CN113899297A - Device and method for measuring position degree of flame tube head of aircraft engine - Google Patents
Device and method for measuring position degree of flame tube head of aircraft engine Download PDFInfo
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- CN113899297A CN113899297A CN202111153001.6A CN202111153001A CN113899297A CN 113899297 A CN113899297 A CN 113899297A CN 202111153001 A CN202111153001 A CN 202111153001A CN 113899297 A CN113899297 A CN 113899297A
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- 238000000034 method Methods 0.000 title claims abstract description 15
- 238000003825 pressing Methods 0.000 claims description 23
- 238000001514 detection method Methods 0.000 abstract description 19
- 238000013461 design Methods 0.000 abstract description 5
- 238000002679 ablation Methods 0.000 abstract description 4
- 238000006243 chemical reaction Methods 0.000 abstract description 2
- 238000009434 installation Methods 0.000 description 5
- 239000000295 fuel oil Substances 0.000 description 4
- 230000035882 stress Effects 0.000 description 4
- 239000000306 component Substances 0.000 description 3
- 238000003754 machining Methods 0.000 description 3
- 239000003921 oil Substances 0.000 description 3
- 238000012360 testing method Methods 0.000 description 3
- 238000003466 welding Methods 0.000 description 3
- 230000002159 abnormal effect Effects 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 229910052751 metal Inorganic materials 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 150000002739 metals Chemical class 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
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Classifications
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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
- G01B7/00—Measuring arrangements characterised by the use of electric or magnetic techniques
- G01B7/003—Measuring arrangements characterised by the use of electric or magnetic techniques for measuring position, not involving coordinate determination
-
- 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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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Testing Of Engines (AREA)
Abstract
The invention discloses a measuring tool and a measuring method for the position degree of the head of a flame tube of an aero-engine, belonging to the technical field of aero-engine detection. And finally, detecting the position degree data of the end of the core rod body through three coordinates, and obtaining the actual position degree data corresponding to the theoretical design point through conversion. The measuring device of the invention is used for measuring the position degree of the flame tube head, and can directly reflect the deviation condition of the position degree of the head. The problems that assembly detection is qualified due to the fact that the flame tube is assembled into the clamp with assembly stress due to external force deformation and head position data cannot be reflected visually are avoided, head position deviation is covered, and faults of cracks, ablation, block falling and the like of the flame tube are reduced. The practicality is stronger, is fit for popularizing and applying.
Description
Technical Field
The invention belongs to the technical field of aero-engine detection, and relates to a measuring tool and a measuring method for the position degree of a flame tube head of an aero-engine.
Background
The flame tube is a core component of an aircraft engine and is one of the most important heat-receiving components of the engine. It is the main component of the combustion chamber and the site of tissue combustion. When the engine works, fuel oil and high-pressure air enter the flame tube to be continuously mixed and combusted, so that chemical energy of the fuel oil is converted into heat energy, the fuel oil continuously works in a high-temperature environment, and the fuel oil bears great thermal stress, creep stress and fatigue stress. Some flame tubes are welded parts of thin-wall tube bodies and head assemblies, the parts are complex in structure, welding seams are multiple, the thickness of the tube body is about 1mm, and a plurality of small gas film holes are distributed on the surface of the tube body, so that the deformation is easily generated at high temperature, and the head position of the flame tube deviates from a design specified value.
At present, because the head structure is complicated, the space of a part to be detected is limited, the shape is complicated, the head structure is formed by welding a plurality of parts and is easy to deform, the position degree of the head part is difficult to measure, a detection tool similar to a go-no-go gauge principle is actually adopted on site at present to detect the position degree of the head part, a pin shaft designed according to the theoretical position degree on the tool is inserted into a hole of the head part, if the pin shaft is smoothly inserted, the position degree of the part is qualified in detection, if the pin shaft cannot be inserted or interfered, the position degree of the part is judged to be unqualified, and the pin shaft is corrected by other methods and then measured, so the main problem of the old detection method is that: 1) the position degree numerical value of the part cannot be directly reflected, the repair according to the data value cannot be guided when the part is repaired by workers, the part can only be continuously and repeatedly corrected and continuously checked, the period is long, and time and labor are wasted; 2) only the record of whether the part is qualified is reflected, and the part processing condition cannot be accurately reflected; 3) when the pin shaft on the old-fashioned detection tool is inserted into the head, the part can generate certain deformation according to the difference of force applied to the hand of a worker, and the deformation is caused by the characteristics that the part structure is a sheet metal part and a plurality of sheet metals and machined parts are welded, so that the false appearance of the inserted head is easily caused, and the true situation of the position degree of the head cannot be reflected.
In summary, the space of the flame tube head is limited, the assembly structure is complex, the head position cannot be directly detected, and a method of indirect control by a clamp is mostly adopted for replacement. However, since the thin-wall part is easy to deform, the part can meet the assembly requirement through deformation under the clamping of the clamp, and the false impression that the position degree of the head is qualified and the assembly requirement is met is generated. And further, the real situation of the deviation of the head position degree is covered, so that when the engine works, the flow field in the flame tube is not uniformly distributed, and a local oil-rich phenomenon occurs, so that an abnormal high-temperature area is generated on the wall surface of the flame tube, finally, faults such as cracks, ablation, block falling and the like of the flame tube are caused, and the performance and the use of the engine are even affected in serious cases, so that serious economic loss is caused.
Disclosure of Invention
The invention aims to overcome the defects that in the prior art, the traditional measuring tool has the measuring false appearance problem possibly existing in the using process and covers the real situation of head deviation, so that the local oil supply quantity of a flame tube is large, and further the faults of cracks, ablation and the like are caused, and provides the measuring tool and the detecting method for the head position degree of the flame tube of the aircraft engine.
In order to achieve the purpose, the invention adopts the following technical scheme to realize the purpose:
the utility model provides a measuring device for aeroengine flame tube head position degree, the flame tube is equipped with the outer wall, the flame tube head includes first swirler, the second swirler, sleeve and outer wall, first swirler and second swirler fixed connection, second swirler and sleeve fixed connection, measuring device includes the plug, clamp plate and nut, the plug cover is established at sleeve inside and with sleeve coaxial line, the plug includes base and barred body, the end of barred body is fixed on the base, the top at the barred body is installed to the clamp plate, the upper surface at the clamp plate is fixed to the nut, and fix clamp plate and barred body, the clamp plate passes the barred body and is located the terminal surface of first swirler.
Preferably, the mandrel is a clearance fit with the sleeve.
Preferably, the clearance between the core rod and the sleeve is 0-0.03 mm.
Preferably, the base is formed by superposing two cylinders with different diameters, namely a large cylinder and a small cylinder positioned on the top surface of the large cylinder;
the diameter of the rod body is smaller than that of the small cylinder on the base.
Preferably, the rod is integrated with the base, and the rod is located at the center of the top surface of the base.
Preferably, the measuring device further comprises a support pad placed at the bottom of the outer wall to fix the outer wall.
Preferably, the supporting cushion blocks are provided with a plurality of supporting cushion blocks which are dispersedly arranged at the bottom of the outer wall.
Preferably, the pressure plate is a circular plate, and the diameter of the pressure plate is larger than that of the rod body.
Preferably, the inner diameter of the nut is greater than the diameter of the barrel.
A measuring method based on the measuring device for the aircraft engine flame tube head position degree comprises the following steps:
step 1) temporarily fixing the outer wall;
step 2) aligning the core rod to the center of the sleeve, enabling the rod body to penetrate through center holes of the first vortex device and the second vortex device, and enabling the base to be matched with the outer circle of the sleeve;
and 3) pressing the pressing plate to the end face of the first swirler, then screwing the nut, and finally detecting the position degree of the top end of the rod body, namely the position degree of the head of the flame tube.
Compared with the prior art, the invention has the following beneficial effects:
the invention discloses a device for measuring the position degree of the head of a flame tube of an aircraft engine, which comprises a mandrel, a pressing plate and a nut, wherein the mandrel is tightly attached to a reference by using a confined space and a machined surface on a complex structure assembly as the reference, the pressing plate penetrates through central holes of a first swirler and a second swirler, the pressing plate is pressed on the second swirler, and the nut is screwed, so that the installation of the mandrel is completed. And finally, detecting the position degree data of the end of the core rod body through three coordinates, and obtaining the actual position degree data corresponding to the theoretical design point through conversion. The measuring device of the invention is used for measuring the position degree of the flame tube head, and can directly reflect the deviation condition of the position degree of the head. The problem that the flame tube is deformed due to external force, assembly stress is assembled into the clamp, and the data of the position degree of the head cannot be visually reflected, so that the qualified false appearance of assembly detection is avoided, and the head position deviation is covered is solved. The problems that the position degree of the head of the flame tube is not detected, the flow field inside the flame tube is not uniformly distributed after the flame tube is assembled and used, local rich oil and abnormal high-temperature areas occur, and the faults of cracks, ablation, block falling and the like of the flame tube are reduced. The practicality is stronger, is fit for popularizing and applying.
Furthermore, the principle of mandrel size design firstly needs to reasonably use the existing machining surface with higher precision of the measured piece as a positioning reference to ensure the accuracy of subsequent measured data, and secondly needs to realize positioning and use in a narrow space and facilitate installation and detection due to the structural design of the mandrel.
The invention also discloses a measuring method of the position degree of the head of the flame tube of the aircraft engine, which is completed based on the measuring tool, the outer wall is firstly fixed, then the installation position of the core rod is determined, and finally the core rod is fixed through a pressing plate; secondly, the measuring method is simple, and the detection period is shortened; finally, the measuring tool used by the measuring method is convenient to mount and use, large assembly stress cannot be applied to the head, the deformation of the measured piece is avoided, the detection data is real, reliable basis is provided for the repair scheme after the position degree of the head exceeds the standard, the on-site repair is effectively guided, and the repair qualified rate and the product delivery quality are improved.
Drawings
FIG. 1 is a schematic structural view of a part under test;
FIG. 2 is a schematic structural diagram of the measuring tool;
FIG. 3 is a schematic diagram of the components of the part under test after the test tool is installed;
wherein: 1-a core rod; 2-pressing a plate; 3-a nut; 4-a first swirler; 5-a second swirler; 6-a sleeve; 7-outer wall; 8-supporting cushion blocks.
Detailed Description
The invention is described in further detail below with reference to the accompanying drawings:
example 1
A measuring device for the position degree of a flame tube head of an aircraft engine is provided with an outer wall 7, the flame tube head comprises a first swirler 4, a second swirler 5 and a sleeve 6 as shown in figure 1, the first swirler 4 is fixedly connected with the second swirler 5, the second swirler 5 is fixedly connected with the sleeve 6, the measuring device comprises a core rod 1, a pressing plate 2 and a nut 3 as shown in figure 2, the core rod 1 is sleeved inside the sleeve 6 and coaxial with the sleeve 6, the core rod 1 comprises a base 11 and a rod body 12, the tail end of the rod body 12 is fixed on the base 11, the pressing plate 2 is installed at the top end of the rod body 12, the nut 3 is fixed on the upper surface of the pressing plate 2 and fixes the pressing plate 2 and the rod body 12, and the pressing plate 2 penetrates through the rod body 12 and is located on the end face of the first swirler 4.
Example 2
The contents are the same as those of example 1 except for the following.
The base 11 is formed by superposing two cylinders with different diameters, namely a large cylinder and a small cylinder positioned on the top surface of the large cylinder; the diameter of the rod 12 is smaller than that of the small cylinder on the base 11. The rod 12 is integrated with the base 11, and the rod 12 is located at the center of the top surface of the base 11. The base 11 is the big end of the core rod 1, and the rod body 12 is the small end of the core rod 1. The core rod 1 is clearance fitted with the sleeve 6. The clearance between the core rod 1 and the sleeve 6 is 0-0.03 mm.
Example 3
The measuring device consists of a core rod 1, a pressing plate 2 and a nut 3. The mandrel 1 is positioned by means of a machining surface in a welding assembly at the head of the flame tube, the pressing plate 2 is a circular plate, and the diameter of the pressing plate 2 is larger than that of the rod body 12. The inner diameter of the nut 3 is larger than the diameter of the rod 12. The core rod is fixed by the nut 3, and the position degree of the head of the flame tube is indirectly reflected by detecting the position degree of the core rod body 12. The axial positioning surface of the core rod 1 (see the attached figure 1 as the end surface F of the second swirler 5, the central line positioning is the machining outer circular surface of the sleeve 6 (matched with the inner circular surface of the outer wall 7, the end part of the core rod 1 is in a threaded connection mode, the actual position degree and the angular position of the flame tube head are indirectly obtained by detecting the center coordinates of the end surface circle of the tool and the central line of the cylinder, the radial vortex number is first at the K groove, the reverse heading direction is increased anticlockwise in sequence until the position degree detection of all the flame tube heads is completed, the measuring device further comprises a supporting cushion block 8 which is placed at the bottom of the outer wall 7 and used for fixing the outer wall 7, and the supporting cushion block 8 can be a rectangular block (a cuboid with extremely high precision and a plurality of supporting cushion blocks 8 are arranged at the bottom of the outer wall 7 in a scattered manner.
Core rod critical dimension, radial positioning reference Φ a 1: in order to ensure the positioning precision, the clearance is 0-0.03 mm when the sleeve 6 is matched. And controlling the distance from the axial positioning reference of the core rod to the head theoretical position measuring point.
Example 4
A method for measuring the position degree of the head of a flame tube of an aircraft engine comprises the following steps:
step 1) temporarily fixing the outer wall 7, supporting the bottom surface C1 reference of the outer wall 7 by the supporting cushion block 8, positioning the center hole inner circle B1 reference, and determining the angular position by the D1 reference, wherein the references are shown in FIG. 3.
And 2) aligning the core rod 1 to the center of the sleeve 6, and enabling the rod body 12 to penetrate through the central holes of the first swirler 4 and the second swirler 5, so that the base 11 is matched with the outer circle of the sleeve 6.
And 3) pressing the pressing plate 2 to the end face of the first swirler 4, then screwing the nut 3, and finally detecting the position degree of the top end of the rod body 12 to indirectly reflect the position degree of the head of the flame tube.
It should be noted that, because the core rod 1 and the sleeve 6 are positioned in a small clearance fit manner, the base 11 and the outer circle of the sleeve 6 need to be ensured to be matched and not to be skewed during installation, and whether the radial positioning surface of the core rod 1 and the outer circle of the sleeve 6 are matched in place or not can be reflected through the fitting degree of the pressing plate 2 and the first swirler 4.
The measurement procedure of example 4 was followed to determine the degree of positioning of the flame tube heads in two stages, as shown in tables 1 and 2.
TABLE 1 first stage liner head position detection
TABLE 2 second stage liner head position detection
As can be seen from the table above, the detection data can reflect the situation that the position degree of the flame tube head actually deviates from the designed theoretical position, the detection data has high precision, and the field use requirements can be met; through the measuring device, the self processing surface of the measured part is reasonably used as a positioning reference, the measuring device is installed and positioned, the theoretical head position is successfully converted to the core rod, and the detection of the head position degree of the flame tube with a complex structure in a narrow space is realized.
In conclusion, when the measuring tool is used for measuring the head position of the flame tube of the aero-engine, the head position data can be indirectly detected; the measuring device has the advantages of simple structure, convenience in installation and use, small accumulated error, high measuring precision and real and reliable detection data by combining three-coordinate detection, provides effective evidence for a repair scheme after the head position degree exceeds the standard, and improves the repair qualified rate and the product delivery quality; meanwhile, the measuring tool does not need to be calibrated to ensure assembly, and the calibration link is subtracted for 2-3 days, so that the measuring period is greatly shortened.
The above-mentioned contents are only for illustrating the technical idea of the present invention, and the protection scope of the present invention is not limited thereby, and any modification made on the basis of the technical idea of the present invention falls within the protection scope of the claims of the present invention.
Claims (10)
1. A measuring device for the position degree of a flame tube head of an aircraft engine is provided with an outer wall (7), the flame tube head comprises a first swirler (4), a second swirler (5) and a sleeve (6), the first swirler (4) is fixedly connected with the second swirler (5), the second swirler (5) is fixedly connected with the sleeve (6), the device is characterized in that the measuring device comprises a core rod (1), a pressing plate (2) and a nut (3), the core rod (1) is sleeved inside a sleeve (6) and coaxial with the sleeve (6), the core rod (1) comprises a base (11) and a rod body (12), the tail end of the rod body (12) is fixed on the base (11), the pressing plate (2) is installed at the top end of the rod body (12), the nut (3) is fixed on the upper surface of the pressing plate (2), and the pressure plate (2) and the rod body (12) are fixed, and the pressure plate (2) penetrates through the rod body (12) and is positioned on the end face of the first swirler (4).
2. The device for measuring the degree of position of the head of a flame tube of an aircraft engine according to claim 1, characterised in that the mandrel (1) is clearance-fitted with the sleeve (6).
3. The device for measuring the position degree of the head of the flame tube of the aircraft engine is characterized in that the clearance between the core rod (1) and the sleeve (6) is 0-0.03 mm.
4. The device for measuring the position of the head of a flame tube of an aircraft engine according to claim 1, characterized in that the base (11) is formed by superposing two cylinders with different diameters, namely a large cylinder and a small cylinder positioned on the top surface of the large cylinder;
the diameter of the rod body (12) is smaller than that of a small cylinder on the base (11).
5. The device for measuring the position of the head of a flame tube of an aircraft engine according to claim 1, characterized in that the rod (12) is integrated with the base (11) and the rod (12) is located in the center of the top surface of the base (11).
6. The device for measuring the position of the head of a flame tube of an aircraft engine according to claim 1, characterized in that the device further comprises a support block (8) placed at the bottom of the outer wall (7) and used for fixing the outer wall (7).
7. The device for measuring the position of the head of a flame tube of an aircraft engine according to claim 6, characterized in that the supporting cushion blocks (8) are provided in a plurality and are arranged at the bottom of the outer wall (7) in a dispersed manner.
8. The device for measuring the position of the head of a flame tube of an aircraft engine according to claim 1, characterized in that the pressure plate (2) is a circular plate, the diameter of the pressure plate (2) being greater than the diameter of the rod (12).
9. The device for measuring the degree of positioning of the head of a flame tube for an aircraft engine according to claim 1, characterized in that the internal diameter of the nut (3) is greater than the diameter of the rod (12).
10. A measuring method for a measuring device for the position degree of a flame tube head of an aircraft engine based on any one of claims 1-9 is characterized by comprising the following steps:
step 1) temporarily fixing the outer wall (7);
step 2), aligning the core rod (1) to the center of the sleeve (6), enabling the rod body (12) to penetrate through center holes of the first swirler (4) and the second swirler (5), and enabling the base (11) to be matched with the outer circle of the sleeve (6);
and 3) pressing the pressing plate (2) to the end face of the first swirler (4), then screwing the nut (3), and finally detecting the position degree of the top end of the rod body (12), namely the position degree of the head of the flame tube.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111153001.6A CN113899297A (en) | 2021-09-29 | 2021-09-29 | Device and method for measuring position degree of flame tube head of aircraft engine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111153001.6A CN113899297A (en) | 2021-09-29 | 2021-09-29 | Device and method for measuring position degree of flame tube head of aircraft engine |
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| CN113899297A true CN113899297A (en) | 2022-01-07 |
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| CN202111153001.6A Pending CN113899297A (en) | 2021-09-29 | 2021-09-29 | Device and method for measuring position degree of flame tube head of aircraft engine |
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| GB9801102D0 (en) * | 1997-01-28 | 1998-03-18 | Helmut Fischer Gmbh & Co | Method and device for measuring the coating thickness on cylindrical workpieces |
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2021
- 2021-09-29 CN CN202111153001.6A patent/CN113899297A/en active Pending
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| GB9801102D0 (en) * | 1997-01-28 | 1998-03-18 | Helmut Fischer Gmbh & Co | Method and device for measuring the coating thickness on cylindrical workpieces |
| CN208155185U (en) * | 2018-04-17 | 2018-11-27 | 中国第一汽车股份有限公司 | Synchronous ring cubing |
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