematic diagram of Aero-engine Bearing cavity pressure controlling device in the utility model one embodiment;
Fig. 2 is the schematic diagram of modulating valve in the utility model one embodiment in Fig. 1;
Fig. 3 is the schematic diagram of flexible thin object in Fig. 2;
Fig. 4 is the schematic diagram of slider in Fig. 2;
Fig. 5 is in the schematic diagram of closed condition for the pressure regulator shown in Fig. 1;
Fig. 6 is in the schematic diagram of normal working for the pressure regulator shown in Fig. 1;
Fig. 7 is in the schematic diagram of extreme working position for the pressure regulator shown in Fig. 1.
Embodiment
Below in conjunction with specific embodiments and the drawings, the utility model is described in further detail; set forth more details in the following description so that fully understand the utility model; but the utility model obviously can be implemented with multiple this alternate manner described that is different from; those skilled in the art when doing similar popularization, deduction without prejudice to when the utility model intension according to practical situations, therefore can should not limit protection domain of the present utility model with the content of this specific embodiment.
It should be noted that Fig. 1 to Fig. 7 all only exemplarily, it is not draw according to the condition of equal proportion, and should not be construed as limiting in this, as to the protection domain of the utility model actual requirement.
As shown in Figure 1, Aero-engine Bearing cavity pressure controlling device is for regulating the pressure in bearing bore 7, bearing bore 7 accommodates bearing 9, bearing 9, for being supported on fixed component 81 by rotatable parts 82, being sealed by labyrinth seal assemblies 71 between rotatable parts 82 and fixed component 81 and surrounds bearing bore 7.Pressure regulator comprise bearing bore 7 axle center ventilated port 72, communicate with axle center ventilated port 72 and be positioned at the air channel 830 (as shown in Figure 2) of the rotating shaft 820 of rotatable parts 82 and be arranged on the pressure regulator valve in air channel 830, pressure regulator valve as shown in Figure 2 is probably arranged on position 100 place.
As shown in Figure 2, pressure regulator valve comprises support, flexible thin object 1 and elastic connecting device.Support has multiple guide rod 61 and axle center supporting element 64, and axle center supporting element 64 is arranged at axle center, air channel 830, and multiple guide rod 61 outwards distributes radially centered by axle center supporting element 64, and each guide rod 61 configures this elastic connecting device.This elastic connecting device comprises slider 3 and elastic component 5, elastic component 5 one end is fixed and the other end connects slider 3, slider 3 can be round, such as steel ball, and the heart arranges penetration hole wherein, run through for guide rod 61, in addition as shown in Figure 4, hook 31 is set at its radially inner side, for hooking elastic component 5, hook 31 has elasticity breach 310, for interlocking with flexible thin object 1.Elastic component 5 can be helical spring, and it is enclosed within guide rod 61.The fixed end of elastic component 5 can be connected on axle center supporting element 64 or rotating shaft 820 inwall 2 on, also can be fixed on guide rod 61.The peripheral edge of flexible thin object 1 connects slider 3 and inner periphery is fixed on axle center supporting element 64, the rotating speed of rotating shaft 820 raises, slider 3 is outwards movement under the influence of centrifugal force, therefore flexible thin object 1 can raise with the rotating speed of rotating shaft 820 and outwards be guided by slider 3 and expand, and the elastic force that elastic component 5 provides the flexible thin object 1 making expansion to shrink.Guide rod 61 can be polished rod, and its radial inner end is fixed on axle center supporter 64, and its radial outer end can be connected on the inwall 2 of rotating shaft 820.Axle center supporter 64 can be a ring part or other shapes.Flexible thin object 1 can be the film possessing stronger bearing capacity, and its peripheral edge arranges multiple hole 11, so that connect with the hook 31 shown in Fig. 4.
As shown in Figure 1, high pressure air is introduced to bearing bore 7 from gas compressor, pressurized gas are introduced according to the direction of arrow A, pressurized gas part is by labyrinth seal assemblies 71, by throttling, expanding stops lubricating oil in bearing 9 place outwardly, thus forms sealing, the air pressure in bearing bore 7 and atm difference few, its air pressure exceeded is by axle center ventilated port 72 removal, and air-flow is according to the direction flowing shown in arrow B, C.Labyrinth seal assemblies 71 can be castor tooth black box, it bears larger pressure reduction, when not arranging modulating valve, along with the rotating speed of rotating shaft 820 increases, from the pressure just increase of the pressurized gas that gas compressor is introduced, and the pressure at axle center ventilated port 72 place and atm difference are few, therefore the pressure reduction that bears of labyrinth seal assemblies 71 is larger.
In Fig. 5 to Fig. 7, lines F represents the flow path of air-flow.As shown in Figure 5, when rotating shaft 820 non rotating or when rotating with comparatively low speed, the pulling force that slider 3 is subject to elasticity thing 5 remains on the end points place of the radially inner side of guide rod 61.When the rotating speed of rotating shaft 820 increases, due to centrifugal action, slider 3 is along guide rod 61 radial outward movement, and when centrifugal force is less, flexible thin object 1 expansionary effect thereupon taken up is also less, less for the increase of bearing bore 7 back pressure.When high engine speeds operates, slider 3 is subject to larger centrifugal force, and move towards away from axis direction, flexible thin object 1 is significantly pulled open thereupon, as shown in Figure 6, now runner position 100 major part that occupies in air channel 830 of flexible thin object 1, adds the back pressure of bearing bore 7, reduce the flow flowing through bearing bore 7, empty pressure difference in bearing bore 7 is compared when not having modulating valve and obviously reduces.Under Fig. 7 shows extreme working position, flexible thin object 1 launches completely, very big to the mobile obstacle after bearing cavity 7, only allows less air mass flow to pass through.
Be appreciated that by aforementioned explanation, can remain in a constant pressure differential range inside and outside bearing bore according to pressure regulator of the present utility model, even if when engine speed raises, bearing bore 7 bleed air pressure raises, and its back pressure correspondingly raises, therefore flow through air mass flow reduction in bearing bore 7.
Previous embodiment tool of the present utility model has the following advantages:
Even if after engine speed raises, axle center ventilated port 72 place air pressure flow also can not obviously raise, and therefore can not damage labyrinth seal assemblies 71, and reduce and expend high pressure and to obturage gas;
Along with engine speed raise time, modulating valve controls the rear back pressure of bearing bore 7 automatically, this makes the flow flowing through bearing bore 7 keep within the specific limits, pressure reduction before and after labyrinth seal assemblies 71 all there will not be larger change at all engine condition points, and the life-span of labyrinth seal assemblies 71 is significantly increased;
Because the flow flowing through bearing bore 7 reduces, the lubricating oil consumption that the air quantity that can reduce to flow to air pipeline is taken away;
By heightening bearing bore 7 internal pressure, the working efficiency of lubricating oil dump pump also can increase, and therefore can reduce discharge capacity, reduces the size of pump.
Although the utility model with preferred embodiment openly as above, but it is not for limiting the utility model, any those skilled in the art are not departing from spirit and scope of the present utility model, can make possible variation and amendment, such as slider 3 can be made of one with flexible thin object 1.Therefore, every content not departing from technical solutions of the utility model, any amendment done above embodiment according to technical spirit of the present utility model, equivalent variations and modification, all fall within protection domain that the utility model claim defines.
Claims (10)
1. Aero-engine Bearing cavity pressure controlling device, for regulating the pressure in bearing bore, described bearing bore accommodates bearing, described bearing is used for rotatable parts to be supported on fixed component, sealed by labyrinth seal assemblies between described rotatable parts and described fixed component and surround described bearing bore, this pressure regulator comprises the axle center ventilated port of described bearing bore, that communicate with described axle center ventilated port and be positioned at the air channel of the rotating shaft of described rotatable parts and be arranged on the pressure regulator valve in described air channel, it is characterized in that, described pressure regulator valve comprises flexible thin object, flexible thin object is arranged at the axle center in described air channel and is in contraction state, and can open gradually from described contraction state until open completely under centrifugal action with the rotating speed rising of described rotating shaft, reduce gradually to make the latus rectum in described air channel, and then make the pressure remained steady of described bearing bore.
2. Aero-engine Bearing cavity pressure controlling device as claimed in claim 1, it is characterized in that, described pressure regulator valve also comprises support and elastic connecting device, described support has multiple guide rod and axle center supporting element, described axle center supporting element is arranged at axle center, described air channel, described multiple guide rod outwards distributes radially centered by the supporting element of described axle center, each described guide rod configures described elastic connecting device, described elastic connecting device comprises slider and elastic component, described elastic component one end is fixedly installed and the other end connects described slider, the peripheral edge of described flexible thin object connects described slider and inner periphery is fixed on the supporting element of described axle center, described flexible thin object can raise with the rotating speed of described rotating shaft and outwards be guided by described slider and expand, and the elastic force that described elastic component provides the described flexible thin object making expansion to shrink.
3. Aero-engine Bearing cavity pressure controlling device as claimed in claim 2, is characterized in that, described slider is run through by described guide rod and can be free to slide on described guide rod.
4. Aero-engine Bearing cavity pressure controlling device as claimed in claim 2, it is characterized in that, described elastic component is the spring being sheathed on described guide rod, and one end described in it is fixed on the supporting element of described axle center.
5. Aero-engine Bearing cavity pressure controlling device as claimed in claim 2, it is characterized in that, the radial outer end of described guide rod connects the inwall of described rotating shaft.
6. modulating valve, for being arranged in the runner of the rotor that can rotate, it is characterized in that, described modulating valve comprises flexible thin object, flexible thin object is arranged at the axle center of described runner and is in contraction state, and can open gradually from described contraction state until open completely under centrifugal action with the rotating speed rising of described rotor, reduce gradually to make the latus rectum of described runner.
7. modulating valve as claimed in claim 6, it is characterized in that, described modulating valve also comprises support and elastic connecting device, described support has multiple guide rod and axle center supporting element, described multiple guide rod outwards distributes radially centered by the supporting element of described axle center, each described guide rod configures described elastic connecting device, described elastic connecting device comprises slider and elastic component, described elastic component one end is fixedly installed and the other end connects described slider, the peripheral edge of described flexible thin object connects described slider and inner periphery is fixed on the supporting element of described axle center, described flexible thin object can raise with the rotating speed of described rotor and outwards be guided by described slider and expand, and the elastic force that described elastic component provides the described flexible thin object making expansion to shrink.
8. modulating valve as claimed in claim 7, is characterized in that, described slider is run through by described guide rod and can be free to slide on described guide rod.
9. modulating valve as claimed in claim 7, it is characterized in that, described elastic component is the spring being sheathed on described guide rod, and one end described in it is fixed on the supporting element of described axle center.
10. modulating valve as claimed in claim 7, it is characterized in that, the radial outer end of described guide rod connects the inwall of described rotor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520217117.5U CN204922126U (en) | 2015-04-10 | 2015-04-10 | Aeroengine bearing bore pressure adjustment assembly and governing valve thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520217117.5U CN204922126U (en) | 2015-04-10 | 2015-04-10 | Aeroengine bearing bore pressure adjustment assembly and governing valve thereof |
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| Publication Number | Publication Date |
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| CN204922126U true CN204922126U (en) | 2015-12-30 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201520217117.5U Active CN204922126U (en) | 2015-04-10 | 2015-04-10 | Aeroengine bearing bore pressure adjustment assembly and governing valve thereof |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111320219A (en) * | 2020-04-18 | 2020-06-23 | 章志娟 | Ecological restoration device for removing pollutants from polluted drainage basin |
| CN114649896A (en) * | 2022-05-23 | 2022-06-21 | 南昌三瑞智能科技有限公司 | Flexible variable runner heat dissipation motor and driver |
| CN114837813A (en) * | 2021-02-02 | 2022-08-02 | 中国航发商用航空发动机有限责任公司 | Gas turbine engine and bearing cavity pressure adjusting device thereof |
| CN116412163A (en) * | 2023-05-26 | 2023-07-11 | 浙江巴腾动力系统有限公司 | Air inlet adjusting device of hydrogen circulating pump |
-
2015
- 2015-04-10 CN CN201520217117.5U patent/CN204922126U/en active Active
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111320219A (en) * | 2020-04-18 | 2020-06-23 | 章志娟 | Ecological restoration device for removing pollutants from polluted drainage basin |
| CN114837813A (en) * | 2021-02-02 | 2022-08-02 | 中国航发商用航空发动机有限责任公司 | Gas turbine engine and bearing cavity pressure adjusting device thereof |
| CN114837813B (en) * | 2021-02-02 | 2023-08-22 | 中国航发商用航空发动机有限责任公司 | Gas turbine engine and bearing cavity pressure adjusting device thereof |
| CN114649896A (en) * | 2022-05-23 | 2022-06-21 | 南昌三瑞智能科技有限公司 | Flexible variable runner heat dissipation motor and driver |
| US11777365B1 (en) | 2022-05-23 | 2023-10-03 | Nanchang Sanrui Intelligent Technology Co., Ltd | Motor with flexible variable flow channel |
| CN116412163A (en) * | 2023-05-26 | 2023-07-11 | 浙江巴腾动力系统有限公司 | Air inlet adjusting device of hydrogen circulating pump |
| CN116412163B (en) * | 2023-05-26 | 2023-09-12 | 浙江巴腾动力系统有限公司 | Air inlet adjusting device of hydrogen circulating pump |
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Legal Events
| Date | Code | Title | Description |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 200241 Minhang District Lianhua Road, Shanghai, No. 3998 Patentee after: China Hangfa commercial aviation engine limited liability company Address before: 200241 Minhang District Lianhua Road, Shanghai, No. 3998 Patentee before: AVIC Commercial Aircraft Engine Co.,Ltd. |
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| CP01 | Change in the name or title of a patent holder |