CN205157148U - Test device can be assessd to super large fan blade fatigue performance - Google Patents
Test device can be assessd to super large fan blade fatigue performance Download PDFInfo
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- CN205157148U CN205157148U CN201520945864.0U CN201520945864U CN205157148U CN 205157148 U CN205157148 U CN 205157148U CN 201520945864 U CN201520945864 U CN 201520945864U CN 205157148 U CN205157148 U CN 205157148U
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- briquetting
- fan blade
- super large
- large fan
- base
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Abstract
The utility model discloses a test device can be assessd to super large fan blade fatigue performance, test device includes base, briquetting and clamp bolt, it is trapezoidal that the briquetting is the right -angle side, the branch body structure of briquetting and lower briquetting in the adoption, the terminal surface is equipped with the inclined plane with lower briquetting up end under going up the briquetting, and the symmetry is the horn mouth form, be equipped with gantry beam on the base, the gantry beam up end is equipped with two connecting thread holes, down the briquetting is fixed places on the base, and the terminal surface is placed on briquetting down under the blade switching section, and blade tenon working face and time briquetting beveled laminate, go up the briquetting and place at blade switching section up end, and blade tenon working face and last briquetting beveled laminate, clamp bolt compresses tightly the briquetting through the connecting thread hole, will go up briquetting, briquetting and base rigid connection integrative fixed blade switching section cheng down. The technical scheme of the utility model make simply, structural design is reasonable, and maneuverability is strong.
Description
Technical field
The utility model relates to engine vane fatigue examination field, particularly a kind of super large fan blade fatigue behaviour certification test device.
Background technology
In aeromotor development, producing, the consumable accessorys such as blade need to carry out a large amount of fatigue behaviour certification tests, the fixture total quality of Fig. 1 is light, rigidity is weak, two bolts are only relied on to be connected with electromagnetic vibration generator system, fixture and shaking table can not be formed and be rigidly connected, therefore produce vibration and the fretting wear of fixture and shaking table; Again because blade dimensions is large, tenon is less, and only completes the fastening of blade and fixture with a puller bolt, makes tenon and fixture tongue-and-groove produce serious fretting wear, causes blade tenon to rupture.Blade is in tired certification test, and blade tenon again and again ruptures and causes test to carry out, and a large amount of blade cannot be installed, and has had a strong impact on production task.General fatigue test clamper cannot improve the rigidity of fixture, the stability of blade vibration and reduce blade tenon wearing and tearing.
Utility model content
For solving the problems of the technologies described above, the purpose of this utility model is to provide a kind of super large fan blade fatigue behaviour certification test device, and concrete technical scheme is as follows:
A kind of super large fan blade fatigue behaviour certification test device, described test unit comprises base, briquetting and hold-down bolt;
Described briquetting shape is that right-angle side is trapezoidal, adopts the Split type structure of upper holder block and lower lock block; Upper holder block lower surface and lower lock block upper surface are provided with inclined-plane, symmetrical in bell mouth shape;
Described base is provided with gantry beam, and described gantry beam upper surface is provided with two threaded holes;
Described lower lock block fixed placement is on base, and super large fan blade group section lower surface is placed on lower lock block, and fits in super large fan blade rabbet working face and lower lock block inclined-plane;
Described upper holder block is placed on super large fan blade group section upper surface, and fits in super large fan blade rabbet working face and upper holder block inclined-plane;
Described hold-down bolt is screwed into threaded hole and compresses upper holder block, is rigidly connected integral by upper holder block, super large fan blade, lower lock block and base.Improve the stability of blade vibration and reduce the fretting wear of blade tenon, avoiding blade tenon to rupture;
Described a kind of super large fan blade fatigue behaviour certification test device, is characterized in that: described base circumference uniform distribution is provided with 8 mounting holes, is fixed on a vibration table by base by bolt.Strengthen the stability of whole test unit.
The beneficial effects of the utility model: the technical solution of the utility model manufacture is simple, convenient, workable, solve universal fatigue test fixture because poor rigidity, vibration are large, blade tenon serious wear, again and again to rupture the problem such as cause that test cannot be carried out at torture test Leaf tenon.Scheme of the present utility model changes traditional tenon installation way, adopt the clamping of blade group section place stressed, briquetting adopts upper and lower two pieces of Split type structures, and tail end is bell mouth shape, limits the front and back play of blade, change vane stress position, base adopts circular 8 bolts to connect, and improves being rigidly connected between shaking table, fixture, blade three, enhances the stability of blade fatigue examination, discharge the fretting wear between tenon and fixture, ensure that carrying out smoothly of tired certification test.Therefore this structure is adopted to have great Social benefit and economic benefit.
Accompanying drawing explanation
Fig. 1 is universal fatigue guaranteed performance test device schematic diagram;
Fig. 2 is a kind of super large fan blade fatigue behaviour certification test device schematic diagram;
Fig. 3 is Fig. 2 vertical view.
In figure: 1 is base, 2 is upper holder block, and 3 is lower lock block, and 4 is hold-down bolt, and 5 is threaded hole, and 6 is mounting hole, and 7 is group section, and 8 is super large fan blade, and 9 is gantry beam.
Embodiment
A super large fan blade fatigue behaviour certification test device as shown in Figure 2,3, described test unit comprises base 1, briquetting and hold-down bolt 4;
Described briquetting shape is that right-angle side is trapezoidal, adopts the Split type structure of upper holder block 2 and lower lock block 3; Upper holder block 2 lower surface and lower lock block 3 upper surface are provided with inclined-plane, symmetrical in bell mouth shape;
Described base 1 is provided with gantry beam 9, and described gantry beam 9 upper surface is provided with two threaded holes 5;
Described lower lock block 3 fixed placement is on base 1, and super large fan blade 8 group section 7 lower surface is placed on lower lock block 3, and fits in super large fan blade 8 rabbet working face and lower lock block 3 inclined-plane;
Described upper holder block 2 is placed on super large fan blade 8 group section 7 upper surface, and fits in super large fan blade 8 rabbet working face and upper holder block 2 inclined-plane;
Described hold-down bolt 4 is screwed into threaded hole 5 and compresses upper holder block 2, is rigidly connected integral by upper holder block 2, super large fan blade 8, lower lock block 3 and base 1.
Described base 1 circumference uniform distribution is provided with 8 mounting holes 6, is fixed on a vibration table by base by bolt.
Claims (2)
1. a super large fan blade fatigue behaviour certification test device, is characterized in that:
Described test unit comprises base, briquetting and hold-down bolt;
Described briquetting shape is that right-angle side is trapezoidal, adopts the Split type structure of upper holder block and lower lock block; Upper holder block lower surface and lower lock block upper surface are provided with inclined-plane, symmetrical in bell mouth shape;
Described base is provided with gantry beam, and described gantry beam upper surface is provided with two threaded holes;
Described lower lock block fixed placement is on base, and super large fan blade group section lower surface is placed on lower lock block, and fits in super large fan blade rabbet working face and lower lock block inclined-plane;
Described upper holder block is placed on super large fan blade group section upper surface, and fits in super large fan blade rabbet working face and upper holder block inclined-plane;
Described hold-down bolt is screwed into threaded hole and compresses upper holder block, is rigidly connected integral by upper holder block, super large fan blade, lower lock block and base.
2. a kind of super large fan blade fatigue behaviour certification test device as claimed in claim 1, is characterized in that: described base circumference uniform distribution is provided with 8 mounting holes, is fixed on a vibration table by base by bolt.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520945864.0U CN205157148U (en) | 2015-11-23 | 2015-11-23 | Test device can be assessd to super large fan blade fatigue performance |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520945864.0U CN205157148U (en) | 2015-11-23 | 2015-11-23 | Test device can be assessd to super large fan blade fatigue performance |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205157148U true CN205157148U (en) | 2016-04-13 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520945864.0U Expired - Fee Related CN205157148U (en) | 2015-11-23 | 2015-11-23 | Test device can be assessd to super large fan blade fatigue performance |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205157148U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106248331A (en) * | 2016-08-30 | 2016-12-21 | 中国人民解放军空军工程大学航空航天工程学院 | Vibration amplifier and the test method of simulation blade high-order nonlinear vibrating fatigue |
| CN108106829A (en) * | 2017-12-14 | 2018-06-01 | 中国人民解放军空军工程大学 | A kind of high-cycle fatigue test method and apparatus of gas turbine large size blade |
| CN109029889A (en) * | 2018-08-27 | 2018-12-18 | 烟台大学 | A kind of the vibration-testing experimental rig and its test method of blade of aviation engine |
| CN112525736A (en) * | 2021-02-08 | 2021-03-19 | 中国航发上海商用航空发动机制造有限责任公司 | Fan blade cantilever beam element level strength test method |
| CN112781812A (en) * | 2019-11-01 | 2021-05-11 | 上海羿弓氢能科技有限公司 | Fatigue testing method for metal diaphragm of diaphragm compressor |
-
2015
- 2015-11-23 CN CN201520945864.0U patent/CN205157148U/en not_active Expired - Fee Related
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106248331A (en) * | 2016-08-30 | 2016-12-21 | 中国人民解放军空军工程大学航空航天工程学院 | Vibration amplifier and the test method of simulation blade high-order nonlinear vibrating fatigue |
| CN108106829A (en) * | 2017-12-14 | 2018-06-01 | 中国人民解放军空军工程大学 | A kind of high-cycle fatigue test method and apparatus of gas turbine large size blade |
| CN109029889A (en) * | 2018-08-27 | 2018-12-18 | 烟台大学 | A kind of the vibration-testing experimental rig and its test method of blade of aviation engine |
| CN109029889B (en) * | 2018-08-27 | 2023-09-26 | 烟台大学 | Vibration test device and method for aero-engine blade |
| CN112781812A (en) * | 2019-11-01 | 2021-05-11 | 上海羿弓氢能科技有限公司 | Fatigue testing method for metal diaphragm of diaphragm compressor |
| CN112525736A (en) * | 2021-02-08 | 2021-03-19 | 中国航发上海商用航空发动机制造有限责任公司 | Fan blade cantilever beam element level strength test method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 110043 Dong TA street, Dadong District, Shenyang, Liaoning Province, No. 6 Patentee after: Chinese Hangfa Shenyang Liming Aero engine limited liability company Address before: 110043 Dong TA street, Dadong District, Shenyang, Liaoning Province, No. 6 Patentee before: Liming Aeroplane Engine (Group) Co., Ltd., Shenyang City |
|
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160413 Termination date: 20201123 |