CN104793007A - Device for measuring rotation speed of aviation engine rotor - Google Patents
Device for measuring rotation speed of aviation engine rotor Download PDFInfo
- Publication number
- CN104793007A CN104793007A CN201510177972.2A CN201510177972A CN104793007A CN 104793007 A CN104793007 A CN 104793007A CN 201510177972 A CN201510177972 A CN 201510177972A CN 104793007 A CN104793007 A CN 104793007A
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- CN
- China
- Prior art keywords
- gear shaft
- supercharge pump
- rotation speed
- aviation engine
- booster pump
- 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.)
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- Rotary Pumps (AREA)
Abstract
The invention relates to a device for measuring the rotation speed of an aviation engine rotor. The device is mounted on the booster pump of the fuel control system of an aviation engine. The device comprises a gear shaft (7) connected with the power input shaft (1) of the booster pump. The gear shaft (7) drives the booster pump to rotate. The gear shaft (7) is fixedly mounted on the shell (9) of the booster pump through a bearing (8) and a support (5) for fixing the bearing (8). The gear shaft (7) is provided with a gear plate (10) matched with a magnetoelectric tachometric transducer (6). The magnetoelectric tachometric transducer (6) for measuring the rotation speed of the gear plate (10) is mounted on the shell (9) of the booster pump and mounted on the lateral side of the outer periphery of the gear plate (10). Compared with the prior art, the device has the advantage that the rotation speed of the aviation engine rotor can be measured by using existing transducers without being affected by aviation engine mounting and temperature.
Description
Technical field
The present invention is a kind of device for aeroengine rotor tachometric survey, belongs to field of measuring technique.
Background technology
Generally, aeroengine rotor rotating speed directly measures on the engine.Because the rotating speed of engine is comparatively large, particularly medium and small aeromotor maximum (top) speed is more than 50000r/min, and environment temperature is high, directly measures rotating speed on the engine, by the impact of space, rotating speed and temperature, increases the difficulty of engine design on the one hand; The difficulty too increasing the high rotating speed of development measurement, high-temperature speed probe on the other hand.
Summary of the invention
The present invention designs for above-mentioned problems of the prior art just and provides a kind of device for aeroengine rotor tachometric survey, its objective is and can adopt existing sensor measurement aeroengine rotor rotating speed, and not by the installation of aeromotor, the impact of temperature.
The object of the invention is to be achieved through the following technical solutions:
This kind is for the device of aeroengine rotor tachometric survey, it is characterized in that: this device is arranged on the supercharge pump of aeromotor fuel control system, this device comprises and a gear shaft (7) be connected with supercharge pump power input shaft (1), gear shaft (7) drives supercharge pump to rotate, gear shaft (7) is fixedly mounted on the housing (9) of supercharge pump by the support (5) of bearing (8) and solid bearing (8), the toothed disc (10) that gear shaft (7) coordinates with magnetoelectric tachometric transducer (6) with one, at the magnetoelectric tachometric transducer (6) of the upper installation one of the housing (9) of supercharge pump for prototype gear dish (10) rotating speed, magnetoelectric tachometric transducer (6) is arranged on the side of toothed disc (10) excircle.
The number of teeth on toothed disc (10) excircle is 20 ~ 22.
In aeroengine control system, the supercharge pump of aeromotor fuel control system is arranged on the transmission casing of engine, for fuel regulator carries out initial pressurization, relative to the assembly of other fuel control system, this installation site operating ambient temperature is lower, the low also relatively good measurement of supercharge pump input speed, this rotating speed also can be indirect, react aeroengine rotor rotating speed exactly, and supercharge pump self structure allows, so measurement mechanism is combined with supercharge pump by technical solution of the present invention, make supercharge pump can realize its intrinsic functional characteristic, too increase the function measuring rotating speed simultaneously.
In the structural design of measurement mechanism, the toothed disc (10) that will coordinate with magnetoelectric tachometric transducer (6) is one-body molded with the gear shaft (7) of supercharge pump, so just can pass through the rotating speed that toothed disc (10) directly measures gear shaft (7), make structure space compact simultaneously.During pump work, toothed disc (10) is with gear shaft (7) High Rotation Speed, the magnetoelectric tachometric transducer (6) that supercharge pump is installed produces the electric signal of near sinusoidal ripple by the toothed disc (10) gathered, and realizes the measurement to aeroengine rotor rotating speed.
Advantage of the present invention is the difficult point and the deficiency that overcome prior art, can realize the existing function of supercharge pump; Indirect inspection engine speed can be realized again; And reduce engine and high rotating speed, high-temperature speed probe develop difficulty and cost; Have reliability high, the life-span is long, and cost is low, the feature that development difficulty is relatively low.
Accompanying drawing explanation
Fig. 1 is the structural representation of apparatus of the present invention
Fig. 2 is A-A cut-open view in Fig. 1
Embodiment
Below with reference to drawings and Examples, technical solution of the present invention is further described:
Shown in accompanying drawing 1 ~ 2, this kind is for the device of aeroengine rotor tachometric survey, it is characterized in that: this device is arranged on the supercharge pump of aeromotor fuel control system, this device comprises and a gear shaft 7 be connected with supercharge pump power input shaft 1, gear shaft 7 drives supercharge pump to rotate, gear shaft 7 is fixedly mounted on the housing 9 of supercharge pump by the support 5 of bearing 8 and solid bearing 8, support 5 is spacing by copper bearing 4, fixed by elastic washer 3 and transmission end cap 2 outside copper bearing 4, the toothed disc 10 that gear shaft 7 coordinates with magnetoelectric tachometric transducer 6 with one, the number of teeth on toothed disc 10 excircle is 20 ~ 22, the housing 9 of supercharge pump installs a magnetoelectric tachometric transducer 6 for prototype gear dish 10 rotating speed, magnetoelectric tachometric transducer 6 is arranged on the side of toothed disc 10 excircle.During work, by power input shaft 1 driven gear axle 7 High Rotation Speed, by magnetoelectric tachometric transducer 6 rotating speed.
Compared with prior art, technical solution of the present invention can adopt existing sensor measurement aeroengine rotor rotating speed, and not by the installation of aeromotor, the impact of temperature.
Claims (2)
1. the device for aeroengine rotor tachometric survey, it is characterized in that: this device is arranged on the supercharge pump of aeromotor fuel control system, this device comprises and a gear shaft (7) be connected with supercharge pump power input shaft (1), gear shaft (7) drives supercharge pump to rotate, gear shaft (7) is fixedly mounted on the housing (9) of supercharge pump by the support (5) of bearing (8) and solid bearing (8), the toothed disc (10) that gear shaft (7) coordinates with magnetoelectric tachometric transducer (6) with one, at the magnetoelectric tachometric transducer (6) of the upper installation one of the housing (9) of supercharge pump for prototype gear dish (10) rotating speed, magnetoelectric tachometric transducer (6) is arranged on the side of toothed disc (10) excircle.
2. the device for aeroengine rotor tachometric survey according to claim 1, is characterized in that: the number of teeth on toothed disc (10) excircle is 20 ~ 22.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510177972.2A CN104793007A (en) | 2015-04-15 | 2015-04-15 | Device for measuring rotation speed of aviation engine rotor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510177972.2A CN104793007A (en) | 2015-04-15 | 2015-04-15 | Device for measuring rotation speed of aviation engine rotor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104793007A true CN104793007A (en) | 2015-07-22 |
Family
ID=53557983
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510177972.2A Pending CN104793007A (en) | 2015-04-15 | 2015-04-15 | Device for measuring rotation speed of aviation engine rotor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104793007A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108089023A (en) * | 2017-12-13 | 2018-05-29 | 陕西宝成航空仪表有限责任公司 | Screening arrangement of the fine module gear rotational speed counting close to switch |
| CN108120848A (en) * | 2017-12-12 | 2018-06-05 | 中国航发动力股份有限公司 | A kind of aero-engine centrifuges sensor input speed test device |
| CN110940827A (en) * | 2019-10-30 | 2020-03-31 | 北京遥测技术研究所 | Magnetoelectric revolution speed transducer suitable for large-interval measurement |
| CN113533773A (en) * | 2021-08-17 | 2021-10-22 | 中国航发贵阳发动机设计研究所 | Aircraft engine fan rotational speed measuring device |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108120848A (en) * | 2017-12-12 | 2018-06-05 | 中国航发动力股份有限公司 | A kind of aero-engine centrifuges sensor input speed test device |
| CN108089023A (en) * | 2017-12-13 | 2018-05-29 | 陕西宝成航空仪表有限责任公司 | Screening arrangement of the fine module gear rotational speed counting close to switch |
| CN110940827A (en) * | 2019-10-30 | 2020-03-31 | 北京遥测技术研究所 | Magnetoelectric revolution speed transducer suitable for large-interval measurement |
| CN110940827B (en) * | 2019-10-30 | 2022-02-01 | 北京遥测技术研究所 | Magnetoelectric revolution speed transducer suitable for large-interval measurement |
| CN113533773A (en) * | 2021-08-17 | 2021-10-22 | 中国航发贵阳发动机设计研究所 | Aircraft engine fan rotational speed measuring device |
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| PB01 | Publication | ||
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| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20150722 |