CN117595156A - High-temperature strain gauge wiring method for rear-stage integral multi-stage disc mortise connection structure blade - Google Patents
High-temperature strain gauge wiring method for rear-stage integral multi-stage disc mortise connection structure blade Download PDFInfo
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- CN117595156A CN117595156A CN202410057897.5A CN202410057897A CN117595156A CN 117595156 A CN117595156 A CN 117595156A CN 202410057897 A CN202410057897 A CN 202410057897A CN 117595156 A CN117595156 A CN 117595156A
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- 238000009413 insulation Methods 0.000 claims description 5
- 230000000694 effects Effects 0.000 claims description 4
- 238000009417 prefabrication Methods 0.000 description 9
- 230000008569 process Effects 0.000 description 9
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 5
- 239000000919 ceramic Substances 0.000 description 5
- 239000000853 adhesive Substances 0.000 description 4
- 230000001070 adhesive effect Effects 0.000 description 4
- 238000007664 blowing Methods 0.000 description 4
- 239000004568 cement Substances 0.000 description 4
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- 229910052751 metal Inorganic materials 0.000 description 3
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- 238000000576 coating method Methods 0.000 description 2
- 229910052802 copper Inorganic materials 0.000 description 2
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- 238000011161 development Methods 0.000 description 2
- WABPQHHGFIMREM-UHFFFAOYSA-N lead(0) Chemical compound [Pb] WABPQHHGFIMREM-UHFFFAOYSA-N 0.000 description 2
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- 235000010585 Ammi visnaga Nutrition 0.000 description 1
- 244000153158 Ammi visnaga Species 0.000 description 1
- 229920000742 Cotton Polymers 0.000 description 1
- 229910001069 Ti alloy Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 230000004907 flux Effects 0.000 description 1
- 239000011888 foil Substances 0.000 description 1
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- 238000009662 stress testing Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000004083 survival effect Effects 0.000 description 1
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- 230000007704 transition Effects 0.000 description 1
Classifications
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02G—INSTALLATION OF ELECTRIC CABLES OR LINES, OR OF COMBINED OPTICAL AND ELECTRIC CABLES OR LINES
- H02G1/00—Methods or apparatus specially adapted for installing, maintaining, repairing or dismantling electric cables or lines
- H02G1/06—Methods or apparatus specially adapted for installing, maintaining, repairing or dismantling electric cables or lines for laying cables, e.g. laying apparatus on vehicle
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B21/00—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant
- G01B21/32—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant for measuring the deformation in a solid
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L5/00—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
- G01R31/12—Testing dielectric strength or breakdown voltage ; Testing or monitoring effectiveness or level of insulation, e.g. of a cable or of an apparatus, for example using partial discharge measurements; Electrostatic testing
- G01R31/1227—Testing dielectric strength or breakdown voltage ; Testing or monitoring effectiveness or level of insulation, e.g. of a cable or of an apparatus, for example using partial discharge measurements; Electrostatic testing of components, parts or materials
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
- G01R31/50—Testing of electric apparatus, lines, cables or components for short-circuits, continuity, leakage current or incorrect line connections
- G01R31/66—Testing of connections, e.g. of plugs or non-disconnectable joints
- G01R31/67—Testing the correctness of wire connections in electric apparatus or circuits
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02G—INSTALLATION OF ELECTRIC CABLES OR LINES, OR OF COMBINED OPTICAL AND ELECTRIC CABLES OR LINES
- H02G3/00—Installations of electric cables or lines or protective tubing therefor in or on buildings, equivalent structures or vehicles
- H02G3/02—Details
- H02G3/04—Protective tubing or conduits, e.g. cable ladders or cable troughs
- H02G3/0437—Channels
- H02G3/045—Channels provided with perforations or slots permitting introduction or exit of wires
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Architecture (AREA)
- Civil Engineering (AREA)
- Structural Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention provides a high-temperature strain gauge wiring method for a rear-stage integral multi-stage disc mortise connection structure blade, which is used for wiring a front-stage disc, a middle-stage disc and a tested-stage disc, and comprises the following steps of: the air inlet edges of the front stage disc and the middle stage disc are provided with first through holes, and the air outlet edges of the front stage disc and the middle stage disc are provided with second through holes; a first through hole is formed in the air inlet side of the tested stage disc; sequentially penetrating the armor wires reserved on the front-stage blisk into the hub barrel of the front-stage blisk of the integral multi-stage blisk, penetrating the armor wires into the mortises of the front-stage blisk from the first through holes of the front-stage blisk, entering the hub barrel through the second through holes of the front-stage blisk, and spot-welding the armor wires to the middle-stage blisk along the path; penetrating the armor wires into the mortises of the intermediate stage disc from the first through holes of the intermediate stage disc, and then entering the inside of the hub through the second through holes of the intermediate stage disc, and spot welding the armor wires to the tested stage disc along the path.
Description
Technical Field
The invention relates to the technical field of high-temperature dynamic stress testing of aero-engine compressors, in particular to a high-temperature strain gauge wiring method for a rear-stage integral multi-stage disc mortise connection structure blade.
Background
With the demand of three highs (high temperature, high pressure and high rotation speed) of engine development, the faults of the rotor blades of the compressor are highlighted. In the development process of the engine, a sticking contact type high-temperature strain gauge is usually adopted, a dynamic strain signal is led out through a remote sensing or current-guiding device signal transmission system, and a wiring method from a high-temperature strain gauge grid wire to a high-temperature wire to a remote sensing system is very important.
In the dynamic stress test wiring process of the rear-stage integral multistage disc mortise connection blade of the compressor, the most direct method is to open holes in discs which are radially close to the blade position in advance, and the strain gauge is led to the front journal position to enter a remote measuring or electricity guiding device through the through holes of the discs after entering the hub barrel hole. However, for the following stage of the overall multi-stage disc structure, a plurality of discs are connected together, the space between the discs is small, and holes cannot be drilled on the discs which are close to the radial positions of the blades. Meanwhile, a telemetry module is required to be installed at the front position of the front journal in the high-temperature dynamic stress test modification process. The strain gauge wiring of the rear-stage integral multi-stage disc is connected with the telemetry module through the front journal after passing through the front-stage integral blisk. The assembly sequence of the compressor is that a front journal is firstly assembled and then a front-stage blisk is assembled and then a rear-stage blisk is assembled, so that strain leads also need to be wired at the journal position and then pass through the front stage and then are connected through strain foil grid wires arranged on blades of the rear-stage blisk in advance, the blades are in air flow, spot welding wiring work of the armor wires is not allowed on blade bodies, and the process also presents a great challenge for the connection process.
Disclosure of Invention
In view of this, the embodiments of the present disclosure provide a method for routing high temperature strain gages of a rear stage integral multi-stage disk dovetail connection structure blade, which is used for testing dynamic stress of the rear stage integral multi-stage disk dovetail connection structure blade of a compressor.
The embodiment of the specification provides the following technical scheme: a high-temperature strain gauge wiring method for a rear-stage integral multi-stage disc mortise connection structure blade is used for wiring a front-stage disc, a middle-stage disc and a tested-stage disc, and comprises the following steps of: the air inlet edges of the front stage disc and the middle stage disc are provided with first through holes, and the air outlet edges of the front stage disc and the middle stage disc are provided with second through holes; a first through hole is formed in the air inlet side of the tested stage disc; sequentially penetrating the armor wires reserved on the front-stage blisk into the hub barrel of the front-stage blisk of the integral multi-stage blisk, penetrating the armor wires into the mortises of the front-stage blisk from the first through holes of the front-stage blisk, entering the hub barrel through the second through holes of the front-stage blisk, and spot-welding the armor wires to the middle-stage blisk along the path; penetrating the armor wires into the mortises of the intermediate stage disc from the first through holes of the intermediate stage disc, then entering the inside of the hub through the second through holes of the intermediate stage disc, and performing spot welding to the tested stage disc along the path; and penetrating the armor wires from the first through holes of the tested stage disc into the mortises of the tested stage disc, and switching the armor wires with the armor wires of the test stage strain gauges of the integral multistage disc of the later stage.
Further, the first through hole is bored from the outer side of the hub mortise to the inner side of the hub, and an included angle between an axis of the first through hole and a horizontal plane is in a range of 45 ° to 60 °.
Further, the second through hole is perforated from the outer side of the hub mortise to the inner side of the hub, and an included angle between an axis of the second through hole and a horizontal plane is in a range of 120 DEG to 135 deg.
Further, the method further comprises the following steps: the welding point part at the joint of the armor wires and the armor wires of the rear-stage integral multi-stage disc test-stage strain gauge is protected and laminated through the skin; injecting white tooth-sleeved insulating glue into the skin protection layer until the white tooth-sleeved insulating glue fills the whole skin protection layer; after standing for 4 to 6 hours, the signal state and insulation effect of the armor wires of the rear-stage integral multi-stage disc test-stage strain gauge were tested.
Further, the method further comprises the following steps: the armor wires of the subsequent stage integral multi-stage disc test stage strain gage were preformed into a coil spring-like structure and placed at the blade dovetail.
Further, pulling the armor wires by a rod-like object while the armor wires are being passed from the first through-hole of the preceding stage disc to the second through-hole of the intermediate stage disc; alternatively, the armor wires are pulled by a wand-like object as they pass from the first through-hole of the intermediate stage tray into the second through-hole of the intermediate stage tray.
Further, the axis of the first through hole and the axis of the second through hole are both located in the same radial plane.
Compared with the prior art, the beneficial effects that above-mentioned at least one technical scheme that this description embodiment adopted can reach include at least: the high-temperature strain gauge lead wire under the condition of reverse threading of the strain lead wire due to structure and assembly limitation is realized, and a foundation is laid for realizing the dynamic stress test of the rear-stage integral multistage disc mortise connection structure blade of the compressor.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic diagram of a wiring structure according to an embodiment of the present invention.
FIG. 2 is a schematic view of a tongue and groove blade.
Reference numerals: 1. a front journal; 2. copper wire; 3. armor wires; 4. a front stage blisk; 5. middle stage blisk; 6. a rear-stage integral multi-stage tray; 7. a first through hole; 8. a second through hole; 9. a tongue and groove; 10. a strain gage; 11. a tongue-and-groove blade; 12. spring structure.
Detailed Description
Embodiments of the present application are described in detail below with reference to the accompanying drawings.
Other advantages and effects of the present application will become apparent to those skilled in the art from the present disclosure, when the following description of the embodiments is taken in conjunction with the accompanying drawings. It will be apparent that the described embodiments are only some, but not all, of the embodiments of the present application. The present application may be embodied or carried out in other specific embodiments, and the details of the present application may be modified or changed from various points of view and applications without departing from the spirit of the present application. It should be noted that the following embodiments and features in the embodiments may be combined with each other without conflict. All other embodiments, which can be made by one of ordinary skill in the art based on the embodiments herein without making any inventive effort, are intended to be within the scope of the present application.
As shown in FIG. 1, in one embodiment, the high temperature strain gauge routing method for the rear stage integral multi-stage disk tongue and groove connection structure blade comprises the following steps: copper wires 2 and armor wires 3 are arranged on the inner wall of the front journal 1 of the compressor, one end of each copper wire 2 is connected with the corresponding telemetry, and the other end of each copper wire extends to one side of the integral multi-stage disc after being connected with the corresponding armor wires 3 in a switching mode and is used for being connected with the armor wires on the tested integral multi-stage disc blades.
The detected compressor rear stage integral multi-stage disk 6 has 4 stages, namely a third stage disk, a fourth stage disk, a fifth stage disk and a sixth stage disk. The first stage blisk is a leading stage blisk 4 and the second stage blisk is a middle stage blisk 5. First through holes 7 are respectively prefabricated on the air inlet edges of the third-stage disc, the fourth-stage disc and the fifth-stage disc of the rear-stage integrated multi-stage disc 6, and second through holes 8 are respectively prefabricated on the air outlet edges of the third-stage disc, the fourth-stage disc and the fifth-stage disc of the rear-stage integrated multi-stage disc 6. The first through holes 7 are prefabricated on the sixth-stage disc of the subsequent-stage integrated multi-stage disc 6. Copper wires 2 and armor wires 3 are connected on a front journal 1, the other ends of the armor wires 3 enter first-stage disc inner routing along through holes of a first-stage blisk, the second-stage blisk inner routing is entered through holes of a second-stage blisk, the armor wires 3 enter third-stage disc air inlet side prefabrication first through holes 7 of a rear-stage blisk 6, enter third-stage disc air outlet side prefabrication second through holes 8 and enter fourth-stage disc hub inner routing after entering third-stage disc air outlet side prefabrication second through holes 8, the armor wires 3 enter fourth-stage disc air inlet side prefabrication first through holes 7 of a rear-stage blisk 6, enter fourth-stage disc air outlet prefabrication second through holes 8 and enter fourth-stage disc hub inner routing after entering through holes of a second-stage blisk 6, the armor wires 3 enter fifth-stage disc air inlet side prefabrication first through holes 7 of the fifth-stage blisk 6, enter fifth-stage disc air outlet prefabrication second through holes 8 and enter fifth-stage hub inner routing after entering the fifth-stage blisk, and the armor wires 3 enter test-stage sixth-stage disc air inlet side prefabrication wire length after entering the sixth-stage blisk side prefabrication through holes. The strain gauge 10 is arranged on a mortise blade 11 connected with a mortise of a sixth-stage disk, the tenon of the mortise blade 11 is switched into the armor wire 3, after a spring structure 12 is manufactured on the tenon of the mortise blade 11, the armor wire 3 on the blade is switched with the armor wire 3 reserved on the air inlet edge of the sixth-stage disk at the mortise position of the sixth-stage disk test blade.
A plurality of high-temperature strain gauges are arranged on the circumference of a measured disc of the rear-stage integral multi-stage disc 6, the high-temperature strain gauges are adhered to blades 11 with different mortises, the corresponding circumference positions of the blades to be tested are provided with lead holes along the front journal 1, the front-stage blisk 4 and the middle-stage blisk 5 of the path, and the air inlet edges and the air outlet edges of the third-stage, fourth-stage and fifth-stage discs of the rear-stage integral multi-stage disc 6 are provided with through holes and are in a circumferential angle with the blades to be measured.
When the transfer is carried out in the mortises 9 of the tested stage of the rear stage integral multi-stage disc 6, a yurt type protective umbrella is manufactured in advance by using the skin, and a hole with the size of the needle head of the medical injector is manufactured in advance at the highest position of the protective layer. The skin protection layer is laminated on two spot welding heads of two armor wires 3, and the white tooth-sleeved insulating adhesive which is adjusted in advance is injected into the skin protection umbrella which is manufactured in advance by a medical injector needle until the white tooth-sleeved insulating adhesive fills the whole insulation protection umbrella. And after waiting for 4-6 hours, testing the signal state and the insulation effect of the strain gauge armor wires.
In the process that a first through hole 7 is formed in the third-stage disc and the fourth-stage disc of the detected rear-stage integrated multi-stage disc 6 from the outer side of a hub mortice to the inner side of the hub, the processing inclination angle is 45-60 degrees, so that the hub mortice is prevented from being damaged; then, in the process of opening the second through hole 8 on the exhaust edge of the third-stage disc and the fourth-stage disc of the detected rear-stage integrated multi-stage disc 6, the holes are formed from the outer side of the tenon groove of the disc hub to the inner side of the disc hub, and the processing inclination angle is 120-135 degrees, so that the tenon groove structure of the hub barrel is prevented from being damaged. In order not to damage the armor wires, in the process of leading the first through holes 7 to the second through holes 8, thin rod-shaped structural objects such as cotton swabs, toothpicks and the like are required to be used for leading the armor wires into the mortice exhaust side holes at one point.
It should be noted that, the circumferential positions of the through holes of the inlet side and the outlet side of the front stage preset in advance are corresponding to the circumferential positions of the inlet side of the blade of the test stage, and are corresponding to the positions of the mortises of the blade of the test stage one by one.
As shown in fig. 2, in an embodiment, the routing method further includes: and sticking a strain gauge 10 on a measured blade, and making a spring structure 12 after the grid wires of the strain gauge 10 are connected with the armor wires 3 at the tenon position under the blade edge plate.
It should be noted that, the corresponding length of the armor wires 3 is reserved in advance at the tenon position, and the length of the armor wires 3 is larger than the maximum radial serial amount in the working process of the mortise blade 11.
The tongue-and-groove blade 11 is installed at the tongue-and-groove 9 during operation, there is radial transmission, in order to avoid the armor line rupture, and ensure that the radial transmission in-process of tongue-and-groove blade 11 is not broken, need make spring structure 12 in advance on tongue-and-groove blade 11, the number of spring turns is approximately 3~4, and the diameter is about 1mm, guarantees to hide under the marginal plate between two blades, and can not influence the normal work of blade.
Optionally, the step of transferring the grid wires to the armor wires 3 on the underblade dovetail comprises: blowing sand at the switching position, coating ceramic cement glue at the sand blowing area, and respectively carrying out spot welding on the armoring wires reserved on the blades and the disc and the armoring wires by using spot welding flux and a pen point spot welding head to form two welding heads which cannot be contacted; after the two welding heads are covered with the insulating felt, the metal skin is fixed on the insulating felt.
Preferably, the armoured wires with springs at the positions of the blade tenons are switched with the armoured wires preset in advance on the rear-stage integral multi-stage disc test stage on the detected rear-stage integral multi-stage disc test stage mortises.
The method comprises the following specific steps: blowing sand at a mortise switching position of a blade mounting position of a strain gauge of a rear-stage integral multi-stage disc test stage, and coating ceramic cement glue at the sand blowing position; and respectively carrying out spot welding on the armoring wires reserved on the blade and the disc and the armoring wires by utilizing the spot welding sister and the nib spot welding head to form two welding heads, wherein the two welding heads cannot be contacted.
In one embodiment of the invention, in order to ensure that the test grade blade mortise has a switching operation position and a spring placement space, the lead holes of the armor wires arranged in advance by the test grade are not at a radial angle with the circumferential direction of the blade of the actual test strain gage, and the opening position of the test hole is different from the circumferential position of the test integrity blade by about 5 blades.
Optionally, when the dynamic stress test of the multi-stage rotor blade at the later stage is realized through simultaneous test, the number of the holes in the mortises of each stage of disc needs to be arranged in advance, and the circumferential angle needs to be planned in advance. The armor wires of the rear stage of the test rear stage monolith plate need to enter the intermediate stage tongue and groove leads through the front stage tongue and groove lead holes of the rear stage monolith plate and finally reach the rear test stage of the horse face stage monolith plate. The front two-stage test lead hole of the rear stage integral disk is in a radial angle, the size of the opening of the first stage of the rear stage integral disk is larger than 2mm, and the diameter of each armor wire is usually 2mm, two armor wires are arranged in advance in each hole, the first armor wires are used for switching a first stage strain gauge of the rear stage integral disk, and the second armor wires enter a second stage lead hole to be switched with a second stage strain gauge of the rear stage integral disk. The circumferential location of the lead holes of the preceding stage for the transition of the subsequent stage of the ensemble She Pandi three and fourth stage armor wires ensures that neither of the passes intersect the armor wires of the first and second stages.
In the above embodiments of the present invention, armor wires are resistant to 900 ℃ and 0.75-1.2mm in diameter and cannot be connected to telemetry modules.
The white insulating adhesive is ceramic adhesive which can be cured at normal temperature to meet the insulation pain at 900 ℃.
The switching metal skin is a titanium alloy metal sheet.
The ceramic cement is high-temperature resistant ceramic cement glue, has temperature resistance of 870 ℃, and is arranged on the surface of the test piece through a corresponding installation process.
The high temperature is 250-1000 ℃.
The invention realizes the attachment and wiring of the strain gauge of the rear-stage integral multi-stage disc mortise connection structure blade of the compressor, overcomes the difficulty that the integral disc cannot be wired between discs, and realizes the switching between the armor wires under the condition of small space in the mortise. The dynamic stress test of the rear-stage integral multi-stage disc mortise connecting structure blade of the compressor under the conditions of complex structures and assembly limitations is realized, the survival rate of the strain gauge reaches more than 80%, the dynamic stress data of the rear-stage integral multi-stage disc mortise connecting structure blade of the compressor is effectively obtained, and a solid technical foundation is laid for realizing the full-stage dynamic test of the compressor.
The foregoing is merely specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions easily conceivable by those skilled in the art within the technical scope of the present application should be covered in the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (7)
1. A high-temperature strain gauge wiring method for a rear-stage integral multi-stage disc mortise connection structure blade is used for wiring of a front-stage disc, a middle-stage disc and a tested-stage disc and is characterized by comprising the following steps of:
the air inlet edges of the front stage disc and the middle stage disc are provided with first through holes, and the air outlet edges of the front stage disc and the middle stage disc are provided with second through holes; a first through hole is formed in the air inlet side of the tested stage disc;
sequentially penetrating the armor wires reserved on the front-stage blisk into the hub barrel of the front-stage blisk of the integral multi-stage blisk, penetrating the armor wires into the mortises of the front-stage blisk from the first through holes of the front-stage blisk, entering the hub barrel through the second through holes of the front-stage blisk, and spot-welding the armor wires to the middle-stage blisk along the path;
penetrating the armor wires into the mortises of the intermediate stage disc from the first through holes of the intermediate stage disc, then entering the inside of the hub through the second through holes of the intermediate stage disc, and performing spot welding to the tested stage disc along the path;
and penetrating the armor wires from the first through holes of the tested stage disc into the mortises of the tested stage disc, and switching the armor wires with the armor wires of the test stage strain gauges of the integral multistage disc of the later stage.
2. The method for routing the high-temperature strain gauge of the rear-stage integral multi-stage disc mortise connection structure blade according to claim 1 is characterized in that,
the first through hole is perforated from the outer side of the hub mortises to the inner side of the hub, and the included angle between the axis of the first through hole and the horizontal plane is 45-60 degrees.
3. The method for routing the high-temperature strain gauge of the rear-stage integral multi-stage disc mortise connection structure blade according to claim 1 is characterized in that,
the second through hole is perforated from the outer side of the hub mortises to the inner side of the hub, and the included angle between the axis of the second through hole and the horizontal plane is 120-135 degrees.
4. The method for routing the high-temperature strain gauge of the rear-stage integral multi-stage disk tongue-and-groove connection structure blade according to claim 1, further comprising:
the welding point part at the joint of the armor wires and the armor wires of the rear-stage integral multi-stage disc test-stage strain gauge is protected and laminated through the skin;
injecting white tooth-sleeved insulating glue into the skin protection layer until the white tooth-sleeved insulating glue fills the whole skin protection layer;
after standing for 4 to 6 hours, the signal state and insulation effect of the armor wires of the rear-stage integral multi-stage disc test-stage strain gauge were tested.
5. The method for routing the high-temperature strain gauge of the rear-stage integral multi-stage disk tongue-and-groove connection structure blade according to claim 1, further comprising: the armor wires of the subsequent stage integral multi-stage disc test stage strain gage were preformed into a spiral spring structure and placed at the blade dovetail.
6. The method for routing the high-temperature strain gauge of the rear-stage integral multi-stage disc mortise connection structure blade according to claim 1 is characterized in that,
pulling the armor wires through the rod-shaped objects when the armor wires pass through the second through holes of the middle stage disc from the first through holes of the front stage disc; or,
the armor wires are pulled by the rod-like objects as they pass from the first through holes of the intermediate stage trays to the second through holes of the intermediate stage trays.
7. The method for routing the high-temperature strain gauge of the rear-stage integral multi-stage disk tongue-and-groove connection structure blade according to claim 1, wherein the axis of the first through hole and the axis of the second through hole are located in the same radial plane.
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| CN202410057897.5A CN117595156B (en) | 2024-01-16 | 2024-01-16 | High-temperature strain gauge wiring method for rear-stage integral multi-stage disc mortise connection structure blade |
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| CN202410057897.5A CN117595156B (en) | 2024-01-16 | 2024-01-16 | High-temperature strain gauge wiring method for rear-stage integral multi-stage disc mortise connection structure blade |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN101839216A (en) * | 2010-05-11 | 2010-09-22 | 无锡风电设计研究院有限公司 | Intelligent blade of wind power generator with strain sensors |
| CN202266495U (en) * | 2011-07-19 | 2012-06-06 | 中航商用航空发动机有限责任公司 | Central draw bar type high pressure compressor rotor |
| CN107367344A (en) * | 2017-07-05 | 2017-11-21 | 南京理工大学 | A kind of mixer mechanics parameter measurement apparatus |
| CN111140542A (en) * | 2020-01-16 | 2020-05-12 | 北京航空航天大学 | Element-level tenon type blade with front edge provided with three pressure sensing holes |
| US20200164704A1 (en) * | 2018-11-27 | 2020-05-28 | Aperia Technologies, Inc. | Hub-integrated inflation system |
| CN212130865U (en) * | 2020-03-24 | 2020-12-11 | 珠海格力电器股份有限公司 | Chassis and air outlet device |
| CN116380295A (en) * | 2023-06-05 | 2023-07-04 | 中国航发四川燃气涡轮研究院 | Wiring method for high-temperature strain gauge of middle-stage blisk blade of air compressor |
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2024
- 2024-01-16 CN CN202410057897.5A patent/CN117595156B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101839216A (en) * | 2010-05-11 | 2010-09-22 | 无锡风电设计研究院有限公司 | Intelligent blade of wind power generator with strain sensors |
| CN202266495U (en) * | 2011-07-19 | 2012-06-06 | 中航商用航空发动机有限责任公司 | Central draw bar type high pressure compressor rotor |
| CN107367344A (en) * | 2017-07-05 | 2017-11-21 | 南京理工大学 | A kind of mixer mechanics parameter measurement apparatus |
| US20200164704A1 (en) * | 2018-11-27 | 2020-05-28 | Aperia Technologies, Inc. | Hub-integrated inflation system |
| CN111140542A (en) * | 2020-01-16 | 2020-05-12 | 北京航空航天大学 | Element-level tenon type blade with front edge provided with three pressure sensing holes |
| CN212130865U (en) * | 2020-03-24 | 2020-12-11 | 珠海格力电器股份有限公司 | Chassis and air outlet device |
| CN116380295A (en) * | 2023-06-05 | 2023-07-04 | 中国航发四川燃气涡轮研究院 | Wiring method for high-temperature strain gauge of middle-stage blisk blade of air compressor |
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| CN117595156B (en) | 2024-05-03 |
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