CN116175990B - Device and method for solving oil leakage faults of aeroengine parting film - Google Patents
Device and method for solving oil leakage faults of aeroengine parting film Download PDFInfo
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- CN116175990B CN116175990B CN202310444001.4A CN202310444001A CN116175990B CN 116175990 B CN116175990 B CN 116175990B CN 202310444001 A CN202310444001 A CN 202310444001A CN 116175990 B CN116175990 B CN 116175990B
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- film
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
- B29C65/56—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using mechanical means or mechanical connections, e.g. form-fits
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P21/00—Machines for assembling a multiplicity of different parts to compose units, with or without preceding or subsequent working of such parts, e.g. with programme control
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/748—Machines or parts thereof not otherwise provided for
- B29L2031/749—Motors
Abstract
The invention belongs to the technical field of aeroengine parts, and particularly relates to a device and a method for solving the oil leakage fault of an aeroengine add-divide film.
Description
Technical Field
The invention belongs to the technical field of aero-engine parts, and particularly relates to a device and a method for solving oil leakage faults of an aero-engine parting film.
Background
The forced fuel distributor is a control accessory widely used on the engine with forced turbofan, and is called "forced fuel distributor" for short.
Each adding part is divided into three groups of film components, the film material is polyimide and is used for isolating P6 air and fuel oil, once the film is broken, the fuel oil can flow into a P6 air-entraining pipe to enter an afterburner, and the temperature of the afterburner is higher, so that tail nozzle fire accidents happen for a plurality of times, and great harm is caused to engines and airplanes. For a long time, whether imported or domestic new engines are added or batch repaired engines are added, oil leakage faults caused by film breakage can occur in the using process, the number of the oil leakage faults of the added films is between 20 and 30 in an inner factory and an outer factory according to statistics, the faults are not radically cured for decades, the root cause is that the stress generated in working exceeds the strength limit of the film, the film breakage occurs, the service life of the film assembly is greatly reduced, and finally the film oil leakage faults without a service life rule are displayed.
The method for assembling the stress application fuel dispenser in the prior art has the problems of uneven stress and mechanical damage of the film, is difficult to overcome the problems of manual operation, interference among working procedures and the like, and needs to comprehensively control the generation of the working stress of the film from the aspects of components, operation methods, interference among working procedures and the like associated with the film, realize the working procedure links, mainly adopt targeted control measures from four links of fault detection, repair, assembly and test, and reduce the working stress of the film.
Disclosure of Invention
In order to solve the technical problems, the invention adopts the following technical scheme:
a set of methods for resolving oil leakage faults in an aircraft engine parting film comprising the steps of:
s1, checking sharp edges and burr defects of edges of a disc and a mounting seat and performing defect treatment;
s2, stacking a plurality of films on the film concentricity maintaining device by adopting the film concentricity maintaining device, integrally moving the films into the mounting seat, fixing the disc by adopting the disc fixing device, and assembling the film assembly;
s3, placing the film components assembled in the S2 into corresponding cavities of the stress application fuel distributor shell by using the film concentric components, screwing the screw plugs, compacting and fixing the film components, ensuring that the cover is compacted with the film, and completing the assembly of the stress application fuel distributor;
and S4, delivering and checking the stress application fuel oil distributor assembled with the film assembly in the step S3, loosening the screw plug, replacing the adjusting gasket with proper thickness according to the performance requirement, and reassembling according to the step S3.
Further, in S2, when the disc fixing device is used, the locking plate is clamped and bent by the safety tongs, so that the tail part of the locking plate is vertically bent and is attached to the right-angle side of the disc, and the assembly of the thin film assembly is completed.
Further, in S3, after the membrane component is put into the shell, a spring seat, a spring, an adjusting gasket and a cover are sequentially installed, and then the screw plug is rotated.
Further, the tightening torque is performed using a torque wrench, and the cap is not loosened during one-time tightening until the torque is 24.5n·m to 29.4n·m.
Further, a tightening torque is performed using a torque wrench, and the tightening torque of the plug screw is set to 12±0.5n·m.
In step S3, after the stress application fuel distributor is assembled, a rotary mark is drawn on the cover and the shell by using a marker pen.
Further, in S1, sharp edges and burr defects are polished by fine sand paper.
Further, in S4, the cap is fixed using a screw stopper fixing device, and the screw stopper is loosened again using a wrench.
The invention also discloses a group of devices for solving the oil leakage faults of the aeroengine parting film, which comprises a disc fixing device, wherein the disc fixing device is provided with a cover body which is downwards opened, a through hole for a fixing screw to extend out and a notch for embedding a locking plate are formed in the top of the cover body, a fixing ring seat is also arranged on the periphery of the bottom of the cover body, a plurality of grooves are uniformly formed in the circumference of the fixing ring seat, and the device also comprises a screw plug fixing device, the screw plug fixing device is provided with a handle body and a fixing head part connected with one side of the handle body, and the fixing head part is in a downward convex arc shape.
Compared with the prior art, the invention has the following beneficial effects:
the invention designs a targeted device in each procedure link from the procedures of fault detection, repair, assembly and test, and assists a corresponding new process method to reduce the working stress of the film assembly, prevent the interference between procedures, reduce the working stress of the film assembly to the minimum and greatly improve the service life of the film assembly.
Drawings
FIG. 1 is a schematic view of a membrane module according to an embodiment of the present invention;
FIG. 2 is a schematic view of a film concentricity apparatus according to an embodiment of the present invention;
FIG. 3 is a schematic top view of a disk fixture according to an embodiment of the present invention;
FIG. 4 is a schematic cross-sectional view of a disc fixture according to an embodiment of the present invention;
FIG. 5 is a schematic view of the structure of the safety tongs according to the embodiment of the present invention;
FIG. 6 is a schematic cross-sectional view of a housing according to an embodiment of the present invention;
FIG. 7 is a schematic view of a transfer joint according to an embodiment of the present invention;
FIG. 8 is a schematic top view of a screw plug fixture according to an embodiment of the present invention;
FIG. 9 is a schematic diagram showing a front view of a screw plug fixing device according to an embodiment of the present invention;
reference numerals in the drawings of the specification include:
Detailed Description
In order that those skilled in the art will better understand the present invention, the following technical scheme of the present invention will be further described with reference to the accompanying drawings and examples.
Wherein the drawings are for illustrative purposes only and are shown in schematic, non-physical, and not intended to be limiting of the present patent; for the purpose of better illustrating embodiments of the invention, certain elements of the drawings may be omitted, enlarged or reduced and do not represent the size of the actual product; it will be appreciated by those skilled in the art that certain well-known structures in the drawings and descriptions thereof may be omitted.
Examples:
the method for solving the oil leakage faults of the film added to the aero-engine is divided into a fault detection process, a repair process, a film assembly and a test process.
As shown in fig. 1, the film assembly 1 mainly comprises a fixing screw 11, a locking plate 12, a disc 13, 4 films 14, a sealing ring 15 and a mounting seat 16, wherein the films 14 are clamped and fixed by the disc 13 and the mounting seat 16, when the film assembly 1 works, the films 14 move up and down under the alternating action of air pressure and oil pressure, the films 14 are repeatedly bent and extruded with the edges of the disc 13 and the mounting seat 16 to generate stress concentration, the disc 13 and the mounting seat 16 are easy to generate sharp edges, burrs and other defects in the manufacturing and using processes, the stress concentration of the films 14 is aggravated under the working condition, and the edges of the disc 13 and the mounting seat 16 are required to be subjected to targeted fault detection and repair.
In the specific improvement implementation, the checking procedure adopts visual checking to check whether the edges of the disk 13 and the mounting seat 16 have sharp edges, burrs and other defects, ensures that the parts directly contacted with the film 14 have no mechanical damage, and if the defects and the damage are found, enters the repairing procedure, and uses fine sand paper to polish the edges of the disk 13 and the mounting seat 16 so as to eliminate the sharp edges, the burrs and other defects.
Because 4 films 14 are stacked and installed, a certain gap exists between the central hole of each film 14 and the supporting column of the installation seat 16, and the stacking non-concentricity of the 4 films 14 is easy to occur, so that the stress of the films is uneven, the overall strength of the film assembly 1 is reduced, the installation concentricity of the 4 films 14 needs to be controlled, in the assembly of the film assembly, the 4 films 14 are stacked on the film concentricity maintaining device 2 by adopting the film concentricity maintaining device 2, and then the 4 films 14 are integrally placed on the installation seat 16.
The main body of the film concentricity keeping device 2 is provided with a taper, the film 14 can realize automatic concentricity under the action of gravity, and the film 14 is circular due to the fact that the center of the film 14 is provided with a hole, the thickness of the film is only 0.2mm, the film is made of polyimide, the film has adsorptivity, and concentricity cannot be lost again in transferring, as shown in fig. 2.
The film 14 is fixed between the disk 13 and the mounting seat 16, and is fixed through the set screw 11, the locking plate 12 and the sealing ring 15, the tail part of the locking plate 12 is required to be perpendicularly bent and overlaid on the right-angle side of the disk 13, the set screw 11 is required to be screwed up by 3.5N.m moment, the traditional bare-handed mounting is adopted, the locking plate 12 can be rotated along with the set screw 11, the control is difficult, the tail part of the locking plate 12 is required to be perpendicularly bent and overlaid on the right-angle side of the disk 13 only by repeated disassembly and assembly, the film 14 is damaged in the repeated disassembly and assembly process, the service life of the film is greatly reduced, and the repeated disassembly and assembly of the film 14 are required to be avoided when the film is fixed.
According to the improved method, as shown in fig. 3-5, when the disc 13 is installed, the disc 13 and the locking plate 12 are limited and fixed by the disc fixing device 3 and the film 14 is protected, the locking plate 12 is bent and pressed by the safety tongs 4 to complete the assembly of the film assembly, as shown in fig. 3 and 4, the disc fixing device 3 is provided with a cover body 30 with a downward opening, a through hole 31 for extending a fixing screw 11 and a notch 32 for embedding the locking plate 12 are formed in the top of the cover body 30, in addition, a fixing ring seat 33 is further formed in the periphery of the bottom of the cover body 30, a plurality of grooves 34 are uniformly formed in the periphery of the fixing ring seat 33, the part to be bent of the locking plate 12 is horizontally embedded into the notch 32, the locking plate 12 can be prevented from following rotation when the fixing screw 11 is screwed with the aid of the disc fixing device 3, the whole disc fixing device 3 is removed to avoid shielding, and then the locking plate 12 is bent by the safety tongs 4.
As shown in fig. 5, the safety tongs 4 include a jaw 41, a right jaw 42, a left jaw 43, a countersunk head rivet 44, a half head rivet 45, and a countersunk head rivet 46.
The separated shell 5 cavity is shown in fig. 6, after the membrane component 1 is independently assembled, the membrane component 1 is installed and fixed in the shell 5 cavity, the traditional installation method is adopted to visually observe and align, the concentricity of the membrane component 1 and the shell 5 circular cavity cannot be effectively ensured, when the membrane component 1 moves up and down in the shell 5 cavity, deflection stress concentration occurs, the service life of the membrane component 1 is reduced, effective measures are needed to be taken to control the concentricity of the membrane component 1 installed and fixed in the shell 5 cavity, the membrane concentric component for installing the membrane component 1 into the shell 5 cavity of the forced fuel distributor is adopted to ensure the concentricity of the membrane component 1 in the shell 5 cavity, the membrane concentric component is in the prior art, a guide channel is formed by designing a leakage inclined plane, the membrane concentric component is firstly installed in the shell 5, then the membrane component 1 is installed to the center position of the shell 5 cavity along the wall surface of the membrane concentric component, and the specific structure of the membrane concentric component is not repeated.
As shown in FIG. 6, after the membrane module 1 is put into the cavity of the housing 5, the membrane 14 needs to be compressed by the cover plate 520, the stop ring 52 is put on, and then the cover 59 with the divided sealing ring 510 and the fluoroplastic ring 511 is used to rotate and compress the stop ring 52 and the cover plate 520, so that the compression fixation of the membrane module 1 is realized, the traditional screwing method adopts forward rotation for 1 turn and backward back loosening for 0.5 turn, repeated screwing and back loosening are performed for a plurality of times, and finally the stop ring 52, the cover plate 520 and the membrane module 1 are compressed by a torque of 24.5N.m-29.4N.m.
According to the invention, after the thin film component 1 is assembled and fixed, the spring seat 53, the spring 57 and the adjusting gasket 56 are sequentially installed, wherein the spring 57 is arranged in the spring cavity 54 and then is rotationally fixed by the screw plug 55 with the sealing ring, in the original process method, the screwing moment of the screw plug 55 is not regulated, only the screwing moment is required, as the screw plug 55 and the cover 59 for fixing the thin film component 1 are in the same direction, the screwing moment is 24.5N.m-29.4N.m when the cover 59 is fixed, the screw plug 55 has no moment control requirement, the situation that the cover 59 is screwed or unscrewed exists when the screw plug 55 is screwed or unscrewed, the assembly structure can know that the installation and the fixation of the thin film component 1 is completely determined by the cover 59, once the cover 59 is screwed, the thin film component 1 is twisted under the action of the spring 57 and the spring seat 53, the stress concentration is generated, the service life is greatly reduced, and measures are required to avoid the screw plug 55 from screwing the cover 59.
In the assembly process of the stressing fuel dispenser, the screwing mode of the cover 59 is improved, the traditional screwing mode is changed from the screwing mode of 1 circle to the unscrewing mode of 0.5 circle, and repeated operation is repeated until the screwing mode is changed to the screwing mode of 24.5 N.m-29.4 N.m, the unscrewing is not performed in one-time screwing mode until the screwing mode is changed to the screwing mode of 24.5 N.m-29.4 N.m, the moment of the screw plug 55 is formulated, the screw plug 55 is prevented from rotating the cover 59, through multiple test verification, the screwing moment of the screw plug 55 is set to be 12+/-0.5 N.m, and when the screwing moment is implemented, the special torque wrench adapter 6 for the screw plug 55 can be designed.
In addition, a rotational marking of the cover 59 can be identified on the housing 5, wherein the adapter, as shown in fig. 7, the torque wrench adapter 6 comprises a socket 60, a connecting head 61.
By adopting the steps, after the screw plug 55 and the cover 59 are assembled, the relative positions of the cover 59 and the shell 5 are not changed when the screw plug and the cover 59 are transferred to a test procedure.
After finishing the final assembly of the adding part, the mixture is required to be sent to a laboratory for performance test, the screw plug 55 is loosened and taken down according to the requirement of the performance parameters of the product, the thickness of the adjusting gasket 56 is adjusted, and then the adjusting gasket 56, the sealing ring and the screw plug 55 are restored to be assembled according to the assembly requirement, wherein the adjusting gasket 56 is replaced, so that the adjusting gasket 56 is changed to adjust the performance parameters of the adding part to meet the process requirement.
Since the tightening torque of the screw plug 55 is not specified in the conventional process, randomness exists in the tightness of the screw plug 55, when the screw plug 55 is loosened, the cover 59 is rotated, so that the original assembly position of the film assembly 1 is changed, and finally the film 14 is subjected to stress concentration, effective measures are required, and when the screw plug 55 is loosened and fixed, the cover 59 is ensured not to rotate.
In the test procedure, the screw plug 55 is fixed by the screw plug fixing device 7, so that the cover 59 does not rotate when the screw plug 55 is loosened.
In the specific implementation, the cover 59 is checked for rotation marks, if the mark line on the housing 5 is misaligned with the mark line on the cover 59, the mark line is returned to the assembling process, the film assembly 1 is disassembled, the parts such as the fixed film assembly 1 are reinstalled according to the new assembling method, the assembly is resumed, and then the parts are sent to the test for debugging, in addition, the adjusting gasket 56 is replaced according to the performance requirement, and the assembly is resumed according to the new requirement of the assembling screw plug 55.
As shown in fig. 8 and 9, the screw fixing device 7 has a shank 70 and a fixing head 71 connected to one side of the shank 70, the fixing head 71 has a downward convex arc shape, and when the screw fixing device 7 is in use, the fixing head 71 of the screw fixing device 7 is engaged into a peripheral hexagonal groove of the cap 59, the shank 70 is held by a hand to apply downward force, the fixing head 71 abuts against the cap 59, the cap 59 is pressed and fixed, and the screw 55 is screwed into the screw 55 by a wrench to rotate the screw 55 in a loosening direction.
By adopting the method and the device, the invention carries out targeted control from the whole working procedure, eliminates the operation interference existing in the original process method, reduces the working stress of the film assembly 1 to the minimum, greatly prolongs the service life of the film assembly 1, and solves the common multiple faults which plague enterprises for decades by the fact that the actual system verification of enterprises and the actual installation application are carried out, the new process method is used for accumulating batch delivery and adding 950 steps, the film oil leakage fault condition does not occur in the internal and external fields, and the film oil leakage fault condition is greatly reduced by 20 to 30 years. In the aspect of economic benefit, the cost of personnel business trip, delay of construction period, replacement and the like caused by thin film oil leakage is greatly saved, the cost is saved by 20-30 ten thousand for enterprises in one year according to 1 ten thousand yuan per time, and the recovery value of equipment quality image is immeasurable.
The foregoing is merely exemplary of the present invention, and the specific structures and features well known in the art are not described in any way herein, so that those skilled in the art will be able to ascertain all prior art in the field, and will not be able to ascertain any prior art to which this invention pertains, without the general knowledge of the skilled person in the field, before the application date or the priority date, to practice the present invention, with the ability of these skilled persons to perfect and practice this invention, with the help of the teachings of this application, with some typical known structures or methods not being the obstacle to the practice of this application by those skilled in the art. It should be noted that modifications and improvements can be made by those skilled in the art without departing from the structure of the present invention, and these should also be considered as the scope of the present invention, which does not affect the effect of the implementation of the present invention and the utility of the patent.
Claims (7)
1. The method for solving the oil leakage fault of the aeroengine parting film is characterized by comprising the following steps of: the method comprises the following steps:
s1, checking sharp edges and burr defects of edges of a disc and a mounting seat and performing defect treatment;
s2, stacking a plurality of films on the film concentricity maintaining device by adopting the film concentricity maintaining device, integrally moving the films into the mounting seat, fixing the disc by adopting the disc fixing device, and assembling the film assembly;
s3, placing the film components assembled in the S2 into corresponding cavities of the stress application fuel distributor shell by using the film concentric components, screwing the screw plugs, compacting and fixing the film components, ensuring that the cover is compacted with the film, and completing the assembly of the stress application fuel distributor;
s4, delivering and checking the stress application fuel oil distributor assembled with the film assembly in the S3, loosening the screw plug, replacing an adjusting gasket with proper thickness according to the performance requirement, and reassembling according to the S3;
the disc fixing device in S2 is provided with a cover body with a downward opening, a through hole for a fixing screw to extend out and a notch for embedding a locking plate are formed in the top of the cover body, a fixing ring seat is further arranged on the periphery of the bottom of the cover body, and a plurality of grooves are uniformly formed in the circumference of the fixing ring seat;
in S4, a screw plug fixing device is used for fixing the cover, and a spanner is used for loosening the screw plug;
the screw plug fixing device is provided with a handle body and a fixing head connected with one side of the handle body, and the fixing head is in a downward convex arc shape;
the film concentricity maintaining device body is provided with a taper, and the film can realize automatic concentricity under the action of gravity.
2. A set of methods for resolving oil leakage faults in aircraft engine parting films as claimed in claim 1, wherein: s2, when the disc fixing device is used, the locking plate is clamped and bent by the safety tongs, so that the tail part of the locking plate is vertically bent and is attached to the right-angle side of the disc, and the assembly of the film component is completed.
3. A set of methods for resolving oil leakage faults in aircraft engine parting films as claimed in claim 1, wherein: s3, after the film component is put into the shell, a spring seat, a spring, an adjusting gasket and a cover are sequentially installed, and then the screw plug is rotated.
4. A set of methods for resolving oil leakage faults in aircraft engine parting films as claimed in claim 3, characterised in that: the tightening torque is performed using a torque wrench, and the cap is not loosened during one-time tightening until the torque is 24.5n·m to 29.4n·m.
5. A set of methods for resolving oil leakage faults in aircraft engine parting films as claimed in claim 3, characterised in that: the tightening torque is performed using a torque wrench, and the tightening torque of the plug screw is set to 12±0.5n·m.
6. A set of methods for resolving oil leakage faults in aircraft engine parting films as claimed in claim 1, wherein: in the step S3, after the stress application fuel distributor is assembled, a rotary mark is drawn on the cover and the shell by using a marker pen.
7. A set of methods for resolving oil leakage faults in aircraft engine parting films as claimed in claim 1, wherein: in S1, sharp edges and burr defects are polished by fine sand paper.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310444001.4A CN116175990B (en) | 2023-04-24 | 2023-04-24 | Device and method for solving oil leakage faults of aeroengine parting film |
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| CN202310444001.4A CN116175990B (en) | 2023-04-24 | 2023-04-24 | Device and method for solving oil leakage faults of aeroengine parting film |
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| CN116175990B true CN116175990B (en) | 2023-07-11 |
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| CN106392153A (en) * | 2016-11-16 | 2017-02-15 | 中国人民解放军第五七九工厂 | Engine honeycombed embedded block inner moulded surface repairing device and repairing method thereof |
| CN113165100A (en) * | 2018-12-13 | 2021-07-23 | 豪梅特航空航天有限公司 | Rivet dispensing system and method of use |
| CN114472931A (en) * | 2022-02-18 | 2022-05-13 | 西安航天发动机有限公司 | Single-hinge type titanium alloy diaphragm turning method |
| CN115519315A (en) * | 2022-10-24 | 2022-12-27 | 中国航发南方工业有限公司 | Temperature difference method dismouting device of preceding baffle |
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