CN114749907B - Device and method for pre-checking involution state of aero-engine and radiator - Google Patents
Device and method for pre-checking involution state of aero-engine and radiator Download PDFInfo
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- 210000001503 joint Anatomy 0.000 claims abstract description 5
- 238000005259 measurement Methods 0.000 claims description 38
- 230000000712 assembly Effects 0.000 claims description 9
- 238000000429 assembly Methods 0.000 claims description 9
- 230000003247 decreasing effect Effects 0.000 claims description 4
- 238000007621 cluster analysis Methods 0.000 claims description 3
- 230000000087 stabilizing effect Effects 0.000 claims description 3
- 238000009434 installation Methods 0.000 description 15
- 230000013011 mating Effects 0.000 description 4
- 238000000691 measurement method Methods 0.000 description 4
- 238000013461 design Methods 0.000 description 2
- 238000001514 detection method Methods 0.000 description 2
- 230000017525 heat dissipation Effects 0.000 description 2
- 238000005304 joining Methods 0.000 description 2
- 238000003064 k means clustering Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
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- 230000004075 alteration Effects 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
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- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P19/00—Machines for simply fitting together or separating metal parts or objects, or metal and non-metal parts, whether or not involving some deformation; Tools or devices therefor so far as not provided for in other classes
- B23P19/10—Aligning parts to be fitted together
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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
- G01B5/00—Measuring arrangements characterised by the use of mechanical techniques
- G01B5/003—Measuring of motor parts
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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
- G01B5/00—Measuring arrangements characterised by the use of mechanical techniques
- G01B5/14—Measuring arrangements characterised by the use of mechanical techniques for measuring distance or clearance between spaced objects or spaced apertures
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Abstract
The invention relates to the technical field of a butt joint machine of an aircraft engine and a radiator, in particular to a device and a method for pre-checking the butt joint state of the aircraft engine and the radiator. The device comprises a leveling support seat assembly, a support pillar, a radiator positioning and mounting assembly, an inspection ring support assembly, a gap adjusting gasket and an opposite-joint surface inspection ring for inspecting the step difference gap of the opposite-joint surface of the radiator; by adopting the device, the radiator and the engine are checked in advance and the repair parameters are obtained before the radiator and the engine are closed, so that the repair work of the radiator can be conveniently and rapidly completed before the engine and the radiator are closed, and the closing and repairing efficiency is improved.
Description
Technical Field
The invention relates to the technical field of a butt joint machine of an aircraft engine and a radiator, in particular to a device and a method for pre-checking the butt joint state of the aircraft engine and the radiator.
Background
The aircraft engine and the radiator are large parts formed by integrating and assembling thousands of parts, the aircraft engine is formed by integrating and assembling a plurality of parts, and machining, manufacturing and assembling errors are accumulated; the radiator is a welded sheet metal part, and the tolerance of the overall dimension is large. The front end of the radiator is connected with the air inlet, and the rear end of the radiator is jointed with the engine. The fitting surface of the radiator and the engine has two important parameters: firstly, the end face clearance requirement; the second is the step difference of the inner diameter of the fitting surface, namely the coaxiality requirement. Because the manufacturing assembly errors of the engine and the radiator are accumulated, the actual installation position of the engine and the radiator after the matching is finished has larger deviation from the theoretical position, so the step gap of the matching surface is difficult to meet the requirement, and the matching is difficult to succeed at one time. The end face of the radiator is provided with a margin, and the radiator can be repaired on site according to requirements. Therefore, when the alignment data of the engine and the radiator does not meet the requirements, the alignment surface of the radiator needs to be repaired, and the engine and the radiator need to be repeatedly separated and aligned at the time, so that the alignment efficiency is low and the quality is difficult to control.
At present, in order to ensure the joining quality of an engine and a radiator, a pre-joining repair method or an accurate measurement method is generally adopted. The pre-alignment repair method requires repeated "alignment, separation, alignment, and alignment", and is inefficient and prone to quality problems. The accurate measurement method is characterized in that a laser radar or a laser tracker is used for accurately measuring a large part system, and a radiator is repaired according to measurement data and a matching relation, so that the success rate of combination can be improved, but a large amount of time is needed for accurate measurement, and the problem of low efficiency also exists. Therefore, the conventional pre-alignment correction method and the conventional precision measurement method have the problem that the efficiency is low and the batch alignment of the engine and the radiator cannot be adapted.
Disclosure of Invention
The invention aims to provide a device and a method for pre-checking the involution state of an aircraft engine and a radiator, aiming at the problem that the prior art is low in efficiency and cannot adapt to the batch involution of an engine and a radiator.
Firstly, the invention provides a device for pre-checking the involution state of an aircraft engine and a radiator. The device comprises a leveling support seat assembly, a support pillar, a radiator positioning and mounting assembly, an inspection ring support assembly, a gap adjusting gasket and an opposite-fit surface inspection ring for inspecting the step difference gap of the opposite-fit surface of the radiator;
the leveling support seat assembly is positioned at the bottom end of the whole device and is used for supporting and stabilizing the whole device; the radiator positioning and mounting assembly, the inspection ring supporting assembly, the gap adjusting gasket and the fitting surface inspection ring are all mounted above the leveling supporting seat assembly through the supporting pillars; the radiator positioning and mounting assembly and the inspection ring supporting assembly are directly mounted on the supporting strut, and the positioning surface of the radiator positioning and mounting assembly is consistent with the mounting surface of the radiator in position; the gap adjusting shim is positioned between the inspection ring supporting assembly and the fitting surface inspection ring and used for adjusting the vertical distance between the fitting surface inspection ring and the radiator positioning and mounting assembly.
By adopting the device for pre-checking the involution state of the aero-engine and the radiator, the repair work of the radiator can be conveniently and rapidly completed before the involution of the engine and the radiator, and the involution and repair efficiency is improved.
Furthermore, in order to better realize the invention, a supporting pillar, a radiator positioning and mounting component arranged in the middle of the supporting pillar and an inspection ring supporting component arranged on the upper part of the supporting pillar jointly form a group of positioning and supporting components, the number of the positioning and supporting components is N, and N is a positive integer not less than 2; the positioning surfaces of all the radiator positioning and mounting assemblies in the N positioning and supporting assemblies are kept consistent with the positions of the mounting surfaces of the radiators, and the positioning surfaces of all the inspection ring supporting assemblies are positioned on the same plane.
Furthermore, in order to better implement the invention, the radiator positioning and mounting assembly and the inspection ring supporting assembly are both fixedly mounted on the supporting columns; the fitting surface inspection ring is detachably mounted on the inspection ring supporting component.
Further, in order to better implement the invention, the radiator positioning and mounting assembly and the inspection ring supporting assembly are welded on the supporting columns.
Further, in order to better implement the present invention, the mating surface inspection ring is mounted on the inspection ring support assembly by a threaded pin.
Further, in order to better implement the invention, the leveling support seat assembly comprises a support plate and a leveling bolt installed at the bottom of the support plate.
The invention further provides a method for assembling the aircraft engine and the radiator, wherein the device pre-inspection data is acquired by the device based on the state pre-inspection of the aircraft engine and the radiator, the pre-inspection data is combined with the measured data on the machine, the assembling parameters before assembling are acquired, and the aircraft engine and the radiator are assembled after assembling.
Further, in order to better implement the present invention, the method for assembling the assembly machine specifically includes the following steps:
step S1: before the engine and the radiator are combined, a pre-checking device with an adjustable combined surface checking ring is used for pre-checking and measuring the combined state of the radiator to obtain the step gap between the radiator to be combined and the combined surface checking ring, and the step gap data is recorded as device pre-checking data;
step S2: carrying out the operation of the step S1 on a plurality of groups of involutory engines and radiators, and counting pre-inspection data of devices before involutory of a plurality of airplanes and actual measurement data on the airplanes after involutory;
and step S3: performing K-means cluster analysis on the pre-inspection data of the multiple groups of devices and the measured data on the machine, analyzing and calculating the device measurement data of the successful primary involution of the engine and the radiator, and adjusting the involution inspection circle according to the analyzed device measurement data;
and step S4: and (4) repairing the radiator before the alignment according to the measurement data of the device, and assembling the radiator after the repair is finished.
Further, in order to better implement the present invention, in step S3, the fitting surface inspection circle is adjusted according to the analyzed device measurement data, specifically: and adjusting the position of the fitting surface inspection ring by increasing or decreasing the thickness and the number of the gap adjusting gaskets according to the analyzed device measurement data.
Further, in order to better implement the present invention, in step S4, the repair before the alignment of the heat sink is performed according to the measurement data of the device, specifically, the repair before the alignment of the heat sink is performed: after the position of the fitting surface inspection ring is adjusted in the step S3, a clearance and a step difference between the fitting surface inspection ring and the fitting surface of the radiator are measured by using a feeler gauge, and the position of the radiator which does not meet the inspection requirement of the device is subjected to repairing position and marking of repairing amount; and disassembling the fitting surface inspection ring on the inspection device, and repairing the radiator according to the marked repairing position and repairing amount.
The invention has the following beneficial effects:
(1) According to the device for pre-checking the involution state of the aero-engine and the radiator, the step gap from the involution surface of the radiator to the involution surface checking ring is measured through the flexible detection and repair device of the radiator, the data measured by the analysis device and the data measured by the installation device are analyzed, and the checking ring of the flexible detection and repair device is adjusted, so that the checking and repairing work of the radiator is quickly completed before the engine and the radiator are involuted, the involution and repair efficiency is improved, and the device can be used for the batch involution of the engine and the radiator;
(2) The invention provides a device for pre-checking the involution state of an aircraft engine and a radiator, which is essentially equivalent to a device integrating the involution surface checking and repairing of the radiator.
(3) The method for assembling and assembling the aircraft engine and the radiator improves the one-time assembling success rate of the engine and the radiator, thereby avoiding repeated separation and assembling of the engine and the radiator and improving the assembling efficiency and the repairing quality.
Drawings
Fig. 1 is a schematic perspective view of a device for pre-inspecting the alignment state of an aircraft engine and a radiator according to the present invention.
FIG. 2 is a schematic view of the front view of the device for pre-inspecting the alignment state of the aircraft engine and the radiator in the present invention.
FIG. 3 is a schematic view of the bottom orientation of the device for pre-checking the alignment state of the aircraft engine and the radiator in the present invention.
Fig. 4 is a schematic view of the fitting surface position of the heat sink during inspection.
FIG. 5 is a schematic diagram of a plurality of sets of device measurements and on-board measurement data.
Wherein, 1, support the disc; 2. leveling bolts; 3. a support pillar; 4. a heat sink positioning and mounting assembly; 5. an inspection ring support assembly; 6. a gap adjustment shim; 7. checking a circle of the involution surface; 8. and (4) a threaded pin.
Detailed Description
The present invention will be described in further detail with reference to the following examples. This should not be understood as limiting the scope of the above-described subject matter of the present invention to the following examples. Various substitutions and alterations according to the general knowledge and the conventional means in the art are included in the scope of the present invention without departing from the technical idea of the present invention.
Example 1:
the embodiment provides a device for pre-checking the joint state of an aircraft engine and a radiator.
As shown in fig. 1-3, the device comprises a leveling support seat assembly, a support pillar 3, a radiator positioning and mounting assembly 4, an inspection ring support assembly 5, a gap adjusting gasket 6 and an opposite-fit surface inspection ring 7 for inspecting the opposite-fit surface step gap of the radiator.
The leveling support seat assembly is positioned at the bottom end of the whole device and is used for supporting and stabilizing the whole device; the radiator positioning and mounting assembly 4, the inspection ring supporting assembly 5, the gap adjusting gasket 6 and the fitting surface inspection ring 7 are all mounted above the leveling supporting seat assembly through the supporting columns 3; the radiator positioning and mounting assembly 4 and the inspection ring supporting assembly 5 are directly mounted on the supporting strut 3, and the positioning surface of the radiator positioning and mounting assembly 4 is consistent with the mounting surface of a radiator in position; the gap adjusting shim 6 is positioned between the inspection ring supporting component 5 and the fitting surface inspection ring 7 and is used for adjusting the vertical distance between the fitting surface inspection ring 7 and the radiator positioning and mounting component 4.
By adopting the device for pre-checking the involution state of the aero-engine and the radiator, the repair work of the radiator can be conveniently and rapidly completed before the involution of the engine and the radiator, and the involution and repair efficiency is improved.
The distance between the radiator positioning and mounting assembly 4 and the inspection ring supporting assembly 5 in the device is smaller than the distance from the mounting surface of the radiator to the opposite surface by D, so that the distance from the opposite surface inspection ring 7 to the opposite surface is adjusted by increasing or decreasing the thickness and the number of the gap adjusting gaskets 6. In order to quickly and accurately measure the gap and the step difference between the contraposition checking ring 7 and the contraposition surface of the radiator by using the feeler gauge, D is usually set to be 2mm-3mm. Wherein, the gap adjusting shim 6 adopts a standard shim. At the moment, the device can conveniently, quickly and visually check the step gap between the fitting surface of the radiator and the fitting surface check ring 7 by using the feeler gauge.
In another embodiment, the mating inspection ring 7 is mounted on the inspection ring support assembly 5 by a threaded pin 8. The fitting surface inspection ring 7 can be quickly assembled, disassembled and adjusted through the threaded pin 8.
In another embodiment, the leveling support base assembly includes a support plate 1 and a leveling bolt 2 installed at the bottom of the support plate 1. The working surface of the whole device is leveled by adjusting the leveling bolts 2.
Example 2:
in this embodiment, an optimization design is performed based on embodiment 1, and a design scheme of four sets of positioning support assemblies is adopted.
A supporting pillar 3, a radiator location installation component 4 installed in the middle of the supporting pillar 3, an inspection ring supporting component 5 installed on the upper portion of the supporting pillar 3 jointly form a group of location supporting components, the number of the location supporting components is N, and N is 4.
The positioning surfaces of the four radiator positioning and mounting assemblies 4 are consistent with the positions of the mounting surfaces of the radiators, and the positioning surfaces of the four inspection ring supporting assemblies 5 are in the same plane.
In another specific embodiment, the heat sink positioning and mounting assembly 4 and the inspection ring support assembly 5 are both fixedly mounted on the support pillar 3; the fitting surface inspection ring 7 is detachably mounted on the inspection ring support component 5.
In another embodiment, the heat sink positioning and mounting assembly 4 and the inspection ring support assembly 5 are welded to the support posts 3.
Other parts of this embodiment are the same as embodiment 1, and thus are not described again.
Example 3:
in the present embodiment, a method for assembling an aircraft engine and a radiator is provided in addition to embodiments 1 and 2.
Step S1: collecting data;
before the engine and the radiator are combined, the combined state of the radiator is preliminarily checked and measured through a preliminary checking device with an adjustable combined surface checking ring 7, the step gap between the radiator to be combined and the combined surface checking ring 7 is obtained and recorded as device preliminary checking data, and after the engine and the radiator are combined, the step gap data after combination is measured on the machine and recorded as on-machine actual measuring data.
In this step, the alignment state of the heat sink is preliminarily checked and measured by using the device described in embodiment 1, and the alignment position of the heat sink is shown in fig. 4. When the radiator is measured, the threaded pin 8 needs to be opened, the 4 fitting surface inspection rings 7 need to be disassembled, the radiator is placed on the bracket of the radiator positioning and mounting component 4, the radiator is adjusted to be aligned with the positioning hole of the radiator positioning and mounting component 4, and the positioning bolt is inserted. After the radiator is positioned and installed on the device, the fitting surface inspection ring 7 is installed, and the gap adjusting shim 6 is adjusted according to the gap between the fitting surface inspection ring 7 and the fitting surface of the radiator during installation to ensure that the gap is
So as to facilitate the measurement by using the feeler gauge. Using feelers to uniformly distribute and measure 10-point step difference gaps along the involution surface of the radiator, and recording the gaps of data points
Recording step difference data points
. After the radiator and the engine are aligned, the actual measurement of the installation machine is completed, and the actual measurement gap data of the installation machine of the corresponding point position of the aligned surface of the radiator and the engine is recorded
Measured step numberAccording to
。
Step S2: collecting repeated data;
and (3) carrying out the operation of the step S1 on a plurality of groups of involutory engines and radiators, and counting pre-inspection data of devices before involution of a plurality of airplanes and actual measurement data on the airplane after involution.
In the step, repeated data acquisition is performed on the radiators of the multiple installation machines, and the more the data is, the higher the reliability is.
And step S3: and performing K-means cluster analysis on the multiple groups of device pre-inspection data and the on-board measured data, analyzing and calculating device measurement data of the engine and the radiator which are successfully aligned at one time, and adjusting an alignment inspection ring 7 according to the analyzed device measurement data.
Specifically, the statistical analysis is carried out on the device measurement data of the parts which meet the requirements after the radiator and the engine are combined and the machine measurement data form gap data
、
、……
(ii) a Step data
、
……
The meaning of the data is that the device measurement data and the installed actual measurement data form a two-dimensional data point.
Analyzing two-dimensional data points formed by the measured data of the device and the measured data on the engine for identifying the parts of the radiator and the engine which meet the requirements after the combinationMeasuring data of the device and actual measurement data of the installation, calculating the clustering centroid position of data points meeting the requirements of the installation by adopting a K-means clustering algorithm, calculating the data clustering centroid position qualified by one-time installation according to the measurement data of the gap device and the actual measurement data of the installation as shown in figure 5
The cluster center satisfies the following requirement.
Wherein,
the number of qualified data points of the installation machine,
denotes the first
The coordinates of the points are such that,
representing the data cluster centroid location.
Next, the centroid positions are clustered according to the data
The qualified optimal solution of one-time installation, the fitting surface inspection ring 7 of the adjusting device and the position of the fitting surface inspection ring 7 of the adjusting device are adjusted by increasing and decreasing the thickness of the gap adjusting shim 6 and the quantity, and the gap between the fitting surface inspection ring 7 and the fitting surface of the radiator is controlled to be between
And (4) the following steps. In order to conveniently use the feeler to measure the step difference gap of the coincidence plane,
the preferred value of (b) is 0.5mm to 2mm.
And step S4: and (4) repairing the radiator before the alignment according to the measurement data of the device, and assembling the radiator after the repair is finished.
Specifically, after the position of the fitting surface inspection ring 7 is adjusted in the step S3, the step gap between the fitting surface of the radiator and the fitting surface inspection ring 7 is inspected according to the optimal solution, the clearance and the step difference between the fitting surface inspection ring 7 and the fitting surface of the radiator are measured by a feeler gauge, and the position of the radiator which does not meet the inspection requirements of the device and the mark of the fitting amount are marked; and disassembling the fitting surface inspection ring 7 on the inspection device, and repairing the radiator according to the marked repairing position and repairing amount.
And after the repairing is finished, installing the fitting surface inspection ring 7 again, and inspecting the repairing quality to ensure that the step difference gap between the fitting surface of the radiator and the fitting surface inspection ring 7 is the optimal solution. The radiator after the device inspection and repair can be directly assembled and closed. In this step, the device measurement data is measured on the heat sink by the device described in embodiment 1, and the measurement method is the same as step S1, and therefore is not described again.
The method of this embodiment is based on the integrated device for measuring and repairing the mating surface of the heat dissipation device in embodiment 1, and the inspection and the repair of the mating surface can be completed at one time by using the device before the alignment of the heat dissipation device. And the K-means clustering algorithm is adopted, the device measurement data and the installation actual measurement data of the parts which meet the requirements after the radiator and the engine are combined are statistically analyzed, the position of the inspection ring and the inspection data before combination are calculated and determined, the measurement and the repair of the radiator before combination can be realized, the measurement and the repair of the radiator and the engine are avoided being repeatedly combined and separated, the radiator installation after the repair is finished is realized, and the one-time installation qualification rate of the radiator and the engine is improved.
While the invention has been described with reference to specific embodiments, it will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the appended claims.
Claims (8)
1. A method for assembling an aircraft engine and a radiator is characterized in that a device pre-inspection data is acquired based on an assembling state pre-inspection device of the aircraft engine and the radiator, and a pre-assembling parameter is acquired in combination with actual measurement data on a machine, and the machine is assembled after the assembling is finished;
the device for pre-checking the involution state of the aircraft engine and the radiator comprises a leveling support seat assembly, a support pillar (3), a radiator positioning and mounting assembly (4), a checking ring support assembly (5), a gap adjusting gasket (6) and an involution checking ring (7) for checking the involution step difference gap of the radiator;
the leveling support seat assembly is positioned at the bottom end of the whole device and is used for supporting and stabilizing the whole device; the radiator positioning and mounting assembly (4), the inspection ring supporting assembly (5), the gap adjusting gasket (6) and the butt joint surface inspection ring (7) are all mounted above the leveling supporting seat assembly through the supporting strut (3); the radiator positioning and mounting assembly (4) and the inspection ring supporting assembly (5) are directly mounted on the supporting strut (3), and the positioning surface of the radiator positioning and mounting assembly (4) is consistent with the mounting surface of a radiator in position; the gap adjusting gasket (6) is positioned between the inspection ring supporting assembly (5) and the fitting surface inspection ring (7) and is used for adjusting the vertical distance between the fitting surface inspection ring (7) and the radiator positioning and mounting assembly (4);
the assembling machine assembling method specifically comprises the following steps:
step S1: before the engine and the radiator are combined, a pre-inspection device with an adjustable combined surface inspection ring (7) is used for pre-inspecting and measuring the combined state of the radiator to obtain the step gap between the radiator to be combined and the combined surface inspection ring (7) and recording the step gap as device pre-inspection data, and after the engine and the radiator are combined, the step gap data after combination is measured on the machine and recorded as on-machine measured data;
step S2: carrying out the operation of the step S1 on a plurality of groups of involutive engines and radiators, and counting device pre-inspection data before involution of a plurality of airplanes and on-board actual measurement data after involution;
and step S3: performing K-means cluster analysis on the multiple groups of device pre-inspection data and the measured data on the machine, analyzing and calculating the device measurement data of the successful primary involution of the engine and the radiator, and adjusting an involution inspection ring (7) according to the analyzed device measurement data;
and step S4: and (4) repairing the radiator before the alignment according to the measurement data of the device, and assembling the radiator after the repair is finished.
2. The method for assembling and disassembling an aircraft engine and a radiator according to claim 1, wherein in step S3, the assembling and disassembling check ring (7) is adjusted according to the analyzed device measurement data, specifically: according to the analyzed measurement data of the device, the position of the fitting surface inspection ring (7) is adjusted by increasing or decreasing the thickness and the number of the gap adjusting gaskets (6).
3. The assembling method for the aircraft engine and the radiator according to claim 2, wherein in the step S4, the radiator is repaired before being assembled according to the device measurement data, specifically: after the position of the fitting surface inspection ring (7) is adjusted in the step S3, a clearance and a step difference between the fitting surface inspection ring (7) and the fitting surface of the radiator are measured by using a feeler gauge, and the position and the amount of the fitting are marked on the part of the radiator which does not meet the requirement of device inspection; and disassembling the fitting surface inspection ring (7) on the inspection device, and repairing the radiator according to the marked repairing position and repairing amount.
4. The method for assembling and assembling the aircraft engine and the radiator according to claim 1, wherein a supporting pillar (3), a radiator positioning and mounting component (4) mounted in the middle of the supporting pillar (3), and an inspection ring supporting component (5) mounted on the upper portion of the supporting pillar (3) jointly form a group of positioning and supporting components, the number of the positioning and supporting components is N, and N is a positive integer not less than 2; the positioning surfaces of all radiator positioning and mounting assemblies (4) in the N positioning and supporting assemblies are kept consistent with the positions of the mounting surfaces of the radiators, and the positioning surfaces of all inspection ring supporting assemblies (5) are positioned on the same plane.
5. An assembling method for an aircraft engine and a radiator according to claim 1, wherein the radiator positioning and mounting assembly (4) and the inspection ring supporting assembly (5) are both fixedly mounted on the supporting strut (3); the fitting surface inspection ring (7) is detachably mounted on the inspection ring supporting component (5).
6. An assembling method of an aircraft engine and a radiator according to claim 5, characterized in that the radiator positioning and mounting assembly (4) and the inspection ring supporting assembly (5) are welded on the supporting strut (3).
7. An aircraft engine and radiator assembly method according to claim 5, characterized in that the assembly check ring (7) is mounted on the check ring support assembly (5) by means of a threaded pin (8).
8. An assembling method for an aircraft engine and a radiator according to claim 1, wherein the leveling support seat assembly comprises a support plate (1) and a leveling bolt (2) installed at the bottom of the support plate (1).
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Family Cites Families (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090165540A1 (en) * | 2007-12-29 | 2009-07-02 | Craig Terry A | Method for measuring blade tip clearance |
| CN103512506B (en) * | 2013-08-12 | 2016-01-27 | 浙江豪情汽车制造有限公司 | Gap between automobile front and back door and jump range estimation training station |
| CN103901852B (en) * | 2014-03-27 | 2016-10-05 | 浙江大学 | A kind of aircraft is fitted to each other face digitized cushioning method |
| US10450053B2 (en) * | 2016-05-11 | 2019-10-22 | The Boeing Company | Methods using predictive shimming to optimize part-to-part alignment |
| CN107316298B (en) * | 2017-07-10 | 2020-06-02 | 北京深度奇点科技有限公司 | Real-time measurement method and device for welding gap and electronic equipment |
| CN107328337A (en) * | 2017-08-09 | 2017-11-07 | 南宁燎旺车灯股份有限公司 | A kind of car headlamp lamp assembly simulates entrucking detection means |
| CN108151660B (en) * | 2017-12-29 | 2019-07-30 | 西北工业大学 | A kind of aircraft components butt-joint clearance and the measurement equipment of scale, method and system |
| CN108151615B (en) * | 2017-12-29 | 2023-06-23 | 江西鑫田车业有限公司 | Distance inspection tool and distance inspection method for wind ring and bracket of radiator |
| CN108928502B (en) * | 2018-07-05 | 2021-03-19 | 南京航空航天大学 | Tool for assembling composite material wing box and method for assembling wing box by using tool |
| US11280222B2 (en) * | 2019-02-26 | 2022-03-22 | The Boeing Company | Bulkhead shims for curvilinear components |
| CN210036491U (en) * | 2019-04-24 | 2020-02-07 | 苏州鲁卡斯金属科技有限公司 | Automobile air conditioner radiator expansion valve assembly precision detection equipment |
| CN110044230B (en) * | 2019-05-29 | 2021-01-15 | 盐城工学院 | Novel spare part assembly error detects device |
| CN110953949B (en) * | 2019-11-20 | 2021-03-19 | 中国航发沈阳黎明航空发动机有限责任公司 | Method for controlling assembly clearance of flow distribution ring of intermediate case of aircraft engine |
| CN112577735B (en) * | 2020-10-19 | 2022-12-16 | 江苏华永复合材料有限公司 | Axle differential preassembly tool |
| CN113192122B (en) * | 2021-04-28 | 2023-07-28 | 西安电子科技大学 | Optical center extraction method in visual detection process of assembly pose of large equipment |
| CN113305767B (en) * | 2021-06-17 | 2022-07-12 | 陕西飞机工业有限责任公司 | Method and clamp for assembling head cover |
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2022
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