CN103728111A - Balancing weight connection structure capable of reducing blade high-cycle fatigue test article frequency - Google Patents
Balancing weight connection structure capable of reducing blade high-cycle fatigue test article frequency Download PDFInfo
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- CN103728111A CN103728111A CN201310684834.4A CN201310684834A CN103728111A CN 103728111 A CN103728111 A CN 103728111A CN 201310684834 A CN201310684834 A CN 201310684834A CN 103728111 A CN103728111 A CN 103728111A
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Abstract
The invention belongs to the technical field of engine testing and particularly relates to a balancing weight connection structure capable of reducing the blade high-cycle fatigue test article frequency. The balancing weight connection structure capable of reducing the blade high-cycle fatigue test article frequency is characterized by being composed of a bolt (1), a blade test article (2), a nut (3), a blade basin face balancing weight (4), a blade back face balancing weight (5) and a locking sheet (6). The blade basin face balancing weight (4) and the blade back face balancing weight (5) are connected with the blade test article (2) through the bolt (1) and the nut (3). The locking sheet (6) is located among the balancing weights, the nut and a bolt head. In the time of assembly, the locking sheet is locked with the balancing weights, the nut and the bolt head respectively. According to the balancing weight connection structure capable of reducing the blade high-cycle fatigue test article frequency, the blade inherent frequency can be greatly reduced, and therefore the blade high-cycle fatigue test can be carried out smoothly. The balancing weight connection structure capable of reducing the blade high-cycle fatigue test article frequency is applicable to blades with the high blade frequency and the large balance weight. The two balancing weights are connected through the bolt to reduce the blade inherent frequency, the problem that the connection strength of an adhesion method is excessively low is solved and the problem that the blade can be flawed due to welding is also solved.
Description
Technical field
The invention belongs to engine test technical field, particularly relate to a kind of balancing weight syndeton that reduces blade high-cycle fatigue test part frequency.
Background technology
To the high-cycle fatigue test of blade of aviation engine is many, on shaking table, carrying out, is exactly blade frequency reducing problem and high frequency blade is carried out to the problem that first high-cycle fatigue test will solve on shaking table.Conventionally, reduce blade frequencies method and have two kinds: a kind of method realizes frequency reducing by removing the material of blade root part; Another kind method realizes frequency reducing by adding counterweight in close blade tip position.Remove the structure influence test effect that material method not only can change blade itself, for high frequency blade (removing more material), also relate to the problem of processing difficulties.At present, adopt of blade frequency reducing added to ballasting method more.The previous ballasting method that adds is normally bonding by counterweight or be welded near blade tip.But two kinds of methods all exist unavoidable problem, the degree of being connected firmly of bonding method is lower, is generally only applicable to low exciting force blade, and higher to bonding agent and bonding plane quality requirements; Although welding process degree of being connected firmly, produces unforeseen defect thereby the high temperature producing while welding can destroy the crystalline phase tissue of weld, in addition, welding technology, welding position are chosen, weld seam size etc. all can exert an influence to test findings.
Summary of the invention
The technical problem to be solved in the present invention:
The balancing weight that the invention connects by tackbolt on high frequency blade, significantly reduces Natural Frequency of Blade, thereby guarantees that the high-cycle fatigue test of high frequency blade on shaking table is able to smooth enforcement.The frequency reducing that the present invention is directed to high frequency blade has proposed new structure solution, for promoting the high-cycle fatigue test of my the various engine blade of institute, provides effective technology solution route.
Technical scheme of the present invention:
A kind of balancing weight syndeton that reduces blade high-cycle fatigue test part frequency, this structure is comprised of bolt 1, blade testpieces 2, nut 3, leaf pelvic surface of sacrum balancing weight 4, leaf back balancing weight 5 and locking plate 6, wherein, leaf pelvic surface of sacrum balancing weight 4, leaf back balancing weight 5 are connected with blade testpieces 2 with nut 3 by bolt 1, locking plate 6 is between balancing weight and nut, bolt head, and during assembling, locking plate will be locked respectively with balancing weight and nut, bolt head.
Leaf pelvic surface of sacrum balancing weight 4 and leaf back balancing weight 5 uniform qualities.
Balancing weight is consistent with the design of blade surface of contact silhouette edge K and the blade design of corresponding position.
Leaf pelvic surface of sacrum balancing weight 4 and leaf back balancing weight 5 are processed into plane with the mating surface of nut, bolt head.
Bolt 1 is polished rod with blade testpieces 2, balancing weight 4 and 5 cooperation places, and its length is not less than balancing weight and vane thickness sum.The screw-down torque of nut 3 should reach higher limit.
Between balancing weight and blade surface of contact, add the copper backing that thickness is 0.1mm adding.
Bolt 1 and blade testpieces 2, leaf pelvic surface of sacrum balancing weight 4 and 5 perforates of leaf back balancing weight adopt interference fit.
Beneficial effect of the present invention:
The present invention can significantly reduce Natural Frequency of Blade, thereby guarantees that the high-cycle fatigue test of blade is able to smooth enforcement.It is high that the present invention is particularly useful for blade frequencies, the blade that weight mass is large.By bolt is connected to two balancing weights, reduce Natural Frequency of Blade, both avoided the too low problem of bonding method strength of joint, the defect problem of having avoided again welding to cause blade.
Accompanying drawing explanation
A kind of bolt fastening structure schematic diagram that reduces blade high-cycle fatigue test part frequency of Fig. 1, wherein, 1-bolt; 2-blade testpieces; 3-nut; 4-leaf pelvic surface of sacrum balancing weight; 5-leaf back balancing weight; 6-locking plate
Embodiment
The present invention, by the balancing weight connecting in the tackbolt of the blade middle and upper part of blade testpieces, reaches the object that significantly reduces Natural Frequency of Blade.Structural representation of the present invention as shown in Figure 1.
Structure of the present invention is comprised of bolt 1, blade testpieces 2, nut 3, leaf pelvic surface of sacrum balancing weight 4, leaf back balancing weight 5 and locking plate 6.Leaf pelvic surface of sacrum balancing weight 4, leaf back balancing weight 5 are connected with blade testpieces 2 by bolt 1, with nut 3, tighten web member.Locking plate 6 is between balancing weight and nut, bolt head, and during assembling, locking plate will be locked respectively with balancing weight and nut, bolt head, occurs loosening while preventing from vibrating between bolt and balancing weight.
The structural representation of bolt 1 as shown in Figure 1, when the design of bolt 1 is designed, is designed to polished rod by bolt 1 and blade testpieces 2, balancing weight 4 and 5 cooperation places, and its length is not less than balancing weight and vane thickness sum; The screw thread matching with nut 3 is processed into in bolt 1 and nut 3 junctions.Bolt 1 and nut 3 are considered high-intensity aeronautical material when material selection.The screw-down torque of nut 3 should reach higher limit.Bolt 1 and 2 perforates of blade testpieces adopt interference fit.
When leaf pelvic surface of sacrum balancing weight 4 and leaf back balancing weight 5 structural design, guarantee that two balancing weight quality approach.The blade design of the design reference corresponding position of balancing weight and blade surface of contact silhouette edge K, is radially dividing cross section, provides each cross-section radial height of silhouette edge K and contour curve data.After balancing weight machines, balancing weight and blade surface of contact need to be carried out to repair one to one, and between balancing weight and blade surface of contact, add the copper backing that thickness is 0.1mm adding.Leaf pelvic surface of sacrum balancing weight 4, leaf back balancing weight 5 are interference fit with bolt 1.By leaf pelvic surface of sacrum balancing weight 4 coordinate with nut 3, leaf back balancing weight 5 is processed into plane with bolt 1 mating surface.Blade testpieces 2 clamping faces are processed into parallel surface, add the depth of parallelism that should guarantee clamping face man-hour.
The present invention is connected to balancing weight on blade by bolt, thereby reach, has significantly reduced Natural Frequency of Blade.This structure has novelty, has considered the matching problem of balancing weight design problem, balancing weight and blade, the problems such as matching problem of bolt design problem and bolt and blade, balancing weight during structural design.At present, this invention has been applied to the high-cycle fatigue strength test of engine high pressure turbine rotor blade, and this design proposal of evidence is feasible.
Claims (8)
1. a balancing weight syndeton that reduces blade high-cycle fatigue test part frequency, it is characterized in that, this structure is comprised of bolt (1), blade testpieces (2), nut (3), leaf pelvic surface of sacrum balancing weight (4), leaf back balancing weight (5) and locking plate (6), wherein, leaf pelvic surface of sacrum balancing weight (4), leaf back balancing weight (5) are connected with blade testpieces (2) with nut (3) by bolt (1), locking plate (6) is between balancing weight and nut, bolt head, and during assembling, locking plate will be locked respectively with balancing weight and nut, bolt head.
2. a kind of balancing weight syndeton that reduces blade high-cycle fatigue test part frequency as claimed in claim 1, is characterized in that, leaf pelvic surface of sacrum balancing weight (4) and leaf back balancing weight (5) uniform quality.
3. a kind of balancing weight syndeton that reduces blade high-cycle fatigue test part frequency as claimed in claim 2, is characterized in that, balancing weight is consistent with the design of blade surface of contact silhouette edge K and the blade design of corresponding position.
4. a kind of balancing weight syndeton that reduces blade high-cycle fatigue test part frequency as claimed in claim 3, is characterized in that, leaf pelvic surface of sacrum balancing weight (4) and leaf back balancing weight (5) are processed into plane with the mating surface of nut, bolt head.
5. a kind of balancing weight syndeton that reduces blade high-cycle fatigue test part frequency as claimed in claim 3, it is characterized in that, bolt (1) is polished rod with blade testpieces (2), balancing weight (4) and (5) cooperation place, its length is not less than balancing weight and vane thickness sum, and the screw-down torque of nut (3) should reach higher limit.
6. a kind of balancing weight syndeton that reduces blade high-cycle fatigue test part frequency as claimed in claim 3, is characterized in that, adds the copper backing that thickness is 0.1mm adding between balancing weight and blade surface of contact.
7. a kind of balancing weight syndeton that reduces blade high-cycle fatigue test part frequency as claimed in claim 3, is characterized in that, bolt (1) and blade testpieces (2), leaf pelvic surface of sacrum balancing weight (4) and leaf back balancing weight (5) perforate adopt interference fit.
8. a kind of balancing weight syndeton that reduces blade high-cycle fatigue test part frequency as claimed in claim 3, is characterized in that, blade testpieces (2) clamping face is processed into parallel surface, adds the depth of parallelism that should guarantee clamping face man-hour.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201310684834.4A CN103728111B (en) | 2013-12-13 | 2013-12-13 | Balancing weight connection structure capable of reducing blade high-cycle fatigue test article frequency |
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| CN201310684834.4A CN103728111B (en) | 2013-12-13 | 2013-12-13 | Balancing weight connection structure capable of reducing blade high-cycle fatigue test article frequency |
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| CN103728111A true CN103728111A (en) | 2014-04-16 |
| CN103728111B CN103728111B (en) | 2017-04-19 |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107796696A (en) * | 2017-11-30 | 2018-03-13 | 中国航发沈阳黎明航空发动机有限责任公司 | The clamping device of aero-engine high-pressure turbine blade fatigue behaviour examination |
| CN108204887A (en) * | 2018-02-02 | 2018-06-26 | 北京化工大学 | A kind of crop leaf measuring platform |
| CN108254144A (en) * | 2017-12-25 | 2018-07-06 | 中国航发四川燃气涡轮研究院 | A kind of Split vane frequency reducing structure measured for the high cycle fatigue limit |
| CN109625314A (en) * | 2018-10-12 | 2019-04-16 | 江西昌河航空工业有限公司 | A kind of assembly method of helicopter composite material paddle fatigue test piece |
| US11230926B2 (en) | 2019-12-09 | 2022-01-25 | Rolls-Royce Corporation | High cycle fatigue design for gas turbine engines |
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| JP2006105735A (en) * | 2004-10-04 | 2006-04-20 | Yokohama Rubber Co Ltd:The | Fatigue tester |
| CN101263278A (en) * | 2005-06-28 | 2008-09-10 | 曼涡轮机股份公司 | Turbine rotor and method for the production thereof |
| CN101308057A (en) * | 2008-06-06 | 2008-11-19 | 北京航空航天大学 | Vibration damping test device possessing dry damping structure vane |
| US20120093650A1 (en) * | 2009-04-16 | 2012-04-19 | Robert Bosch Gmbh | Fan wheel for a blower module |
| CN202471379U (en) * | 2012-01-20 | 2012-10-03 | 中航惠腾风电设备股份有限公司 | Fatigue test device for shimmy direction of large-scale wind wheel blade |
| CN103196644A (en) * | 2013-04-09 | 2013-07-10 | 中国航空动力机械研究所 | Testing device and testing method of integral-impeller blade vibration fatigue |
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2013
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Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| JP2006105735A (en) * | 2004-10-04 | 2006-04-20 | Yokohama Rubber Co Ltd:The | Fatigue tester |
| CN101263278A (en) * | 2005-06-28 | 2008-09-10 | 曼涡轮机股份公司 | Turbine rotor and method for the production thereof |
| CN101308057A (en) * | 2008-06-06 | 2008-11-19 | 北京航空航天大学 | Vibration damping test device possessing dry damping structure vane |
| US20120093650A1 (en) * | 2009-04-16 | 2012-04-19 | Robert Bosch Gmbh | Fan wheel for a blower module |
| CN202471379U (en) * | 2012-01-20 | 2012-10-03 | 中航惠腾风电设备股份有限公司 | Fatigue test device for shimmy direction of large-scale wind wheel blade |
| CN103196644A (en) * | 2013-04-09 | 2013-07-10 | 中国航空动力机械研究所 | Testing device and testing method of integral-impeller blade vibration fatigue |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107796696A (en) * | 2017-11-30 | 2018-03-13 | 中国航发沈阳黎明航空发动机有限责任公司 | The clamping device of aero-engine high-pressure turbine blade fatigue behaviour examination |
| CN108254144A (en) * | 2017-12-25 | 2018-07-06 | 中国航发四川燃气涡轮研究院 | A kind of Split vane frequency reducing structure measured for the high cycle fatigue limit |
| CN108204887A (en) * | 2018-02-02 | 2018-06-26 | 北京化工大学 | A kind of crop leaf measuring platform |
| CN109625314A (en) * | 2018-10-12 | 2019-04-16 | 江西昌河航空工业有限公司 | A kind of assembly method of helicopter composite material paddle fatigue test piece |
| US11230926B2 (en) | 2019-12-09 | 2022-01-25 | Rolls-Royce Corporation | High cycle fatigue design for gas turbine engines |
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| CN103728111B (en) | 2017-04-19 |
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Address after: No. 999, Xuefu Road, Xindu, Chengdu, Sichuan 610500 Patentee after: AECC SICHUAN GAS TURBINE Research Institute Address before: 621703 Jiangyou 305 mailbox operation monitoring department, Mianyang City, Sichuan Province Patentee before: CHINA GAS TURBINE EST |
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