CN115950639B - Dynamic stress test line switching method for disc separation fan rotor blade - Google Patents
Dynamic stress test line switching method for disc separation fan rotor blade Download PDFInfo
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- CN115950639B CN115950639B CN202310218525.1A CN202310218525A CN115950639B CN 115950639 B CN115950639 B CN 115950639B CN 202310218525 A CN202310218525 A CN 202310218525A CN 115950639 B CN115950639 B CN 115950639B
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- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/70—Wind energy
- Y02E10/72—Wind turbines with rotation axis in wind direction
Abstract
The invention provides a dynamic stress test line switching method for a rotor blade of a disc separation fan, which comprises the following steps: step 1, leading out an adapter lead of a strain gauge on a blade to one side of a front baffle ring of the end face of a fan blade disc; step 2, one end of a dynamic measurement lead is connected to a remote measurement system, and the other end of the dynamic measurement lead passes through a threading hole on a fan booster stage hub barrel and is led out to one side of a front baffle ring of the end face of a fan blade disc; and step 3, connecting the switching lead wire with the movable testing lead wire in a dislocation way on one side of the baffle ring in front of the end face of the fan blade disc. The method for switching the dynamic stress test line can solve the problem of transmission of dynamic test signals caused by the influence of structural constraint and assembly sequence of the lead wire of the dynamic stress test line of the rotor blade of the disc separation type fan.
Description
Technical Field
The invention relates to the technical field of dynamic stress testing of fan rotor blades of aeroengines, in particular to a dynamic stress testing line switching method for separating fan rotor blades from discs.
Background
In the development process of the aeroengine, the dynamic stress of the component is measured to determine the stress characteristic in the working rotating speed range, and whether harmful resonance exists is judged, so that corresponding optimization measures are formulated for the fan rotor blade. The dynamic testing of the fan rotor blade is an essential path in the development stage of the aeroengine, and the determination of the wiring method for testing the dynamic stress of the fan rotor plays an important role in ensuring the accurate transmission of dynamic testing signals.
Currently, in certain types of aircraft engine assembly sequences, the disc-separated fan rotor blade installation lags behind the fan booster stage, and the telemetry device is installed within the fan booster stage hub such that the dynamic sensing leads cannot pass along the fan rotor blade through the fan disc through holes directly into the fan booster stage hub. Thus, limited to the above-described assembly sequence, the access of the dynamic wire to the telemetry system, and the accurate transmission of the dynamic wire signal presents a number of new challenges.
In view of this, under the influence of structural constraints and assembly sequences, a new patch cord method must be designed to ensure that dynamic stress data of the fan rotor is smoothly input into the data acquisition system.
Disclosure of Invention
The invention aims to disclose a dynamic stress test wire switching method for a disc separation fan rotor blade, which is used for solving the problem of dynamic test signal transmission caused by the influence of structural constraint and assembly sequence of a disc separation fan rotor blade dynamic stress test wire lead.
The technical scheme for realizing the aim of the invention is as follows: a dynamic stress test line switching method for a disc separation fan rotor blade, comprising the steps of:
and step 3, connecting the switching lead wire with the movable testing lead wire in a dislocation way on one side of the baffle ring in front of the end face of the fan blade disc.
In step 1, the strain gauge is arranged on a position to be measured on the surface of the blade, and the transfer lead of the strain gauge is led out from the surface of the blade until reaching the front baffle ring side of the end face of the fan blade disc.
In step 3, the transfer lead and the movable test lead are connected in a staggered manner by soldering.
Furthermore, the connection position of the switching lead and the dynamic measurement lead is wrapped by a polytetrafluoroethylene film.
Further, the switching lead and the dynamic measurement lead are covered wires.
Furthermore, an annular allowance is arranged at one end of the transfer lead, which is connected with the movable test lead.
In step 2, the threading hole is arranged on the fan booster stage hub and is matched with the fan blade disc, and the threading hole is plugged in a spot welding skin mode.
Compared with the prior art, the invention has the beneficial effects that: according to the dynamic stress test line switching method for designing the disc separation fan rotor blade, a sectional wiring mode is adopted, then each section is connected in a soldering mode, so that the dynamic stress signal monitored by the strain gauge is accurately transmitted into the data acquisition system from the fan blade to the telemetry system through the fan blade disc and the fan booster stage hub, and the influence on the wiring of the dynamic stress test line due to the assembly sequence of the engine is avoided;
meanwhile, the movable test lines are connected in a staggered manner through soldering staggered connection, and insulation protection is carried out through a polytetrafluoroethylene film, so that the influence of short circuit and the like after the connection parts of all the sections are contacted can be avoided; through carrying out spot welding covering to the through wires hole in the fan booster stage hub section of thick bamboo, can stop external gas inflow hub section of thick bamboo intracavity, and carry out the surplus design and adopt whole spot welding covering's mode to moving the survey line and can avoid moving survey line and take place cracked phenomenon because of drawing, realized moving survey signal acquisition, provide powerful technical support for realizing fan rotor blade dynamic stress test on-line monitoring.
Drawings
In order to more clearly illustrate the technical solution of the embodiments of the present invention, the drawings that are needed in the description of the embodiments will be briefly described.
FIG. 1 is a schematic illustration of a disk separation fan rotor blade dynamic stress testing system in accordance with an embodiment;
FIG. 2 is a flow chart of a dynamic stress test line switchover method for a disk separation fan rotor blade of the present invention;
FIG. 3 is a schematic diagram of a transfer wire and a moving wire being subjected to offset welding in an embodiment;
wherein, 1, the blade; 2. strain gauges; 3. a fan boost stage hub; 4. a telemetry system; 5. a fan blade disc; 11. a transfer lead; 12. a dynamic measurement lead; 14. and a threading hole.
Detailed Description
The invention will be further described with reference to specific embodiments, and advantages and features of the invention will become apparent from the description. These examples are merely exemplary and do not limit the scope of the invention in any way. It will be understood by those skilled in the art that various changes and substitutions of details and forms of the technical solution of the present invention may be made without departing from the spirit and scope of the present invention, but these changes and substitutions fall within the scope of the present invention.
Referring to fig. 1, a schematic diagram of a disk separation fan rotor blade dynamic stress testing apparatus is shown, wherein strain gauges 2 are provided on the surface of the blade 1 at the points to be measured, and the strain gauges 2 are connected to a telemetry system located within the fan booster stage hub 3. In this embodiment, the mounting of the disc-separated fan rotor blades is delayed from the fan boost stage during engine assembly, but the telemetry system is mounted within the fan boost stage hub 3, thus preventing dynamic stress test wires from passing along the blades 1 through the fan disc 5 through holes into the fan boost stage hub 3 directly into the telemetry system 4.
On the basis, the embodiment discloses a dynamic stress test line switching method for a rotor blade of a disc separation fan, and referring to fig. 2, the dynamic stress test line switching method comprises the following steps:
and 3, connecting the switching lead 11 and the movable measuring lead 12 in a staggered manner on one side of the baffle ring in front of the end face of the fan blade disc 5.
The dynamic stress testing line is segmented, the segmented dynamic stress testing line is respectively wired, and then the segmented dynamic stress testing line is connected, so that the dynamic stress signals monitored by the strain gauge are accurately transmitted into the data acquisition system from the fan blade to the telemetry system through the fan blade disc and the fan booster stage hub, and the influence on wiring of the dynamic stress testing line due to the assembly sequence of the engine is avoided.
In one embodiment, in step 1, referring to fig. 1, the strain gauge 2 is disposed on the surface of the blade 1 at a site to be measured, and the transfer lead 11 of the strain gauge 2 is led out from the surface of the blade 1 to the front baffle ring side of the end face of the fan blade disc 5.
In one embodiment, in step 2, referring to fig. 1, the threading hole 14 is disposed on the fan booster stage hub 3 and at an end surface position matching with the fan blade disc 5, and the threading hole is plugged by spot welding with a skin. When the movable measuring lead 12 is connected with the telemetry system 4, firstly, the movable measuring lead 12 is penetrated out from the threading hole 14 processed on the fan booster stage hub 3, then the threading hole 14 is plugged in a skin welding mode, and finally, the movable measuring lead 12 penetrating out of the threading hole 14 is connected with the telemetry system 4. The threading hole 14 is plugged by spot welding the skin, so that external air can be prevented from entering the fan booster stage hub 3 through the threading hole 14.
In one embodiment, in step 3, referring to fig. 3, the transfer lead 11 and the movable lead 12 are connected in a staggered manner by soldering. In this embodiment, the distance between the connection points may be set to 3-5 mm, so as to avoid the occurrence of abnormal signal caused by short circuit due to contact between adjacent dynamic stress test lines.
In an embodiment not shown in the drawings, the connection position of the switching lead 11 and the dynamic testing lead 12 is wrapped with a polytetrafluoroethylene film, and a spot welding metal skin is adopted to achieve the purposes of avoiding the short circuit between the dynamic stress testing line and the engine and protecting the fixed dynamic stress testing line, and achieve the purpose that a dynamic testing signal is accessed into the telemetry system 4 from the blade 1, so that the dynamic stress of the blade 1 is tested.
In an alternative embodiment, the transfer lead 11 and the dynamic measurement lead 12 are covered wires.
In an alternative embodiment, the end of the transfer lead 11 connected to the moving wire 12 is provided with an annular allowance, and the annular allowance has an anti-tear effect, so that the effect of breaking the moving wire due to circumferential movement in the working state of the disc separation type blade can be avoided. In this embodiment, the length of the annular margin may be set to 10 to 15mm.
According to the dynamic stress test wire switching method disclosed by the specific embodiment, the sectional wiring mode is adopted, then each section is connected through soldering or skin spot welding, the fact that the dynamic stress signal monitored by the strain gauge is accurately transmitted into the data acquisition system from the fan blade to the telemetry system 4 through the fan blade disc and the fan booster stage hub 3 is ensured, and the influence on the wiring of the dynamic stress test wire due to the assembly sequence of the engine is avoided.
Meanwhile, the movable test lines are connected in a staggered manner in a manner of insulating protection and soldering fixation through the polytetrafluoroethylene film, so that the influence of short circuit and the like caused by contact of the connecting parts of all the sections can be avoided; through carrying out spot welding covering to the through wires hole 14 in the fan booster stage hub section of thick bamboo 3, can stop external gas inflow fan booster stage hub section of thick bamboo 3 intracavity, and carry out the surplus design to moving survey line 12 and adopt whole spot welding covering's mode can avoid moving survey line and take place cracked phenomenon because of drawing, realized moving survey signal acquisition, provide powerful technical support for realizing fan rotor blade dynamic stress test on-line monitoring.
The foregoing description of the preferred embodiments of the invention is not intended to be limiting, but rather is intended to cover all modifications, equivalents, alternatives, and improvements that fall within the spirit and scope of the invention.
Furthermore, it should be understood that although the present disclosure describes embodiments, not every embodiment is provided with a separate embodiment, and that this description is provided for clarity only, and that the disclosure is not limited to the embodiments described in detail below, and that the embodiments described in the examples may be combined as appropriate to form other embodiments that will be apparent to those skilled in the art.
Claims (6)
1. A dynamic stress test line switching method for a disc separation fan rotor blade, comprising the steps of:
step 1, leading out an adapter lead of a strain gauge on a blade to one side of a front baffle ring of the end face of a fan blade disc;
step 2, one end of a dynamic measurement lead is connected to a remote measurement system, and the other end of the dynamic measurement lead passes through a threading hole on a fan booster stage hub barrel and is led out to one side of a front baffle ring of the end face of a fan blade disc;
and step 3, connecting the switching lead wire with the movable testing lead wire in a dislocation way on one side of the baffle ring in front of the end face of the fan blade disc.
2. The method according to claim 1, wherein in step 3, the transfer lead and the dynamic test lead are connected in a staggered manner by soldering.
3. The method for switching a dynamic stress test wire according to claim 2, wherein a polytetrafluoroethylene film is wrapped at a connection position of the switching lead and the dynamic test lead.
4. The method of claim 2, wherein the transfer leads and the dynamic test leads are wire-wrapped wires.
5. The method for transferring dynamic stress test wires according to any one of claims 1 to 4, wherein an annular margin is provided at an end of the transfer lead connected to the dynamic test wire.
6. The method according to claim 1, wherein in step 2, the threading hole is provided on the fan booster stage hub and at an end surface position matching with the fan blade disc, and the threading hole is plugged by spot welding.
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| CN202310218525.1A CN115950639B (en) | 2023-03-09 | 2023-03-09 | Dynamic stress test line switching method for disc separation fan rotor blade |
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| CN202310218525.1A CN115950639B (en) | 2023-03-09 | 2023-03-09 | Dynamic stress test line switching method for disc separation fan rotor blade |
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| CN115950639B true CN115950639B (en) | 2023-06-30 |
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| CN116793685B (en) * | 2023-05-26 | 2024-02-20 | 中国航发四川燃气涡轮研究院 | Blind cavity dynamic stress test lead wire of aero-engine rotor and fixing method thereof |
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