CN102109336A - Method for detecting wall thickness of working blade of complex hollow turbine - Google Patents

Method for detecting wall thickness of working blade of complex hollow turbine Download PDF

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Publication number
CN102109336A
CN102109336A CN 200910248662 CN200910248662A CN102109336A CN 102109336 A CN102109336 A CN 102109336A CN 200910248662 CN200910248662 CN 200910248662 CN 200910248662 A CN200910248662 A CN 200910248662A CN 102109336 A CN102109336 A CN 102109336A
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CN
China
Prior art keywords
blade
thickness
point
template
complexity
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CN 200910248662
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Chinese (zh)
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CN102109336B (en
Inventor
彭志江
于颖
韩大平
史凤岭
唐晓东
张泽海
邹建波
孙革
Original Assignee
沈阳黎明航空发动机(集团)有限责任公司
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Priority to CN 200910248662 priority Critical patent/CN102109336B/en
Publication of CN102109336A publication Critical patent/CN102109336A/en
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Publication of CN102109336B publication Critical patent/CN102109336B/en

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Abstract

The invention relates to a method for detecting the wall thickness of a working blade of a complex hollow turbine. The blade is detected by an ultrasonic thickness measuring method and a special template; and the template comprises a blade basin template and a blade back template. The method for detecting the wall thickness of the blade comprises the following steps of: selecting two detection points, namely a point P and a point Q on the air inlet side of the blade; on the premise that the wall thickness of the point P or/and the point Q is detected to be qualified, selecting a point R on an internal channel of a margin plate of the blade; relatively fixing the blade and the blade basin template or/and the blade back template by using the points P, Q and R as positioning points, and finding each monitoring point on a blade basin or/and a blade back of the blade through a detection hole (3); and measuring the wall thickness of the blade basin or/and the blade back of the blade respectively. The method is high in operability and convenient, the position of a blade wall thickness measuring point is accurate, a wall thickness measured value is accurate, and the qualification rate and accuracy can reach 100 percent.

Description

The hollow moving turbine blade wall thickness detecting of a kind of complexity method
Technical field:
The present invention relates to not have surplus, the detection technique of complexity, hollow high-pressure turbine working blade foundry goods, finished product blade wall thickness, the hollow moving turbine blade wall thickness detecting of a kind of complexity method is provided especially.
Background technology:
In the prior art, the hollow blade that certain overhaul machine high-pressure turbine working blade belongs to convection current impact, the compound air cooling of air film is the small-sized complex structural member of a kind of thin-walled (wall thickness variable cross section), inner chamber complexity, plane of bending structure; Blade is a hollow-core construction, and cavity shape leaf basin, blade back are the bar shaped overlapping mode, and the transversal section of bar shaped is a sphere, and rib width is very narrow.
The inner-cavity structure of this complexity makes blade foundry goods difficulty when carrying out wall thickness detecting very big.Therefore, people catch at good, the workable complicated hollow moving turbine blade wall thickness detecting method of a kind of technique effect.
Summary of the invention:
The purpose of this invention is to provide good, the workable complicated hollow moving turbine blade wall thickness detecting method of a kind of technique effect.
The invention provides the hollow moving turbine blade wall thickness detecting of a kind of complexity method, utilize the ultrasonic thickness test method to detect; It is characterized in that:
Use dedicated templates that blade is detected; Described template specifically is divided into two kinds of leaf basin template and blade back templates, and its two structural requirement is: described main template body partly is template matrix 1, the contour shape of described template matrix 1 and size and blade adapt (its thickness does not have strict demand); Described template matrix 1 is provided with and detects hole 3, and the concrete position in described detection hole 3 and number meet blade and detect requirement, and detecting hole 3 numbers is 4~100, and each detects hole 3 and is evenly arranged on the template matrix 1;
The specific requirement of the hollow moving turbine blade wall thickness detecting of described complexity method is: at first select 2 check points at the blade leading edge: P point and Q point; Detect these 2 one or both of the wall thickness of locating then;
At the P point or/and under the qualified prerequisite of the wall thickness detecting that Q is ordered; On blade listrium internal channel, select 1 R; Utilize 3 of P, Q, R as anchor point with blade and described leaf basin template or/and blade back template relative fixed, and find out the leaf basin of blade or/and each monitoring point on the blade back by means of detecting hole 3; Afterwards respectively to the leaf basin of blade or/and the wall thickness of blade back measure.
The hollow moving turbine blade wall thickness detecting of complexity of the present invention method, the also claimed preferred content of number down:
In the hollow moving turbine blade wall thickness detecting of the described complexity method, 2 two ends at the distance leading edge of P, Q are not less than in the scope of 3mm and select, and the distance between 2 is not less than 5mm;
The R point is not less than 3mm apart from leading edge or exhaust limit.
Further preferred content require be: in the hollow moving turbine blade wall thickness detecting of the described complexity method, 2 two ends at the distance leading edge of P, Q are not less than in the scope of 5mm and select; The R point is not less than 5mm apart from leading edge or exhaust limit.
In the hollow moving turbine blade wall thickness detecting of the described complexity method, on perpendicular to the blade major axes orientation, 4 measurement cross sections are set at least, measure the δ on each cross section respectively 1, δ 2, δ 3, δ 4, δ 5min, δ 6min, δ 7, m, n amount at least 9 points; Each is measured the cross section and is parallel to each other.
In the hollow moving turbine blade wall thickness detecting of the described complexity method, also be provided with fixed sturcture 2 on the employed dedicated templates, described fixed sturcture 2 specifically with P, Q, 3 corresponding settings of R, be used for fixing the relative position relation of dedicated templates and tested blade.
Very complicated because of the blade inner-cavity structure, when blade is carried out wall thickness detecting, need on blade, need to select three anchor points, dedicated templates is positioned on blade, could measure the blade wall thickness.
Because the blade inner-cavity structure is very complicated, so the detection of blade wall thickness seems particularly important and crucial.By designing requirement, every blade A 1~A 547 points need be detected in the cross section, and whether the measured value of each point accurately depends on the correctness of wall thickness measuring point position.Adopt this process can solve the blade casting section thickness and detect difficult problem.
What need Special attention will be given to is that among the present invention, the use of dedicated templates is an outstanding innovative point; The detection method of the present invention that cooperates dedicated templates and use also has novelty.
The present invention takes blade leading edge (2 points), blade back listrium internal channel (a bit) location, uses dedicated templates and cooperates ultrasonic method to detect the blade wall thickness, and not only the position of blade wall thickness measurement point is accurate, and its wall thickness measuring value is accurate.
In terms of existing technologies, depend on external import in the past, grasp after this technology, can solve problem under one's control, satisfy the active demand of engine overhaul, reduce its overhaul cost at certain overhaul machine high-pressure turbine working blade.
Utilize blade leading edge (2 points), listrium internal channel (a bit) location, detect the blade wall thickness, workable, convenient, the position of blade wall thickness measurement point is accurate, the wall thickness measuring value is accurate, qualified, accuracy rate can reach 100%.
According to this process, promptly utilize blade leading edge P, Q 2 points, 1 R location of blade back listrium internal channel is used dedicated templates and is cooperated ultrasonic method to detect the blade wall thickness, the position of blade wall thickness measurement point is accurate, the wall thickness measuring value is accurate, qualified, accuracy rate can reach 100%.
Description of drawings:
Fig. 1 is blade A 1~A 5The position view of cross section wall thickness measurement point;
Fig. 2 is the position view of three anchor points on the blade foundry goods;
Fig. 3 is three point measurement method leading edge δ 7The wall thickness measuring principle schematic;
Fig. 4 is one of leaf basin formwork structure synoptic diagram;
Fig. 5 is two of a leaf basin formwork structure synoptic diagram;
Fig. 6 is one of leaf basin formwork structure synoptic diagram;
Fig. 7 is two of a leaf basin formwork structure synoptic diagram;
Fig. 8 is blade blade A 1~A 5One of sectional view;
Fig. 9 is blade blade A 1~A 5Two of sectional view.
Embodiment:
Embodiment 1
The hollow moving turbine blade wall thickness detecting of a kind of complexity method (shown in accompanying drawing 1~9), carry out following operation successively:
Fig. 2 is seen in design and selection that blade casting section thickness detection P, Q and R are ordered.
Blade foundry goods P, Q two place's wall thickness, δ 7Fig. 3 is seen in the qualified detection of wall thickness.
P, the Q two wall thickness δ of place 7After qualified, determine the position of the wall thickness measuring point on the blade to detect the blade wall thickness then with the dedicated templates of Fig. 4.
Specific requirement is as follows:
1) position of blade foundry goods blade wall thickness measuring point: blade foundry goods blade A 1~A 5Five cross section wall thickness measurement points have δ 1, δ 2, δ 3, δ 4, δ 5min, δ 6min, δ 7, m, n etc. amount to 45 points, Fig. 1 is seen in the position of each cross section wall thickness measurement point.
2) blade casting section thickness detection and location technology: it is P point and Q point that three anchor points on the blade are chosen in two of leading edges, and one of listrium internal channel is the R point, sees Fig. 2.
3), detect the wall thickness δ of 2 of leading edge P, Q with three point measurement methods 7: after three anchor points on blade are determined,, earlier blade foundry goods leading edge P, Q two A of place, B, C are measured (the method is called three point measurement methods) at 3, its objective is and measure B point δ exactly according to shown in Figure 3 7Thickness.
4) determining and detection of blade wall thickness measuring point position: leading edge wall thickness δ 7Detect qualified after, with the dedicated templates of Fig. 4, lean against respectively on the anchor point of blade P, Q, R, see through the aperture of Φ 2mm on the dedicated templates with crayon, the position of leaf basin, blade back wall thickness check point is decided, respectively the wall thickness of blade and blade basin, blade back is measured then.
According to this process, promptly utilize blade leading edge P, Q 2 points, 1 R location of blade back listrium internal channel is used dedicated templates and is cooperated ultrasonic method to detect the blade wall thickness, the position of blade wall thickness measurement point is accurate, the wall thickness measuring value is accurate, qualified, accuracy rate can reach 100%.
Now involved relevant device is described in detail as follows:
1, adopt " three point method " to measure leading edge δ among Fig. 3 7The employed locating template figure of wall thickness pattern in kind see Fig. 4~7.
2, the positioning principle process of using dedicated templates to carry out auxiliary positioning is: 1. locating template and blade are close to by anchor point on Fig. 2 with locating template earlier, with marking pen the measurement point on each cross section of blade leading edge is seen through aperture point on the locating template on blade (leading edge), this point is exactly the B point; 2. then locating template is taken off, find out A, C 2 points again near the B point, the leading edge of blade is thrown repaiied, deburring YT-603 type supersonic thickness meter wall-thickness measurement is thrown on the limit, also will measure the size of each cross section outer mold surface simultaneously with the model of leading edge; 3. leading edge B point δ 7Wall thickness qualified after, again locating template and blade are close to, see through aperture point on the locating template blade on the blade of blade with marking pen; 4. use YT-603 type supersonic thickness meter to measure the wall thickness of measurement point on the blade of blade again.
3, measure the used utility appliance of blade wall thickness:
(1) YT-603 type supersonic thickness meter (Russian import);
(2) C1-114/1 type oscillograph is used with YT-603 type supersonic thickness meter, is used for measuring the big arc surface of radius small curve specially.
(3) with three of the test pieces of blade same material, thickness is respectively 0.5mm, 1.0mm, 4.0mm.
(4) glycerine (glycerine) couplant.
4, ultrasonic thickness test principle:
(1) preoperative preparation: dip in the probe of supersonic thickness meter and to get an amount of glycerine (glycerine) couplant and in 0.5mm, 1.0mm and three test pieces of 4.0mm, proofread and correct respectively, again the measurement point of blade is tested after qualified (referring to that the oscillographic reading of C1-114/1 type equates with above three numerical value), observe the oscillographic reading of thicknessmeter while surveying, and outcome record is got off.
(2) blade leading edge A 1~A 5Cross section δ 7The measurement of wall thickness:
Use the blade back template at A earlier 1~A 5Each δ of cross section 7Find out A, B, C 3 points on the sectional position of point, see Fig. 3, and note measured value, throw while measuring and repair, up to all δ 7Till the some wall thickness is qualified.
(3) blade blade A 1~A 5The measurement of cross section wall thickness:
With leading edge R 1Profile and wall thickness δ 7The circular hole that all qualified blade foundry goods sees through template with wall thickness measuring point with the marking pen of redness or black at leaf basin and blade back respectively with template identifies the position of tested point, A 1~A 5Fig. 1 is seen in the position of cross section wall thickness measurement point, notes the wall thickness measuring value simultaneously.
(4) A 1~A 5Sectional view 8,9.
Very complicated because of the blade inner-cavity structure, when blade is carried out wall thickness detecting, need on blade, need to select three anchor points, dedicated templates is positioned on blade, could measure the blade wall thickness.
Because the blade inner-cavity structure is very complicated, so the detection of blade wall thickness seems particularly important and crucial.By designing requirement, every blade A 1~A 545 points need be detected in the cross section, and whether the measured value of each point accurately depends on the correctness of wall thickness measuring point position.Adopt this process can solve the blade casting section thickness and detect difficult problem.
Embodiment 2
The hollow moving turbine blade wall thickness detecting of a kind of complexity method utilizes the ultrasonic thickness test method to detect; Its technical essential is:
Use dedicated templates that blade is detected; Described template specifically is divided into two kinds of leaf basin template and blade back templates, and its two structural requirement is: described main template body partly is template matrix 1, the contour shape of described template matrix 1 and size and blade adapt (its thickness does not have strict demand); Described template matrix 1 is provided with and detects hole 3, and the concrete position in described detection hole 3 and number meet blade and detect requirement, and detecting hole 3 numbers is 4~100, and each detects hole 3 and is evenly arranged on the template matrix 1;
The specific requirement of the hollow moving turbine blade wall thickness detecting of described complexity method is: at first select 2 check points at the blade leading edge: P point and Q point; Detect these 2 one or both of the wall thickness of locating then;
At the P point or/and under the qualified prerequisite of the wall thickness detecting that Q is ordered; On blade listrium internal channel, select 1 R; Utilize 3 of P, Q, R as anchor point with blade and described leaf basin template or/and blade back template relative fixed, and find out the leaf basin of blade or/and each monitoring point on the blade back by means of detecting hole 3; Afterwards respectively to the leaf basin of blade or/and the wall thickness of blade back measure.
In the hollow moving turbine blade wall thickness detecting of the described complexity method, 2 two ends at the distance leading edge of P, Q are not less than in the scope of 3mm and select, and the distance between 2 is not less than 5mm;
The R point is not less than 3mm apart from leading edge or exhaust limit.
In the hollow moving turbine blade wall thickness detecting of the described complexity method, on perpendicular to the blade major axes orientation, 4 measurement cross sections are set at least, measure the δ on each cross section respectively 1, δ 2, δ 3, δ 4, δ 5min, δ 6min, δ 7, m, n amount at least 9 points; Each is measured the cross section and is parallel to each other.
In the hollow moving turbine blade wall thickness detecting of the described complexity method, also be provided with fixed sturcture 2 on the employed dedicated templates, described fixed sturcture 2 specifically with P, Q, 3 corresponding settings of R, be used for fixing the relative position relation of dedicated templates and tested blade.
Very complicated because of the blade inner-cavity structure, when blade is carried out wall thickness detecting, need on blade, need to select three anchor points, dedicated templates is positioned on blade, could measure the blade wall thickness.
Because the blade inner-cavity structure is very complicated, so the detection of blade wall thickness seems particularly important and crucial.By designing requirement, every blade A 1~A 547 points need be detected in the cross section, and whether the measured value of each point accurately depends on the correctness of wall thickness measuring point position.Adopt this process can solve the blade casting section thickness and detect difficult problem.
What need Special attention will be given to is that in the present embodiment, the use of dedicated templates is an outstanding innovative point; The detection method of the present invention that cooperates dedicated templates and use also has novelty.
Present embodiment is taked blade leading edge (2 points), blade back listrium internal channel (a bit) location, uses dedicated templates and cooperates ultrasonic method to detect the blade wall thickness, and not only the position of blade wall thickness measurement point is accurate, and its wall thickness measuring value is accurate.
In terms of existing technologies, depend on external import in the past, grasp after this technology, can solve problem under one's control, satisfy the active demand of engine overhaul, reduce its overhaul cost at certain overhaul machine high-pressure turbine working blade.
Utilize blade leading edge (2 points), listrium internal channel (a bit) location, detect the blade wall thickness, workable, convenient, the position of blade wall thickness measurement point is accurate, the wall thickness measuring value is accurate, qualified, accuracy rate can reach 100%.
According to this process, promptly utilize blade leading edge P, Q 2 points, 1 R location of blade back listrium internal channel is used dedicated templates and is cooperated ultrasonic method to detect the blade wall thickness, the position of blade wall thickness measurement point is accurate, the wall thickness measuring value is accurate, qualified, accuracy rate can reach 100%.
Embodiment 3
Present embodiment and embodiment 2 contents are basic identical, and its difference is:
In the hollow moving turbine blade wall thickness detecting of the described complexity method, on perpendicular to the blade major axes orientation, 5 measurement cross sections are set, measure the δ on each cross section respectively 1, δ 2, δ 3, δ 4, δ 5min, δ 6min, δ 7, m, n amount at least 9 points; Each is measured the cross section and is parallel to each other.
2 two ends at the distance leading edge of P, Q are not less than in the scope of 5mm and select; The R point is not less than 5mm apart from leading edge or exhaust limit.

Claims (5)

1. the hollow moving turbine blade wall thickness detecting of a complexity method utilizes the ultrasonic thickness test method to detect; It is characterized in that:
Use dedicated templates that blade is detected; Described template specifically is divided into two kinds of leaf basin template and blade back templates, and its two structural requirement is: described main template body partly is template matrix (1), and the contour shape of described template matrix (1) and size adapt with blade; Described template matrix (1) is provided with and detects hole (3), and the concrete position in described detection hole (3) and number meet blade and detect requirement, and detecting hole (3) number is 4~100, and each detects hole (3) and is evenly arranged on the template matrix (1);
The specific requirement of the hollow moving turbine blade wall thickness detecting of described complexity method is: at first select 2 check points at the blade leading edge: P point and Q point; Detect these 2 one or both of the wall thickness of locating then;
At the P point or/and under the qualified prerequisite of the wall thickness detecting that Q is ordered; On blade listrium internal channel, select 1 R; Utilize 3 of P, Q, R as anchor point with blade and described leaf basin template or/and blade back template relative fixed, and find out the leaf basin of blade or/and each monitoring point on the blade back by means of detecting hole (3); Afterwards respectively to the leaf basin of blade or/and the wall thickness of blade back measure.
2. according to the hollow moving turbine blade wall thickness detecting of the described complexity of claim 1 method, it is characterized in that: in the hollow moving turbine blade wall thickness detecting of the described complexity method, 2 two ends at the distance leading edge of P, Q are not less than in the scope of 3mm and select, and the distance between 2 is not less than 5mm;
The R point is not less than 3mm apart from leading edge or exhaust limit.
3. according to the hollow moving turbine blade wall thickness detecting of the described complexity of claim 2 method, it is characterized in that: in the hollow moving turbine blade wall thickness detecting of the described complexity method, 2 two ends at the distance leading edge of P, Q are not less than in the scope of 5mm and select;
The R point is not less than 5mm apart from leading edge or exhaust limit.
4. according to claim 1 or the hollow moving turbine blade wall thickness detecting of 2 or 3 described complexity method, it is characterized in that: in the hollow moving turbine blade wall thickness detecting of the described complexity method, on perpendicular to the blade major axes orientation, 4 measurement cross sections are set at least, measure the δ on each cross section respectively 1, δ 2, δ 3, δ 4, δ 5min, δ 6min, δ 7, m, n amount to 9 points; Each is measured the cross section and is parallel to each other.
5. according to the hollow moving turbine blade wall thickness detecting of the described complexity of claim 4 method, it is characterized in that: in the hollow moving turbine blade wall thickness detecting of the described complexity method, also be provided with fixed sturcture (2) on the employed dedicated templates, described fixed sturcture (2) specifically with P, Q, 3 corresponding settings of R, be used for fixing the relative position relation of dedicated templates and tested blade.
CN 200910248662 2009-12-23 2009-12-23 Method for detecting wall thickness of working blade of complex hollow turbine CN102109336B (en)

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Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103557812A (en) * 2013-10-19 2014-02-05 沈阳黎明航空发动机(集团)有限责任公司 Template used for measuring thickness of wall of high pressure turbine blade and application thereof
CN103673829A (en) * 2013-12-15 2014-03-26 无锡透平叶片有限公司 Method for quickly detecting thickness of lower surface of blade in high-temperature thermal state
CN104457501A (en) * 2014-11-29 2015-03-25 无锡透平叶片有限公司 Method for rapidly detecting thickness size of section of vane
CN106500640A (en) * 2016-10-11 2017-03-15 中国航空工业集团公司北京航空精密机械研究所 A kind of method calibrated by engine blade measurement apparatus
CN107990854A (en) * 2017-12-01 2018-05-04 中国航发动力股份有限公司 A kind of multi-joint guide vane ultrasonic thickness measurement method of engine
CN109373944A (en) * 2018-12-04 2019-02-22 湖南大学 A kind of air foil bearing air-film thickness measuring system based on ultrasound and method
CN109613027A (en) * 2018-11-29 2019-04-12 中国航发沈阳黎明航空发动机有限责任公司 To the process unit and method of turbo blade leading edge air film hole X-ray detection
CN110296644A (en) * 2019-06-24 2019-10-01 中国航发动力股份有限公司 The tooling and method of variable quantity are repaired in a kind of measurement blade throwing
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

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2900471B1 (en) * 2006-04-26 2008-12-26 Snecma Sa MEASUREMENT OF WALL THICKNESS, IN PARTICULAR OF DAWN, BY CURRENTS OF FOUCAULT

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103557812A (en) * 2013-10-19 2014-02-05 沈阳黎明航空发动机(集团)有限责任公司 Template used for measuring thickness of wall of high pressure turbine blade and application thereof
CN103673829A (en) * 2013-12-15 2014-03-26 无锡透平叶片有限公司 Method for quickly detecting thickness of lower surface of blade in high-temperature thermal state
CN104457501A (en) * 2014-11-29 2015-03-25 无锡透平叶片有限公司 Method for rapidly detecting thickness size of section of vane
CN104457501B (en) * 2014-11-29 2017-07-28 无锡透平叶片有限公司 A kind of method of quick detection blade sectional thickness size
CN106500640A (en) * 2016-10-11 2017-03-15 中国航空工业集团公司北京航空精密机械研究所 A kind of method calibrated by engine blade measurement apparatus
CN107990854A (en) * 2017-12-01 2018-05-04 中国航发动力股份有限公司 A kind of multi-joint guide vane ultrasonic thickness measurement method of engine
CN109613027A (en) * 2018-11-29 2019-04-12 中国航发沈阳黎明航空发动机有限责任公司 To the process unit and method of turbo blade leading edge air film hole X-ray detection
CN109373944A (en) * 2018-12-04 2019-02-22 湖南大学 A kind of air foil bearing air-film thickness measuring system based on ultrasound and method
CN110296644A (en) * 2019-06-24 2019-10-01 中国航发动力股份有限公司 The tooling and method of variable quantity are repaired in a kind of measurement blade throwing
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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Address after: 110043 Dong TA street, Dadong District, Shenyang, Liaoning Province, No. 6

Patentee after: Chinese Hangfa Shenyang Liming Aero engine limited liability company

Address before: 110043 Dong TA street, Dadong District, Shenyang, Liaoning Province, No. 6

Patentee before: Liming Aeroplane Engine (Group) Co., Ltd., Shenyang City