CN114136168A - Aero-engine rotor disc drum assembly detection device and assembly method - Google Patents
Aero-engine rotor disc drum assembly detection device and assembly method Download PDFInfo
- Publication number
- CN114136168A CN114136168A CN202010925630.5A CN202010925630A CN114136168A CN 114136168 A CN114136168 A CN 114136168A CN 202010925630 A CN202010925630 A CN 202010925630A CN 114136168 A CN114136168 A CN 114136168A
- Authority
- CN
- China
- Prior art keywords
- drum
- disc
- detection device
- adjacent
- drums
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000001514 detection method Methods 0.000 title claims abstract description 66
- 238000000034 method Methods 0.000 title claims description 35
- 238000009434 installation Methods 0.000 claims description 9
- 238000003825 pressing Methods 0.000 claims description 5
- 230000008569 process Effects 0.000 description 12
- 238000007689 inspection Methods 0.000 description 7
- 238000012360 testing method Methods 0.000 description 5
- 238000005259 measurement Methods 0.000 description 3
- 230000015572 biosynthetic process Effects 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 239000000470 constituent Substances 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
Images
Classifications
-
- 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
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The utility model relates to an aeroengine rotor dish drum assembly detection device and aeroengine, wherein detection device includes: an operation lever (61); a mounting portion provided at one end of the operating lever (61); and a plug piece (63) connected to the mounting portion, the plug piece (63) being disposed at an angle to the operating lever (61); the operating rod (61) is configured to enable one end of the mounting portion to extend into the first hole (11) and the second hole (21) when detection is needed, and the plug piece (63) is configured to be inserted into a gap between the disc drum (10) and the spigot (4) of the blade disc (1) in the axial direction.
Description
Technical Field
The disclosure relates to the technical field of aero-engine assembly, in particular to an aero-engine rotor disc drum assembly detection device and an aero-engine rotor disc drum assembly detection method.
Background
The high-pressure compressor rotor is an important component of an aeroengine, and when the aeroengine works, the high-pressure rotor rotates at a high speed, so that the requirement on the assembly stability of the high-pressure rotor is high.
The high-pressure compressor rotor is composed of multiple stages of disc drums, in order to guarantee the connection stability of the high-pressure rotor, multiple bolts are usually adopted for short seam allowances for connection, the seam allowances for connection of adjacent disc drums are in large interference fit, and the difficulty of assembling adjacent disc drums in place is greatly increased due to large interference.
In order to ensure that the disk drums are assembled in place, whether the connecting surfaces of the adjacent disk drums of the rotor are attached to each other needs to be checked after assembly. However, the connecting seam allowance of the adjacent disk drums of the compressor rotor is invisible inside the disk cavity, so that whether the connecting surfaces of the adjacent disk drums are attached or not is difficult to check, and the assembling difficulty is increased.
Disclosure of Invention
The embodiment of the disclosure provides an aeroengine rotor disc drum assembly detection device and an aeroengine rotor disc drum assembly detection method, which can reduce the assembly difficulty of an aeroengine rotor disc drum.
According to one aspect of the disclosure, an assembly detection device for a rotor disc drum of an aircraft engine is provided, wherein the rotor disc drum comprises at least two stages of disc drums arranged along an axial direction, each stage of disc drum comprises a blade disc and a drum barrel, at least one end of the drum barrel along the axial direction is connected with the connected blade disc through a spigot, a plurality of first holes are formed in the blade disc along the circumferential direction, a plurality of second holes are formed in the drum barrel along the circumferential direction, the first holes and the second holes extend along the axial direction, the blade disc and the drum barrel penetrate through the first holes and the second holes through fasteners to be fixed, and the detection device comprises:
an operating lever;
a mounting portion provided at one end of the operating lever; and
the plug sheet is connected with the mounting part and arranged at an angle with the operating rod;
the operating rod is configured to enable one end of the mounting portion to extend into the first hole and the second hole when detection is needed, and the plug piece is configured to be inserted into a gap between the disc drum and the spigot of the leaf disc in the axial direction.
In some embodiments, the patch is removably disposed relative to the mounting portion.
In some embodiments, the operating rod comprises a rod part and a limiting part connected to one end of the rod part, and the rod part is provided with a threaded section;
the mounting portion includes: the plug piece is positioned between the two clamping blocks, and the nut is matched with the thread section and presses the other clamping block to clamp the plug piece.
In some embodiments, the plug is perpendicular to the lever.
In some embodiments, the thickness of the plug sheet is the maximum clearance allowed in the axial direction between the spigot of the disk drum and the blisk.
According to another aspect of the disclosure, an assembly method of an aeroengine rotor disc drum assembly detection device based on the above embodiment is provided, and includes:
connecting the axial end part of the drum barrel of one of the adjacent drum drums with the leaf disc of the other drum through a spigot;
fixing adjacent disk drums through a part of fasteners, wherein the fasteners penetrate through the first holes and the second holes at corresponding positions;
extending the assembly detection device into the first hole and the second hole which are not provided with the fasteners from one end where the mounting part is located;
and adjusting the extending position of the assembly detection device, checking whether the plug sheet can be inserted into the gap between the disc drum and the spigot of the leaf disc, judging that the adjacent disc drums are not assembled in place under the condition that the plug sheet can be inserted, and judging that the adjacent disc drums are assembled in place under the condition that the plug sheet cannot be inserted.
In some embodiments, in the case where it is determined that the adjacent disk drum is not fitted in place, further comprising:
removing the installed fasteners on the adjacent disk drums;
applying local pressing force to the position of the disc drum with the gap, and fixing the adjacent disc drums through partial fasteners;
and then the assembly detection device is extended into the first hole and the second hole without the fastener for detection.
In some embodiments, in the case where it is determined that the adjacent disk drum is not fitted in place, further comprising:
removing the installed fasteners on the adjacent disk drums;
the adjacent drum is disassembled and reinstalled.
In some embodiments, in the case where it is determined that the adjacent disk drum has been fitted in place, further comprising:
and finishing the installation of the remaining fasteners on the adjacent drum.
In some embodiments, when adjacent drums are fixed by partial fasteners, the partial fasteners are uniformly distributed along the circumferential direction and are installed in a symmetrical screwing mode.
In some embodiments, before connecting the adjacent disk drums, further comprising:
and heating the spigot of one of the adjacent disc drums.
In some embodiments, the joining location of adjacent drums at the seam allowance is brought back to room temperature prior to testing by the fit testing device.
In some embodiments, further comprising an assembly formation detection device, the assembly formation detection device comprising:
the two clamping blocks and the nut are sequentially sleeved on the rod part of the operating rod;
inserting the plug sheet between the two clamping blocks;
and screwing the nut along the thread section on the rod part, so that the nut pushes one of the clamping blocks to move until the other clamping block abuts against the limiting part connected to one end of the rod part in the operating rod, and the two clamping blocks clamp the plug sheet.
In some embodiments, the nut is unscrewed to replace the patch in the event of damage to the patch.
According to the aero-engine rotor disc drum assembly detection device provided by the embodiment of the disclosure, whether the high-pressure compressor rotor disc drum is assembled in place or not is judged by judging whether the connecting seam allowance of the adjacent disc drums is attached or not through the fastener installation holes of the adjacent disc drums, the thin plug piece is clamped by the operating rod and extends into the fastener installation holes, whether the drum barrel and the seam allowance of the adjacent disc drums are attached or not is checked through the boundaries of the plug piece in the first hole and the second hole, and the plug piece is not inserted into the gap between the drum barrel and the seam allowance of the adjacent disc drums, so that the rotor disc drum is assembled in place, the multistage rotor disc drum assembly in-place inspection time is greatly reduced, the inspection accuracy is improved, and the process cost is greatly reduced.
Drawings
The accompanying drawings, which are included to provide a further understanding of the disclosure and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the disclosure and together with the description serve to explain the disclosure and not to limit the disclosure. In the drawings:
FIG. 1 is a schematic view of a connection structure of a rotor disc drum of an aircraft engine according to the disclosure;
FIG. 2 is a schematic view of the determination of assembly in place by the aero-engine rotor disc drum assembly detection device of the present disclosure;
FIG. 3 is a cross-sectional view of an aircraft engine rotor disc drum assembly detection device of the present disclosure determining assembly in place;
FIG. 4 is a schematic structural diagram of some embodiments of an aircraft engine rotor disc drum assembly detection device of the present disclosure;
FIG. 5 is a cross-sectional view of some embodiments of an aircraft engine rotor disc drum assembly detection device of the present disclosure.
Description of the reference numerals
10. A drum; 10A, a first drum; 10B, a second drum; 10C, a third drum; 1. a leaf disc; 11. a first hole; 2. a drum; 21. a second hole; 22. a flange; 3. a blade; 4. stopping the opening; 51. a fastener; 52. a nut; 6. a detection device; 61. an operating lever; 611. a rod portion; 612. a limiting part; 62. a clamping block; 63. a plug sheet; 64. and a nut.
Detailed Description
The present disclosure is described in detail below. In the following paragraphs, different aspects of the embodiments are defined in more detail. Aspects so defined may be combined with any other aspect or aspects unless clearly indicated to the contrary. In particular, any feature considered to be preferred or advantageous may be combined with one or more other features considered to be preferred or advantageous.
The terms "first", "second", and the like in the present disclosure are merely for convenience of description to distinguish different constituent elements having the same name, and do not denote a sequential or primary-secondary relationship.
In the description of the present invention, it is to be understood that the terms "inner", "outer", "upper", "lower", "left", "right", "front" and "rear", etc., indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present invention, and do not indicate or imply that the device referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore, should not be taken as limiting the scope of the present invention. Also, references hereinafter to "axial," "radial," and "circumferential" are based on the engine.
As shown in fig. 1, in order to ensure the connection stability of the high-pressure rotor of the aircraft engine, a plurality of bolts are generally used for connecting short spigots, the connecting spigots of adjacent-stage disk drums are in large interference fit, the interference magnitude is greater than 0.15mm, and the difficulty of assembling the adjacent-stage disk drums 10 in place is greatly increased due to the large interference magnitude. In order to ensure that the disk drums are assembled in place, whether the connecting surfaces of the adjacent disk drums of the rotor are attached to each other needs to be checked after assembly.
Because the connecting seam allowance of the disc drum 10 of the adjacent stage of the compressor rotor shown in the figure 1 is positioned in the disc cavity and is invisible, the diameter of the disc center is small (phi value is small), the seam allowance connecting position is deeper from the disc center (A value is large, A is larger than phi), the axial distance of the adjacent disc drum 10 is small (H value is small), a standard feeler gauge (a plug sheet) cannot be fed into the adjacent disc cavity by bare hands, and whether the connecting surface of the adjacent disc drum 10 is attached or not is checked.
Under the conventional process, after all fasteners of a rotor disc drum are assembled, whether adjacent disc drums are assembled in place or not is judged by considering, the constraint of the process is restrained, the solving method is how to plug a standard feeler into a gap on the edge of a connecting flange through a narrow disc cavity, the disc cavity is narrow and invisible, the feeler is extremely soft, the realization difficulty is extremely high, the current assembly process can only judge whether the disc drum 10 is assembled in place or not through a size chain inspection mode, and the judgment period of the disc drum assembling in place is longer due to the influence of multiple parameter measurement and measurement errors.
As shown in fig. 1, the axial height L1 from the mounting reference of the rear end surface of the first disk drum 10A is measured before assembly, the blisk thickness L3 of the adjacent second disk drum 10B is measured, the axial distance L2 from the mounting reference surface of the rear end surface of the second disk drum 10B is measured after the first disk drum 10A and the second disk drum 10B are assembled, and whether the first disk drum 10A and the second disk drum 10B are assembled in place is judged by calculating the values of L2-L1-L3. For example, the dimension chain piece meets L2-L1-L3 is less than or equal to 0.03, the chain piece is regarded as being assembled in place, a plurality of measuring points are required to be selected along the circumferential direction by adopting the mode, a large amount of data are measured to judge whether the drum 10 is assembled in place, the measured data are more, the period is longer, three parameters are required for the whole dimension chain, measuring errors cannot be avoided in the measuring process, the dimension chain piece is often difficult to meet, but the dimension chain piece cannot be judged to be not met due to the measuring errors, or the dimension chain piece cannot be met due to the fact that the drum 10 is not assembled in place. These disadvantages result in long high pressure rotor assembly cycles, which require a long time to verify whether the rotor disc drum is assembled in place.
In order to improve the assembly efficiency of the rotor disc drum, the disclosure provides an aeroengine rotor disc drum assembly detection device, and the detection device can be used for an aeroengine high-pressure compressor rotor. In some embodiments, as shown in fig. 1, the rotor disk drum includes at least two stages of disk drums 10 arranged in the axial direction, for example, three stages of disk drums 10 are illustrated in fig. 1, including a first disk drum 10A, a second disk drum 10B, and a third disk drum 10C connected in series in the axial direction. Each stage of disc drum 10 comprises a blade disc 1 and a drum barrel 2, a plurality of blades 3 are arranged on the outer side wall of each blade disc 1 at intervals along the circumferential direction, the drum barrels 2 are connected between the blade discs 1 of the adjacent disc drums 10, and the drum barrels 2 are located at the positions, close to the periphery, of the blade discs 1.
At least one end of the drum 2 in the axial direction is connected with the connected bladed disc 1 through a spigot 4, a plurality of first holes 11 are formed in the bladed disc 1 in the circumferential direction, a plurality of second holes 21 are formed in the drum 2 in the circumferential direction, the first holes 11 and the second holes 21 extend in the axial direction, the bladed disc 1 and the drum 2 penetrate through the first holes 11 and the second holes 21 through fasteners 51, and the fasteners 51 can be bolts, screws and the like, for example, the specification is M8, and are fixed through nuts 52, or pins can also be adopted.
For example, one end of a drum 2 of a first drum 10A is integrally fixed with a leaf disc 1, the other end of the drum 2 of the first drum 10A is connected with a leaf disc 1 of an adjacent second drum 10B through a spigot 4, a fastener 51 passes through a first hole 11 and a second hole 21 to fix the first drum 10A and the second drum 10B, in order to facilitate the connection of the drum 2 with the leaf disc 1, a flange 22 extending radially inwards is arranged at the end of the drum 2, and is connected and fixed with the leaf disc 1 through the flange 22, and specifically, the drum 2 is positioned in contact with the spigot 4 through the flange 22 when the adjacent drum 10 is assembled in place; one end of a drum barrel 2 of the second drum 10B is integrally fixed with the leaf disc 1, and the other end of the drum barrel 2 of the second drum 10B is connected with the leaf disc 1 of the adjacent third drum 10C through a seam allowance 4; one end of a drum barrel 2 of the third drum 10C is connected with the leaf disc 1 through the seam allowance 4, and the fastening piece 51 penetrates through the second hole 21, the first hole 11 and the second hole 21 in sequence to achieve fixing of the second drum 10B and the third drum 10C.
Based on such a rotor disc drum, as shown in fig. 2 to 5, the detection device 6 includes: an operating lever 61, a mounting portion and a plug 63. The mounting portion is provided at one end of the operating lever 61, and may be provided at the end of the operating lever 61, for example. The plug 63 is connected to the mounting portion, and the plug 63 is disposed at an angle to the operating lever 61. Preferably, the plug 63 may be disposed perpendicular to the operating rod 61, forming an L-shaped structure.
As shown in fig. 1, the operating rod 61 is configured such that, when an assembly test is required, one end of the mounting portion is inserted into the first hole 11 and the second hole 21, the first hole 11 and the second hole 21 form a mounting hole of the fastener 51, and the plug 63 is configured to be inserted into a gap between the hub 10 and the spigot 4 of the blisk 1 in the axial direction. If the plug piece 63 can be inserted into the gap, the adjacent disk drums 10 are judged not to be assembled in place, and the end parts of the disk drums 10 are not tightly attached to the spigot 4 in the axial direction; if the plug 63 cannot be inserted into the gap, it is determined that the adjacent disk drum 10 is assembled in place and the end of the disk drum 10 is in close axial engagement with the spigot 4.
Since the lateral dimension of the detecting means 6 at the stopper 63 is the largest, which is the dimension perpendicular to the longitudinal direction of the operating lever 61, the lateral dimension of the detecting means 6 at the stopper 63 should be smaller than the diameters of the first hole 11 and the second hole 21 so that the detecting means 6 can be smoothly inserted, and there is a position adjustment space to accurately judge whether the stopper 63 can be inserted into the gap.
According to the embodiment, whether the high-pressure compressor rotor disc drum is assembled in place or not is judged by judging whether the connection seam allowance of the adjacent disc drums is attached or not through the fastener installation holes of the adjacent disc drums 10, the thin plug piece 63 is clamped by the operating rod 61 and extends into the fastener installation holes, whether the drum barrel 2 and the seam allowance 4 of the adjacent disc drums 10 are attached or not is checked through the boundary of the plug piece 63 between the first hole 11 and the second hole 21, and the rotor disc drum is assembled in place if the plug piece 63 cannot be inserted through the gap between the drum barrel 2 and the seam allowance 4 of the adjacent disc drums 10, so that the time for inspecting the multistage rotor disc drum in place is greatly shortened, the inspection accuracy is improved, and the process cost is greatly reduced.
Because the mounting hole of the fastener 51 is small, the plug piece 63 is soft and is not easy to be directly plugged into a gap at the joint of the adjacent drum 10 from the mounting hole, the thin plug piece 63 is clamped by the operating rod 61 and extends into the mounting hole of the fastener 51 for detection, and the reliability and the success rate of detection can be improved.
In some embodiments, the patch 63 is removably disposed relative to the mounting portion. Because the plug piece 63 is thin and soft, the plug piece is easy to deform and damage in the detection process, the plug piece 63 serving as a loss piece can be conveniently replaced by a detachable structure, the replacement efficiency is high, the process cost is low, and the smooth assembly of the rotor disc drum of the aircraft engine can be ensured.
In some embodiments, the operating lever 61 includes a shaft portion 611 and a stopper portion 612 connected to one end of the shaft portion 611, and the shaft portion 611 has a threaded section. The mounting portion includes: a nut 64 and two clamping blocks 62, wherein the clamping blocks 62 can adopt a disc-shaped, cuboid-shaped or water-drop-shaped structure. The two clamping blocks 62 and the nut 64 are sequentially sleeved on the rod portion 611, one clamping block 62 abuts against the limiting portion 612, the plug 63 is located between the two clamping blocks 62, and the nut 64 is matched with the threaded section and presses the other clamping block 62 to clamp the plug 63.
The plug 63 can be directly fixed by the clamping force of the two clamping blocks 62, so that when the plug 63 is damaged and needs to be replaced, the nut 64 is directly unscrewed, and the new plug 63 can be conveniently replaced. Alternatively, the plug 63 may be provided with a hole, and the plug 63 is also sleeved on the rod portion 611.
This embodiment can realize the fixed of cock stem 63 through the mode of centre gripping, because cock stem 63 is thin softer, easy deformation and damage, loosen nut 64 and can realize the dismantlement and the change of cock stem 63, easily operation, it is convenient to use, and the change is inefficient, and technology cost is low. And moreover, the detection of the connection clearance between the adjacent disk drums 10 is more accurate, the assembly performance of the rotor disk drums is improved, and the assembly efficiency of the rotor disk drums of the aircraft engine can be improved.
In some embodiments, the plug 63 is perpendicular to the lever 61. The structure is easy to operate and convenient to detect.
In some embodiments, the thickness of the plug 63 is the maximum clearance allowed in the axial direction between the disk drum 10 and the spigot 4 of the blisk 1. For example, the allowable maximum clearance is 0.02mm, the thickness of the plug 63 is also designed to be 0.02mm, if the plug 63 can be inserted into the clearance between the disk drum 10 and the spigot 4 of the blisk 1 in the axial direction during the detection, it is indicated that the actual clearance is larger than the allowable maximum clearance by 0.02mm, it is determined that the adjacent disk drum 10 is not assembled in place, if the plug 63 cannot be inserted into the clearance between the disk drum 10 and the spigot 4 of the blisk 1 in the axial direction during the detection, it is indicated that the actual clearance is smaller than the allowable maximum clearance by 0.02mm, it is possible to select multiple points in the entire circumferential direction for the detection, and if none of the plug 63 can be inserted into the clearance, it is determined that the adjacent disk drum 10 is assembled in place.
Through the embodiment, the detection device 6 disclosed by the invention can be used for rapidly judging whether the rotor disc drum is assembled in place or not, so that the inspection accuracy is improved, the inspection time is shortened, and the process cost is greatly reduced; and the tool has simple structure, easy operation, low production cost and high measurement efficiency.
Secondly, the present disclosure provides an assembly method of an aeroengine rotor disc drum assembly detection device based on the above embodiments, and in some embodiments, the assembly method includes:
step 101, connecting the axial end part of the drum barrel 2 of one drum 10 of the adjacent drums 10 with the leaf disc 1 of the other drum 10 through a spigot 4, namely inserting the end part of the drum barrel 2 into the spigot 4, and connecting the drum barrel 2 with the spigot 4 through tight fit;
102, fixing the adjacent drum 10 by a part of fasteners 51, wherein the fasteners 51 penetrate through the first holes 11 and the second holes 21 at corresponding positions;
103, extending the assembly detection device 6 into the first hole 11 and the second hole 21 of the non-installed fastener 51 from one end where the installation part is located;
step 104, adjusting the extending position of the assembly detection device 6, checking whether the plug piece 63 can be inserted into the gap between the disc drum 10 and the spigot 4 of the leaf disc 1, and judging that the adjacent disc drums 10 are not assembled in place under the condition that the plug piece can be inserted; wherein, as long as the detecting device 6 detects that the plug 63 can be inserted into the gap in one of the sets of the first hole 11 and the second hole 21 where the fastener 51 is not installed, it is determined that the adjacent drum 10 is not assembled in place.
Wherein, steps 102 to 104 are performed sequentially. According to the embodiment, the adjacent disc drums 10 are fixed through part of the fasteners 51, the leaf discs 1 and the rabbets 4 of the adjacent disc drums 10 are relatively stable, relative dislocation cannot occur under the action of external force, then the detection device 6 extends into the mounting holes of the fasteners 51 to be detected, and the detection accuracy in the assembling process can be improved.
And whether the high-pressure compressor rotor disc drum is assembled in place or not is judged by judging whether the connection seam allowance of the adjacent disc drums is jointed or not through the fastener installation holes of the adjacent disc drums 10, the thin plug piece 63 clamped by the operating rod 61 extends into the fastener installation holes, whether the drum barrel 2 and the seam allowance 4 of the adjacent disc drums 10 are jointed or not is checked through the boundary of the plug piece 63 between the first hole 11 and the second hole 21, and the rotor disc drum is assembled in place if the plug piece 63 cannot be inserted through the gap between the drum barrel 2 and the seam allowance 4 of the adjacent disc drums 10, so that the time for inspecting the multistage rotor disc drum in place is greatly shortened, the inspection accuracy is improved, and the process cost is greatly reduced.
In some embodiments, in the case where it is determined by step 104 that the adjacent disk drum 10 is not assembled in place, the assembling method of the present disclosure further includes:
105, removing the mounted fasteners 51 on the adjacent drum 10;
step 106, applying local pressing force adjustment to the position where the disc drum 10 has the gap; (ii) a
And step 107, fixing the adjacent disk drum 10 again through a part of the fasteners 51, and detecting by extending the assembly detection device 6 into the first holes 11 and the second holes 21 without the fasteners 51.
Wherein, the steps 105 and 107 are performed sequentially. This embodiment enables the adjacent drum 10 to be adjusted to be mounted in place by locally applying a pressing force when the adjacent drum 10 is not mounted in place, which is suitable for a case where the adjustment amount is small, and can improve the assembly efficiency.
In some embodiments, in the case where it is determined by step 104 that the adjacent disk drum 10 is not assembled in place, the assembling method of the present disclosure further includes:
step 108, removing the installed fasteners 51 on the adjacent drum 10;
step 109, disassembling and re-installing the adjacent disk drums 10;
and step 107, fixing the adjacent disk drum 10 again through a part of the fasteners 51, and detecting by extending the assembly detection device 6 into the first holes 11 and the second holes 21 without the fasteners 51.
Wherein steps 108, 109 and 107 are performed sequentially. This embodiment enables adjustment by removing and reinstalling the adjacent drum 10 when the adjacent drum 10 is not installed in place, which is suitable for the case where the adjustment amount is large and cannot be adjusted by locally applying the pressing force.
In some embodiments, the assembly method of the present disclosure further comprises:
step 201, when the plug piece 63 cannot be inserted into the gap between the disc drum 10 and the spigot 4 of the blisk 1, the detection device 6 is made to extend into the first hole 11 and the second hole 21 of the next group of non-installed fasteners 51, and if the position of each group of non-installed fasteners 51 cannot be used for inserting the plug piece 63 into the gap between the disc drum 10 and the spigot 4 of the blisk 1, the adjacent disc drum 10 is judged to be assembled in place.
The embodiment can comprehensively consider the assembling clearance conditions of a plurality of positions of the adjacent disk drums 10 along the circumferential direction, can more accurately and objectively reflect the assembling conditions of the adjacent disk drums 10, and can improve the assembling performance of the rotor disk drum of the aircraft engine.
In some embodiments, in the case where it is determined that the adjacent disk drum 10 has been fitted in place, the fitting method of the present disclosure further includes:
and step 202, finishing installing the remaining fasteners 51 on the adjacent drum 10 to complete the assembly of the adjacent drum 10.
After the adjacent disk drums 10 are connected and mounted, the next disk drum 10 can be mounted in sequence.
In some embodiments, when the adjacent drums 10 are fixed by the partial fastening members 51, the partial fastening members 51 are uniformly distributed in the circumferential direction and are installed in a symmetrical tightening manner. For example, 6 dots, 8 dots, 12 dots, 16 dots, etc. may be employed. The embodiment can ensure that the stress of the adjacent disk drums 10 is uniform after the adjacent disk drums are connected at each position in the circumferential direction, and prevent the generation of unbalanced force from influencing the gap between the adjacent disk drums 10, so that the gap detection can reflect the actual assembly condition of the adjacent disk drums 10.
In some embodiments, prior to connecting adjacent disk drums 10, the assembly method of the present disclosure further includes:
the spigot 4 of one of the adjacent disc drums 10 is heated.
The embodiment adopts a hot-assembly mode to realize the connection of the adjacent disc drums 10, so that the assembly can be smoothly realized when the leaf discs 1 and the drum cylinders 2 of the disc drums 10 are in tight fit.
In some embodiments, the connection of adjacent drums 10 at the seam allowance 4 is brought back to room temperature before testing by the fit testing device 6.
The embodiment detects when the temperature is restored to the room temperature, and can enable the detection of the assembly gap to be more accurate, so that whether the adjacent disc drums 10 are assembled in place or not can be more accurately judged, and the assembly performance is improved.
In some embodiments, the assembly method of the present disclosure further includes assembling the form detection device 6, the assembling the form detection device 6 including:
step 301, sequentially sleeving the two clamping blocks 62 and the nut 64 on the rod part 611 of the operating rod 61;
step 302, inserting the plug 63 between the two clamping blocks 62;
step 303, screwing the nut 64 along the thread section on the rod portion 611, so that the nut 64 pushes one of the clamping blocks 62 to move until the other clamping block 62 abuts against the limiting portion 612 of the operating rod 61 connected to one end of the rod portion 611, and the two clamping blocks 62 clamp the plug 63.
Wherein, steps 301 to 303 are executed sequentially. This embodiment can realize the fixed of plug piece 63 through the mode of centre gripping, simple to operate can improve the assembly efficiency of rotor drum.
In some embodiments, in the event of damage to the patch 63, the nut 64 is unscrewed to replace the patch 63.
Because the plug piece 63 is thin and soft and is easy to deform and damage, the plug piece 63 can be detached and replaced by loosening the nut 64, the operation is easy, the use is convenient and fast, the replacement efficiency is low, and the process cost is low.
The aero-engine rotor disc drum assembly detection device and the aero-engine provided by the disclosure are described in detail above. The principles and embodiments of the present disclosure are explained herein using specific examples, which are set forth only to help understand the method and its core ideas of the present disclosure. It should be noted that, for those skilled in the art, it is possible to make several improvements and modifications to the present disclosure without departing from the principle of the present disclosure, and such improvements and modifications also fall within the scope of the claims of the present disclosure.
Claims (15)
1. An aircraft engine rotor drum assembly detection device, wherein the rotor drum comprises at least two stages of drums (10) arranged along an axial direction, each stage of the drums (10) comprises a blade disc (1) and a drum barrel (2), at least one end of the drum barrel (2) along the axial direction is connected with the connected blade disc (1) through a seam allowance (4), a plurality of first holes (11) are formed in the blade disc (1) along the circumferential direction, a plurality of second holes (21) are formed in the drum barrel (2) along the circumferential direction, the first holes (11) and the second holes (21) extend along the axial direction, the blade disc (1) and the drum barrel (2) are fixed through the first holes (11) and the second holes (21) through fasteners (51), and the detection device (6) comprises:
an operation lever (61);
a mounting portion provided at one end of the operating lever (61); and
a plug piece (63) connected to the mounting portion, the plug piece (63) being disposed at an angle to the operating lever (61);
the operating rod (61) is configured to enable one end where the mounting portion is located to extend into the first hole (11) and the second hole (21) when detection is needed, and the plug piece (63) is configured to be inserted into a gap between the disc drum (10) and the spigot (4) of the blade disc (1) in the axial direction.
2. An aircraft engine rotor disc drum assembly detection device according to claim 1, wherein the plug piece (63) is removably arranged with respect to the mounting portion.
3. The aircraft engine rotor disc drum assembly detection device according to claim 1 or 2, wherein the operating rod (61) comprises a rod part (611) and a limiting part (612) connected to one end of the rod part (611), and the rod part (611) is provided with a threaded section;
the mounting portion includes: the plug piece comprises a nut (64) and two clamping blocks (62), the two clamping blocks (62) and the nut (64) are sequentially sleeved on the rod portion (611), one clamping block (62) abuts against the limiting portion (612), the plug piece (63) is located between the two clamping blocks (62), and the nut (64) is matched with the threaded section and presses the other clamping block (62) to clamp the plug piece (63).
4. An aircraft engine rotor disc drum assembly detection device according to claim 1, wherein the plug piece (63) is perpendicular to the operating rod (61).
5. An aircraft engine rotor disc drum assembly detection device according to claim 1, wherein the thickness of the plug piece (63) is the maximum clearance allowed in the axial direction of the disc drum (10) and the spigot (4) of the blisk (1).
6. An assembly method based on the aeroengine rotor disc drum assembly detection device of any one of claims 1-5 comprises the following steps:
the drum barrel (2) of one of the adjacent drum drums (10) is connected with the leaf disc (1) of the other drum (10) through a spigot (4) along the axial end part;
fixing the adjacent disk drum (10) by a part of fasteners (51), wherein the fasteners (51) pass through the first holes (11) and the second holes (21) at corresponding positions;
extending the assembly detection device (6) from the end where the mounting portion is located into the first hole (11) and the second hole (21) where no fastener (51) is mounted;
adjusting the extending position of the assembly detection device (6), checking whether the plug piece (63) can be inserted into the gap between the disc drum (10) and the spigot (4) of the blade disc (1), and judging that the adjacent disc drums (10) are not assembled in place under the condition that the plug piece can be inserted.
7. The fitting method according to claim 6, wherein in the case where it is determined that the adjacent disk drum (10) is not fitted in place, further comprising:
removing the fasteners (51) installed on the adjacent drum (10);
applying local pressing force adjustment to the position of the disc drum (10) with a gap;
and fixing the adjacent disk drum (10) again through a part of the fasteners (51), and detecting by the assembly detection device (6) extending into the first hole (11) and the second hole (21) without the fasteners (51).
8. The fitting method according to claim 6, wherein in the case where it is determined that the adjacent disk drum (10) is not fitted in place, further comprising:
removing the fasteners (51) installed on the adjacent drum (10);
detaching and reinstalling the adjacent disk drums (10);
and fixing the adjacent disk drum (10) again through a part of the fasteners (51), and detecting by the assembly detection device (6) extending into the first hole (11) and the second hole (21) without the fasteners (51).
9. The assembling method according to claim 6, further comprising:
when the plug piece (63) cannot be inserted into the gap between the disc drum (10) and the spigot (4) of the blisk (1), the detection device (6) is made to extend into the first hole (11) and the second hole (21) of the next group of non-installed fasteners (51), and if the positions of the non-installed fasteners (51) of all the groups cannot enable the plug piece (63) to be inserted into the gap between the disc drum (10) and the spigot (4) of the blisk (1), the adjacent disc drum (10) is judged to be assembled in place.
10. The fitting method according to claim 9, wherein in the case where it is determined that the adjacent disk drum (10) has been fitted in place, further comprising:
and finishing the installation of the remaining fasteners (51) on the adjacent drums (10).
11. The assembling method according to claim 6, wherein when the adjacent disk drums (10) are fixed by the partial fastening pieces (51) firstly, the partial fastening pieces (51) are uniformly distributed along the circumferential direction and are installed in a symmetrically screwed mode.
12. The assembling method according to claim 6, wherein, before connecting the adjacent disk drums (10), further comprising:
the spigot (4) of one of the adjacent disc drums (10) is heated.
13. The assembly method according to claim 6, wherein the connection site of adjacent disc drums (10) at the seam allowance (4) is returned to room temperature before the detection by the assembly detection device (6).
14. The assembly method according to claim 6, further comprising assembling to form the detection device (6), the assembling to form the detection device (6) comprising:
two clamping blocks (62) and a nut (64) are sequentially sleeved on a rod part (611) of the operating rod (61);
-inserting the plug (63) between the two blocks (62);
and screwing a nut (64) along the thread section on the rod part (611) to enable the nut (64) to push one clamping block (62) to move until the other clamping block (62) abuts against a limiting part (612) connected to one end of the rod part (611) in the operating rod (61), and the two clamping blocks (62) clamp the plug sheet (63).
15. An assembly method according to claim 14, wherein, in the event of damage to the plug (63), the nut (64) is unscrewed to replace the plug (63).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010925630.5A CN114136168A (en) | 2020-09-04 | 2020-09-04 | Aero-engine rotor disc drum assembly detection device and assembly method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010925630.5A CN114136168A (en) | 2020-09-04 | 2020-09-04 | Aero-engine rotor disc drum assembly detection device and assembly method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114136168A true CN114136168A (en) | 2022-03-04 |
Family
ID=80438458
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010925630.5A Pending CN114136168A (en) | 2020-09-04 | 2020-09-04 | Aero-engine rotor disc drum assembly detection device and assembly method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114136168A (en) |
Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202304708U (en) * | 2011-10-25 | 2012-07-04 | 潍柴动力股份有限公司 | Measuring tool |
| CN103847981A (en) * | 2014-03-17 | 2014-06-11 | 沈阳飞机工业（集团）有限公司 | Assembly and inspection method of dual-curvature skin type part |
| CN204183185U (en) * | 2014-11-10 | 2015-03-04 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of device turning stator part assembling for aero-engine and measure |
| CN104949601A (en) * | 2015-07-15 | 2015-09-30 | 南车株洲电机有限公司 | Motor bearing assembling clearance detecting method and device |
| CN205001254U (en) * | 2015-09-29 | 2016-01-27 | 中航商用航空发动机有限责任公司 | Rotor blade dish, compressor and aeroengine |
| CN108797796A (en) * | 2018-06-11 | 2018-11-13 | 上海通用建筑工程有限公司 | A kind of construction of steel construction fastening bolt and method of quality control |
| CN208588303U (en) * | 2018-06-26 | 2019-03-08 | 广州广日电梯工程有限公司 | A kind of safety tongs clearance measuring tool |
| CN110397613A (en) * | 2019-07-09 | 2019-11-01 | 中国航发哈尔滨东安发动机有限公司 | A kind of measurement method in overall structure compressor gap |
| CN209743166U (en) * | 2018-12-27 | 2019-12-06 | 上海连成（集团）有限公司 | Sectional type multistage pump structure |
| CN110608224A (en) * | 2019-09-22 | 2019-12-24 | 中国航发沈阳发动机研究所 | Rotor disk assembly bolt anti-disengaging structure |
| EP3593939A1 (en) * | 2018-07-13 | 2020-01-15 | Schaaf GmbH & Co. KG | Method for screwing a flange connection, measuring cart and robot |
-
2020
- 2020-09-04 CN CN202010925630.5A patent/CN114136168A/en active Pending
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202304708U (en) * | 2011-10-25 | 2012-07-04 | 潍柴动力股份有限公司 | Measuring tool |
| CN103847981A (en) * | 2014-03-17 | 2014-06-11 | 沈阳飞机工业（集团）有限公司 | Assembly and inspection method of dual-curvature skin type part |
| CN204183185U (en) * | 2014-11-10 | 2015-03-04 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of device turning stator part assembling for aero-engine and measure |
| CN104949601A (en) * | 2015-07-15 | 2015-09-30 | 南车株洲电机有限公司 | Motor bearing assembling clearance detecting method and device |
| CN205001254U (en) * | 2015-09-29 | 2016-01-27 | 中航商用航空发动机有限责任公司 | Rotor blade dish, compressor and aeroengine |
| CN108797796A (en) * | 2018-06-11 | 2018-11-13 | 上海通用建筑工程有限公司 | A kind of construction of steel construction fastening bolt and method of quality control |
| CN208588303U (en) * | 2018-06-26 | 2019-03-08 | 广州广日电梯工程有限公司 | A kind of safety tongs clearance measuring tool |
| EP3593939A1 (en) * | 2018-07-13 | 2020-01-15 | Schaaf GmbH & Co. KG | Method for screwing a flange connection, measuring cart and robot |
| CN209743166U (en) * | 2018-12-27 | 2019-12-06 | 上海连成（集团）有限公司 | Sectional type multistage pump structure |
| CN110397613A (en) * | 2019-07-09 | 2019-11-01 | 中国航发哈尔滨东安发动机有限公司 | A kind of measurement method in overall structure compressor gap |
| CN110608224A (en) * | 2019-09-22 | 2019-12-24 | 中国航发沈阳发动机研究所 | Rotor disk assembly bolt anti-disengaging structure |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US7912587B2 (en) | Method of balancing a gas turbine engine rotor | |
| US10189125B2 (en) | Assembly inspection method and associated device | |
| CN110397613B (en) | Method for measuring gap of compressor with integral structure | |
| CN110878762A (en) | Pin-connected gas turbine compressor rotor and installation method thereof | |
| US20030178847A1 (en) | Threaded connection makeup method | |
| CN114136168A (en) | Aero-engine rotor disc drum assembly detection device and assembly method | |
| CN116338669A (en) | Offset correction processing method for blade mounting holes of aeroengine air inlet guide casing | |
| CN115510594B (en) | Connection interface state control and detection method | |
| CN113199237B (en) | Method for assembling low-pressure turbine guider of aircraft engine and coaxiality auxiliary control device | |
| CN114700537B (en) | Positioning numerical milling fixture and numerical milling processing method for metal sealing ring of power turbine casing | |
| CN214173235U (en) | Cylinder jacket hole examines utensil on line | |
| CN213274663U (en) | Torque measuring device for bearing sealing element | |
| JP2013040647A (en) | Gasket interference measuring method of flange | |
| US9925876B2 (en) | Flow master for apparatus testing | |
| CN113600976A (en) | DN650 metal flexible connecting pipe installation size control method | |
| WO2016133128A1 (en) | Fixing device, rotary machine, method for manufacturing, method for assembling and method for disassembling rotary machine | |
| CN218764963U (en) | Auxiliary tool for installing fatigue test piece of propeller blade | |
| CN113565850B (en) | Non-unbalance-load constant-tension accurate fastening method | |
| CN217122952U (en) | Workpiece clamping device for dynamic balance process | |
| CN112698132B (en) | Durability test method for steering engine | |
| CN220380973U (en) | Friction coefficient testing device for screw fastener | |
| CN117029639A (en) | Rotor assembly blade torsion angle measuring device and method | |
| US20230194371A1 (en) | Method and device for checking the tightening tension of a fastening bolt for fastening aeronautical parts | |
| CN117663945A (en) | Constraint detection method and device for non-rigid annular part | |
| CN115597460A (en) | Edge plate grinding amount detection tool |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |