CN105043616A - Aviation engine blade measuring clamp - Google Patents
Aviation engine blade measuring clamp Download PDFInfo
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- CN105043616A CN105043616A CN201510390764.0A CN201510390764A CN105043616A CN 105043616 A CN105043616 A CN 105043616A CN 201510390764 A CN201510390764 A CN 201510390764A CN 105043616 A CN105043616 A CN 105043616A
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Abstract
Provided is a civil aviation engine blade measuring clamp. The measuring clamp comprises a fixed base (1) with a vertical plate, and an outwards extending horizontal protruding shaft (2) is arranged on the vertical plate. The measuring clamp comprises a revolving base (3). A horizontal blind shaft hole is formed in the inner side surface of the revolving base. The revolving base and the horizontal protruding shaft of the fixed base are in cooperation rotation connection through the horizontal blind shaft hole. A radial through hole (5) is formed in the revolving base, and an oil path and external connection hydraulic system is formed. A groove corresponding to a root of a blade (7) is formed in the front side surface of the revolving base. At least one end of the groove is opened. At least an axial horizontal piston hole communication oil path is formed at the bottom of the groove. A piston (6) is arranged in the piston hole. A horizontal positioning hole (8) is formed in the revolving base. Two right angle positioning holes (9) corresponding to the horizontal positioning hole of the revolving base are formed in the vertical plate of the fixed base, and the difference of the two right angle positioning holes is just 90 degrees. The measuring result is accurate, and measuring data needed by a new calculation method for a blade can be obtained through one-time clamping.
Description
Technical field
The present invention relates to a kind of civil engine Blade measuring fixture, especially relate to a kind of measured material of CFM56-7 type blade of aviation engine.
Background technology
The blade of a circle is equipped with in aeromotor rotating shaft front end, and these blades are identical in theory, is equal to the moment of inertia of engine shaft, and aeromotor rotating shaft so just can be made to reach transient equilibrium.But in fact due to the reason of processing and fabricating, no matter these blades all can not be completely the same in shape size or weight center of gravity, have some differences, weight such as, may differ several grams or tens grams, for sometimes weighing the blade of tens kilograms, be a very little error, but this is for the aeromotor of rotating speed thousands of turns, is unallowable.
To measure each fan leaf in practice, find the center of gravity of every section of blade and radial moment Value Data, again according to the concrete data of each blade, certain computing method specific are adopted to calculate design blade arrangement mode, also namely: the mutual relationship of each blade is specific, reaches transient equilibrium in the hope of aeromotor rotating shaft.
In prior art, the measured material being used for measuring blade of aviation engine merely provides blade and lays space and position-limit mechanism, does not design vaned clamp system, makes blade when measuring like this, because of blade with lay space and have gap, so measurement result is not accurate enough; Existing Blade measuring fixture also has a problem to only have a station exactly, can only measure the radial moment Value Data of blade.This just can not achieve required more data during computing method calculating blade arrangement mode that employing is new.
Summary of the invention
Technical matters to be solved by this invention, is just to provide the civil engine Blade measuring fixture that a kind of measurement result is accurate, clamped one time just can complete measurement data needed for new calculation method.
Solve the problems of the technologies described above, the technical solution used in the present invention is as follows:
A kind of civil engine Blade measuring fixture, is characterized in that comprising:
One holder 1 with vertical riser, described riser is provided with the convex axle 2 of overhanging level;
Single-revolution seat 3, inboard face has the blind axis hole of level, and revolving bed to be coordinated with the convex axle 2 of the level of described holder 1 by the blind axis hole of level and is rotatably connected;
On described revolving bed, also have radial direction through hole 5 and form oil circuit and external hydraulic system; On the leading flank of described revolving bed, have the groove corresponding to described blade 7 root, described groove at least one end is opening, the bottom of described groove, and the horizontal piston hole at least having an axis is communicated with described oil circuit, is provided with piston 6 in described piston hole; Three pistons can upper, middle and lower three points of support blade, are used for keeping better the levelness of blade.
On described revolving bed, also have a horizontal location hole 8, the vertical riser of described holder has two right angle pilot holes 9 corresponding to described revolving bed horizontal location hole, when making to insert two right angles pilot holes location revolving bed respectively from horizontal location hole by latch, revolving bed just rotates 90 degree.
The described separate assembling of revolving bed 3 for being bolted together, is divided into leading flank to open reeded anterior 31 and the middle rear portion 32 having oil circuit and piston hole.
Certain revolving bed can also be decomposed into more, and such as considering from technique can by independent again with fixed rotating shaft mating part.
Described piston 6 structure is: be inserted with opening inner core backwards in opening urceolus forward, connect a top bottom inner core with bolt.
Described oil circuit 5 entrance point is provided with valve.
This fixture is added various survey sensor just can measure various data, revolving shaft and holder are split type, and revolving shaft is by holder, and various component is passed to a moment and claims, moment claims to be provided with various sensor.
Beneficial effect: measurement result of the present invention is accurate, clamped one time just can complete measurement data needed for new calculation method, the moment values of the more different directions of fan blade can be recorded, to simulate fan blade unbalance dynamic state more really, the vibrations of the low-pressure section reducing this engine are reached by new computing method, increase work efficiency, extend the life-span of engine.
Accompanying drawing explanation
Fig. 1 is the composition analysed and observe of band of the present invention and annexation band cross-sectional schematic;
Fig. 2 is the left view of Fig. 1;
Fig. 3 is the vertical view of Fig. 1;
Fig. 4 is embodiments of the invention schematic perspective view;
Fig. 5 is the left view of embodiment;
Fig. 6 is the B-B cut-open view of Fig. 5;
Fig. 7 is the C-C cut-open view of Fig. 5;
Fig. 8 is the D-D cut-open view of Fig. 5;
Fig. 9 is the A-A cut-open view of Fig. 5;
Figure 10 is the E-E cut-open view of Fig. 5;
Figure 11 is the schematic perspective view of embodiment revolving bed front portion;
Figure 12 is the volume rendering schematic diagram at embodiment revolving bed rear portion.
Embodiment
As shown in Figure 1 to Figure 3, be civil engine Blade measuring fixture composition of the present invention and principle schematic, comprise the holder 1 that has vertical riser, riser is provided with the convex axle 2 of overhanging level; Single-revolution seat 3, inboard face has the blind axis hole of level, and revolving bed is coordinated by the convex axle 2 of the blind axis hole of level and the level of holder 1 and is rotatably connected.
On revolving bed, also have radial direction through hole 5 and form oil circuit and external Manual hydraulic system (not shown), on the leading flank of revolving bed, have the groove corresponding to blade 7 root, groove two ends are all openings, go out to be provided with locating piece locating blades at one section of mouth; In addition, in the bottom of groove, the horizontal piston hole having 3 axis is communicated with oil circuit, is provided with piston 6 in piston hole.
On revolving bed, also have a horizontal location hole 8, the vertical riser of holder has two right angle pilot holes 9 corresponding to revolving bed horizontal location hole, when making to insert two right angles pilot holes location revolving bed respectively from horizontal location hole by latch, revolving bed just rotates 90 degree.
Fig. 4 to Figure 12 is specific embodiments of the invention (having drawn partial blade), on the composition basis of such as Fig. 1-Fig. 3, further perfect, that is: the separate assembling of revolving bed 3 for being bolted together, is divided into leading flank to open reeded anterior 31 and the middle rear portion 32 having oil circuit and piston hole.See Figure 11 and Figure 12.
Certain revolving bed can also be decomposed into more, and specific embodiment is also like this, and such as considering from technique can by independent again with fixed rotating shaft mating part.See Fig. 6, Fig. 7, Fig. 8.
See Fig. 9, piston 6 structure of specific embodiment is: be inserted with opening inner core backwards in opening urceolus forward, connect a top bottom inner core with bolt.Oil circuit 5 entrance point is provided with valve.
Claims (4)
1. a civil engine Blade measuring fixture, is characterized in that comprising:
One holder (1) with vertical riser, described riser is provided with the convex axle of overhanging level (2);
Single-revolution seat (3), inboard face has the blind axis hole of level, and revolving bed is coordinated with the convex axle of level (2) of described holder (1) be rotatably connected by the blind axis hole of level;
On described revolving bed, also have radial direction through hole (5) and form oil circuit and external hydraulic system; On the leading flank of described revolving bed, have the groove corresponding to described blade (7) root, described groove at least one end is opening, the bottom of described groove, the horizontal piston hole at least having an axis is communicated with described oil circuit, is provided with piston (6) in described piston hole;
On described revolving bed, also have a horizontal location hole (8), the vertical riser of described holder has two right angle pilot holes (9) corresponding to described revolving bed horizontal location hole, when making to insert two right angles pilot holes location revolving bed respectively from horizontal location hole by latch, revolving bed just rotates 90 degree.
2. civil engine Blade measuring fixture according to claim 1, it is characterized in that: described revolving bed (3) separate assembling for being bolted together, being divided into leading flank to open reeded front portion (31) and the middle rear portion (32) having oil circuit and piston hole.
3. civil engine Blade measuring fixture according to claim 2, is characterized in that: described piston (6) structure is: be inserted with opening inner core backwards in opening urceolus forward, connect a top bottom inner core with bolt.
4. civil engine Blade measuring fixture according to claim 3, is characterized in that: described oil circuit (5) entrance point is provided with valve.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510390764.0A CN105043616B (en) | 2015-07-03 | 2015-07-03 | A kind of blade of aviation engine measured material |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510390764.0A CN105043616B (en) | 2015-07-03 | 2015-07-03 | A kind of blade of aviation engine measured material |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105043616A true CN105043616A (en) | 2015-11-11 |
| CN105043616B CN105043616B (en) | 2018-03-13 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510390764.0A Active CN105043616B (en) | 2015-07-03 | 2015-07-03 | A kind of blade of aviation engine measured material |
Country Status (1)
| Country | Link |
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| CN (1) | CN105043616B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106767230A (en) * | 2016-11-09 | 2017-05-31 | 珠海保税区摩天宇航空发动机维修有限公司 | A kind of CFM56 aero-engines low-pressure turbine blade sealing teeth notch dimension control instrument |
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| CN101786237A (en) * | 2009-12-29 | 2010-07-28 | 东方电气集团东方汽轮机有限公司 | Fixture used for processing small moving blade in turbine and processing method thereof |
| CN201592361U (en) * | 2009-10-22 | 2010-09-29 | 常州卓润风能设备有限公司 | 2-degree oblique rotary jig |
| CN102147286A (en) * | 2010-11-20 | 2011-08-10 | 无锡透平叶片有限公司 | Double-plunger frequency measurement device |
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| CN104236879A (en) * | 2014-08-25 | 2014-12-24 | 合肥工业大学 | Engine blade dynamic and static detecting method based on machine vision |
| CN104440161A (en) * | 2014-11-13 | 2015-03-25 | 沈阳黎明航空发动机(集团)有限责任公司 | Method and clamp for eliminating deformation of blade caused by machining stress |
| CN104515478A (en) * | 2014-12-11 | 2015-04-15 | 华中科技大学 | Automatic three-dimensional measuring method and automatic three-dimensional measuring system for high-precision blade of aviation engine |
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| CN2786576Y (en) * | 2005-04-29 | 2006-06-07 | 东方汽轮机厂 | Steamer lamina frequency measuring equipment |
| CN201366623Y (en) * | 2009-03-20 | 2009-12-23 | 无锡润和叶片制造有限公司 | Clamp for horizontal machining center for machining small-margin die forging part with small vanes |
| CN201592361U (en) * | 2009-10-22 | 2010-09-29 | 常州卓润风能设备有限公司 | 2-degree oblique rotary jig |
| CN101786237A (en) * | 2009-12-29 | 2010-07-28 | 东方电气集团东方汽轮机有限公司 | Fixture used for processing small moving blade in turbine and processing method thereof |
| CN102147286A (en) * | 2010-11-20 | 2011-08-10 | 无锡透平叶片有限公司 | Double-plunger frequency measurement device |
| CN102615534A (en) * | 2012-04-10 | 2012-08-01 | 西北工业大学 | Hydraulic fixture used for machining precision forging blade tenon root |
| CN203542127U (en) * | 2013-09-27 | 2014-04-16 | 南通中能机械制造有限公司 | Two-shoulder arc blade root milling tool clamp for diamond-shaped blade |
| CN104236879A (en) * | 2014-08-25 | 2014-12-24 | 合肥工业大学 | Engine blade dynamic and static detecting method based on machine vision |
| CN104440161A (en) * | 2014-11-13 | 2015-03-25 | 沈阳黎明航空发动机(集团)有限责任公司 | Method and clamp for eliminating deformation of blade caused by machining stress |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106767230A (en) * | 2016-11-09 | 2017-05-31 | 珠海保税区摩天宇航空发动机维修有限公司 | A kind of CFM56 aero-engines low-pressure turbine blade sealing teeth notch dimension control instrument |
| CN106767230B (en) * | 2016-11-09 | 2018-11-27 | 珠海保税区摩天宇航空发动机维修有限公司 | A kind of CFM56 aero-engine low-pressure turbine blade sealing teeth notch dimension control tool |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105043616B (en) | 2018-03-13 |
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