CN106596089A - Aero-engine hollow blade core space flow adjusting and measuring method - Google Patents
Aero-engine hollow blade core space flow adjusting and measuring method Download PDFInfo
- Publication number
- CN106596089A CN106596089A CN201611189007.8A CN201611189007A CN106596089A CN 106596089 A CN106596089 A CN 106596089A CN 201611189007 A CN201611189007 A CN 201611189007A CN 106596089 A CN106596089 A CN 106596089A
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- adjusting
- sealing
- flow
- block
- air outlet
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- 238000000034 method Methods 0.000 title claims abstract description 25
- 238000007789 sealing Methods 0.000 claims abstract description 63
- 238000003825 pressing Methods 0.000 claims abstract description 62
- 238000005259 measurement Methods 0.000 claims abstract description 12
- 238000013461 design Methods 0.000 claims abstract description 11
- 230000000994 depressogenic effect Effects 0.000 claims description 15
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 11
- 238000005219 brazing Methods 0.000 claims description 9
- 230000001105 regulatory effect Effects 0.000 claims description 8
- 230000003750 conditioning effect Effects 0.000 claims 1
- 238000009415 formwork Methods 0.000 claims 1
- 238000012797 qualification Methods 0.000 abstract description 3
- 238000004891 communication Methods 0.000 abstract 1
- 238000010586 diagram Methods 0.000 description 4
- 239000000463 material Substances 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 1
- 238000005299 abrasion Methods 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 230000001276 controlling effect Effects 0.000 description 1
- 229910052802 copper Inorganic materials 0.000 description 1
- 239000010949 copper Substances 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Measuring Volume Flow (AREA)
Abstract
The invention provides an aero-engine hollow blade core space flow adjusting and measuring method, comprising: A) providing a device; for one air outlet mouth whose flow needs to be measured, placing a corresponding adjusting block; placing in the other three middle communication grooves with corresponding sealing blocks respectively so that the pressing rod, the adjusting block and the sealing blocks are in contact; B) using the sealing blocks to seal their corresponding air outlet mouths; detecting the sealing conditions of the air outlet mouths; C) measuring the flow value if the sealing is valid; D) if the flow value does not meet the design requirement, making the adjusting block extrude downwards the corresponding cover plate until the flow value meets the design requirement so as to complete the measurement and adjustment to the flow of the first air outlet mouth; and E) for the rest three air outlet mouths, repeating the step A to D so as to complete the measurement and adjustment of the blade core space flow. According to the aero-engine hollow blade core space flow adjusting and measuring method provided by the invention, the qualification rate of parts and the stability of product quality are increased substantially.
Description
Technical Field
The invention relates to the technical field of aero-engines, in particular to a method for measuring and adjusting flow of an inner cavity of a hollow blade of an aero-engine.
Background
In order to adapt to severe cold environment, an aeroengine is designed with a hollow copper blade containing a cavity as a 0-level guide blade for air entraining and anti-icing, fig. 1 is an exploded structure schematic diagram of the blade of the aeroengine, fig. 2 is a combined state overlooking structure schematic diagram of the blade of fig. 1, and as shown in fig. 1 and fig. 2, the blade 1 is a hollow blade which is combined by a cover plate 11 and a base body 12 through brazing, the geometric shape and the inner cavity profile of the blade are free curved surfaces, the requirement on dimensional accuracy is high, the blade belongs to a thin-wall blade, an air inlet 13 is arranged at the shaft end of the base body 12, a depressed part communicated with the air inlet 13 is arranged on the blade body of the base body 12, three support ribs 121 are arranged in the depressed part, the cover plate 11 and the base body 12 are combined through brazing and then separated from the depressed part into four air outlets 14 by the support ribs 121, each air outlet 14 is provided with, after brazing, the flow change of the air outlet 14 is affected by a small change of the inner cavity space of each air outlet 14, and the flow value of each air outlet 14 is also affected by the difference of the shape and the size of each air outlet 14, so that the difficulty of controlling the air flow of a part is high, and the part is often scrapped due to the over-difference of the air flow.
In the traditional single-port flow measuring method, three positions of the four air outlets 14 are blocked by using the melted wax every time, and the wax sealing and the melted wax are alternately carried out for four times, so that the flow of the four air outlets 14 is detected. The wax sealing and melting of the wax require time for each time, and the wax flowing into the inner cavity is difficult to clean after the wax is melted. The working efficiency is low, and meanwhile, the excess materials in the inner cavity cannot be controlled.
Disclosure of Invention
The invention aims to provide a method for regulating and measuring the flow of an inner cavity of a hollow blade of an aeroengine, so as to reduce or avoid the problems.
In order to solve the technical problem, the invention provides a method for regulating and measuring the flow of an inner cavity of a hollow blade of an aeroengine, wherein the hollow blade is a hollow blade and is combined with a base body through brazing by a cover plate, an air inlet is arranged at the shaft end of the base body, a depressed part communicated with the air inlet is arranged on a blade body of the base body, three support ribs are arranged in the depressed part, the depressed part is separated from four air outlets by the cover plate and the base body after being combined through brazing and the support ribs, and each air outlet is provided with a depressed flow channel outside the cover plate, the method comprises the following steps:
step A, providing a device which comprises a bottom box and a base which is in telescopic connection with the bottom box, wherein the base is provided with a supporting block, the base is fixedly connected with an adjusting frame through a pair of upright posts, and an upper template is slidably connected on the upright posts between the adjusting frame and the supporting block;
the supporting block is provided with a top surface corresponding to the profile size of the lower surface of the base body,
the upper template is provided with a bottom surface corresponding to the molded surface of the upper surface of the blade, the upper template is provided with a middle through groove corresponding to the air outlet and the sunken flow channel, an adjusting pressing block and a sealing pressing block which are detachably connected are arranged corresponding to each middle through groove, the adjusting pressing block is provided with a bottom surface corresponding to the molded surface of the cover plate corresponding to the middle through groove, the sealing pressing block is provided with an L-shaped sealing gasket corresponding to the molded surfaces of the cover plate and the sunken flow channel corresponding to the middle through groove,
the adjusting frame is provided with four guide holes corresponding to the through grooves, and four pressure rods are rotatably connected to the adjusting frame through the guide holes.
Raising the upper template to place the blade on the supporting block, then lowering the upper template to place the upper template above the blade, enabling the through grooves to correspond to the air outlets and the sunken flow channels, fixing the upper template, enabling the upper template and the supporting block to clamp the blade, for one air outlet needing to measure flow, placing corresponding adjusting pressing blocks in the corresponding through grooves, placing corresponding sealing pressing blocks in the other three through grooves respectively, and connecting the pressing rods in the guide holes to enable the pressing rods to be in contact with the adjusting pressing blocks and the sealing pressing blocks;
b, rotating the pressure rod connected with the sealing pressing block to enable the sealing pressing block to seal the corresponding air outlet, connecting the air inlet with an air source and an air flow meter and ventilating, then injecting water into the bottom box to enable the upper surface of the blade to be kept below the water surface, and checking the sealing condition of the sealing pressing block on the air outlet;
step C, if the sealing pressing block in the step B is not good in sealing the air outlet and leaks air, the position of the sealing pressing block is further adjusted through the pressing rod to enable the sealing pressing block to be good in sealing, and if the sealing pressing block is effectively sealed with the air outlet, the flow value measured by the gas flowmeter is the flow value of the air outlet corresponding to the adjusting pressing block;
and step D, if the flow value of the gas outlet corresponding to the adjusting pressure block meets the design requirement, completing flow measurement, if the flow value of the gas outlet corresponding to the adjusting pressure block does not meet the design requirement, rotating the pressure rod connected with the adjusting pressure block to enable the adjusting pressure block to downwards extrude the corresponding contact part of the cover plate and deform the contact part, observing the flow value measured by the gas flowmeter in the process, and when the flow value measured by the gas flowmeter meets the design requirement, stopping rotating the adjusting pressure block corresponding to the adjusting pressure block to complete the flow measurement adjusting process of the first gas outlet 14, lifting the base from the bottom box, and enabling the base to be located above the water surface.
And E, repeating the steps A-D for the other three air outlets to complete the flow measurement of the inner cavity of the blade.
Preferably, in step a, the top of each of the adjusting press block and the sealing press block may be provided with a rotatable disk for connecting with the pressure rod.
The method for regulating and measuring the flow of the inner cavity of the hollow blade of the aero-engine breaks through the traditional measuring and processing separated mode, and the qualification rate of parts and the stability of product quality are greatly improved.
Drawings
The drawings are only for purposes of illustrating and explaining the present invention and are not to be construed as limiting the scope of the present invention. Wherein,
FIG. 1 is an exploded view of a blade for an aircraft engine;
FIG. 2 is a schematic top view of the blade of FIG. 1 in an assembled state,
fig. 3 is an exploded schematic structural diagram of a device used in a method for regulating and measuring the flow of the inner cavity of the hollow blade of the aircraft engine according to an embodiment of the invention.
Detailed Description
In order to more clearly understand the technical features, objects, and effects of the present invention, embodiments of the present invention will now be described with reference to the accompanying drawings. Wherein like parts are given like reference numerals.
FIG. 1 is an exploded view of a blade for an aircraft engine; fig. 2 is a schematic top view of the blade of fig. 1 in an assembled state, and fig. 3 is a schematic exploded structural diagram of a device used in a method for regulating and measuring the flow rate of the hollow blade cavity of an aircraft engine according to an embodiment of the invention. Referring to fig. 1-3, the invention provides a method for regulating and measuring the flow of an inner cavity of a hollow blade of an aircraft engine, wherein the blade 1 is a hollow blade, a cover plate 11 and a base body 12 are combined together through brazing, an air inlet 13 is arranged at the shaft end of the base body 12, a depressed part communicated with the air inlet 13 is arranged on a blade body of the base body 12, three support ribs 121 are arranged in the depressed part, the depressed part is separated into four air outlets 14 by the cover plate 11 and the base body 12 after being combined through brazing and the support ribs 121, and each air outlet 14 is provided with a depressed flow channel 141 outside the cover plate 11, the method comprises the following steps:
step A, providing a device which comprises a bottom box 6 and a base 2 which is telescopically connected with the bottom box 6, wherein the base 2 is provided with a supporting block 21, the base 2 is fixedly connected with an adjusting frame 5 through a pair of upright posts 22, and an upper template 3 can be slidably connected on the upright posts 22 between the adjusting frame 5 and the supporting block 21;
the supporting block 21 is provided with a top surface corresponding to the profile dimension of the lower surface of the base body 12,
the upper die plate 3 is provided with a bottom surface corresponding to the profile of the upper surface of the blade 1, the upper die plate 3 is provided with a central through groove 31 corresponding to the air outlet 14 and the recessed flow passage 141, and an adjusting press block 32 and a sealing press block 33 (only one adjusting press block 32 and three sealing press blocks 33 are shown in fig. 3) detachably connected to each central through groove 31, but it should be understood by those skilled in the art that an adjusting press block 32 and a sealing press block 33 are provided to each central through groove 31, the adjusting press block 32 is provided with a bottom surface corresponding to the profile of the cover plate 11 corresponding to the central through groove 31, the sealing press block 33 is provided with an L-shaped sealing pad 331 corresponding to the profiles of the cover plate 11 and the recessed flow passage 141 corresponding to the central through groove,
the adjusting frame 5 is provided with four guide holes 51 corresponding to the through groove 31, and four pressure rods 52 are rotatably connected to the adjusting frame through the guide holes 51.
In a preferred embodiment, the upper plate 3 may be provided with two connecting arms 300 connected to the upright 22, so that the material and weight of the upper plate 3 can be greatly reduced.
Raising the upper die plate 3 to place the blade 1 on the supporting block 21, then lowering the upper die plate 3 to place above the blade 1, so that the through slots 31 correspond to the air outlets 14 and the recessed flow channels 141, fixing the upper die plate 3 (nuts may be provided on the columns 22 for adjusting and fixing the positions of the upper die plate 3), so that the upper die plate 3 and the supporting block 21 clamp the blade 1, for one air outlet 14 whose flow is to be measured, placing a corresponding adjusting pressing block 32 in the through slot 31 corresponding to the air outlet 14, placing corresponding sealing pressing blocks 33 in the other three through slots 31, respectively, connecting the pressure rods 52 in the guide holes 51, and contacting the pressure rods 52 with the adjusting pressing blocks 32 and the sealing pressing blocks 33;
the base 2 with end box 6 telescopic connection, for example, end box 6 bottom can be provided with two hydraulic lifting rod with base 2 is connected, works as like this in the end box 6 water injection back, can be very convenient with through hydraulic lifting rod base 2 submerges and rises out of the water.
The adjusting frame 5 is fixedly connected with the base 2 through a pair of upright posts 22, and the upper template 3 is arranged on the upright posts 22 between the adjusting frame 5 and the supporting block 21, so that the positions of the supporting block 21, the upper template 3 and the adjusting frame 5 are relatively fixed, and the corresponding positions can be well corresponded.
The supporting block 21 is provided with a top surface corresponding to the profile size of the lower surface of the base body 12, that is, the supporting block 21 can be well attached to the blade 1 when the blade is placed on the supporting block 21. The area of the top surface of the supporting block 21 may be larger than that of the lower surface of the base body 12, and may be marked by a scribe line or the like at a position corresponding to the size of the profile of the lower surface of the base body 12, so that the vane 1 may be easily placed,
the upper template 3 is provided with a bottom surface corresponding to the molded surface of the upper surface of the blade 1, and a through groove 31 is provided corresponding to the air outlet 14 and the recessed flow passage 141, that is, after the upper template 3 is attached to the upper surface of the blade 1, the upper template can be effectively attached to other positions of the upper surface of the blade 1 except the recessed flow passage 141 and the part above the air outlet 14 and the cover plate 11.
The width of the through groove 31 may be slightly greater than the width of the corresponding recessed channel 141, for example, the width of the through groove 31 may be 2mm greater than the width of the corresponding recessed channel 141, that is, the corresponding sealing pressing block 33 may be 1mm greater on each of two sides of the recessed channel 141, so that effective sealing of the sealing pressing block 33 on the recessed channel 141 can be ensured. The length of the through groove 31 may be greater than that of the recessed channel 141, for example, the length of the through groove 31 may be greater than that of the recessed channel 141 by 5-8mm, which may ensure that the sealing pressing block 33 may effectively seal the upper portion of the air outlet 14 and may ensure that the adjusting pressing block 32 contacts the cover plate 11 exposed in the through groove 31 on the upper portion of the air outlet 14.
In a preferred embodiment, the top of the adjusting pressing block 32 and the top of the sealing pressing block 33 can be provided with a rotatable disc 34 for connecting with the pressing rod 52, and the disc 34 can be connected with the adjusting pressing block 32 and the sealing pressing block 33 through bearings, so that the adjusting pressing block 32 and the sealing pressing block 33 are prevented from being driven to rotate when the pressing rod 52 is rotated to press down, and displacement or abrasion is caused.
Step B, the pressure rod 52 connected with the sealing pressure block 33 is rotated to enable the sealing pressure block 33 to seal the corresponding air outlet 14, the air inlet 13 is connected with an air source and an air flow meter and is ventilated, then water is injected into the bottom box 6 to enable the upper surface of the blade 1 to be kept below the water surface, and the sealing condition of the sealing pressure block 33 on the air outlet 14 is checked;
step C, if the sealing pressing block 33 in the step B is not good in sealing the air outlet 14 and air leaks, the position of the sealing pressing block 33 is further adjusted through the pressure rod 52 to enable the sealing to be good, and if the sealing pressing block 33 is effectively sealed on the air outlet 14, the flow value measured by the gas flowmeter at the moment is the flow value of the air outlet 14 corresponding to the adjusting pressing block 32;
and D, completing flow measurement if the flow value of the gas outlet 14 corresponding to the adjusting pressure block 32 meets the design requirement, rotating the pressure rod 52 connected with the adjusting pressure block 32 if the flow value of the gas outlet 14 corresponding to the adjusting pressure block 32 does not meet the design requirement, so that the adjusting pressure block 32 downwards presses the corresponding contact part of the cover plate 11 and deforms the contact part, observing the flow value measured by the gas flowmeter in the process, stopping rotating the adjusting pressure block 52 corresponding to the adjusting pressure block 32 when the flow value measured by the gas flowmeter meets the design requirement, completing the flow measurement adjusting process for the first gas outlet 14, lifting the base 2 from the bottom box 6, and enabling the base 2 to be located above the water surface.
And E, repeating the steps A-D for the other three air outlets 14 to complete the flow measurement of the inner cavity of the blade 1.
The biggest difference between the device and the prior art is that the device is provided, the adjusting pressing block 32 and the sealing pressing block 33 are arranged corresponding to each air outlet 14, so that each air outlet 14 can be sealed in a mechanical mode, the measured air outlet 14 can be subjected to real-time flow adjustment through the adjusting pressing block 32, the traditional mode of separating measurement and processing is broken, and the qualification rate of parts and the stability of product quality are greatly improved.
It should be appreciated by those of skill in the art that while the present invention has been described in terms of several embodiments, not every embodiment includes only a single embodiment. The description is given for clearness of understanding only, and it is to be understood that all matters in the embodiments are to be interpreted as including technical equivalents which are related to the embodiments and which are combined with each other to illustrate the scope of the present invention.
The above description is only an exemplary embodiment of the present invention, and is not intended to limit the scope of the present invention. Any equivalent alterations, modifications and combinations can be made by those skilled in the art without departing from the spirit and principles of the invention.
Claims (4)
1. A method for regulating and measuring the flow of an inner cavity of a hollow blade of an aircraft engine is characterized in that the blade is formed by combining a cover plate and a base body through brazing, an air inlet hole is formed in the shaft end of the base body, a depressed part communicated with the air inlet hole is formed in the blade body of the base body, three support ribs are arranged in the depressed part, the depressed part is separated from four air outlets by the cover plate and the base body through brazing combination and the support ribs, and each air outlet is provided with a depressed flow channel outside the cover plate, and the method comprises the following steps:
step A, providing a device which comprises a bottom box and a base which is in telescopic connection with the bottom box, wherein the base is provided with a supporting block, the base is fixedly connected with an adjusting frame through a pair of upright posts, and an upper template is slidably connected on the upright posts between the adjusting frame and the supporting block;
the supporting block is provided with a top surface corresponding to the profile size of the lower surface of the base body,
the upper template is provided with a bottom surface corresponding to the molded surface of the upper surface of the blade, the upper template is provided with a middle through groove corresponding to the air outlet and the sunken flow channel, an adjusting pressing block and a sealing pressing block which are detachably connected are arranged corresponding to each middle through groove, the adjusting pressing block is provided with a bottom surface corresponding to the molded surface of the cover plate corresponding to the middle through groove, the sealing pressing block is provided with an L-shaped sealing gasket corresponding to the molded surfaces of the cover plate and the sunken flow channel corresponding to the middle through groove,
the adjusting frame is provided with four guide holes corresponding to the through grooves, and four pressure rods are rotatably connected to the adjusting frame through the guide holes.
Raising the upper template to place the blade on the supporting block, then lowering the upper template to place the upper template above the blade, enabling the through grooves to correspond to the air outlets and the sunken flow channels, fixing the upper template, enabling the upper template and the supporting block to clamp the blade, for one air outlet needing to measure flow, placing corresponding adjusting pressing blocks in the corresponding through grooves, placing corresponding sealing pressing blocks in the other three through grooves respectively, and connecting the pressing rods in the guide holes to enable the pressing rods to be in contact with the adjusting pressing blocks and the sealing pressing blocks;
b, rotating the pressure rod connected with the sealing pressing block to enable the sealing pressing block to seal the corresponding air outlet, connecting the air inlet with an air source and an air flow meter and ventilating, then injecting water into the bottom box to enable the upper surface of the blade to be kept below the water surface, and checking the sealing condition of the sealing pressing block on the air outlet;
step C, if the sealing pressing block in the step B is not good in sealing the air outlet and leaks air, the position of the sealing pressing block is further adjusted through the pressing rod to enable the sealing pressing block to be good in sealing, and if the sealing pressing block is effectively sealed with the air outlet, the flow value measured by the gas flowmeter is the flow value of the air outlet corresponding to the adjusting pressing block;
and step D, if the flow value of the gas outlet corresponding to the adjusting pressure block meets the design requirement, completing flow measurement, if the flow value of the gas outlet corresponding to the adjusting pressure block does not meet the design requirement, rotating the pressure rod connected with the adjusting pressure block to enable the adjusting pressure block to downwards extrude the corresponding contact part of the cover plate and deform the contact part, observing the flow value measured by the gas flowmeter in the process, and when the flow value measured by the gas flowmeter meets the design requirement, stopping rotating the adjusting pressure block corresponding to the adjusting pressure block to complete the flow measurement adjusting process of the first gas outlet 14, lifting the base from the bottom box, and enabling the base to be located above the water surface.
And E, repeating the steps A-D for the other three air outlets to finish the flow measurement adjustment of the inner cavity of the blade.
2. The method of claim 1, wherein in step a, the top of both the conditioning compact and the sealing compact may be provided with a rotatable disc for connection with the pressure rod.
3. Method according to claims 1-2, characterized in that the upper formwork is provided with two link arms connected to the uprights.
4. A method according to any of claims 1 to 3, wherein the width of the through slot 31 is 2mm wider than its corresponding recessed channel 141.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611189007.8A CN106596089B (en) | 2016-12-21 | 2016-12-21 | A kind of aero-engine hollow blade inner flow adjusting, measuring method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611189007.8A CN106596089B (en) | 2016-12-21 | 2016-12-21 | A kind of aero-engine hollow blade inner flow adjusting, measuring method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106596089A true CN106596089A (en) | 2017-04-26 |
| CN106596089B CN106596089B (en) | 2019-03-26 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201611189007.8A Active CN106596089B (en) | 2016-12-21 | 2016-12-21 | A kind of aero-engine hollow blade inner flow adjusting, measuring method |
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| Country | Link |
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| CN (1) | CN106596089B (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS6454330A (en) * | 1987-08-26 | 1989-03-01 | Hitachi Ltd | Manufacture of flow rate control valve |
| CN103481219A (en) * | 2013-09-16 | 2014-01-01 | 西安航空动力股份有限公司 | Guide blade water flow measuring clamp and guide blade water flow measuring method |
| CN203752004U (en) * | 2014-03-03 | 2014-08-06 | 中国燃气涡轮研究院 | Flow testing fixture for guide vanes of turbine |
| CN104849014A (en) * | 2015-05-05 | 2015-08-19 | 中国南方航空工业(集团)有限公司 | Flow fixture for air cooling flow test on hollow blades |
| CN105269494A (en) * | 2015-11-26 | 2016-01-27 | 中国南方航空工业(集团)有限公司 | Blade flow test clamp |
| CN205254840U (en) * | 2015-12-11 | 2016-05-25 | 株洲中航动力精密铸造有限公司 | Blade exhaust hole flow measures anchor clamps |
-
2016
- 2016-12-21 CN CN201611189007.8A patent/CN106596089B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS6454330A (en) * | 1987-08-26 | 1989-03-01 | Hitachi Ltd | Manufacture of flow rate control valve |
| CN103481219A (en) * | 2013-09-16 | 2014-01-01 | 西安航空动力股份有限公司 | Guide blade water flow measuring clamp and guide blade water flow measuring method |
| CN203752004U (en) * | 2014-03-03 | 2014-08-06 | 中国燃气涡轮研究院 | Flow testing fixture for guide vanes of turbine |
| CN104849014A (en) * | 2015-05-05 | 2015-08-19 | 中国南方航空工业(集团)有限公司 | Flow fixture for air cooling flow test on hollow blades |
| CN105269494A (en) * | 2015-11-26 | 2016-01-27 | 中国南方航空工业(集团)有限公司 | Blade flow test clamp |
| CN205254840U (en) * | 2015-12-11 | 2016-05-25 | 株洲中航动力精密铸造有限公司 | Blade exhaust hole flow measures anchor clamps |
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| CN106596089B (en) | 2019-03-26 |
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Address after: 412002 Dong Jiaduan, Zhuzhou, Hunan Patentee after: China Hangfa South Industrial Co. Ltd. Address before: 412002 Dong Jiaduan, Zhuzhou, Hunan Patentee before: China Southern Airlines Industry (Group) Co., Ltd. |
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