CN110842842A - Force-limiting assembly method and device for components of turbofan aircraft engine lubricating oil system - Google Patents
Force-limiting assembly method and device for components of turbofan aircraft engine lubricating oil system Download PDFInfo
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- CN110842842A CN110842842A CN201911135692.XA CN201911135692A CN110842842A CN 110842842 A CN110842842 A CN 110842842A CN 201911135692 A CN201911135692 A CN 201911135692A CN 110842842 A CN110842842 A CN 110842842A
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- China
- Prior art keywords
- oil system
- aircraft engine
- assembly
- lubricating oil
- turbofan aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25B—TOOLS OR BENCH DEVICES NOT OTHERWISE PROVIDED FOR, FOR FASTENING, CONNECTING, DISENGAGING OR HOLDING
- B25B27/00—Hand tools, specially adapted for fitting together or separating parts or objects whether or not involving some deformation, not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25B—TOOLS OR BENCH DEVICES NOT OTHERWISE PROVIDED FOR, FOR FASTENING, CONNECTING, DISENGAGING OR HOLDING
- B25B11/00—Work holders not covered by any preceding group in the subclass, e.g. magnetic work holders, vacuum work holders
Abstract
The invention discloses a force-limiting assembly method and device for a turbofan aircraft engine lubricating oil system component, wherein the device comprises a fixed seat, an annular groove (2), spline grooves (3) and a connecting seat, a plurality of connecting assembly holes (1) are formed in the connecting end surface of the fixed seat, the positions of the connecting assembly holes (1) correspond to the positions of component assembly holes (5) in the component one by one, the annular groove (2) is positioned on the connecting end surface, the depth of the annular groove (2) is greater than the height of a boss (6), and the spline grooves (3) are arranged in the annular groove (2); the connecting seat is connected with the lower end of the fixing seat, and a plurality of fixing holes (4) are formed in the bottom surface of the connecting seat along the circumferential direction. The invention solves the problems of limited freedom degree and easy deformation of the components, provides an accurate and efficient assembly mode and improves the working efficiency.
Description
Technical Field
The invention relates to the field of machine manufacturing, in particular to a force-limiting assembling device and method for a turbofan aircraft engine lubricating oil system component.
Background
The assembly of spare part in turbofan aircraft engine lubricating oil system lacks special frock always, leads to the assembly process difficulty to various problems appear easily, mainly have the assembly of limited force requirement to this spare part hardly the limit power, other also have like part deformation, part cooperation not good etc..
The current assembly scheme of the component is as follows: one of the 5 component assembling holes at the bottom of the part component is selected, any universal tool with similar assembling holes is screwed down by a bolt, a boss at the bottom is propped against the edge of the tool, and at least two workers hold the side surface of the component to fix the component.
The scheme mainly has the following defects:
1. it is difficult to achieve the force limiting requirements of some of the parts on the assembly. The freedom of assembling parts is not completely limited, and the parts can be rotated about the bolt without a worker holding the assembly. Even if the assembly is held, the assembly can shake to a small extent, and the force limiting assembly of the force limiting part can be influenced. Meanwhile, as one shaft in the component is required to be capable of rotating in the component in design, the shaft cannot be fixed by the shaft, and the force limiting requirements of some force limiting parts on the shaft are difficult to achieve;
2. the part may be deformed. The force limiting requirement during the installation of the force limiting part is more than 85 N.m, the moment is large, a worker is difficult to hold the component when holding the component and is easy to hurt, and the stress part is deformed because the component manufacturing material has poor rigidity and the stress position only has the lug boss edge and the bolt connection part during the assembly. This problem is also encountered during disassembly;
3. the assembly process is time consuming and labor intensive. The assembly of this subassembly needs two at least workers to hold the spare part specially to make it stable as far as possible, do not produce and rock and rotate, and the workman of assembly need be when guaranteeing the assembly power limit requirement pay attention to avoid the part assembly process because extrusion scheduling problem produces the deformation, therefore the assembly process is very consummated, and inefficiency.
In conclusion, the existing assembly scheme is not mature, and needs to be improved to some extent.
Disclosure of Invention
The invention aims to provide a force-limiting assembly method and device for a turbofan aircraft engine lubricating oil system component, which are used for force-limiting assembly of the turbofan aircraft engine lubricating oil system component and solve the problems that the existing assembly mode cannot effectively limit force, parts are easy to deform, efficiency is low and the like.
The force-limiting assembly device for the components of the turbofan aircraft engine lubricating oil system comprises,
the upper end of the fixed seat is a connecting end face for connecting with a turbofan aircraft engine lubricating oil system component, a plurality of connecting assembly holes are formed in the connecting end face, and the positions of the connecting assembly holes correspond to the positions of assembly holes in the turbofan aircraft engine lubricating oil system component one by one;
the annular groove is positioned on the connecting end face, the position of the annular groove corresponds to the position of a boss on a turbofan aircraft engine lubricating oil system component, and the depth of the annular groove is greater than the height of the boss;
the spline groove is arranged in the annular groove;
the connecting seat is connected with the lower end of the fixing seat, and a plurality of fixing holes are formed in the bottom surface of the connecting seat along the circumferential direction.
Preferably, the connecting assembly hole is a threaded hole, and the diameter and the threads of the connecting assembly hole are consistent with those of the assembly hole.
Preferably, the spline groove is located in a cavity cylinder, and the upper end of the cavity cylinder is not higher than the connecting end face of the fixing seat.
Preferably, the plurality of fixing holes on the bottom surface of the connecting seat are arranged on a circumference, and the vertical projection of the plurality of connecting assembly holes on the bottom surface of the connecting seat is arranged in the circumference.
A force limiting assembly method for a turbofan aircraft engine lubricating oil system component by adopting the device comprises the following steps:
connecting the turbofan aircraft engine lubricating oil system components with a fixed seat, connecting all connecting assembly holes on the fixed seat with assembly holes on the turbofan aircraft engine lubricating oil system components through connecting bolts, and ensuring that the connecting end surfaces on the fixed seat are tightly attached to the turbofan aircraft engine lubricating oil system components;
mounting a shaft on the turbofan aircraft engine lubricating oil system component, and extending the shaft into the component from the center of the top of the turbofan aircraft engine lubricating oil system component and matching with the spline groove on the fixed seat;
and step three, installing a force limiting part.
And in the second step, the shaft extends into the assembly from the center of the top of the turbofan aircraft engine lubricating oil system component until the shaft touches the fixed seat, and the position of the shaft is adjusted and slowly rotated to enable the shaft to be matched with the spline groove on the fixed seat.
Compared with the prior art, the novel tool is used for assembling the parts and components, and has the following three advantages:
1. the problems that the freedom degree of the component is not completely limited, the large-force-distance force-limiting part is difficult to meet the force-limiting requirement during assembly, and the part is easy to deform are solved;
2. the problem that a shaft on a component is difficult to fix, so that the force of an upper force limiting part of the shaft cannot be limited is solved;
3. an accurate and efficient assembly mode is provided, and the working efficiency is improved. In the past, the assembly and disassembly of the parts are completed by at least three workers, take at least 30 minutes, and are labor-consuming and easily injured; if the assembly device and the method are used for completing assembly, only one worker is needed, and only about 10 minutes of time is needed, so that the efficiency is improved by nearly 10 times, and the accuracy and the safety are also improved.
Drawings
FIG. 1 is a perspective view of a force limiting assembly device for components of a turbofan aircraft engine lubricating oil system;
FIG. 2 is a perspective view of a turbofan aircraft engine oil lubrication system component;
FIG. 3 is a schematic view of an assembly state of a force-limiting assembly device of a turbofan aircraft engine lubricating oil system component in cooperation with the turbofan aircraft engine lubricating oil system component.
Detailed Description
The present invention will be further described with reference to the accompanying drawings and specific embodiments, but it should not be understood that the scope of the subject matter of the present invention is limited to the following embodiments, and various modifications, substitutions and alterations made based on the common technical knowledge and conventional means in the art without departing from the technical idea of the present invention are included in the scope of the present invention.
When a design scheme of a force-limiting assembly device for a turbofan aircraft engine lubricating oil system component is formulated, the following factors are mainly considered:
1. how to limit the freedom degree of the whole turbofan aircraft engine lubricating oil system components and parts, so that the whole turbofan aircraft engine lubricating oil system components and parts are completely fixed;
2. how to ensure the force limit requirement in the assembly process, reduce the part deformation and ensure the form and position precision of the assembly;
3. on the premise of ensuring the former two, the assembly process is quick, simple and convenient, and the assembly efficiency is improved.
After the consideration of the three factors, the design scheme is obtained as follows:
the design shape profile and the size of fixing base in turbofan aircraft engine lubricating oil system spare part limit of force fit device are unanimous basically with this spare part bottom, and correspond with 5 subassembly pilot holes 5 in the spare part bottom and have 5 same position and the connection pilot hole 1 of size, connect pilot hole 1 through these 5 and fix this spare part completely with the bolt, guarantee that the part degree of freedom is restricted completely. The position of the boss 6 at the bottom of the component corresponds to the annular groove 2 with a slightly larger diameter, so that the boss 6 can go deep, and the bottom end face and the connecting end face of the fixing seat are completely attached and leveled. The design can ensure that the force limiting requirement can be met and the part can be prevented from deforming in the assembly of the force limiting part.
A cavity cylinder is arranged in the middle of the annular groove 2, and the spline grooves 3 are machined in the inner wall of the cavity cylinder and can be matched with a shaft on the component, so that the shaft is fixed, and the force limiting requirement of the force limiting part on the shaft is met.
As shown in fig. 1 to 3, the assembly device and the components of the turbofan aircraft engine lubricating oil system function as follows:
the 5 connecting assembly holes 1 on the assembly device correspond to the 5 assembly holes 5 on the assembly one by one, have the same diameter and thread, and can be screwed down by bolts to fix the assembly on a fixed seat of the assembly device and be attached to the connecting end surface of the fixed seat;
and the annular groove 2 is used for extending the boss 6 on the component into the annular groove so that the bottom surface of the component can be attached to the connecting end surface of the fixing seat of the assembling device, and the connecting assembling hole 1 and the component assembling hole 5 can be screwed up by using a bolt. The depth of the annular groove 2 is slightly larger than the height of the boss 6;
and the spline groove 3 is used for being matched with a spline 7 on a shaft protruding from the assembly so as to fix the shaft, and the subsequent force limiting assembly is facilitated. The spline grooves 3 are in clearance fit with the splines 7 on the shaft;
4 fixing holes 4 for fixing the assembling device on a workbench to facilitate subsequent assembling work;
the 5 assembly holes 5 on the assembly correspond to the 5 connecting and assembling holes 1 on the assembling device one by one, have the same diameter and thread, and can be screwed down by bolts to fix the assembly on a fixed seat of the assembling device and be attached to the connecting end surface of the fixed seat;
the boss 6 can extend into the annular groove 2 of the assembly device so as to facilitate the screwing of the connecting assembly hole 1 and the assembly 5 and the fitting of the bottom surface;
and the spline 7 can be matched with the spline groove 3 of the assembling device so as to fix the shaft, so that the subsequent force limiting assembly is facilitated.
The force limiting assembly method for the components of the turbofan aircraft engine lubricating oil system comprises the following steps:
1. completely attaching the bottom of the part to the connecting end surface at the upper end of the fixed seat as shown in fig. 3, vertically placing the part on the fixed seat of the assembly device, corresponding 5 assembly holes at the bottom of the part to 5 same connecting assembly holes 1 on the fixed seat one by one, and extending the bosses 6 into the annular grooves 2 of the fixed seat;
2. the 5 connecting assembly holes 1 and the assembly holes 5 are combined and screwed down by bolts, so that the components are completely fixed;
3. when a shaft on a component is installed, the shaft extends into the component from the center of the top of the component until the shaft touches the fixed seat, the position of the shaft is adjusted and the shaft slowly rotates, so that the shaft is matched with the spline groove 3 on the fixed seat, and the rotation of the shaft is limited;
4. when a large-torque force limiting part is installed, force is limited on the component directly. The moment is transmitted to the bolt from the assembly assembling hole 5 of the bottom 5, so that the assembly cannot deform;
5. when the force limiting part on the shaft is mounted, the force is limited on the shaft directly. The shaft is also fixed by the tool and cannot rotate relative to the tool, so that the force limiting requirement can be well met;
6. the disassembly of the components is similar to the assembly.
Claims (6)
1. Turbofan aeroengine lubricating oil system spare part limit force assembly's device, its characterized in that: comprises the steps of (a) preparing a mixture of a plurality of raw materials,
the upper end of the fixed seat is a connecting end face for connecting with turbofan aircraft engine lubricating oil system components, a plurality of connecting assembly holes (1) are formed in the connecting end face, and the positions of the connecting assembly holes (1) correspond to the positions of assembly holes (5) in the turbofan aircraft engine lubricating oil system components one by one;
the annular groove (2) is positioned on the connecting end face, the position of the annular groove (2) corresponds to the position of a boss (6) on a turbofan aircraft engine lubricating oil system component, and the depth of the annular groove (2) is greater than the height of the boss (6);
the spline grooves (3) are arranged in the annular grooves (2);
the connecting seat is connected with the lower end of the fixing seat, and a plurality of fixing holes (4) are formed in the bottom surface of the connecting seat along the circumferential direction.
2. The turbofan aircraft engine oil system component force limiting assembly apparatus of claim 1 wherein: the connecting and assembling hole (1) is a threaded hole, and the diameter and the thread of the connecting and assembling hole are consistent with those of the assembly and assembling hole (5).
3. The turbofan aircraft engine oil system component force limiting assembly apparatus of claim 1 wherein: the spline groove (3) is positioned in a cavity cylinder, and the upper end of the cavity cylinder is not higher than the connecting end surface of the fixed seat.
4. The turbofan aircraft engine oil system component force limiting assembly apparatus of claim 1 wherein: a plurality of fixing holes (4) on the bottom surface of the connecting seat are arranged on the same circumference, and the vertical projection of a plurality of connecting assembly holes (1) on the bottom surface of the connecting seat is positioned in the circumference.
5. A force-limiting assembly method for components of a turbofan aircraft engine oil system using the device of claim 1, comprising:
connecting the turbofan aircraft engine lubricating oil system components with a fixed seat, and connecting all connecting assembly holes (1) on the fixed seat with assembly holes (5) on the turbofan aircraft engine lubricating oil system components through connecting bolts to ensure that the connecting end surfaces on the fixed seat are tightly attached to the turbofan aircraft engine lubricating oil system components;
mounting a shaft on a turbofan aircraft engine lubricating oil system component, extending the shaft into the component from the center of the top of the turbofan aircraft engine lubricating oil system component and matching with a spline groove (3) on a fixed seat;
and step three, installing a force limiting part.
6. The force-limiting assembly method of turbofan aircraft engine oil system components according to claim 5, wherein: and in the second step, the shaft extends into the assembly from the center of the top of the turbofan aircraft engine lubricating oil system component until the shaft touches the fixed seat, and the position of the shaft is adjusted and slowly rotated to enable the shaft to be matched with the spline groove (3) on the fixed seat.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201911135692.XA CN110842842B (en) | 2019-11-19 | 2019-11-19 | Force-limiting assembly method and device for components of turbofan aircraft engine lubricating oil system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911135692.XA CN110842842B (en) | 2019-11-19 | 2019-11-19 | Force-limiting assembly method and device for components of turbofan aircraft engine lubricating oil system |
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| CN110842842A true CN110842842A (en) | 2020-02-28 |
| CN110842842B CN110842842B (en) | 2021-10-12 |
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| CN109596980A (en) * | 2018-12-11 | 2019-04-09 | 安徽鸿创新能源动力有限公司 | A kind of motor rotation blockage test tooling and its assembly method |
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2019
- 2019-11-19 CN CN201911135692.XA patent/CN110842842B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH11193596A (en) * | 1997-12-26 | 1999-07-21 | Osaka Gas Co Ltd | Attaching member of ceiling setting instrument |
| SE0901338A1 (en) * | 2009-10-16 | 2010-11-09 | Gilbert Ossbahr | Adjustable bracket in structures |
| CN203426991U (en) * | 2013-08-13 | 2014-02-12 | 中国航空动力机械研究所 | Assembly vehicle used for assembling combustion chambers of aircraft engines |
| CN105345441A (en) * | 2015-11-20 | 2016-02-24 | 广州日滨科技发展有限公司 | Assembling device for electronic plate |
| CN205630456U (en) * | 2016-03-21 | 2016-10-12 | 广州市暨华医疗器械有限公司 | Overflow valve assembly auxiliary device |
| CN107838856A (en) * | 2016-09-20 | 2018-03-27 | 北京汽车动力总成有限公司 | A kind of crankshaft torsion vibration absorber dismounting tooling bracket |
| CN109365947A (en) * | 2018-12-06 | 2019-02-22 | 中国航发贵州黎阳航空动力有限公司 | The vacuum brazing clamp and method of flame tube head component |
| CN109396894A (en) * | 2018-12-11 | 2019-03-01 | 中国航发贵州黎阳航空动力有限公司 | It is a kind of for processing the clamp body in Middle casing degree face and hole |
| CN109596980A (en) * | 2018-12-11 | 2019-04-09 | 安徽鸿创新能源动力有限公司 | A kind of motor rotation blockage test tooling and its assembly method |
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| CN110842842B (en) | 2021-10-12 |
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