CN115828446A - Method for improving rotor stacking optimization quality and calculation speed - Google Patents
Method for improving rotor stacking optimization quality and calculation speed Download PDFInfo
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Abstract
The utility model belongs to aeroengine rotor assembly field, for a method of improving rotor and piling up optimization quality and computational rate, SP benchmark phase place through setting up every rotor single disk is the same with a bolt hole phase place of this rotor single disk, thereby guarantee when rotating rotor single disk parts, bolt or bolt hole align certainly just after the transposition, thereby avoid assembling nearby, the assembly can not produce the phase deviation, use the adjacent bolt hole interval angle of this rotor single disk as the step length simultaneously, traverse all phases except that first order and last level all rotor single disks, SP's calculated amount reduces by a wide margin under this mode, and find all solutions that are less than SP threshold value through the SP threshold value that sets up the rotor subassembly and carry out AP calculation, when the calculated amount further reduces, can find a set of optimal solution that SP and AP are all less, thereby realize piling up optimization algorithm's high efficiency and optimize.
Description
Technical Field
The application belongs to the field of aircraft engine rotor assembly, and particularly relates to a method for improving the stacking optimization quality and the calculation speed of a rotor.
Background
The rotor assembly stacking optimization technology achieves the purpose of controlling the concentricity of the rotor fulcrum by optimizing the installation phase angle among all parts of the rotor. The effect of reducing the initial unbalance amount of the rotor assembly is achieved by controlling the concentricity of the rotor fulcrum.
At present, rotor stacking optimization equipment SPS-1000L developed by Precitech company is generally introduced during assembly of an aeroengine, and prediction and coaxiality optimization of an assembly position are realized, so that the coaxiality after assembly is optimized, and the efficiency and the quality of rotor assembly are improved. However, in the actual assembly and application process, the existing stacking optimization technology does not deeply consider the structural characteristics of the rotor of the gas turbine engine, and the assembly requirements of the rotor of the multistage gas turbine engine cannot be completely met. Therefore, improvement research needs to be carried out on the rotor stacking optimization technology, the defects are overcome, and the stability of the rotor assembly quality is improved.
The stacking optimization principle is shown in fig. 1A and B, the coaxiality of the rotor assembly is comprehensively influenced by the coaxiality and the verticality of a single piece, and the calculation formula is shown in formula (1). The SPS-1000L system obtains the influence quantity SP (Stack preference) of the single disc on the coaxiality of the rotor assembly by measuring the coaxiality and the verticality of the single disc, the SP calculation formula is shown as a formula (2), and the assembly phase of the single disc is changed to optimize the coaxiality of the rotor assembly, so that the assembly quality of the rotor is improved.
In the prior art, the minimum coaxiality of a rotor assembly is taken as an optimization target, 360 phases of each stage of disc in the circumferential direction are calculated in a traversing manner by taking 1 degree as an interval angle, and a rotor coaxiality prediction result of all phase combinations is calculated.
In the formula:
is the coaxiality of the rotor assembly, mm;
di is the diameter of a single connecting surface in mm;
hi is the height from the connecting surface to the optimized connecting surface, and is mm;
n is the number of rotor assembly pieces.
In the formula:
the influence quantity of coaxiality of the rotor assembly is a single disc, and is mm;
di. Hi is as defined above.
The disadvantages of the currently employed stack optimization algorithm are:
when there are more pairsWhen the rotor of the machine element is optimized, the optimization result cannot be calculated due to the large calculation amount; the number of rotor discs of the aircraft engine press is generally more than or equal to 7, and the calculated amount is 360 6 Approximately 20000 billion, the SPS-1000L system cannot calculate the optimization result;
the influence of the mounting side bolt is not considered, the bolt and the bolt hole can only be aligned nearby on the basis of the calculated optimal phase during actual assembly, and the phase deviation after nearby assembly influences the final optimization result; if a certain machine member A is mounted nearby, the maximum error generated by the number N of the connecting side bolts is shown in the formula (3).
In the formula: n is the number of connecting bolts of the machine part A and the previous machine part;
Calculating N to be 30, 40, 50 and 60 according to the formula (3),
0.2mm, 0.1mm,0.05mm
As shown in table 1.
TABLE 1 analysis of the near Assembly impact
As can be seen from table 1, the stacking optimization result is affected in the case of near assembly, the rotor coaxiality is deteriorated, the influence on the coaxiality is larger as the number of bolts is smaller, and the influence on the rotor coaxiality is larger as the number of single disks SP is larger, and when a plurality of disks are all assembled nearby, error accumulation may occur, and therefore the influence on the rotor coaxiality caused by the near assembly cannot be ignored.
The optimal solution calculated by the existing stacking technology can only ensure that the final coaxiality of the rotor assembly is optimal, the influence of the installation phase of machine parts on the axial shape of the rotor assembly is not considered, and the initial unbalance amount of the rotor assembly, namely the assembly balance quality of the rotor, can be directly influenced by the deviation of the single-disc axial line from the rotor assembly. For example, in the three cases shown in fig. 2, the final coaxiality of the rotor assembly is 0mm, but the axes of the single-disk rotors in the installation phases a and B are deviated to one side of the axis of the rotor assembly, and the axes of the single-disk rotors in the installation phase C are uniformly distributed on two sides of the axis of the rotor assembly, so that the assembly mode of the phase C is optimal. The rotor unbalance cannot be optimized only by the existing stack optimization algorithm.
The existing stacking optimization rotor assembly technology cannot realize stacking optimization assembly of a multistage rotor and cannot meet the requirement of assembly balance quality of a gas turbine engine rotor.
Therefore, how to optimize the stacking assembly strategy and improve the efficiency and quality of rotor assembly is a problem to be solved.
Disclosure of Invention
The application aims to provide a method for improving the stacking optimization quality and the calculation speed of a rotor, so as to solve the problems of low calculation efficiency and large calculation error of a stacking optimization algorithm for rotor assembly in the prior art.
The technical scheme of the application is as follows: a method of improving rotor stack optimization quality and computation speed, comprising: determining the number of the rotor single discs to be assembled, setting the SP reference phase of each rotor single disc to be the same as the phase of a bolt hole of the rotor single disc, setting the reference phase of the front mounting edge of each rotor single disc as reference 1, setting the reference phase of the rear mounting edge of each rotor single disc as reference 2, determining reference 1 and reference 2 of each rotor single disc, determining the reference surface of each rotor single disc, and determining the adjacent reference interval theta of each rotor single disc Reference interval (ii) a DeterminingTraversing all phases of all the rotor single disks except the first stage and the last stage by taking the interval angle of the adjacent bolt holes of the rotor single disk as a step length, determining a feasible calculation domain, and calculating SP of all feasible schemes in the feasible calculation domain; and setting an SP threshold of the rotor assembly, calculating solutions smaller than the SP threshold in all SPs, then performing AP calculation on the SP calculation solutions smaller than the SP threshold, and screening out the solution with the smallest AP as an optimal assembly phase.
Preferably, after screening out SP calculation solutions smaller than SP threshold, all the parts under the rotor system are selected
And forming a series of vectors connected end to end, taking the SP midpoint value of each machine element as the influence of each machine element on the axle center AP of the rotor assembly, calculating the AP of each feasible scheme, and selecting the installation phase with the minimum AP as the optimal assembly phase.
Preferably, the calculation formula of the AP is:
in the formula:
x i ＝x i-1 +sp i cos(α i )
y i ＝y i-1 +sp i sin(α i )
α i is the phase, SP, of the machine member i relative to a 0 DEG reference plane of the machine member 1 i Is the SP value of the machine element i, x 0 ＝y 0 ＝0。
Preferably, the specific method for forming the feasible region is as follows:
aligning all rotor single disks according to a datum plane alignment rule, keeping a first-stage rotor single disk and a last-stage rotor single disk still, determining the number of bolts between a last-but-one-stage rotor single disk and the last-stage rotor single disk, enabling the last-but-one-stage rotor single disk to rotate for 1 step length which is spaced from the last-stage rotor single disk by an adjacent bolt, analytically calculating the optimal installation phase of the last-stage rotor single disk, then enabling the last-but-one-stage rotor single disk to rotate for one step length again until the rotation frequency of the last-but-one-stage rotor single disk is the same as the number of bolts between the last-but-one-stage rotor single disk and the last-stage rotor single disk, enabling the last-but-one-second-stage rotor single disk to rotate for one circle, keeping the last-stage rotor single disk still, determining the number of bolts between the last-but-one-two-stage rotor single disk and the last-stage rotor single disk, enabling the last-stage rotor single disk to rotate for 1 step length which is spaced from the adjacent bolt of the last-stage rotor single disk, and enabling the last-one-last-stage rotor single disk to traverse one circle; and sequentially circulating until the second-stage rotor single disc rotates for one circle to form a feasible region.
Preferably, the reference selection rule of the rotor single disc is as follows: when only one bolt mounting edge is arranged, the set reference 1 and the set reference 2 are superposed, and the phase of any bolt hole is taken as the 0-degree reference of the single plate SP, theta Reference interval =0; when two bolt mounting edges are arranged, if the reference 1 is superposed with the reference 2, the phase of any bolt hole is taken as the 0-degree reference of the single-disc SP, theta Reference interval =0 °; if the reference 1 and the reference 2 do not coincide, the reference 1 phase is taken as the 0 degree reference of the single-disc SP, theta Reference interval =0 °; when three bolt mounting edges exist, one end of only one row of bolt mounting edges is taken as a base and is respectively combined with the two rows of bolt mounting edges at the other end to form 2 groups, and the reference 1 and the reference 2 are determined in each group according to the mode that two bolt mounting edges exist.
The method for improving the stacking optimization quality and the calculation speed of the rotor comprises the steps that the SP reference phase of each rotor single disc is set to be the same as the phase of a bolt hole of the rotor single disc, so that when the rotor single disc machine part rotates, the bolt or bolt hole is aligned exactly after transposition, nearby assembly is avoided, phase deviation can not be generated during assembly, meanwhile, the interval angle between the adjacent bolt holes of the rotor single disc is used as the step length, all phases of all the rotor single discs except the first stage and the last stage are traversed, the calculated quantity of SP is reduced greatly in the mode, all solutions smaller than the SP threshold are found through the SP threshold of a rotor assembly for AP calculation, the calculated quantity is further reduced, a group of optimal solutions with smaller SP and smaller AP can be found, and efficient optimization of a stacking optimization algorithm is achieved.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be understood that the drawings described below are merely exemplary of some embodiments of the application.
FIG. 1A is a schematic diagram of stack optimization algorithm single-piece coaxiality solution in the background art; FIG. 1B is a schematic diagram of a single-piece verticality solution of a stack optimization algorithm in the background art;
FIG. 2A is a schematic view of a rotor single-disk axial deviation structure in the prior art; FIG. 2B is a schematic view of a type II rotor single-disk axial deviation structure in the prior art; FIG. 2C is a schematic view of a second type of rotor single-disk axial deviation structure in the prior art;
FIG. 3 is a schematic overall flow chart of the present application;
FIG. 4 is a schematic diagram of selected structures of reference 1 and reference 2 of the present application;
FIG. 5 is a schematic diagram of a bolt hole constraint solution process in the machine part of the present application 4;
FIG. 6 is a schematic diagram of a calculation flow of an improved stack optimization algorithm according to the present application;
fig. 7 is a schematic diagram of AP calculation according to the present application.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.
A method for improving the optimized quality and the calculation speed of rotor stacking is provided, and the influence of the nearby assembly problem generated by mounting side bolts on the coaxiality of a rotor cannot be ignored in the conventional SPS-1000L system. Therefore, the invention increases the constraint of the connecting bolt between the single disks, ensures that the phase of the ergodic calculation can ensure that the single disk of the rotor can be directly installed, and does not need to be assembled nearby any more. In addition, when the phase of the first n-1 (n is the number of single disks of the rotor assembly) single disks of the rotor is known, the phase of the nth single disk SP is necessarily 180 degrees different from that of the first n-1 single disks SP, and the coaxiality of the rotor assembly is best. Therefore, the bolt hole constraint solution method is adopted for the 2 nd to the n-1 th single disks, the n-th single disk adopts the analytic method to obtain all feasible solutions, and the calculation amount is further reduced.
As shown in fig. 3, the method specifically includes the following steps:
step S100, obtaining basic information of algorithm
In order for the results of the stack optimization calculations to avoid near-fitting, specific constraints must be placed on the angles of the individual disks. Since the phase of the single disc SP is not necessarily exactly the bolt hole phase, the present invention sets the phase of the single disc SP with respect to the 0 ° reference to the bolt hole phase.
As shown in fig. 4, the specific design includes: determining the number of the rotor single discs to be assembled, setting the SP reference phase of each rotor single disc to be the same as the phase of a bolt hole of the rotor single disc, setting the reference phase of the front mounting edge of each rotor single disc as reference 1, setting the reference phase of the rear mounting edge of each rotor single disc as reference 2, determining reference 1 and reference 2 of each rotor single disc, determining the reference surface of each rotor single disc, and determining the adjacent reference interval theta of each rotor single disc Reference interval . In FIG. 3, when selecting the reference of the form (1), it is necessary to calculate or measure the phase of the interval as θ Reference interval Wherein A is reference 1 and B is reference 2, and when the reference of the form (2) is selected, θ Reference interval And =0. All rotor disks in the engine can be equivalently selected to be corresponding reference 1 and reference 2.
For single rotors with different forms, the number of the installation edges is different, the selection rule of the reference is also different, and the single rotors can be roughly divided into three types, specifically as follows:
when only one bolt mounting edge is arranged, the setting reference 1 and the setting reference 2 are superposed, and the phase of any bolt hole is taken as the 0-degree reference theta of the single disc SP Reference interval ＝0；
When two bolt mounting edges are arranged, if the reference 1 is superposed with the reference 2, the phase of any bolt hole is taken as the 0-degree reference of the single-disc SP, theta Reference interval =0 °; if the reference 1 and the reference 2 do not coincide, the reference 1 phase is taken as the 0 degree reference of the single-disc SP, theta Reference interval ＝0°；
When three bolt mounting edges exist, one end of only one row of bolt mounting edges is taken as a base and is respectively combined with the two rows of bolt mounting edges at the other end to form 2 groups, and the reference 1 and the reference 2 are determined in each group according to the mode that two bolt mounting edges exist.
Theta when reference 1 and reference 2 Reference interval And =0, the calculation efficiency is higher when SP calculation is performed. Theta when reference 1 and reference 2 Reference interval When the value is not 0, the reference error between reference 1 and reference 2 needs to be calculated, and the calculation efficiency is low when SP calculation is performed.
As the reference of each rotor unit is set on the bolt hole phase, the constraint of connecting bolts between the single rotor discs is increased, the phase of traversal calculation is ensured to enable the single rotor discs to be directly installed, and the close assembly is not needed.
Step S200, determining feasible regions
Namely: and determining the number of connecting bolts of each rotor single disc and the interval angle of adjacent bolt holes of the rotor single disc, and taking the interval angle of the adjacent bolt holes of the rotor single disc as a step length, so that after the next-stage rotor single disc machine member is rotated (the subsequent-stage disc rotates along with the rotor single disc), the bolts or bolt holes are aligned exactly after the rotor single disc machine member is rotated, and a constraint hole solution method is formed.
The constraint hole solution mode is that all phases of all rotor single disks except the first stage and the last stage are traversed, a feasible calculation domain is determined, and SP of all feasible schemes in the feasible calculation domain is calculated;
preferably, the specific method for forming the feasible domain is as follows:
aligning all rotor single disks according to a datum plane alignment rule, keeping a first-stage rotor single disk and a last-stage rotor single disk motionless, determining the number of bolts between a last-but-one-stage rotor single disk and the last-stage rotor single disk, enabling the last-but-one-stage rotor single disk to rotate for 1 step length of an angle between the last-stage rotor single disk and an adjacent bolt, analyzing and calculating the optimal installation phase of the last-stage rotor single disk, then enabling the last-but-one-stage rotor single disk to rotate for one step length again until the number of rotation times of the last-but-one-stage rotor single disk is the same as the number of bolts between the last-but-one-stage rotor single disk and the last-stage rotor single disk, enabling the last-but-one-two-stage rotor single disk to rotate for one circle, keeping the last-but-one-stage rotor single disk motionless, determining the number of bolts between the last-but-one-two-stage rotor single disk and the last-stage rotor single disk, enabling the last-but-one-stage rotor single disk to rotate for 1 step length of an angle between the bolt adjacent to rotate for one-last-stage rotor single disk, and traversing the last-stage rotor single disk; and sequentially circulating until the second-stage rotor single disc rotates for one circle to form a feasible region.
When the method is adopted to calculate the SP, the calculated amount is the multiplication of all the bolt numbers except the first-stage rotor single disc and the last-stage rotor single disc, so that the calculation times of the stacking optimization is reduced to N 2,1 N 3,2 …N n-1,n-2 (Ni, i-1 is the number of connecting bolts between the machine member i and the machine member i-1, n is the number of rotor machine members), compared with the calculated amount of the SPS-1000L system (360L) n-1 )。
For convenience of explaining the solution process of the improved bolt hole constraint method, 4 machine parts are taken as an example in the application, and the solution process is the same when the number of the machine parts is more and the traversal process of the improved stacking optimization method is shown in fig. 5. The 4 elements are designated in sequence "element 1", "element 2", "element 3" and "element 4". The number of bolts N2,1 for connecting the machine member 2 with the machine member 1, the number of bolts N3,2 for connecting the machine member 3 with the machine member 2, and the number of bolts N4,3 for connecting the machine member 4 with the machine member 3. The specific stacking optimization traversal process is shown in fig. 5. Setting the number of bolts N2,1=35, the number of bolts N3,2=36, and the number of times of SP calculation to 35 × 36=1260; the calculation amount of the SPS-1000L system is 360 3 The calculated amount difference of the work pieces of =46656000,4 is different by thousands of times, and the calculated amount difference of the work pieces of 7 is larger, so the calculated amount of the improved algorithm of the application is greatly reduced.
Step S300, calculating SP
Although theoretically, the coaxiality of the rotor assembly can be achieved to a small value (such as 0.000001 mm) according to the stacking optimization method, it is practically difficult to achieve the coaxiality of the rotor assembly to a theoretical calculation value due to the influence of assembly factors (such as a heating/cooling assembly mode, a bolt tightening mode and the like). Thus, excessive pursuit of the theoretical minimum concentricity has little practical significance to the quality of the rotor assembly. In addition, when the rotor assembly SP is minimized, AP is not necessarily minimized. For this, the algorithm is further optimized:
as shown in fig. 6, the specific calculation method is as follows: and setting an SP threshold of the rotor assembly, calculating solutions smaller than the SP threshold in all SPs, then performing AP calculation on the SP calculation solutions smaller than the SP threshold, and screening out the solution with the smallest AP as an optimal assembly phase.
The algorithm does not calculate SP exceeding an SP threshold value, so that the calculation amount is further reduced, and when the solution with the smallest AP is screened out as the optimal assembly phase, the SP is smaller, so that a group of optimal solutions with smaller SP and AP can be found under the algorithm, and the efficient optimization of the stack optimization algorithm is realized.
When calculating the AP, according to the stacking optimization principle, the optimal solution of the stacking optimization can only ensure that the final coaxiality of the rotor assembly is optimal, and the influence of the installation phase of the machine parts on the axial shape of the rotor assembly is not considered. When the machine parts are uniform in density, the centroid offset can directly reflect the unbalance of a single piece, and the initial unbalance of the rotor assembly can be directly influenced by the size of the single disc deviating from the rotor assembly.
Therefore, the present application screens out SP calculation solutions that are less than the SP threshold value, and then screens out all parts under the rotor system
And forming a series of vectors connected end to end, taking the SP midpoint value of each machine element as the influence of each machine element on the axle center AP of the rotor assembly, calculating the AP of each feasible scheme, and selecting the installation phase with the minimum AP as the optimal assembly phase.
As shown in fig. 7, the calculation formula of AP is:
in the formula:
x i ＝x i-1 +sp i cos(α i )
y i ＝y i-1 +sp i sin(α i )
α i is the phase, SP, of the machine member i relative to a 0 DEG reference plane of the machine member 1 i Is the SP value of the machine element i, x 0 ＝y 0 ＝0。
By calculating the AP and selecting the mounting phase with the minimum AP, the crankshaft form can be avoided, and the mass center of the rotor assembly is as close to the axis of the rotor as possible, so that the unbalance of the rotor is optimal.
This application is the same through a bolt hole phase place that sets up the SP benchmark phase place of every rotor single disk and this rotor single disk, thereby guarantee when rotating rotor single disk parts, bolt or bolt hole align certainly just after the transposition, thereby avoid assembling nearby, the assembly can not produce phase deviation, simultaneously use the adjacent bolt hole interval angle of this rotor single disk as the step length, traverse all phases to all rotor single disks except first order and last level, the calculated amount of SP reduces by a wide margin under this mode, and find all solutions that are less than the SP threshold value through the SP threshold value that sets up the rotor subassembly and carry out AP calculation, when the calculated amount further reduces, can find a set of optimal solution that SP and AP are all less, thereby realize piling up the high-efficient optimization of optimization algorithm.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (5)
1. A method of improving rotor stack optimization quality and computation speed, comprising:
determining the number of the rotor single discs to be assembled, setting the SP reference phase of each rotor single disc to be the same as the phase of a bolt hole of the rotor single disc, setting the reference phase of the front mounting edge of each rotor single disc as reference 1, setting the reference phase of the rear mounting edge of each rotor single disc as reference 2, determining reference 1 and reference 2 of each rotor single disc, determining the reference surface of each rotor single disc, and determining the adjacent reference interval theta of each rotor single disc Reference interval ；
Determining the number of connecting bolts of each rotor single disc and the interval angle of adjacent bolt holes of each rotor single disc, traversing all phases of all the rotor single discs except the first stage and the last stage by taking the interval angle of the adjacent bolt holes of each rotor single disc as a step length, determining a feasible region for calculation, and calculating SP of all feasible schemes in the feasible region;
and setting an SP threshold of the rotor assembly, calculating solutions smaller than the SP threshold in all SPs, then performing AP calculation on the SP calculation solutions smaller than the SP threshold, and screening out the solution with the smallest AP as an optimal assembly phase.
2. The method of improving rotor stack optimization quality and computation speed of claim 1, wherein: after screening out SP calculation solutions smaller than SP threshold, all parts under the rotor system are processed
And forming a series of vectors connected end to end, taking the SP midpoint value of each machine element as the influence of each machine element on the axle center AP of the rotor assembly, calculating the AP of each feasible scheme, and selecting the installation phase with the minimum AP as the optimal assembly phase.
3. The method for improving rotor stack optimization quality and computation speed of claim 2, wherein the AP is calculated by the formula:
in the formula:
x i ＝x i-1 +sp i cos(α i )
y i ＝y i-1 +sp i sin(α i )
α i phase of SP of machine part i relative to 0 DEG reference plane of machine part 1, SP i Is the SP value of the machine element i, x 0 ＝y 0 ＝0。
4. The method for improving rotor stack optimization quality and computation speed of claim 1, wherein the feasible region is formed by the following specific method:
aligning all rotor single disks according to a datum plane alignment rule, keeping a first-stage rotor single disk and a last-stage rotor single disk still, determining the number of bolts between a last-but-one-stage rotor single disk and the last-stage rotor single disk, enabling the last-but-one-stage rotor single disk to rotate for 1 step length which is spaced from the last-stage rotor single disk by an adjacent bolt, analytically calculating the optimal installation phase of the last-stage rotor single disk, then enabling the last-but-one-stage rotor single disk to rotate for one step length again until the rotation frequency of the last-but-one-stage rotor single disk is the same as the number of bolts between the last-but-one-stage rotor single disk and the last-stage rotor single disk, enabling the last-but-one-second-stage rotor single disk to rotate for one circle, keeping the last-stage rotor single disk still, determining the number of bolts between the last-but-one-two-stage rotor single disk and the last-stage rotor single disk, enabling the last-stage rotor single disk to rotate for 1 step length which is spaced from the adjacent bolt of the last-stage rotor single disk, and enabling the last-one-last-stage rotor single disk to traverse one circle; and sequentially circulating until the second-stage rotor single disc rotates for one circle to form a feasible region.
5. The method for improving rotor stack optimization quality and computation speed of claim 1, wherein the reference selection rule for a single rotor disk is:
when only one bolt mounting edge is arranged, the setting reference 1 and the setting reference 2 are superposed, and the phase of any bolt hole is taken as the 0-degree reference theta of the single disc SP Reference interval ＝0；
When two bolt mounting edges are arranged, if the reference 1 is superposed with the reference 2, the phase of any bolt hole is taken as the 0-degree reference of the single-disc SP, theta Reference interval =0 °; if the reference 1 and the reference 2 do not coincide, the reference 1 phase is taken as the 0 degree reference of the single-disc SP, theta Reference interval ＝0°；
When three bolt mounting edges exist, one end of only one row of bolt mounting edges is taken as a base and is respectively combined with the two rows of bolt mounting edges at the other end to form 2 groups, and the reference 1 and the reference 2 are determined in each group according to the mode that two bolt mounting edges exist.
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR100873663B1 (en) * | 2007-08-22 | 2008-12-12 | 한국기계연구원 | Laminating method of multistage rotor joining to tie-bolt |
| US20180152064A1 (en) * | 2015-08-21 | 2018-05-31 | Asmo Co., Ltd. | Motor, motor control method and motor control device |
| CN110207644A (en) * | 2018-02-28 | 2019-09-06 | 中国航发商用航空发动机有限责任公司 | Rotor disk stacks assembly method and device |
| CN111384828A (en) * | 2018-12-27 | 2020-07-07 | 中国航发商用航空发动机有限责任公司 | Method for optimizing rotor assembly |
| CN114996917A (en) * | 2022-05-17 | 2022-09-02 | 江苏大学 | Single-disc crack rotor dynamic characteristic evaluation method based on similarity theory |
-
2022
- 2022-11-02 CN CN202211363297.9A patent/CN115828446B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR100873663B1 (en) * | 2007-08-22 | 2008-12-12 | 한국기계연구원 | Laminating method of multistage rotor joining to tie-bolt |
| US20180152064A1 (en) * | 2015-08-21 | 2018-05-31 | Asmo Co., Ltd. | Motor, motor control method and motor control device |
| CN110207644A (en) * | 2018-02-28 | 2019-09-06 | 中国航发商用航空发动机有限责任公司 | Rotor disk stacks assembly method and device |
| CN111384828A (en) * | 2018-12-27 | 2020-07-07 | 中国航发商用航空发动机有限责任公司 | Method for optimizing rotor assembly |
| CN114996917A (en) * | 2022-05-17 | 2022-09-02 | 江苏大学 | Single-disc crack rotor dynamic characteristic evaluation method based on similarity theory |
Non-Patent Citations (1)
| Title |
|---|
| 琚奕鹏;吴法勇;金彬;魏秀鹏;祖建国;: "基于转子跳动和初始不平衡量优化的多级盘转子结构装配工艺", 航空发动机, no. 06 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117277706A (en) * | 2023-11-23 | 2023-12-22 | 四川普什宁江机床有限公司 | Phase difference eliminating method for double-moment motor |
| CN117277706B (en) * | 2023-11-23 | 2024-02-23 | 四川普什宁江机床有限公司 | Phase difference eliminating method for double-moment motor |
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