CN103557812A - Template used for measuring thickness of wall of high pressure turbine blade and application thereof - Google Patents
Template used for measuring thickness of wall of high pressure turbine blade and application thereof Download PDFInfo
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- CN103557812A CN103557812A CN201310492753.4A CN201310492753A CN103557812A CN 103557812 A CN103557812 A CN 103557812A CN 201310492753 A CN201310492753 A CN 201310492753A CN 103557812 A CN103557812 A CN 103557812A
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Abstract
The invention relates to a template used for measuring the thickness of the wall of a high pressure turbine blade and application of the template. According to the technical scheme, the template used for measuring the thickness of the wall of the high pressure turbine blade comprises a concave blade template and a convex blade template; the concave blade template comprises a first shaping plate, a first clamping hook and a first positioning block, and the convex blade template comprises a second shaping plate, a second clamping hook and a second positioning block. According to the template, a wall thickness measuring point of a concave blade of the high pressure turbine blade and a wall thickness measuring point of a convex blade of the high pressure turbine blade can be determined, the thickness of the wall of the high pressure turbine blade can be accurately measured with the template, and the measured thickness of the wall is compared with a standard value to determined whether the high pressure turbine blade is qualified or not.
Description
Technical field
The present invention relates to a kind of measurement module, particularly relate to a kind of for measuring template and the application thereof of high-pressure turbine blade wall thickness.
Background technology
After aeromotor work certain hour, need repairing.Repairing for high-pressure turbine blade during maintenance is particularly important, and as shown in Figure 3, its toponym is leaf basin, blade back, leading edge, listrium to high-pressure turbine blade, and leaf basin is after blade back.The leaf basin of high-pressure turbine blade during repairing, infiltration layer being exceeded standard and blade back part are removed infiltration layer with acid wash, after large area is removed, in leaf basin and the residual infiltration layer dependence of the blade back part surface detail sanding throwing method of repairing of high-pressure turbine blade, remove.By technical requirement, must partly throw the place of repairing to the leaf basin of high-pressure turbine blade and blade back and carry out ultrasonic measurement, whether qualified to judge leaf basin and the blade back part wall thickness at this place.Because leaf basin and the blade back profile of high-pressure turbine blade are complicated, the obvious reference point of nothing in measuring process; And high-pressure turbine blade inner-cavity structure is complicated, rely on universal measurement method cannot determine accurately wall thickness measuring point, do not guarantee the accuracy of the wall thickness value of measurement yet.
Summary of the invention
The invention provides a kind of for measuring the template of high-pressure turbine blade wall thickness, can determine the leaf basin of high-pressure turbine blade and the wall thickness measuring point of blade back, utilize this template can Measurement accuracy high-pressure turbine blade wall thickness, and relatively determine that in standard value whether qualified high-pressure turbine blade is.
Technical scheme of the present invention is as follows:
For measuring a template for high-pressure turbine blade wall thickness, described template comprises leaf basin template and blade back template; Described leaf basin template comprises template one, grab one and locating piece one, it is benchmark that the profile of described template one be take the leaf basin profile coordinate points of standard high-voltage turbo blade (being qualified high-pressure turbine blade), according to the curvature of the leaf basin profile of described standard high-voltage turbo blade, processes; One end that described template one fits in the leading edge of described standard high-voltage turbo blade arranges described grab one, and described grab one can be fitted on the blade back of described standard high-voltage turbo blade; The lower end of described template one arranges described locating piece one, and described locating piece one is fitted on the listrium of described standard high-voltage turbo blade; Described blade back template comprises template two, grab two and locating piece two, and it is benchmark that the profile of described template two be take the blade back profile coordinate points of standard high-voltage turbo blade, according to the curvature of the blade back profile of described standard high-voltage turbo blade, processes; One end that described template two fits in the leading edge of described standard high-voltage turbo blade arranges described grab two, and described grab two can be fitted on the leaf basin of described standard high-voltage turbo blade; The lower end of described grab two arranges described locating piece two, and described locating piece two is fitted on the listrium of described standard high-voltage turbo blade; Described locating piece two is fitted in the position consistency on the listrium that position on the listrium of described standard high-voltage turbo blade and described locating piece one be fitted in described standard high-voltage turbo blade; According to technical requirement, on described standard high-voltage turbo blade, choose a plurality of measurements cross section, then on described measurement cross section, choose a plurality of measurement points; According to the coordinate data of described measurement point, at described leaf basin template and blade back template profile marking round dot, the described round dot of take is got through hole as the center of circle in described leaf basin template and blade back template, makes measured hole.
Preferred version is: described for measuring the template of high-pressure turbine blade wall thickness, described measurement cross section is 5, the described measurement point of measuring described in each on cross section is 6, measures the corresponding described measured hole of described measurement point on cross section in described leaf basin template and above blade back template, respectively have 3 described in each.
The invention also discloses above-mentioned for the template of measuring high-pressure turbine blade wall thickness in the application of measuring the wall thickness of high-pressure turbine blade, described template is applied to measure in the measuring method of wall thickness of high-pressure turbine blade, described measuring method comprises the steps:
(1) utilize the wall thickness of described template measurement standard high-pressure turbine blade
Described leaf basin template and blade back template are enclosed within respectively on described standard high-voltage turbo blade, see through described measured hole described standard high-voltage turbo blade is marked to thickness measuring point, with audiogage, measure the wall thickness of described thickness measuring point, and be recorded as the standard value of the wall thickness of described standard high-voltage turbo blade;
(2) utilize described template to measure the wall thickness of high-pressure turbine blade to be measured
Described leaf basin template and blade back template are enclosed within respectively on described high-pressure turbine blade to be measured, see through described measured hole described high-pressure turbine blade to be measured is marked to thickness measuring point, with audiogage, measure the wall thickness of described thickness measuring point, and be recorded as the measured value of the wall thickness of high-pressure turbine blade to be measured;
(3) judge that whether qualified high-pressure turbine blade to be measured is
The margin tolerance that described standard value is the wall thickness of benchmark regulation high-pressure turbine blade is take in technical requirement, and described measured value is in described margin tolerance, qualified, and described measured value is not in described margin tolerance, defective.
Technique effect of the present invention:
1, the present invention has fundamentally solved high-pressure turbine blade wall thickness measuring problem, and high-pressure turbine blade wall thickness measuring meets blade detection method by template can meet technical requirement, and measuring technique method is feasible, can be used for produced on-site.The blank of domestic measurement blade wall thickness has been filled up in the application of this technology, has guaranteed the technological difficulties such as machining precision of part.The measuring method good manufacturability simultaneously adopting, workable, improved greatly the quality that high-pressure turbine blade is repaired.
If leaf destruction fault Er Fan factory appears in 2 engines in flight course, overhaul cost is very expensive, by the application of measuring technique, guaranteed the requirement of high-pressure turbine blade wall thickness, that has also reduced engine returns factory's number of times, greatly reduces engine overhaul cost.Break away from the situation of frequent replacing high-pressure turbine blade, guaranteed overhaul manufacturing schedule.Therefore the application of high-pressure turbine blade measuring technique has great Social benefit and economic benefit.
Accompanying drawing explanation
Fig. 1 is leaf basin formwork structure schematic diagram;
Fig. 2 is blade back formwork structure schematic diagram;
Fig. 3 is high-pressure turbine blade position schematic diagram;
Fig. 4 is that standard high-voltage turbo blade is measured schematic cross-section;
Fig. 5 is the measurement point coordinate schematic diagram that standard high-voltage turbo blade is measured cross section.
In figure: 1 is that template one, 2 is that grab one, 3 is that locating piece one, 4 is measured hole, 5 is that template two, 6 is that grab two, 7 is that locating piece two, 8 is blade back, and 9 is leading edge, and 10 is listrium.
Embodiment
As illustrated in fig. 1 and 2, a kind of for measuring the template of high-pressure turbine blade wall thickness, described template comprises leaf basin template and blade back template; Described leaf basin template comprises template 1, grab 1 and locating piece 1, it is benchmark that the profile of described template 1 be take the leaf basin profile coordinate points of standard high-voltage turbo blade, curvature according to the leaf basin profile of described standard high-voltage turbo blade processes, and the leaf basin profile of the profile of described template 1 and standard high-voltage turbo blade can fit tightly; One end that described template 1 fits in the leading edge 9 of described standard high-voltage turbo blade arranges described grab 1, and described grab 1 can be fitted on the blade back 8 of described standard high-voltage turbo blade; The lower end of described template 1 arranges described locating piece 1, and described locating piece 1 is fitted on the listrium 10 of described standard high-voltage turbo blade; Described blade back template comprises template 25, grab 26 and locating piece 27, it is benchmark that the profile of described template 25 be take the blade back 8 profile coordinate points of standard high-voltage turbo blade, curvature according to the blade back of described standard high-voltage turbo blade 8 profiles processes, and blade back 8 profiles of the profile of described template 25 and described standard high-voltage turbo blade can fit tightly; One end that described template 25 fits in the leading edge 9 of described standard high-voltage turbo blade arranges described grab 26, and described grab 26 can be fitted on the leaf basin of described standard high-voltage turbo blade; The lower end of described grab 26 arranges described locating piece 27, and described locating piece 27 is fitted on the listrium 10 of described standard high-voltage turbo blade; Described locating piece 27 is fitted in the position consistency on the listrium 10 that position on the listrium 10 of described standard high-voltage turbo blade and described locating piece 1 be fitted in described standard high-voltage turbo blade.
As shown in Figure 4, according to technical requirement, on described standard high-voltage turbo blade, equidistantly choose A1～A5 totally 5 measurement cross sections; As shown in Figure 5, at each, measure on cross section, according to technical requirement, choose δ 1～δ 6 totally 6 measurement points, according to the coordinate data x1～x3 of δ 1～δ 3 measurement points, at described leaf basin template profile subscript, carve 3 round dots, 3 round dots of take are got through hole as the center of circle in described leaf basin template, make measured hole 4, in described leaf basin template, make altogether 15 measured holes 4; According to the coordinate data x4～x6 of δ 4～δ 6 measurement points, at blade back template profile subscript, carve 3 round dots, 3 round dots of take are got through hole as the center of circle in described leaf basin template, make measured hole 4, make altogether 15 measured holes 4 in described blade back template.
Utilize template as above to measure the measuring method of the wall thickness of high-pressure turbine blade, comprise the steps:
(1) utilize the wall thickness of described template measurement standard high-pressure turbine blade
Described leaf basin template and blade back template are enclosed within respectively on described standard high-voltage turbo blade, see through described measured hole described standard high-voltage turbo blade is marked to thickness measuring point, with audiogage, measure the wall thickness of described thickness measuring point, and be recorded as the standard value of the wall thickness of described standard high-voltage turbo blade;
(2) utilize described template to measure the wall thickness of high-pressure turbine blade to be measured
Described leaf basin template and blade back template are enclosed within respectively on described high-pressure turbine blade to be measured, see through described measured hole described high-pressure turbine blade to be measured is marked to thickness measuring point, with audiogage, measure the wall thickness of described thickness measuring point, and be recorded as the measured value of the wall thickness of high-pressure turbine blade to be measured;
(3) judge that whether qualified high-pressure turbine blade to be measured is
The margin tolerance that described standard value is the wall thickness of benchmark regulation high-pressure turbine blade is take in technical requirement, and described measured value is in described margin tolerance, qualified, and described measured value is not in described margin tolerance, defective.
Claims (3)
1. for measuring a template for high-pressure turbine blade wall thickness, it is characterized in that, described template comprises leaf basin template and blade back template;
Described leaf basin template comprises template one, grab one and locating piece one, and it is benchmark that the profile of described template one be take the leaf basin profile coordinate points of standard high-voltage turbo blade, according to the curvature of the leaf basin profile of described standard high-voltage turbo blade, processes; One end that described template one fits in the leading edge of described standard high-voltage turbo blade arranges described grab one, and described grab one can be fitted on the blade back of described standard high-voltage turbo blade; The lower end of described template one arranges described locating piece one, and described locating piece one is fitted on the listrium of described standard high-voltage turbo blade;
Described blade back template comprises template two, grab two and locating piece two, and it is benchmark that the profile of described template two be take the blade back profile coordinate points of standard high-voltage turbo blade, according to the curvature of the blade back profile of described standard high-voltage turbo blade, processes; One end that described template two fits in the leading edge of described standard high-voltage turbo blade arranges described grab two, and described grab two can be fitted on the leaf basin of described standard high-voltage turbo blade; The lower end of described grab two arranges described locating piece two, and described locating piece two is fitted on the listrium of described standard high-voltage turbo blade; Described locating piece two is fitted in the position consistency on the listrium that position on the listrium of described standard high-voltage turbo blade and described locating piece one be fitted in described standard high-voltage turbo blade;
According to technical requirement, on described standard high-voltage turbo blade, choose a plurality of measurements cross section, then on described measurement cross section, choose a plurality of measurement points; According to the coordinate data of described measurement point, at described leaf basin template and blade back template profile marking round dot, the described round dot of take is got through hole as the center of circle in described leaf basin template and blade back template, makes measured hole.
2. according to claim 1 for measuring the template of high-pressure turbine blade wall thickness, it is characterized in that, described measurement cross section is 5, the described measurement point of measuring described in each on cross section is 6, measures the corresponding described measured hole of described measurement point on cross section in described leaf basin template and above blade back template, respectively have 3 described in each.
3. as claimed in claim 1 for measuring the template of high-pressure turbine blade wall thickness in the application of the wall thickness of measurement high-pressure turbine blade, it is characterized in that, described template is applied to measure in the measuring method of wall thickness of high-pressure turbine blade, described measuring method comprises the steps:
(1) utilize the wall thickness of described template measurement standard high-pressure turbine blade
Described leaf basin template and blade back template are enclosed within respectively on described standard high-voltage turbo blade, see through described measured hole described standard high-voltage turbo blade is marked to thickness measuring point, with audiogage, measure the wall thickness of described thickness measuring point, and be recorded as the standard value of the wall thickness of described standard high-voltage turbo blade;
(2) utilize described template to measure the wall thickness of high-pressure turbine blade to be measured
Described leaf basin template and blade back template are enclosed within respectively on described high-pressure turbine blade to be measured, see through described measured hole described high-pressure turbine blade to be measured is marked to thickness measuring point, with audiogage, measure the wall thickness of described thickness measuring point, and be recorded as the measured value of the wall thickness of high-pressure turbine blade to be measured;
(3) judge that whether qualified high-pressure turbine blade to be measured is
The margin tolerance that described standard value is the wall thickness of benchmark regulation high-pressure turbine blade is take in technical requirement, and described measured value is in described margin tolerance, qualified, and described measured value is not in described margin tolerance, defective.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201310492753.4A CN103557812A (en) | 2013-10-19 | 2013-10-19 | Template used for measuring thickness of wall of high pressure turbine blade and application thereof |
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| CN201310492753.4A CN103557812A (en) | 2013-10-19 | 2013-10-19 | Template used for measuring thickness of wall of high pressure turbine blade and application thereof |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109263036A (en) * | 2018-11-27 | 2019-01-25 | 安徽应流航源动力科技有限公司 | A kind of preparation method of turbo blade wall thickness detection control tooling |
| CN109579684A (en) * | 2018-11-07 | 2019-04-05 | 昌河飞机工业（集团）有限责任公司 | A method of pasting tire degree in detection wall plate parts intermediate region |
| CN110926384A (en) * | 2019-11-19 | 2020-03-27 | 中国人民解放军第五七一九工厂 | Method for detecting wall thickness of high-pressure turbine blade of turbojet engine by ultrasonic waves |
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| JP2001280600A (en) * | 2000-03-31 | 2001-10-10 | Hitachi Ltd | Thinning management system |
| JP2002081926A (en) * | 2000-09-06 | 2002-03-22 | Sumitomo Kinzoku Technol Kk | Ultrasonic thickness measuring method and ultrasonic thickness measuring device |
| KR20080086116A (en) * | 2007-03-21 | 2008-09-25 | 에스케이에너지 주식회사 | Device for measuring thickness of inner layer of pressure vessel and measuring method |
| CN201731867U (en) * | 2009-12-23 | 2011-02-02 | 沈阳黎明航空发动机(集团)有限责任公司 | Special template for detecting wall thickness of working blades of complex hollow turbine |
| CN102109336A (en) * | 2009-12-23 | 2011-06-29 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for detecting wall thickness of working blade of complex hollow turbine |
| CN201983773U (en) * | 2010-12-21 | 2011-09-21 | 中国南方航空工业(集团)有限公司 | Blade wall thickness detection clamp |
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2013
- 2013-10-19 CN CN201310492753.4A patent/CN103557812A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2001280600A (en) * | 2000-03-31 | 2001-10-10 | Hitachi Ltd | Thinning management system |
| JP2002081926A (en) * | 2000-09-06 | 2002-03-22 | Sumitomo Kinzoku Technol Kk | Ultrasonic thickness measuring method and ultrasonic thickness measuring device |
| KR20080086116A (en) * | 2007-03-21 | 2008-09-25 | 에스케이에너지 주식회사 | Device for measuring thickness of inner layer of pressure vessel and measuring method |
| CN201731867U (en) * | 2009-12-23 | 2011-02-02 | 沈阳黎明航空发动机(集团)有限责任公司 | Special template for detecting wall thickness of working blades of complex hollow turbine |
| CN102109336A (en) * | 2009-12-23 | 2011-06-29 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for detecting wall thickness of working blade of complex hollow turbine |
| CN201983773U (en) * | 2010-12-21 | 2011-09-21 | 中国南方航空工业(集团)有限公司 | Blade wall thickness detection clamp |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109579684A (en) * | 2018-11-07 | 2019-04-05 | 昌河飞机工业（集团）有限责任公司 | A method of pasting tire degree in detection wall plate parts intermediate region |
| CN109263036A (en) * | 2018-11-27 | 2019-01-25 | 安徽应流航源动力科技有限公司 | A kind of preparation method of turbo blade wall thickness detection control tooling |
| CN110926384A (en) * | 2019-11-19 | 2020-03-27 | 中国人民解放军第五七一九工厂 | Method for detecting wall thickness of high-pressure turbine blade of turbojet engine by ultrasonic waves |
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Application publication date: 20140205 |
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