CN105424233A - Device and method used for measuring axial aeroengine centrifugation flying weight force - Google Patents
Device and method used for measuring axial aeroengine centrifugation flying weight force Download PDFInfo
- Publication number
- CN105424233A CN105424233A CN201510727950.9A CN201510727950A CN105424233A CN 105424233 A CN105424233 A CN 105424233A CN 201510727950 A CN201510727950 A CN 201510727950A CN 105424233 A CN105424233 A CN 105424233A
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- Prior art keywords
- ball bearing
- boss
- short
- shell
- dynamometry part
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- 238000000034 method Methods 0.000 title claims abstract description 11
- 238000005119 centrifugation Methods 0.000 title abstract 3
- 238000005259 measurement Methods 0.000 claims abstract description 20
- 230000007704 transition Effects 0.000 claims abstract description 10
- 239000010687 lubricating oil Substances 0.000 claims description 16
- 229910000831 Steel Inorganic materials 0.000 claims description 3
- 238000005498 polishing Methods 0.000 claims description 3
- 239000010959 steel Substances 0.000 claims description 3
- 238000006243 chemical reaction Methods 0.000 description 4
- 238000006073 displacement reaction Methods 0.000 description 4
- 239000002184 metal Substances 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L1/00—Measuring force or stress, in general
- G01L1/16—Measuring force or stress, in general using properties of piezoelectric devices
Abstract
The invention discloses a device and a method used for measuring axial aeroengine centrifugation flying weight force and solves a technical problem of poor practicality existing in a measurement device in the prior art. The device is characterized by comprising a short guide rod, a micro planar push force ball bearing, a force measurement member, a nut cap, a foundation, a force measurement sensor and a casing, wherein the upper end of the short guide rod contacts a swing arm of a centrifugation flying weight block, the lower end of the short guide rod is provided with a boss in transition matching with a pad at one end of the micro planar push force ball bearing, the other end of the micro planar push force ball bearing is connected with a boss of the force measurement member, the boss of the force measurement member is in transition matching with a lower pad of the micro planar push force ball bearing, the force measurement member is in thread connection with the casing, the short guide rod is fixed through the casing, the nut cap on the force measurement member is used for fixing the casing, the force measurement member is fixed through a circular groove of the foundation, and the force measurement sensor is fixed between the force measurement member and the foundation. The micro planar push force ball bearing is employed, the technical problem of frictional damage of the short guide rod and the swing arm to system structure integrity is solved, the method is simple, and cost is low.
Description
Technical field
The present invention relates to a kind of measurement mechanism, particularly the centrifugal fly weight axial force measuring device of a kind of aeromotor.Also relate to and adopt this measurement mechanism to measure aeromotor centrifugal fly weight axial force method.
Background technology
Aeromotor fuel control system selects engine speed as controlled variable usually, and centrifugal fly weight, as tachosensor, can be used for measuring the rotating speed of engine under various state.The variable quantity of rotating speed can be converted into the variable quantity of displacement by it.
With reference to Fig. 1.Document " " aeroengine control (first volume) " (publishing house of Northwestern Polytechnical University; in June, 2008 publishes) chapter 3 second section (98 pages) " discloses the centrifugal fly weight axial force measuring device of a kind of aeromotor, comprises gear train 1, support 2, centrifugal fly weight block 3, guide rod 4, adjustment spring 5 and swing arm 6.Centrifugal fly weight block 3 is fixed on support 2, and engine drives support 2 to rotate by gear train 1.Centrifugal fly weight block 3 outwards can swing around fulcrum under centrifugal action, the swing arm 6 of centrifugal fly weight block 3 will to lower swing, make the guide rod 4 be in contact with it produce downward axis conversion power, this axial conversion power promotes guide rod 4 with the spring force acting in conjunction of the adjustment spring 5 being arranged on guide rod 4 bottom and moves.Therefore in spring force one timing, a certain rotating speed of corresponding engine has a corresponding axial conversion power, and guide rod 4 just has corresponding displacement, also namely the variable quantity of rotating speed is converted into displacement variable.Therefore, the size of axial force is for determining that the parameters such as spring sizes are most important.
Document gives a kind of computing method of axial conversion power.It rotates the centrifugal force and centrifugal-block barycenter that produce to the distance of rotating shaft by calculating single centrifugal-block respectively, is decomposed by centrifugal force and obtains the axial power that converts.This numerical solution have ignored the friction force of centrifugal-block and supposes that centrifugal force point of resultant force is exactly barycenter, reduces computational solution precision, and in addition, it also needs to introduce guide rod displacement, adds the complexity of measurement.With guide rod 4 for reference frame, centrifugal fly weight block 3 moves in a circle around guide rod 4, and swing arm 6 and guide rod 4 directly contact friction, can cause the wearing and tearing of swing arm 6 and guide rod 4.Be solve swing arm 6 to wear and tear with guide rod 4 and damage the problem of system architecture integrality when measuring centrifugal fly weight axial force in engineering; usual meeting one section of contacting with swing arm 6 on guide rod 4 installs soft metal pad; and adopt the mode often changing pad to ensure that speed measuring system precision is in allowed band, but this method adds complicacy and the experimentation cost of operation undoubtedly.
Summary of the invention
In order to overcome the deficiency of existing aeromotor centrifugal fly weight axial force measuring device poor practicability, the invention provides the centrifugal fly weight axial force measuring device of a kind of aeromotor.This measurement mechanism comprises short-range missile bar, miniature planar thrust ball bearing, dynamometry part, nut, base, force cell and shell.Short-range missile bar upper end contacts with the swing arm of centrifugal fly weight block, lower end has boss to coordinate with the gasket for transition of miniature planar thrust ball bearing one end, the other end of miniature planar thrust ball bearing connects the boss of dynamometry part, the boss of dynamometry part and the lower gasket transition fit of miniature planar thrust ball bearing, dynamometry part and shell are threaded connection, and fix short-range missile bar by shell.Nut on dynamometry part is used for fixed housing; Dynamometry part is fixed by base circular groove, and force cell is fixed between dynamometry part and base, shell has lubricating oil inlet.The present invention does not need to change components and parts such as centrifugal fly weight blocks, reduces the interference to original device structure.Owing to have employed miniature planar thrust ball bearing, short-range missile bar is rotated with swing arm, solve short-range missile bar and swing arm friction, cause short-range missile bar and swing arm to wear and tear and damage the problem of system architecture integrality; Solve when engineering measuring centrifugal fly weight axial force, need the problem frequently changing the complicated operation that soft metal pad causes between short-range missile bar and swing arm, also reduce experimental cost simultaneously.
The present invention also provides and adopts this measurement mechanism to measure aeromotor centrifugal fly weight axial force method.
The technical solution adopted for the present invention to solve the technical problems is: the centrifugal fly weight axial force measuring device of a kind of aeromotor, is characterized in comprising short-range missile bar 7, miniature planar thrust ball bearing 8, dynamometry part 9, nut 10, base 11, force cell 12 and shell 13.The upper end of described short-range missile bar 7 is used for contacting with the swing arm 6 of centrifugal fly weight block 3, there is boss the lower end of short-range missile bar 7, boss coordinates with the gasket for transition of miniature planar thrust ball bearing 8 one end, the other end of miniature planar thrust ball bearing 8 connects the boss of dynamometry part 9, the boss of dynamometry part 9 and the lower gasket transition fit of miniature planar thrust ball bearing 8, dynamometry part 9 and shell 13 are threaded connection, and fix short-range missile bar 7 by shell 13.Nut 10 on dynamometry part 9 is for fixed housing 13, and dynamometry part 9 is fixed by base 11 circular groove, and force cell 12 is fixed between dynamometry part 9 and base 11, shell 13 has lubricating oil inlet 14.
Described miniature planar thrust ball bearing 8, its internal diameter is 4mm, and external diameter is 10mm, and thickness is 4.5mm; In ball bearing, steel ball size is 2mm, quantity eight.
The diameter of described dynamometry part 9 is 16mm.The diameter of described shell 13 is 20mm.
The diameter of described short-range missile bar 7 is 8mm, and its upper surface is through polishing.
The diameter of described lubricating oil inlet 14 is 2mm.
Described force cell 12 is the unidirectional force cells of piezoelectric type.
Aeromotor centrifugal fly weight axial force method measured by the above-mentioned measurement mechanism of a kind of employing, is characterized in adopting following steps:
Step one, the boss of short-range missile bar 7 lower end is placed on the Upper gasket of miniature planar thrust ball bearing 8; The lower gasket of miniature planar thrust ball bearing 8 is placed on the boss of dynamometry part 9, and is connected with shell 13 by screw thread; Force cell 12 is placed between base 11 and dynamometry part 9, and short-range missile bar 7 axis is overlapped with centrifugal fly weight block 3 pivot center.
Step 2, to be fixed by the relative position of nut 10 pairs of dynamometry parts 9 and shell 13.
Step 3, in shell 13, inject lubricating oil from lubricating oil inlet 14.
Step 4, be installed on outside gear train 1 by zanjon bearing 15, movable support bracket 16, is stuck in zanjon bearing 15 in the circular groove of bracket 16.
Step 5, bracket 16, until swing arm 6 contacts with short boss 7, rotate wing screw 17 and fixed by bracket 16.
Step 6, use motor drive gear train 1, and force cell 12 exports axial force.
The aperture of described zanjon bearing 15 is 9mm, and external diameter is 15mm, and width is 6mm.
The invention has the beneficial effects as follows: this measurement mechanism comprises short-range missile bar, miniature planar thrust ball bearing, dynamometry part, nut, base, force cell and shell.Short-range missile bar upper end contacts with the swing arm of centrifugal fly weight block, lower end has boss to coordinate with the gasket for transition of miniature planar thrust ball bearing one end, the other end of miniature planar thrust ball bearing connects the boss of dynamometry part, the boss of dynamometry part and the lower gasket transition fit of miniature planar thrust ball bearing, dynamometry part and shell are threaded connection, and fix short-range missile bar by shell.Nut on dynamometry part is used for fixed housing; Dynamometry part is fixed by base circular groove, and force cell is fixed between dynamometry part and base, shell has lubricating oil inlet.The present invention does not need to change components and parts such as centrifugal fly weight blocks, reduces the interference to original device structure.Owing to have employed miniature planar thrust ball bearing, short-range missile bar is rotated with swing arm, solve short-range missile bar and swing arm friction, cause short-range missile bar and swing arm to wear and tear and damage the problem of system architecture integrality; Solve when engineering measuring centrifugal fly weight axial force, need the problem frequently changing the complicated operation that soft metal pad causes between short-range missile bar and swing arm, also reduce experimental cost simultaneously.
Below in conjunction with the drawings and specific embodiments, the present invention is elaborated.
Accompanying drawing explanation
Fig. 1 is the structural representation of the centrifugal fly weight axial force measuring device of background technology aeromotor.
Fig. 2 is the structural representation of the centrifugal fly weight axial force measuring device of aeromotor of the present invention.
Fig. 3 is instance graph of the present invention.
In figure, 1-gear train, 2-support, the centrifugal fly weight block of 3-, 4-guide rod, 5-adjustment spring, 6-swing arm, 7-short-range missile bar, 8-miniature planar thrust ball bearing, 9-dynamometry part, 10-nut, 11-base, 12-force cell, 13-shell, 14-lubricating oil inlet, 15-zanjon bearing, 16-bracket, 17-wing screw, 18-underframe.
Embodiment
Following examples are with reference to Fig. 2-3.
The centrifugal fly weight axial force measuring device of aeromotor of the present invention comprises short-range missile bar 7, miniature planar thrust ball bearing 8, dynamometry part 9, nut 10, base 11, force cell 12, shell 13 and lubricating oil inlet 14.Be used for through short-range missile bar 7 upper end of polishing contacting with the swing arm 6 of centrifugal fly weight block 3.There is boss short-range missile bar 7 lower end, and boss is stuck in miniature planar thrust ball bearing 8 Upper gasket.Short-range missile bar 7 diameter 8mm.Miniature planar thrust ball bearing 8 internal diameter 4mm, external diameter 10mm, thickness 4.5mm; Steel ball size 2mm, quantity 8.Miniature planar thrust ball bearing 8 other end connects the boss of dynamometry part 9, and boss is stuck in miniature planar thrust ball bearing 8 lower gasket.The diameter of the boss of short-range missile bar 7 lower end boss and dynamometry part 9 is equal with miniature planar thrust ball bearing 8 internal diameter.Dynamometry part 9 diameter is 16mm.There is screw thread dynamometry part 9 outside, is connected by screw thread with shell 13, and fixes short-range missile bar 7 by shell 13.Shell 13 diameter 20mm.Nut 10 on dynamometry part is for locking shell 13.The bottom of dynamometry part 9 is placed in the circular groove of base 11, and force cell 12 is fixed between dynamometry part 9 and base 11.Force cell 12 adopts the unidirectional force cell of piezoelectric type.Shell 13 outside surface has lubricating oil inlet 14 to lubricate miniature planar thrust ball bearing 8 for injecting lubricating oil.
Above-mentioned measurement mechanism is adopted to measure aeromotor centrifugal fly weight axial force method.The boss of short-range missile bar 7 is connected with miniature planar thrust ball bearing 8 Upper gasket; The boss of dynamometry part 9 is connected with miniature planar thrust ball bearing 8 lower gasket, and is connected with shell 13 by screw thread; Base 11 is connected by force cell 12 with dynamometry part 9, and short-range missile bar 7 axis is overlapped with centrifugal fly weight block 3 pivot center.The relative position installing nut 10 pairs of dynamometry parts 9 and shell 13 is fixed.In shell 13, lubricating oil is injected from lubricating oil inlet 14.The measurement mechanism assembled is placed on underframe 18.Zanjon bearing 15 is installed on outside gear train 1, zanjon bearing 15 aperture 9mm; External diameter 15mm; Width 6mm.Movable support bracket 16, is stuck in zanjon bearing 15 in the circular groove of movable support bracket 16.Regulate movable support bracket 16, until swing arm 6 contacts with short boss 7, rotate wing screw 17 and bracket 16 is fixed.Motor drives support 2 to rotate by gear train 1, and the axial force of centrifugal fly weight block 3 acts on short-range missile bar 7 by swinging wall, and due to the existence of miniature planar thrust ball bearing 8, short-range missile bar 7 can rotate with support 2.The axial force acting on miniature planar thrust ball bearing 8 acts on survey sensor 12 by dynamometry part 9, can obtain the size of axial force from force cell 12.
Claims (8)
1. the centrifugal fly weight axial force measuring device of aeromotor, is characterized in that: comprise short-range missile bar (7), miniature planar thrust ball bearing (8), dynamometry part (9), nut (10), base (11), force cell (12) and shell (13); The upper end of described short-range missile bar (7) is used for contacting with the swing arm (6) of centrifugal fly weight block (3), there is boss the lower end of short-range missile bar (7), boss coordinates with the gasket for transition of miniature planar thrust ball bearing (8) one end, the other end of miniature planar thrust ball bearing (8) connects the boss of dynamometry part (9), the boss of dynamometry part (9) and the lower gasket transition fit of miniature planar thrust ball bearing (8), dynamometry part (9) and shell (13) are threaded connection, and by the fixing short-range missile bar (7) of shell (13); Nut (10) on dynamometry part (9) is for fixed housing (13), dynamometry part (9) is fixed by base (11) circular groove, force cell (12) is fixed between dynamometry part (9) and base (11), shell (13) has lubricating oil inlet (14).
2. the centrifugal fly weight axial force measuring device of aeromotor according to claim 1, is characterized in that: described miniature planar thrust ball bearing (8), and its internal diameter is 4mm, and external diameter is 10mm, and thickness is 4.5mm; In ball bearing, steel ball size is 2mm, quantity eight.
3. the centrifugal fly weight axial force measuring device of aeromotor according to claim 1, is characterized in that: the diameter of described dynamometry part (9) is 16mm; The diameter of described shell (13) is 20mm.
4. the centrifugal fly weight axial force measuring device of aeromotor according to claim 1, is characterized in that: the diameter of described short-range missile bar (7) is 8mm, and its upper surface is through polishing.
5. the centrifugal fly weight axial force measuring device of aeromotor according to claim 1, is characterized in that: the diameter of described lubricating oil inlet (14) is 2mm.
6. the centrifugal fly weight axial force measuring device of aeromotor according to claim 1, is characterized in that: described force cell (12) is the unidirectional force cell of piezoelectric type.
7. adopt measurement mechanism described in claim 1 to measure an aeromotor centrifugal fly weight axial force method, it is characterized in that adopting following steps:
Step one, the boss of short-range missile bar (7) lower end is placed on the Upper gasket of miniature planar thrust ball bearing (8); The lower gasket of miniature planar thrust ball bearing (8) is placed on the boss of dynamometry part (9), and is connected with shell (13) by screw thread; Force cell (12) is placed between base (11) and dynamometry part (9), and short-range missile bar (7) axis is overlapped with centrifugal fly weight block (3) pivot center;
Step 2, to be fixed by the relative position of nut (10) to dynamometry part (9) and shell (13);
Step 3, from lubricating oil inlet (14) to shell (13) in inject lubricating oil;
Step 4, zanjon bearing (15) is installed on the outside of gear train (1), movable support bracket (16), is stuck in the circular groove of bracket (16) by zanjon bearing (15);
Step 5, bracket (16), until swing arm (6) contacts with short boss (7), adopt rotation wing screw (17) to be fixed by bracket (16);
Step 6, use motor drive gear train (1), and force cell (12) exports axial force.
8. method according to claim 7, is characterized in that: the aperture of described zanjon bearing (15) is 9mm, and external diameter is 15mm, and width is 6mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510727950.9A CN105424233B (en) | 2015-10-30 | 2015-10-30 | Aero-engine centrifuges fly weight axial force measuring device and method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510727950.9A CN105424233B (en) | 2015-10-30 | 2015-10-30 | Aero-engine centrifuges fly weight axial force measuring device and method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105424233A true CN105424233A (en) | 2016-03-23 |
| CN105424233B CN105424233B (en) | 2018-08-17 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201510727950.9A Expired - Fee Related CN105424233B (en) | 2015-10-30 | 2015-10-30 | Aero-engine centrifuges fly weight axial force measuring device and method |
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| Country | Link |
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| CN (1) | CN105424233B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106595934A (en) * | 2016-12-08 | 2017-04-26 | 西北工业大学 | Device and method of measuring axial force of vertical cylinder vibration eliminating-type centrifugal fly weight |
| CN107478371A (en) * | 2017-08-04 | 2017-12-15 | 西北工业大学 | A kind of vertical cylinder weakening formula centrifuges fly weight axial force measuring device |
| CN107764552A (en) * | 2017-09-04 | 2018-03-06 | 西安工业大学 | Governor weight experimental rig |
| CN111964837A (en) * | 2020-07-29 | 2020-11-20 | 中国航发北京航科发动机控制系统科技有限公司 | Device and method for testing centrifugal flyweight and rotating speed of aircraft engine |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1409839A (en) * | 1920-11-01 | 1922-03-14 | William A Erner | Speed indicator |
| GB617507A (en) * | 1944-06-27 | 1949-02-08 | Michel Gravina | Improvements relating to centrifugal clutches |
| JPS5333275B2 (en) * | 1975-03-08 | 1978-09-13 | ||
| JPS5513310B2 (en) * | 1973-03-05 | 1980-04-08 | ||
| DE2847248C2 (en) * | 1978-10-31 | 1986-12-04 | Robert Bosch Gmbh, 7000 Stuttgart | Speed controller for a fuel injection pump of an internal combustion engine |
| FR2612310A1 (en) * | 1987-03-12 | 1988-09-16 | Menissier Pierre | Centrifugal device with disengagement |
-
2015
- 2015-10-30 CN CN201510727950.9A patent/CN105424233B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1409839A (en) * | 1920-11-01 | 1922-03-14 | William A Erner | Speed indicator |
| GB617507A (en) * | 1944-06-27 | 1949-02-08 | Michel Gravina | Improvements relating to centrifugal clutches |
| JPS5513310B2 (en) * | 1973-03-05 | 1980-04-08 | ||
| JPS5333275B2 (en) * | 1975-03-08 | 1978-09-13 | ||
| DE2847248C2 (en) * | 1978-10-31 | 1986-12-04 | Robert Bosch Gmbh, 7000 Stuttgart | Speed controller for a fuel injection pump of an internal combustion engine |
| FR2612310A1 (en) * | 1987-03-12 | 1988-09-16 | Menissier Pierre | Centrifugal device with disengagement |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106595934A (en) * | 2016-12-08 | 2017-04-26 | 西北工业大学 | Device and method of measuring axial force of vertical cylinder vibration eliminating-type centrifugal fly weight |
| CN107478371A (en) * | 2017-08-04 | 2017-12-15 | 西北工业大学 | A kind of vertical cylinder weakening formula centrifuges fly weight axial force measuring device |
| CN107764552A (en) * | 2017-09-04 | 2018-03-06 | 西安工业大学 | Governor weight experimental rig |
| CN107764552B (en) * | 2017-09-04 | 2023-05-16 | 西安工业大学 | Centrifugal counterweight test device |
| CN111964837A (en) * | 2020-07-29 | 2020-11-20 | 中国航发北京航科发动机控制系统科技有限公司 | Device and method for testing centrifugal flyweight and rotating speed of aircraft engine |
| CN111964837B (en) * | 2020-07-29 | 2022-05-13 | 中国航发北京航科发动机控制系统科技有限公司 | Device and method for testing centrifugal flyweight and rotating speed of aircraft engine |
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| Publication number | Publication date |
|---|---|
| CN105424233B (en) | 2018-08-17 |
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