CN105424233B - Aero-engine centrifuges fly weight axial force measuring device and method - Google Patents
Aero-engine centrifuges fly weight axial force measuring device and method Download PDFInfo
- Publication number
- CN105424233B CN105424233B CN201510727950.9A CN201510727950A CN105424233B CN 105424233 B CN105424233 B CN 105424233B CN 201510727950 A CN201510727950 A CN 201510727950A CN 105424233 B CN105424233 B CN 105424233B
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- ball bearing
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- thrust ball
- shell
- boss
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- 238000000034 method Methods 0.000 title claims abstract description 11
- 238000005119 centrifugation Methods 0.000 claims abstract description 27
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 claims abstract description 23
- 230000007704 transition Effects 0.000 claims abstract description 10
- 239000010687 lubricating oil Substances 0.000 claims description 15
- 230000005540 biological transmission Effects 0.000 claims description 9
- 230000007246 mechanism Effects 0.000 claims description 9
- 210000003813 thumb Anatomy 0.000 claims description 4
- 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
- 238000005461 lubrication Methods 0.000 claims 1
- 238000006243 chemical reaction Methods 0.000 description 5
- 238000006073 displacement reaction Methods 0.000 description 4
- 238000009434 installation Methods 0.000 description 3
- 238000005259 measurement Methods 0.000 description 3
- 239000002184 metal Substances 0.000 description 3
- 238000005299 abrasion Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000000205 computational method Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000008450 motivation Effects 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
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Transmission Devices (AREA)
Abstract
The invention discloses a kind of aero-engine centrifugation fly weight axial force measuring device and method, the technical issues of for solving existing measuring device poor practicability.Technical solution be include short-range missile bar, miniature planar thrust ball bearing, dynamometry part, nut, pedestal, load cell and shell.The swing arm contact of short-range missile bar upper end and centrifugation fly weight block, lower end has boss and the gasket for transition of miniature planar thrust ball bearing one end to coordinate, the boss of the other end connection dynamometry part of miniature planar thrust ball bearing, the boss of dynamometry part coordinates with the lower gasket transition of miniature planar thrust ball bearing, dynamometry part is connected through a screw thread with shell, and fixes short-range missile bar by shell.Nut on dynamometry part is used for fixing shell, and dynamometry part is fixed by pedestal circular groove, and load cell is fixed between dynamometry part and pedestal.As a result of miniature planar thrust ball bearing, solves the technical issues of short-range missile bar is with swing arm friction damage system structure integrality, method is simple, at low cost.
Description
Technical field
The present invention relates to a kind of measuring device, more particularly to a kind of aero-engine centrifuges fly weight axial force measuring device.
It further relates to measure aero-engine centrifugation fly weight axial force method using this measuring device.
Background technology
Aero-engine fuel control system generally selects engine speed as controlled variable, and centrifugation fly weight is as rotating speed
Sensing element can be used for measuring the rotating speed of engine under various states.It can convert the variable quantity of rotating speed to the change of displacement
Change amount.
Referring to Fig.1.Document "《Aero-engine controls (first volume)》(publishing house of Northwestern Polytechnical University, in June, 2008 publish)
Chapter 3, the second section (page 98) " discloses a kind of aero-engine centrifugation fly weight axial force measuring device, including transmission mechanism 1,
Holder 2, guide rod 4, harmonizes spring 5 and swing arm 6 at centrifugation fly weight block 3.Centrifugation fly weight block 3 is fixed on holder 2, and engine is logical
Crossing transmission mechanism 1 drives holder 2 to rotate.Centrifugation fly weight block 3 can be swung out under the action of the centrifugal force around fulcrum, centrifuge fly weight block
3 swing arm 6 will make the guide rod being in contact with it 4 generate downward axial conversion power, axially conversion power and the installation to lower swing
Guide rod 4 is pushed to move in the spring force collective effect of the adjustment spring 5 of 4 lower part of guide rod.Therefore in one timing of spring force, corresponding hair
As soon as a certain rotating speed of motivation has corresponding axial conversion power, guide rod 4 has corresponding displacement, namely the variable quantity of rotating speed is converted into
Displacement variable.Therefore, the size of axial force is most important for determining the parameters such as spring sizes.
Document gives a kind of computational methods of axial conversion power.It is generated by calculating separately single centrifugal-block rotation
Centrifugal force and centrifugal-block barycenter to the distance of shaft, centrifugal force is decomposed and obtains axial conversion power.This numerical solution is ignored
The frictional force of centrifugal-block simultaneously assumes that centrifugal force point of resultant force is exactly barycenter, reduces computational solution precision, in addition, it is also needed
Guide rod displacement is introduced, the complexity of measurement is increased.It is referential with guide rod 4, centrifugation fly weight block 3 does circumference around guide rod 4
Movement, swing arm 6 are in direct contact friction with guide rod 4, can cause the abrasion of swing arm 6 and guide rod 4.Centrifugation is measured in engineering to fly
To solve the problems, such as swing arm 6 and guide rod 4 abrasion damage system structure integrality when weight axial force, it will usually on guide rod 4 and
One section of installation soft metal gasket that swing arm 6 contacts, and ensure speed measuring system essence by the way of replacing gasket often
It spends within the allowable range, but this method undoubtedly increases complexity and the experimentation cost of operation.
Invention content
In order to overcome the shortcomings of that existing aero-engine centrifuges fly weight axial force measuring device poor practicability, the present invention provides
A kind of aero-engine centrifugation fly weight axial force measuring device.The measuring device include short-range missile bar, miniature planar thrust ball bearing,
Dynamometry part, nut, pedestal, load cell and shell.The swing arm contact of short-range missile bar upper end and centrifugation fly weight block, lower end has convex
Platform and the gasket for transition of miniature planar thrust ball bearing one end coordinate, and the other end of miniature planar thrust ball bearing connects dynamometry part
Boss, the boss of dynamometry part and the lower gasket transition of miniature planar thrust ball bearing coordinate, and dynamometry part passes through screw thread with shell
Connection, and short-range missile bar is fixed by shell.Nut on dynamometry part is used for fixing shell；Dynamometry part by pedestal circular groove into
Row is fixed, and load cell is fixed between dynamometry part and pedestal, there is lubricating oil inlet on shell.The present invention need not be to centrifugation
The components such as fly weight block are modified, and reduce the interference to original device structure.As a result of miniature planar thrust ball bearing,
So that short-range missile bar is rotated with swing arm, solve short-range missile bar and swing arm friction, causes short-range missile bar to be worn with swing arm and damage
The problem of system structure integrality；Solve when measuring centrifugation fly weight axial force in engineering, need short-range missile bar and swing arm it
Between frequently replace problem complicated for operation caused by soft metal gasket, while also reducing experimental cost.
The present invention also provides measure aero-engine using this measuring device to centrifuge fly weight axial force method.
The technical solution adopted by the present invention to solve the technical problems is：A kind of aero-engine centrifugation fly weight axial force survey
Device is measured, its main feature is that including short-range missile bar 7, miniature planar thrust ball bearing 8, dynamometry part 9, nut 10, pedestal 11, force-measuring sensing
Device 12 and shell 13.The swing arm 6 that the upper end of the short-range missile bar 7 was used for and centrifuged fly weight block 3 contacts, and the lower end of short-range missile bar 7 has
Boss, boss and the gasket for transition of 8 one end of miniature planar thrust ball bearing coordinate, the other end of miniature planar thrust ball bearing 8
The boss of dynamometry part 9 is connected, the boss of dynamometry part 9 coordinates with the lower gasket transition of miniature planar thrust ball bearing 8, dynamometry part 9
It is connected through a screw thread with shell 13, and short-range missile bar 7 is fixed by shell 13.Nut 10 on dynamometry part 9 is used for fixing shell 13,
Dynamometry part 9 is fixed by 11 circular groove of pedestal, and load cell 12 is fixed between dynamometry part 9 and pedestal 11, shell
There is lubricating oil inlet 14 on 13.
The miniature planar thrust ball bearing 8, internal diameter are 4mm, and outer diameter is 10mm, and thickness is 4.5mm；Steel in ball bearing
Bulb diameter is 2mm, quantity eight.
The diameter of the dynamometry part 9 is 16mm.The diameter of the shell 13 is 20mm.
The diameter of the short-range missile bar 7 is 8mm, and polishing treatment is passed through in end face thereon.
The diameter of the lubricating oil inlet 14 is 2mm.
The load cell 12 is the unidirectional load cell of piezoelectric type.
It is a kind of that aero-engine centrifugation fly weight axial force method is measured using above-mentioned measuring device, its main feature is that using following
Step：
Step 1: the boss of 7 lower end of short-range missile bar is placed on the Upper gasket of miniature planar thrust ball bearing 8；It is miniature flat
The lower gasket of face thrust ball bearing 8 is placed on the boss of dynamometry part 9, and is connect with shell 13 by screw thread；Load cell
12 are placed between pedestal 11 and dynamometry part 9, and 7 axis of short-range missile bar is made to be overlapped with centrifugation 3 pivot center of fly weight block.
Step 2: the relative position of dynamometry part 9 and shell 13 is fixed by nut 10.
Step 3: injecting lubricating oil into shell 13 from lubricating oil inlet 14.
Step 4: zanjon bearing 15 is installed on outside transmission mechanism 1, movable support bracket 16, zanjon bearing 15 is stuck in bracket
In 16 circular groove.
Step 5: adjusting bracket 16, until swing arm 6 is contacted with short boss 7, rotation thumb screw 17 consolidates bracket 16
It is fixed.
Step 6: driving transmission mechanism 1, load cell 12 to export axial force using motor.
The aperture of the zanjon bearing 15 is 9mm, and outer diameter is 15mm, and width is 6mm.
The beneficial effects of the invention are as follows：The measuring device includes short-range missile bar, miniature planar thrust ball bearing, dynamometry part, spiral shell
Cap, pedestal, load cell and shell.Short-range missile bar upper end with centrifugation fly weight block swing arm contact, lower end have boss with it is miniature
The gasket for transition of thrust ball bearing with flat seat one end coordinates, the boss of the other end connection dynamometry part of miniature planar thrust ball bearing,
The boss of dynamometry part coordinates with the lower gasket transition of miniature planar thrust ball bearing, and dynamometry part is connected through a screw thread with shell, and
Short-range missile bar is fixed by shell.Nut on dynamometry part is used for fixing shell；Dynamometry part is fixed by pedestal circular groove,
Load cell is fixed between dynamometry part and pedestal, there is lubricating oil inlet on shell.The present invention need not be to centrifuging fly weight block
Equal components are modified, and reduce the interference to original device structure.As a result of miniature planar thrust ball bearing, make short-range missile
Bar can be rotated with swing arm, solve short-range missile bar and swing arm friction, and short-range missile bar is caused to wear damage system knot with swing arm
The problem of structure integrality；When solving measurement centrifugation fly weight axial force in engineering, need between short-range missile bar and swing arm frequently
Problem complicated for operation caused by soft metal gasket is replaced, while also reducing experimental cost.
It elaborates with reference to the accompanying drawings and detailed description to the present invention.
Description of the drawings
Fig. 1 is the structural schematic diagram of background technology aero-engine centrifugation fly weight axial force measuring device.
Fig. 2 is the structural schematic diagram of aero-engine centrifugation fly weight axial force measuring device of the present invention.
Fig. 3 is present example figure.
In figure, 1- transmission mechanisms, 2- holders, 3- centrifugation fly weight blocks, 4- guide rods, 5- adjustment springs, 6- swing arms, 7- short-range missiles
Bar, 8- miniature planar thrust ball bearings, 9- dynamometry parts, 10- nuts, 11- pedestals, 12- load cells, 13- shells, 14- profits
Lubricating oil inlet, 15- zanjon bearings, 16- brackets, 17- thumb screws, 18- chassis.
Specific implementation mode
Following embodiment is with reference to Fig. 2-3.
Aero-engine centrifugation fly weight axial force measuring device of the present invention includes short-range missile bar 7, miniature planar thrust ball bearing
8, dynamometry part 9, nut 10, pedestal 11, load cell 12, shell 13 and lubricating oil inlet 14.By the short of polishing treatment
The swing arm 6 that 7 upper end of guide rod was used for and centrifuged fly weight block 3 contacts.7 lower end of short-range missile bar has boss, boss to be stuck in miniature planar and push away
8 Upper gasket of power ball bearing.7 diameter 8mm of short-range missile bar.Miniature planar thrust ball bearing 8 internal diameter 4mm, outer diameter 10mm, thickness 4.5mm；
Steel ball size 2mm, quantity 8.8 other end of miniature planar thrust ball bearing connects the boss of dynamometry part 9, and boss is stuck in miniature flat
8 lower gasket of face thrust ball bearing.The diameter of the boss of 7 lower end boss of short-range missile bar and dynamometry part 9 and miniature planar thrust ball bearing 8
Internal diameter is equal.9 a diameter of 16mm of dynamometry part.There is screw thread outside dynamometry part 9, is attached by screw thread with shell 13, and pass through
Shell 13 fixes short-range missile bar 7.13 diameter 20mm of shell.Nut 10 on dynamometry part is for locking shell 13.The bottom of dynamometry part 9
It is placed in the circular groove of pedestal 11, load cell 12 is fixed between dynamometry part 9 and pedestal 11.Load cell 12 uses
The unidirectional load cell of piezoelectric type.13 outer surface of shell has lubricating oil inlet 14 for injecting lubricating oil to miniature planar thrust
Ball bearing 8 is lubricated.
Aero-engine is measured using above-mentioned measuring device and centrifuges fly weight axial force method.By the boss of short-range missile bar 7 with it is micro-
8 Upper gasket of type thrust ball bearing with flat seat connects；The boss of dynamometry part 9 is connect with 8 lower gasket of miniature planar thrust ball bearing, and is led to
Screw thread is crossed to connect with shell 13；Pedestal 11 is connect with dynamometry part 9 by load cell 12, and makes 7 axis of short-range missile bar and centrifugation
3 pivot center of fly weight block overlaps.The relative position of dynamometry part 9 and shell 13 is fixed in installation nut 10.It is noted from lubricating oil
Entrance 14 injects lubricating oil into shell 13.The measuring device assembled is placed on chassis 18.Zanjon bearing 15 is installed on transmission
Outside mechanism 1,15 aperture 9mm of zanjon bearing；Outer diameter 15mm；Width 6mm.Zanjon bearing 15 is stuck in mobile support by movable support bracket 16
In the circular groove of frame 16.Movable support bracket 16 is adjusted, until swing arm 6 is contacted with short boss 7, rotates thumb screw 17 by bracket
16 fix.Motor drives holder 2 to rotate by transmission mechanism 1, the axial force of centrifugation fly weight block 3 by swing wall act on it is short
Guide rod 7, due to the presence of miniature planar thrust ball bearing 8, short-range missile bar 7 can be rotated with holder 2.Miniature planar is acted on to push away
The axial force of power ball bearing 8 acts on measurement sensor 12 by dynamometry part 9, can be obtained axial force from load cell 12
Size.
Claims (8)
1. a kind of aero-engine centrifuges fly weight axial force measuring device, it is characterised in that：Including short-range missile bar (7), miniature planar
Thrust ball bearing (8), dynamometry part (9), nut (10), pedestal (11), load cell (12) and shell (13)；The short-range missile bar
(7) upper end is used for and centrifuges swing arm (6) contact of fly weight block (3), and the lower end of short-range missile bar (7) has boss, boss to be stuck in micro-
Type thrust ball bearing with flat seat (8) Upper gasket；The diameter and miniature planar of the boss of short-range missile bar (7) lower end boss and dynamometry part (9)
Thrust ball bearing (8) internal diameter is equal；Boss and the gasket for transition of miniature planar thrust ball bearing (8) one end coordinate, miniature planar
The boss of the other end connection dynamometry part (9) of thrust ball bearing (8), boss and the miniature planar thrust ball bearing of dynamometry part (9)
(8) lower gasket transition cooperation, dynamometry part (9) are connected through a screw thread with shell (13), and pass through the fixed short-range missile bar of shell (13)
(7)；Miniature planar thrust ball bearing enables short-range missile bar to be rotated with swing arm；Nut (10) on dynamometry part (9) is for fixing
Shell (13), dynamometry part (9) are fixed by pedestal (11) circular groove, and load cell (12) is fixed on dynamometry part (9)
Between pedestal (11), there is lubricating oil inlet (14) on shell (13).
2. aero-engine according to claim 1 centrifuges fly weight axial force measuring device, it is characterised in that：It is described miniature
Thrust ball bearing with flat seat (8), internal diameter are 4mm, and outer diameter is 10mm, and thickness is 4.5mm；Steel ball size is 2mm in ball bearing, number
Amount eight.
3. aero-engine according to claim 1 centrifuges fly weight axial force measuring device, it is characterised in that：The dynamometry
The diameter of part (9) is 16mm；The diameter of the shell (13) is 20mm.
4. aero-engine according to claim 1 centrifuges fly weight axial force measuring device, it is characterised in that：The short-range missile
The diameter of bar (7) is 8mm, and polishing treatment is passed through in end face thereon.
5. aero-engine according to claim 1 centrifuges fly weight axial force measuring device, it is characterised in that：The lubrication
The diameter of oily inlet (14) is 2mm.
6. aero-engine according to claim 1 centrifuges fly weight axial force measuring device, it is characterised in that：The dynamometry
Sensor (12) is the unidirectional load cell of piezoelectric type.
7. a kind of measuring aero-engine centrifugation fly weight axial force method using measuring device described in claim 1, feature exists
In using following steps：
Step 1: the boss of short-range missile bar (7) lower end is placed on the Upper gasket of miniature planar thrust ball bearing (8)；It is miniature flat
The lower gasket of face thrust ball bearing (8) is placed on the boss of dynamometry part (9), and is connect with shell (13) by screw thread；Dynamometry
Sensor (12) is placed between pedestal (11) and dynamometry part (9), and short-range missile bar (7) axis is made to be rotated with centrifugation fly weight block (3)
Axis overlaps；
Step 2: the relative position of dynamometry part (9) and shell (13) is fixed by nut (10)；
Step 3: injecting lubricating oil in from lubricating oil inlet (14) to shell (13)；
Step 4: zanjon bearing (15) is installed on to the outside of transmission mechanism (1), movable support bracket (16), by zanjon bearing (15)
It is stuck in the circular groove of bracket (16)；
Step 5: adjusting bracket (16), until swing arm (6) is contacted with short boss (7), will be held in the palm using rotation thumb screw (17)
Frame (16) is fixed；
Step 6: driving transmission mechanism (1), load cell (12) to export axial force using motor.
8. according to the method described in claim 7, it is characterized in that：The aperture of the zanjon bearing (15) is 9mm, and outer diameter is
15mm, width are 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 CN105424233A (en) | 2016-03-23 |
| CN105424233B true CN105424233B (en) | 2018-08-17 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510727950.9A Expired - Fee Related CN105424233B (en) | 2015-10-30 | 2015-10-30 | Aero-engine centrifuges fly weight axial force measuring device and method |
Country Status (1)
| Country | Link |
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| CN (1) | CN105424233B (en) |
Families Citing this family (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 |
| CN107764552B (en) * | 2017-09-04 | 2023-05-16 | 西安工业大学 | Centrifugal counterweight test device |
| 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 |
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 |
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| CN105424233A (en) | 2016-03-23 |
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