CN202648570U - Comprehensive measuring instrument for gas turbine stator blade - Google Patents
Comprehensive measuring instrument for gas turbine stator blade Download PDFInfo
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- CN202648570U CN202648570U CN 201220251621 CN201220251621U CN202648570U CN 202648570 U CN202648570 U CN 202648570U CN 201220251621 CN201220251621 CN 201220251621 CN 201220251621 U CN201220251621 U CN 201220251621U CN 202648570 U CN202648570 U CN 202648570U
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Abstract
The utility model discloses a comprehensive measuring instrument for a gas turbine stator blade and pertains to the field of blade processing and detection technology. The comprehensive measuring instrument mainly comprises a bottom plate, a blade root supporting block on the bottom plate, a blade crown supporting block, section positioning pins and a profile sample plate. The comprehensive measuring instrument is simple, complete, easy in operation, delicate in design, reasonable and compact in structure, convenient in detection and few in errors; and shapes and sizes of the blade, the blade root and the blade crown, the circular conical surfaces of the intersectional surfaces of the blade root, the blade crown and an airway, the end surfaces of the blade root and the blade crown, the location degree of the airway, the profile tolerance of the airway and the total length of the blade can be detected, the detection efficiency is improved and the detection difficulty and the detection cost are reduced.
Description
Technical field
The utility model relates to a kind of stator blade comprehensive measuring tool, and particularly a kind of gas turbine stator blade comprehensive measuring tool belongs to blade processing detection technique field.
Background technology
The heavy duty gas turbine of combined cycle has the high efficiency of energy utilization, and to improving the level of resources utilization, realizing energy-saving and emission-reduction, promoting sustainable development has outstanding role, has become one of main forms of electricity generation of developed country.Gas turbine stator blade complex structure, the process technology difficulty is large, accuracy requirement is high, because the irregular structure of stator blade blade root, integral shroud and air flue, so that the difficulty that testing becomes, in the test item to stator blade, comprise that blade root and integral shroud physical dimension detect, the molded line of the air flue inner arc of air flue, the air flue back of the body arc, leading edge and trailing edge and the detection of position, also to make detection to blade root and the face that passes through mutually of air flue, integral shroud and air flue, the traditional detection mode adopts three-dimensional to detect, but such detection mode operation is loaded down with trivial details, efficient is lower, and testing cost is also higher; More test item has increased the workload and the testing cost that detect.
In traditional blade measurer, can only make detection to the air flue inner arc molded line of air flue and profile and the position of air flue back of the body camber line, other test item can not be finished in the measurer of design, need again to adopt the three-dimensional detection mode, reduced detection efficiency, increased testing cost, and in the process of clamping repeatedly, caused that easily blade surface scratches or weighs wounded.
Summary of the invention
Goal of the invention of the present utility model is: for the problem of above-mentioned existence, provide a kind of simple and direct, perfect, easy-operating, design precision, compact and reasonable, easy to detect and comprehensive measuring tool that error is minimum, in comprehensive measuring tool, can finish geomery, blade root and the integral shroud of blade root and integral shroud and the circular conical surface of the face that passes through mutually of air flue, the end face of blade root and integral shroud, duct position degree, air flue profile tolerance and blade overall length are made detection, improve detection efficiency, reduce detection difficulty and testing cost.
The technical solution adopted in the utility model is as follows:
A kind of gas turbine stator blade comprehensive measuring tool comprises comprehensive measuring tool body and molded line cam group that mutual coupling detects, and described comprehensive measuring tool body comprises base plate; Described base plate top is provided with blade root back-up block and integral shroud back-up block, described blade root back-up block is the structure that is complementary as positioning reference plane and blade root take the tool back plane of blade root and the side plane of giving vent to anger, this blade root back-up block medial surface is to pass through mutually the consistent circular conical surface of face with blade root, and lateral surface is the circular conical surface consistent with the blade root end face; Described integral shroud back-up block is the structure that is complementary as positioning reference plane and integral shroud take the tool back plane of blade shroud and the side plane of giving vent to anger, and this integral shroud back-up block medial surface is to pass through mutually the consistent circular conical surface of face with integral shroud, and lateral surface is the circular conical surface consistent with the integral shroud end face; On the base plate between described blade root back-up block and the integral shroud back-up block, be provided with the cross section register pin; Described molded line model, comprise air flue inner arc molded line model and air flue back of the body camber line tempte, the location bound feet that is provided with airway cross-section molded line section and can be complementary with the side of base plate on air flue inner arc molded line model and the air flue back of the body camber line tempte, airway cross-section molded line section and air flue inner arc molded line on the described air flue inner arc molded line model are complementary, and airway cross-section molded line section and air flue back of the body camber line on the described air flue back of the body camber line tempte are complementary.
Owing to adopted technique scheme, so that described comprehensive measuring tool body is horizontal type structure, blade root back-up block on the described base plate and integral shroud back-up block are respectively take the tool back plane of blade root and the give vent to anger tool back plane of side plane, blade shroud and the side plane of giving vent to anger as positioning datum, make the structure that is complementary with blade root and integral shroud, after being complementary with the blade root of blade and integral shroud, the Preliminary detection to the profile of blade root and integral shroud can be realized, if meet the requirements, then next step detection can be carried out; The distance of the outside two circular conical surfaces in the blade root back-up block, the distance of passing through mutually face and blade root end face with blade root is consistent, the distance of the outside two circular conical surfaces in the integral shroud back-up block, the distance of passing through mutually face and integral shroud end face with integral shroud is consistent, after mating, can be aided with clearance gauge with mode relatively, can finish blade root is passed through the detection that face, blade root end face, integral shroud pass through face and integral shroud end face mutually mutually; Distance between described blade root back-up block and integral shroud back-up block medial surface, for the blade root of rule blade is passed through the distance that face and integral shroud pass through face mutually mutually, after blade fits into measurer, the inboard circular conical surface of blade root back-up block and blade root are passed through mutually in the face of neat, relatively the integral shroud of opposite side passes through face mutually, can make detection to the length of blade air flue, again the outside circular conical surface of blade root end face with the blade root back-up block compared, the outside circular conical surface of integral shroud end face with the integral shroud back-up block compared, be aided with clearance gauge and can judge the processing dimension of whole blade and whether meet technological requirement; Described cross section register pin, base plate both sides between blade root back-up block and integral shroud back-up block, be divided into the cross section register pin of air flue inner arc molded line model and the cross section register pin of air flue back of the body camber line tempte, two kinds of cross section register pins of identical duct position consist of one group, can be used in the location of the measuring position of described molded line model in blade air flue molded line is measured, and play a supporting role; Described base plate is along the dual-side on the direction blade, can be processed into can with the molded line model on the location side that is complementary of location bound feet, the air flue inner arc molded line model that mutually matches, after air flue back of the body camber line tempte matches mutually with blade air flue molded line, can judge the profile tolerance of blade air flue molded line, described in the airway cross-section molded line section of described molded line model and the junction of air flue molded line, can be aided with edge of a knife chi measures the light leak situation and comes air flue inner arc to blade, air flue back of the body arc, detection is made in molded line and the position of leading edge and trailing edge, in the side edge of described location bound feet and base plate, can be aided with edge of a knife chi measurement light leak situation and come the relative position of blade steam passage is made detection.
Also be provided with the cover plate I on the described blade root back-up block, described cover plate I with can be complementary with blade root after the blade root back-up block cooperates, cover plate I medial surface is to pass through mutually the consistent circular conical surface of face with blade root, lateral surface is the circular conical surface consistent with the blade root end face; Also be provided with the cover plate II on the described integral shroud back-up block, described cover plate II with can be complementary with integral shroud after the integral shroud back-up block cooperates, cover plate II medial surface is to pass through mutually the consistent circular conical surface of face with integral shroud, lateral surface is the circular conical surface consistent with the blade root end face.
Owing to adopted technique scheme, after described blade root back-up block and cover plate I cooperate, can be fully and blade root be complementary, whether the molded line that the lateral surface circular conical surface consistent with the blade root end face can detect the blade root end face meets the requirements, whether cover plate I medial surface passes through the consistent circular conical surface of face mutually with blade root, can further detect blade root and pass through mutually face and meet the requirements; In like manner, identical principle can judge further that with method the integral shroud end face of integral shroud passes through mutually face with integral shroud and whether meets the requirements.
Be provided with straight pin on described blade root back-up block and the integral shroud back-up block, be provided with the cylindrical hole that is complementary with straight pin on described cover plate I and the cover plate II.
Owing to adopted technique scheme, described straight pin and cylindrical hole coupling, can be convenient, flexible the integral shroud back-up block is assembled and dismantles with corresponding cover plate, the loading and unloading of realization blade root and integral shroud and fixing, prevent from simultaneously being subjected to displacement or dropping detecting the operating process cover plate, improve precision and efficiency of detecting.
The quantity of described cross section register pin is 2 to 5 groups.
Owing to adopted technique scheme, can produce according to reality the detection demand of blade, determine the quantity of described cross section register pin, thereby detect on the correspondence position to the air flue molded line of blade, and reasonably adjust check point according to actual conditions.
On the base plate between described blade root back-up block and integral shroud back-up block, also be provided with the model back-up block, be complementary with location bound feet on the described molded line model.
Owing to adopted technique scheme, described model back-up block is the raised platforms that is positioned at register pin bottom, cross section between the blade root back-up block on the base plate and integral shroud back-up block, can being complementary with the location bound feet of molded line model along the edge on the direction blade of platform both sides, platform top can be used in the support of model, further the location of optimized model line model is conducive to improve accuracy of detection.
Be provided with block on the base plate in the described blade root back-up block outside.
Owing to adopted technique scheme, described block can play the effect of keeping out on the blade root end face direction to blade root, prevents from measuring Leaf displacement and landing.
Described cross section register pin is square or circular, and described block is square or circular.
Owing to adopted technique scheme, be convenient to select cross section register pin or block for which kind of shape according to actual conditions, come the appearance design of Optimum Synthesis measurer, if be circular, then need 2 straight pins to realize the location, if be square, then can realize the location with 1 square block.
Be provided with the back-up block straight pin on the described base plate, be provided with the cylindrical hole of coupling on described blade root back-up block and the integral shroud back-up block, described blade root back-up block and integral shroud back-up block are by back-up block straight pin location, and the employing bolt is connected with base plate.
Owing to adopted technique scheme, the back-up block straight pin can carry out the accurate location of blade root back-up block and integral shroud back-up block, connected mode by bolt, blade root back-up block, integral shroud back-up block and base plate separate machined have been made things convenient for, guarantee machining precision, simultaneously can debug and proofread and correct the relative height of blade root back-up block and integral shroud back-up block easily, thereby guarantee accuracy of detection.
The both sides of described comprehensive measuring tool body are provided with handle.
Owing to adopted technique scheme, provide handgrip part at measurer, made things convenient for daily operation and carrying.
In sum, owing to adopted technique scheme, the beneficial effect of a kind of gas turbine stator blade of the utility model comprehensive measuring tool is:
Provide a kind of simple and direct, perfect, easy-operating, design precision, compact and reasonable, easy to detect and comprehensive measuring tool that error is minimum, this comprehensive measuring tool can be finished geomery, blade root and the integral shroud of blade root and integral shroud and the circular conical surface of the face that passes through mutually of air flue, the end face of blade root and integral shroud, duct position degree, air flue profile tolerance and blade overall length are made detection, compare the traditional detection mode, have the operation that reduces repeated clamping, save detection time, avoid the surface tear that causes because of repeated clamping or the advantage such as weigh wounded; Effectively save detection time more than 80%, save testing cost more than 60%, guaranteed that product detects qualification rate 100%.
Description of drawings
Fig. 1 is front view of the present utility model;
Fig. 2 is vertical view of the present utility model;
Fig. 3 is side view of the present utility model;
Fig. 4 is air flue inner arc molded line template drawing of the present utility model;
Fig. 5 is air flue back of the body camber line tempte figure of the present utility model.
Mark among the figure: 1-base plate, 2-blade root back-up block, 3-integral shroud back-up block, 4-cover plate I, 5-cover plate II, 6-cross section register pin, 7-air flue inner arc molded line model, 8-air flue back of the body camber line tempte, 9-airway cross-section molded line section, 10-location bound feet, 11-block, 12-model back-up block, 13-straight pin, 14-back-up block straight pin, 15-bolt, 16-handle.
Embodiment
Below in conjunction with accompanying drawing, the utility model is described in detail.
In order to make the purpose of this utility model, technical scheme and advantage clearer, below in conjunction with drawings and Examples, the utility model is further elaborated.Should be appreciated that specific embodiment described herein only in order to explaining the utility model, and be not used in restriction the utility model.
Embodiment 1, a kind of gas turbine stator blade comprehensive measuring tool of the present utility model, and the comprehensive measuring tool body is as shown in Figure 1 and Figure 2;
Comprehensive measuring tool body processing: blade root back-up block 2 and integral shroud back-up block 3 are set on base plate 1 top, blade root back-up block 2 is processed with the structure that is complementary as positioning reference plane and blade root take the tool back plane of blade root and the side plane of giving vent to anger, these blade root back-up block 2 medial surfaces are processed into blade root and pass through mutually the consistent circular conical surface of face, lateral surface is processed into the circular conical surface consistent with the blade root end face, the distance of the outside two circular conical surfaces in it, the distance of passing through mutually face and end face with the blade root of blade is consistent; Integral shroud back-up block 3 is processed with the structure that is complementary as positioning reference plane and integral shroud take the tool back plane of blade shroud and the side plane of giving vent to anger, these integral shroud back-up block 3 medial surfaces are processed into integral shroud and pass through mutually the consistent circular conical surface of face, lateral surface is processed into the circular conical surface consistent with the integral shroud end face, the distance of the outside two circular conical surfaces in it, the distance of passing through mutually face and end face with the integral shroud of blade is consistent; Blade root back-up block 2 and integral shroud back-up block 3 are by after being positioned at back-up block straight pin 14 location on the base plate 1, the distance of two inboard circular conical surfaces is that the blade root of blade is passed through the distance that face and integral shroud pass through technological requirement between the face mutually mutually, and blade root back-up block 2 and integral shroud back-up block 3 all adopt bolt 15 to be connected and fixed with base plate 1; On the base plate 1 of 3 of blade root back-up block 2 and integral shroud back-up blocks, need the quantity (2 to 5) of detection position according to blade air flue molded line, corresponding arranges 2 groups to the right cross section register pin 6 of 5 assembly, this cross section register pin can be circle, also can be for square, if be circular, this need to have 2 identical straight pins to realize the location, as shown in Figure 2.
Molded line model processing: adopt the suitable sheet material of thickness, in the airway cross-section molded line section 9 of side processing with the air flue inner arc molded line coupling of blade, at the location bound feet 10 that is used for the location that the side of opposite side setting and base plate 1 is complementary, form air flue inner arc molded line model 7, as shown in Figure 4; Same method processing is carried on the back camber line tempte 8 with the air flue of air flue back of the body camber line coupling, as shown in Figure 5; Two molded line models partner, and by processing many covers molded line model of different duct positions place coupling, adopt the molded line cam group that duct position degree and air flue profile tolerance are made detection.
A kind of gas turbine stator blade comprehensive measuring tool of the present utility model, realize in the following manner detecting:
To be detected blade is placed on the comprehensive measuring tool, blade root and the integral shroud of blade are alignd with the locating surface of blade root back-up block and integral shroud back-up block, take the circular conical surface of the inboard of blade root back-up block as benchmark, pass through mutually in the face of neat with blade root, observe blade root and pass through mutually the matching degree of face and the inboard circular conical surface of blade root back-up block, observe the matching degree of circular conical surface and the blade root back-up block outside circular conical surface of blade root end face, whether the Preliminary detection blade root passes through face mutually qualified; The integral shroud that continues the detection blade passes through the relative position of face and integral shroud back-up block mutually, and whether the length that detects the blade air flue meets the requirements; Adopt the circular conical surface that identical method detection blade shroud passes through face and end face mutually whether to meet the requirements; Then match blade root back-up block and cover plate corresponding to integral shroud back-up block, by the circular conical surface of cover plate both sides, further the face that passes through mutually of blade root and integral shroud and the circular conical surface on the end face are done detection; Detect again the end surface shape of blade root and the matching degree of blade root back-up block and cover plate, in like manner detect the end surface shape of integral shroud and the matching degree of integral shroud back-up block and cover plate; Again by relatively, the circular conical surface of the both ends of the surface by blade root and integral shroud detects whole blade overall length; At last, matching type line tempte and location, with the light leak situation by the location bound feet, be aided with edge of a knife chi, can judge blade duct position degree, measure the light leak situation in airway cross-section molded line section and come the air flue inner arc to the air flue molded line, steam passage profile tolerance and the size of the air flue back of the body arc, leading edge and trailing edge to make detection.
A kind of gas turbine stator blade comprehensive measuring tool of the present utility model, compare the traditional detection instrument, can carry out comparatively comprehensively that blade parameter detects, have easy to use, directly perceived, quick, can avoid the surface tear that causes because of repeated clamping or the advantage such as weigh wounded.
The above only is preferred embodiment of the present utility model; not in order to limit the utility model; all any modifications of within spirit of the present utility model and principle, doing, be equal to and replace and improvement etc., all should be included within the protection domain of the present utility model.
Claims (9)
1. a gas turbine stator blade comprehensive measuring tool comprises comprehensive measuring tool body and molded line cam group that mutual coupling detects, it is characterized in that:
Described comprehensive measuring tool body comprises base plate (1); Described base plate (1) top is provided with blade root back-up block (2) and integral shroud back-up block (3), described blade root back-up block (2) is the structure that is complementary as positioning reference plane and blade root take the tool back plane of blade root and the side plane of giving vent to anger, this blade root back-up block (2) medial surface is to pass through mutually the consistent circular conical surface of face with blade root, and lateral surface is the circular conical surface consistent with the blade root end face; Described integral shroud back-up block (3) is the structure that is complementary as positioning reference plane and integral shroud take the tool back plane of blade shroud and the side plane of giving vent to anger, this integral shroud back-up block (3) medial surface is to pass through mutually the consistent circular conical surface of face with integral shroud, and lateral surface is the circular conical surface consistent with the integral shroud end face; On the base plate (1) between described blade root back-up block (2) and the integral shroud back-up block (3), be provided with cross section register pin (6);
Described molded line model, comprise air flue inner arc molded line model (7) and air flue back of the body camber line tempte (8), the location bound feet (10) that is provided with airway cross-section molded line section (9) and can be complementary with the side of base plate (1) on air flue inner arc molded line model (7) and the air flue back of the body camber line tempte (8), airway cross-section molded line section (9) on the described air flue inner arc molded line model (7) is complementary with air flue inner arc molded line, and the airway cross-section molded line section (9) on the described air flue back of the body camber line tempte (8) is complementary with air flue back of the body camber line.
2. gas turbine stator blade comprehensive measuring tool as claimed in claim 1, it is characterized in that: also be provided with cover plate I (4) on the described blade root back-up block (2), described cover plate I (4) with can be complementary with blade root after blade root back-up block (2) cooperates, cover plate I (4) medial surface is to pass through mutually the consistent circular conical surface of face with blade root, and lateral surface is the circular conical surface consistent with the blade root end face; Also be provided with cover plate II (5) on the described integral shroud back-up block (3), described cover plate II (5) with can be complementary with integral shroud after integral shroud back-up block (3) cooperates, cover plate II (5) medial surface is to pass through mutually the consistent circular conical surface of face with integral shroud, and lateral surface is the circular conical surface consistent with the blade root end face.
3. gas turbine stator blade comprehensive measuring tool as claimed in claim 2, it is characterized in that: be provided with straight pin (13) on described blade root back-up block (2) and the integral shroud back-up block (3), be provided with the cylindrical hole that is complementary with straight pin (13) on described cover plate I (4) and the cover plate II (5).
4. such as claim 1 or 2 or 3 described gas turbine stator blade comprehensive measuring tools, it is characterized in that: the quantity of described cross section register pin (6) is 2 to 5 groups.
5. gas turbine stator blade comprehensive measuring tool as claimed in claim 4, it is characterized in that: on the base plate (1) between described blade root back-up block (2) and integral shroud back-up block (3), the location bound feet (10) that also is provided with on model back-up block (12) and the described molded line model is complementary.
6. gas turbine stator blade comprehensive measuring tool as claimed in claim 5 is characterized in that: be provided with block (11) on the base plate (1) in described blade root back-up block (2) outside.
7. gas turbine stator blade comprehensive measuring tool as claimed in claim 6 is characterized in that: described cross section register pin (6) is for square or circular, and described block (11) is square or circular.
8. such as claim 1 or 2 or 3 or 5 or 6 or 7 described gas turbine stator blade comprehensive measuring tools, it is characterized in that: be provided with back-up block straight pin (14) on the described base plate (1), be provided with the cylindrical hole of coupling on described blade root back-up block (2) and the integral shroud back-up block (3), described blade root back-up block (2) and integral shroud back-up block (3) are by back-up block straight pin (14) location, and employing bolt (15) is connected with base plate (1).
9. gas turbine stator blade comprehensive measuring tool as claimed in claim 8, it is characterized in that: the both sides of described comprehensive measuring tool body are provided with handle (16).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220251621 CN202648570U (en) | 2012-05-31 | 2012-05-31 | Comprehensive measuring instrument for gas turbine stator blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220251621 CN202648570U (en) | 2012-05-31 | 2012-05-31 | Comprehensive measuring instrument for gas turbine stator blade |
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| Publication Number | Publication Date |
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| CN202648570U true CN202648570U (en) | 2013-01-02 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220251621 Expired - Fee Related CN202648570U (en) | 2012-05-31 | 2012-05-31 | Comprehensive measuring instrument for gas turbine stator blade |
Country Status (1)
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| CN (1) | CN202648570U (en) |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| 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 |
| CN103575182A (en) * | 2013-11-15 | 2014-02-12 | 中国南方航空工业(集团)有限公司 | Section location degree detecting device and section location degree detecting method |
| 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 |
| CN105444652A (en) * | 2015-11-30 | 2016-03-30 | 保定风帆精密铸造制品有限公司 | Detection method for blade of jet propulsion vane |
| CN106524865A (en) * | 2016-12-28 | 2017-03-22 | 无锡透平叶片有限公司 | Universal type steam turbine diaphragm stator blade total length measuring device |
| CN108120364A (en) * | 2017-11-07 | 2018-06-05 | 武汉船用机械有限责任公司 | A kind of blade profile detection instrument |
| CN108613635A (en) * | 2018-06-07 | 2018-10-02 | 国家海洋技术中心 | Marine tidal-current energy generator blade profile dimensional accuracy detection method based on image measurement |
| CN109682333A (en) * | 2018-12-21 | 2019-04-26 | 贵州大学 | A kind of template detected for carbon fibre material in automobile general assembly line |
| CN110440674A (en) * | 2019-08-29 | 2019-11-12 | 中国航发航空科技股份有限公司 | A kind of detection device of the surface profile of stator blade surface channel |
| CN113084706A (en) * | 2021-03-16 | 2021-07-09 | 中国科学院工程热物理研究所 | Automatic measurement method for grinding blade tips of multistage stationary blades of gas compressor |
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- 2012-05-31 CN CN 201220251621 patent/CN202648570U/en not_active Expired - Fee Related
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| Publication number | Priority date | Publication date | Assignee | Title |
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| 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 |
| CN103575182B (en) * | 2013-11-15 | 2017-01-11 | 中国南方航空工业(集团)有限公司 | Section location degree detecting device and section location degree detecting method |
| CN103575182A (en) * | 2013-11-15 | 2014-02-12 | 中国南方航空工业(集团)有限公司 | Section location degree detecting device and section location degree detecting method |
| 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 |
| CN105444652A (en) * | 2015-11-30 | 2016-03-30 | 保定风帆精密铸造制品有限公司 | Detection method for blade of jet propulsion vane |
| CN106524865A (en) * | 2016-12-28 | 2017-03-22 | 无锡透平叶片有限公司 | Universal type steam turbine diaphragm stator blade total length measuring device |
| CN108120364A (en) * | 2017-11-07 | 2018-06-05 | 武汉船用机械有限责任公司 | A kind of blade profile detection instrument |
| CN108613635A (en) * | 2018-06-07 | 2018-10-02 | 国家海洋技术中心 | Marine tidal-current energy generator blade profile dimensional accuracy detection method based on image measurement |
| CN109682333A (en) * | 2018-12-21 | 2019-04-26 | 贵州大学 | A kind of template detected for carbon fibre material in automobile general assembly line |
| CN110440674A (en) * | 2019-08-29 | 2019-11-12 | 中国航发航空科技股份有限公司 | A kind of detection device of the surface profile of stator blade surface channel |
| CN110440674B (en) * | 2019-08-29 | 2021-07-13 | 中国航发航空科技股份有限公司 | Detection apparatus for face profile tolerance of director blade passageway face |
| CN113084706A (en) * | 2021-03-16 | 2021-07-09 | 中国科学院工程热物理研究所 | Automatic measurement method for grinding blade tips of multistage stationary blades of gas compressor |
| CN113084706B (en) * | 2021-03-16 | 2022-03-08 | 中国科学院工程热物理研究所 | Automatic measurement method for grinding blade tips of multistage stationary blades of gas compressor |
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