CN106197927A - A kind of aero-engine ratchet impact strength test device - Google Patents
A kind of aero-engine ratchet impact strength test device Download PDFInfo
- Publication number
- CN106197927A CN106197927A CN201610485852.3A CN201610485852A CN106197927A CN 106197927 A CN106197927 A CN 106197927A CN 201610485852 A CN201610485852 A CN 201610485852A CN 106197927 A CN106197927 A CN 106197927A
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- China
- Prior art keywords
- ratchet
- impact strength
- aero
- strength test
- seat
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/08—Shock-testing
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The present invention relates to a kind of aero-engine ratchet impact strength test device, fix seat, connecting pin and acceleration transducer including shock machine, impact tup, ratchet；Described shock machine has base and tup seat, impact tup is fixed on described tup seat, ratchet is fixed on ratchet by connecting pin to be fixed on seat and described ratchet is fixed seat and is fixed on described base, and described acceleration transducer is for monitoring the velocity variations of impact process.The aero-engine ratchet impact strength test device of the present invention can complete electromotor ratchet impact strength test, its impact strength and fracture process can be measured accurate, and the aero-engine ratchet impact strength test device of the present invention is applicable to the impact strength test of multiple bias-load through replacing part connection member, there is simple in construction, low cost, the use advantage such as extensively.
Description
Technical field
The invention belongs to aero-engine and gas turbin test field, particularly relate to a kind of aero-engine ratchet impact
Strength test device.
Background technology
The startup of aero-engine and gas turbine is to ratchet by motor shaft and ratchet effect, when reaching certain rotating speed
After, ratchet disengages.It is three ratchets stress simultaneously during normal work, disengages simultaneously, be enough by calculating its margin of safety,
But because produce, assembling and other factor, can produce monodactyle or the situation of double pawl stress, and now margin of safety it is possible to
Deficiency, especially resists the impact strength deficiency under high rotating speed and is probably its main cause having an accident.At present, this structure
Only have its raw-material impact flexibility index, do not measure the effective means of whole parts impact strength.
Ratchet features is: stress is eccentric, speed is fast, and control accuracy is required height.Conventional material impact testing machine
Being only capable of testing losses of potential energy, the method is only applicable to the standard specimen of regular shape, and can not monitor the speed in impact process
Change, process of the test, do not have effective measurement means for sample nonstandard, special-shaped and parts.
Summary of the invention
It is an object of the invention to provide a kind of aero-engine ratchet impact strength test device, for solving current nothing
The problem that method carries out abnormity ratchet load test.
For reaching above-mentioned purpose, the technical solution used in the present invention is: a kind of aero-engine ratchet impact strength test
Device, fixes seat, connecting pin and acceleration transducer including shock machine, impact tup, ratchet；Described shock machine
Having base and tup seat, impact tup is fixed on described tup seat, and ratchet is fixed on ratchet by connecting pin fixes seat
Upper and described ratchet is fixed seat and is fixed on described base, and described acceleration transducer is fixed on assay device, is used for monitoring punching
Hit the velocity variations of process.
Further, the material of described connecting pin and the material of ratchet are identical.
Further, it is bias-load structure that described ratchet fixes seat, and described bias-load structure refers to be subject to ratchet
Power end is exposed out, and guarantees the stress form of ratchet.
Further, described acceleration transducer quantity is two, is respectively arranged on impact tup and ratchet is fixed seat and born
The dead astern of impact.
Further, described impact tup is long strip type.
Further, also including high-speed photography system, described high-speed photography system is for monitoring the racking test mistake of ratchet
Journey.
The aero-engine ratchet impact strength test device of the present invention can complete electromotor ratchet impact strength test, can
At accurate its impact strength and the fracture process measured, and the aero-engine ratchet impact strength test device warp of the present invention
Replace part connection member and be applicable to the impact strength test of multiple bias-load, there is simple in construction, low cost, use wide
The advantage such as general.
Accompanying drawing explanation
Accompanying drawing herein is merged in description and constitutes the part of this specification, it is shown that meet the enforcement of the present invention
Example, and for explaining the principle of the present invention together with description.
Fig. 1 is the aero-engine ratchet impact strength test device schematic diagram of one embodiment of the invention.
Fig. 2 is I position (ratchet the fixes seat) enlarged diagram of one embodiment of the invention.
Fig. 3 is the ratchet impact strength stress schematic diagram of one embodiment of the invention.
Fig. 4 is the ratchet impact strength test schematic diagram of one embodiment of the invention.
Wherein, 1-shock machine, 2-impacts tup, and 3-ratchet fixes seat, 4-connecting pin, 5-acceleration transducer,
6-high-speed photography system, 7-ratchet.
Detailed description of the invention
Clearer for the purpose making the present invention implement, technical scheme and advantage, below in conjunction with in the embodiment of the present invention
Accompanying drawing, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, the most identical or class
As label represent same or similar element or there is the element of same or like function.Described embodiment is the present invention
A part of embodiment rather than whole embodiments.The embodiment described below with reference to accompanying drawing is exemplary type, it is intended to use
In explaining the present invention, and it is not considered as limiting the invention.Based on the embodiment in the present invention, ordinary skill people
The every other embodiment that member is obtained under not making creation type work premise, broadly falls into the scope of protection of the invention.Under
Face combines accompanying drawing and is described in detail embodiments of the invention.
In describing the invention, it is to be understood that term " " center ", " longitudinally ", " laterally ", "front", "rear",
The orientation of the instruction such as "left", "right", " vertically ", " level ", " top ", " end ", " interior ", " outward " or position relationship are for based on accompanying drawing institute
The orientation shown or position relationship, be for only for ease of and describe the present invention and simplify description rather than instruction or the dress of hint indication
Put or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that protect the present invention
The restriction of scope.
As shown in Figure 1 to Figure 3, the aero-engine ratchet impact strength test device of the present invention, it includes impact test
Machine 1, impact tup 2, ratchet fix seat 3, connecting pin 4 and acceleration transducer 5；Shock machine 1 has base and tup
Seat, impact tup 2 is fixed on tup seat, and in the present embodiment, impact tup 2 is long strip type.Ratchet 7 is solid by connecting pin 4
Fix on seat 3 and ratchet is fixed seat 3 and is fixed on by Wedge device on the base of shock machine 1, this wedged dress due to ratchet
Put and to guarantee to strike the head of ratchet 7 and not collide ratchet and fix seat 3 when impacting tup 2 free-falling.Acceleration passes
Sensor 5 is fixed on assay device, for monitoring the velocity variations of impact process.
It should be noted that the material of the connecting pin 4 employed in the present invention is identical with the material of ratchet 7, if making
May have influence on ratchet 7 in impact process with different materials, material as big in use strength ratio ratchet 7 is at impact process
In may destroy ratchet 7, if using the little material of strength ratio ratchet 7 may the power suffered by ratchet 7 also not have in impact process
Reach the limit of, and connecting pin 4 is the worst, cause testing inaccurate.
It should be noted that the ratchet in the present invention fixes seat 3 for bias-load structure, bias-load structure refer to by
Ratchet 7 force side is exposed out, and guarantees the stress form of ratchet 7 as shown in Figure 3.
It should be noted that acceleration transducer 5 quantity is two in the present embodiment, it is respectively arranged on impact tup 2 He
Ratchet fixes the dead astern that seat 3 withstands shocks, and purpose is unlikely to have influence on impact to make acceleration transducer in experimentation
The devices such as tup 2 and tup seat.
It addition, the aero-engine ratchet impact strength test device of the present invention also includes high-speed photography system 6, take the photograph at a high speed
Shadow system 6 is for monitoring the racking test process of ratchet 7.
Concrete, the aero-engine ratchet impact strength test device work process of the present invention is as follows:
1, testpieces (i.e. ratchet 7) is installed:
First impact tup 2 is arranged on the tup seat of shock machine 1, then ratchet 7 is pacified by connecting pin 4
It is contained in ratchet and fixes on seat 3 (as shown in Figure 2), adjust ratchet and fix the position of seat 3, when enabling impact tup 2 free-falling
Strike the head of ratchet 7 and do not collide ratchet fixing device, impact tup 2 is adjusted to Fig. 2 state
2, it is installed and turned on monitoring:
Fix installation acceleration transducer 5 on seat 3 at the back of impact tup 2 and ratchet, acceleration transducer 5 is used for supervising
Velocity variations in control impact process；Distance at distance ratchet about 1.5m places high speed video system 6, is used for monitoring ratchet
Process of the test；Afterwards, acceleration transducer 5, high speed video system 6 are all opened.
3, test:
Hand of dial on shock machine 1 is placed on 300J position (can suitably adjust according to test requirements document), presses
Test is released the button, and quickly presses stop button after having impacted, to prevent jump bit head 2 backswing from destroying the fracture of ratchet 7, with
Time stop high speed video system 6, the measurement system of acceleration transducer 5, read ballistic work and the picture recorded and speed.
4, calculate:
As shown in Figure 4, v1 is the initial velocity of pendulum, and v2 is position after Charpy impact, between solid for ratchet 7 and ratchet
Reservation 3, is calculated by pendulum weight and the elevation angle and arrives the linear velocity at ratchet 7 and impact energy loss, thus calculate ratchet
Impact strength (m (v2-v1)=Ft).
The aero-engine ratchet impact strength test device of the present invention can complete electromotor ratchet impact strength test, can
At accurate its impact strength and the fracture process measured, and the aero-engine ratchet impact strength test device warp of the present invention
Replace part connection member and be applicable to the impact strength test of multiple bias-load, there is simple in construction, low cost, use wide
The advantage such as general.
The above, the only optimum detailed description of the invention of the present invention, but protection scope of the present invention is not limited thereto,
Any those familiar with the art in the technical scope that the invention discloses, the change that can readily occur in or replacement,
All should contain within protection scope of the present invention.Therefore, protection scope of the present invention should be with the protection model of described claim
Enclose and be as the criterion.
Claims (6)
1. an aero-engine ratchet impact strength test device, it is characterised in that include shock machine (1), jump bit
Head (2), ratchet fix seat (3), connecting pin (4) and acceleration transducer (5)；Described shock machine (1) have base with
Tup seat, impacts tup (2) and is fixed on described tup seat, and ratchet (7) is fixed on ratchet by connecting pin (4) fixes seat
(3) upper and described ratchet is fixed seat (3) and is fixed on described base, and described acceleration transducer (5) is for monitoring impact process
Velocity variations.
Aero-engine ratchet impact strength test device the most according to claim 1, it is characterised in that described connecting pin
The material of nail (4) is identical with the material of ratchet (7).
Aero-engine ratchet impact strength test device the most according to claim 1, it is characterised in that described ratchet is solid
Reservation (3) is bias-load structure, and described bias-load structure refers to exposed out for ratchet (7) force side, and guarantees spine
The stress form of pawl (7).
Aero-engine ratchet impact strength test device the most according to claim 1, it is characterised in that described acceleration
Sensor (5) quantity is two, is respectively arranged on impact tup (2) and ratchet fixes the dead astern that seat (3) withstands shocks.
Aero-engine ratchet impact strength test device the most according to claim 1, it is characterised in that described jump bit
Head (2) is long strip type.
Aero-engine ratchet impact strength test device the most according to claim 1, it is characterised in that aero-engine
Ratchet impact strength test device also includes that high-speed photography system (6), described high-speed photography system (6) are used for monitoring ratchet (7)
Racking test process.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610485852.3A CN106197927A (en) | 2016-06-24 | 2016-06-24 | A kind of aero-engine ratchet impact strength test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610485852.3A CN106197927A (en) | 2016-06-24 | 2016-06-24 | A kind of aero-engine ratchet impact strength test device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106197927A true CN106197927A (en) | 2016-12-07 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610485852.3A Pending CN106197927A (en) | 2016-06-24 | 2016-06-24 | A kind of aero-engine ratchet impact strength test device |
Country Status (1)
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| CN (1) | CN106197927A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109186919A (en) * | 2018-10-21 | 2019-01-11 | 西安航天动力测控技术研究所 | A kind of experimental rig impacting igniting composite testing for solid propellant rocket |
| CN110567824A (en) * | 2019-09-16 | 2019-12-13 | 温州跨界环保科技有限公司 | Device capable of fixedly measuring impact toughness of iron hammer |
| CN112924130A (en) * | 2021-03-19 | 2021-06-08 | 中国第一汽车股份有限公司 | Impact test device and method for automobile parts |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109186919A (en) * | 2018-10-21 | 2019-01-11 | 西安航天动力测控技术研究所 | A kind of experimental rig impacting igniting composite testing for solid propellant rocket |
| CN110567824A (en) * | 2019-09-16 | 2019-12-13 | 温州跨界环保科技有限公司 | Device capable of fixedly measuring impact toughness of iron hammer |
| CN110567824B (en) * | 2019-09-16 | 2021-12-14 | 浙江柏盛包装科技有限公司 | Device capable of fixedly measuring impact toughness of iron hammer |
| CN112924130A (en) * | 2021-03-19 | 2021-06-08 | 中国第一汽车股份有限公司 | Impact test device and method for automobile parts |
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Application publication date: 20161207 |