CN201488682U - Comprehensive measurement tool for slender shaft stator blade of airplane engine - Google Patents
Comprehensive measurement tool for slender shaft stator blade of airplane engine Download PDFInfo
- Publication number
- CN201488682U CN201488682U CN2009202029583U CN200920202958U CN201488682U CN 201488682 U CN201488682 U CN 201488682U CN 2009202029583 U CN2009202029583 U CN 2009202029583U CN 200920202958 U CN200920202958 U CN 200920202958U CN 201488682 U CN201488682 U CN 201488682U
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- positioning sliding
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Abstract
The utility model provides a comprehensive measurement tool for a slender shaft stator blade of an airplane engine, and belongs to the technical field of blades of the airplane engine. The measurement tool comprises a pedestal, a bracket, a vertical head, a gear, a gasket, a spring, a combined handle, a chuck, a body pedestal, a positioning bolt, a positioning slide block, a first foot block and a second foot block. The chuck is connected with the vertical head; the body pedestal is fixed on the chuck; the positioning slide block is arranged in the body pedestal; and the positioning bolt is arranged in the positioning slide block. The positioning slide block is provided with the spring. The measurement tool of the utility model has the advantages that: by adopting a form of an angular positioning structure, the measurement tool can realize scientific positioning of the blade, does not cause the deformation of parts, acquires stable data in measurement, improves production efficiency, avoids error waste phenomenon of the blade in the measurement and increases qualification rate of the product.
Description
Technical field
The utility model belongs to the aircraft engine blade technical field, the comprehensive measuring tool of particularly a kind of aircraft engine slender axles stator blade.
Background technology
The present locator meams that adopts, as shown in Figure 3, locating piece 14 is decided angle along pivot pin 15 rotations, so the track of this locating piece 14 is to be the circular arc line in the center of circle with pivot pin 15, arc can make part and be compacted into line and contact to the location, because blade angle is very little to locating surface, has only 1.5mm-3mm, with routine, part just can not be in stable environment in measurement, the data instability of gained in measurement, making fabricator and proofer can't judge that blade is whether qualified also can cause qualified blade mistake useless, be the bottleneck problem in producing, therefore, classic method is inadvisable.
Summary of the invention
At the deficiency that prior art exists, the utility model provides a kind of aircraft engine slender axles stator blade comprehensive measuring tool, by strengthening the structure of locating surface, to reach the purpose to the part positioning stablity.
The technical solution of the utility model is achieved in that this measuring tool comprises base, support, upright head, gear, packing ring, spring, combination handle, chuck, body seat, dog screw, positioning sliding block, first dead head and second dead head; The connection of these measuring tool parts is: chuck connects upright head, and the body seat is fixed on the chuck, and positioning sliding block is installed in the body seat, and dog screw is assemblied in the positioning sliding block.
Described positioning sliding block is equipped with spring.
The course of work of this measuring tool is: this measuring tool is to measure blade profile on blade coordinate directions X, and this direction is finished by the angle location of measuring tool, measures the two states that comprises blade: static, twisting states.If contacting with the line of seal face, part becomes the face contact, the arc that changes routine changes the normal direction front into to the location and decides angular position, at first the center hole at blade two ends is put into first dead head and second dead head, positioning sliding block slides to locating surface along the faceted direction in location, angle by positioning sliding block control blade, increase the stability that compresses, then when positioning sliding block and blade angle to locating surface paste fully and after again by first dead head and the top clamping of second dead head, at this moment blade is in stable duty, can measure each profile of blade; Inlet and outlet limit size; The installing plate size.For guaranteeing that the positioning sliding block of deciding angle can be pressed on the angle reference field of blade reposefully, positioning sliding block and base keep the gap of 0.005-0.01, simultaneously spring are housed in positioning sliding block, and the positioning sliding block of deciding angle is contacted with the blade locating surface all the time.When blade in twisting states following time, the body seat and the chuck at the angle locating piece place of blade connect together, and drive the angle location that positioning sliding block reverses can not influence blade by chuck, have satisfied the measurement requirement of blade.The control snap-in force be in housing screw is made the hexagonal counter sink so that with the size of torque wrench control moment.
The utility model has the advantages that: adopt angle location structure form, the location that can realize science to blade can not caused the distortion of part simultaneously, the data stabilization of gained in the measurement, improve production efficiency, removed the useless phenomenon of blade mistake in measurement, improved the qualification rate of product.
Description of drawings
Fig. 1 is the comprehensive measuring tool structure principle chart of a kind of aircraft engine slender axles of the utility model stator blade.
Fig. 2 is the comprehensive measuring tool structure side of a kind of aircraft engine slender axles of a utility model stator blade view;
Fig. 3 is present clamp structure schematic diagram;
Among the figure: 1 support, 2 upright heads, 3 chucks, 4 body seats, 5 dog screws, 6 positioning sliding blocks, 7 springs, 8 gears, 9 packing rings, 10 bases, 11 combination handles, 12 first dead heads, 13 second dead heads, 14 locating pieces, 15 pivot pins.
Embodiment
The detailed structure of the comprehensive measuring tool of the utility model a kind of aircraft engine slender axles stator blade is illustrated with embodiment in conjunction with the accompanying drawings.
This measuring tool comprises base 10, support 1, upright 2, gear 8, packing ring 9, spring 7, combination handle 11, chuck 3, body seat 4, dog screw 5, positioning sliding block 6, first dead head 12 and second dead head 13 as shown in Figure 1; The connection of these measuring tool parts is: chuck 3 connects upright 2, and body seat 4 is fixed on the chuck 3, and positioning sliding block 6 is installed in the body seat 4, and dog screw 5 is assemblied in the positioning sliding block 6.
Described positioning sliding block 6 is equipped with spring 7.
The course of work of this measuring tool is: this measuring tool is to measure blade profile on blade coordinate directions X, and this direction is finished by the angle location of measuring tool, measures the two states that comprises blade: static, twisting states.If contacting with the line of seal face, part becomes the face contact, the arc that changes routine changes the normal direction front into to the location and decides angular position, at first the center hole at blade two ends is put into first dead head 12 and second dead head 13, positioning sliding block 6 is adjusted into 42 ° of angles as shown in Figure 2, positioning sliding block 6 slides to locating surface along the faceted direction in location, angle by positioning sliding block 6 control blades, increase the stability that compresses, then when positioning sliding block 6 and blade angle to locating surface paste fully and after again by first dead head 12 and the 13 top clampings of second dead head, at this moment blade is in stable duty, can measure each profile of blade; Inlet and outlet limit size; The installing plate size.For guaranteeing that the positioning sliding block 6 of deciding angle can be pressed on the angle reference field of blade reposefully, the gap that positioning sliding block 6 and base 10 keep 0.005-0.01mm, simultaneously spring 7 is housed in positioning sliding block 6, the positioning sliding block 6 of deciding angle is contacted with the blade locating surface all the time.When blade in twisting states following time, the body seat 4 and the chuck 3 at the angle locating piece place of blade connect together, and drive the angle location that positioning sliding blocks 6 reverse can not influence blade by chuck 3, have satisfied the measurement requirement of blade.The control snap-in force be in housing screw is made the hexagonal counter sink so that with the size of torque wrench control moment.
Claims (2)
1. comprehensive measuring tool of aircraft engine slender axles stator blade, this measuring tool is made up of base (10), support (1), upright head (2), gear (8), packing ring (9), spring (7), combination handle (11), and it is characterized in that: this measuring tool also comprises chuck (3), body seat (4), dog screw (5), positioning sliding block (6), first dead head (12) and second dead head (13); The connection of these measuring tool parts is: chuck (3) connects upright head (2), and body seat (4) is fixed on the chuck (3), and positioning sliding block (6) is installed in the body seat (4), and dog screw (5) is assemblied in the positioning sliding block (6).
2. by the comprehensive measuring tool of the described aircraft engine slender axles of claim 1 stator blade, it is characterized in that described positioning sliding block (6) is equipped with spring (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009202029583U CN201488682U (en) | 2009-08-31 | 2009-08-31 | Comprehensive measurement tool for slender shaft stator blade of airplane engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009202029583U CN201488682U (en) | 2009-08-31 | 2009-08-31 | Comprehensive measurement tool for slender shaft stator blade of airplane engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201488682U true CN201488682U (en) | 2010-05-26 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2009202029583U Expired - Fee Related CN201488682U (en) | 2009-08-31 | 2009-08-31 | Comprehensive measurement tool for slender shaft stator blade of airplane engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201488682U (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102147220A (en) * | 2010-11-20 | 2011-08-10 | 无锡透平叶片有限公司 | Measuring device for detecting overall-length conical surface of clapboard stator blade |
| CN102562663A (en) * | 2010-12-30 | 2012-07-11 | 沈阳黎明航空发动机(集团)有限责任公司 | Air compressor case blade installation angle detection method and tool |
| CN103162588A (en) * | 2013-02-25 | 2013-06-19 | 哈尔滨汽轮机厂有限责任公司 | Steam turbine blade blank detection device with pouring square box |
| CN103604397A (en) * | 2013-11-20 | 2014-02-26 | 沈阳黎明航空发动机(集团)有限责任公司 | Multistage general angle self-adaptive blade three-coordinate measuring holder |
| CN103604396A (en) * | 2013-11-20 | 2014-02-26 | 沈阳黎明航空发动机(集团)有限责任公司 | Fixation apparatus for stator blade profile and journal bounce detection |
| CN103630034A (en) * | 2013-11-29 | 2014-03-12 | 四川成发航空科技股份有限公司 | Universal combined test tool for shaft type blade and method for measuring shaft type blade |
| 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 |
| CN108072345A (en) * | 2016-11-14 | 2018-05-25 | 江西昌河航空工业有限公司 | A kind of paddle size composite measurement platform |
-
2009
- 2009-08-31 CN CN2009202029583U patent/CN201488682U/en not_active Expired - Fee Related
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102147220B (en) * | 2010-11-20 | 2012-09-05 | 无锡透平叶片有限公司 | Measuring device for detecting overall-length conical surface of clapboard stator blade |
| CN102147220A (en) * | 2010-11-20 | 2011-08-10 | 无锡透平叶片有限公司 | Measuring device for detecting overall-length conical surface of clapboard stator blade |
| CN102562663B (en) * | 2010-12-30 | 2013-10-23 | 沈阳黎明航空发动机(集团)有限责任公司 | Air compressor case blade installation angle detection method and tool |
| CN102562663A (en) * | 2010-12-30 | 2012-07-11 | 沈阳黎明航空发动机(集团)有限责任公司 | Air compressor case blade installation angle detection method and tool |
| CN103162588B (en) * | 2013-02-25 | 2015-06-17 | 哈尔滨汽轮机厂有限责任公司 | Steam turbine blade blank detection device with pouring square box |
| CN103162588A (en) * | 2013-02-25 | 2013-06-19 | 哈尔滨汽轮机厂有限责任公司 | Steam turbine blade blank detection device with pouring square box |
| CN103604397A (en) * | 2013-11-20 | 2014-02-26 | 沈阳黎明航空发动机(集团)有限责任公司 | Multistage general angle self-adaptive blade three-coordinate measuring holder |
| CN103604396A (en) * | 2013-11-20 | 2014-02-26 | 沈阳黎明航空发动机(集团)有限责任公司 | Fixation apparatus for stator blade profile and journal bounce detection |
| CN103604396B (en) * | 2013-11-20 | 2016-08-17 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of for stator blade profile and the fixing device of axle journal glitch detection |
| CN103630034A (en) * | 2013-11-29 | 2014-03-12 | 四川成发航空科技股份有限公司 | Universal combined test tool for shaft type blade and method for measuring shaft type blade |
| CN103630034B (en) * | 2013-11-29 | 2016-08-17 | 四川成发航空科技股份有限公司 | Spindle-type blade general combination measuring tool and the method measuring spindle-type blade |
| 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 |
| CN108072345A (en) * | 2016-11-14 | 2018-05-25 | 江西昌河航空工业有限公司 | A kind of paddle size composite measurement platform |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20100526 Termination date: 20130831 |