Method for calculating and controlling concentricity of aero-engine bolt flange rotor connection structure

Abstract

The application discloses a concentricity calculation and control method of an aero-engine bolt flange rotor connecting structure, and can realize the concentricity calculation under the condition of double-layer and multi-layer flange connection. Firstly, the connecting form of the rotor, the rotor part series, the flange layer, the centering mode of the connecting structure and the fastening method are confirmed. Secondly, a coordinate system with the center of the ball bearing as the coordinate origin O is defined, and X, Y and Z directions are defined. Then, necessary dimensions and geometric position tolerances of the parts are obtained. The part offset is calculated according to the geometric relationship, and finally the rotor concentricity is calculated through a formula. If the calculated rotor concentricity is too large in the design, the size and tolerance can be adjusted to control the rotor concentricity. In the assembly, the geometric position tolerances of each rotor are measured, the angular position is analyzed, and the rotor concentricity is controlled to be at a minimum value through the misalignment assembly and stacking optimization technology.

Description

Technical Field

[0001] The invention belongs to the technical field of aero-engines, and in particular relates to a method for calculating and controlling the concentricity of a bolt flange rotor connection structure of an aero-engine. Background Art

[0002] Bolted flange connections are one of the most widely used and common connection structures in aircraft engine design. Modern aircraft engines often utilize a dual-rotor structure, characterized by rolling bearings, multi-stage rotor blades, complex excitation frequencies, and harsh operating environments. With the continuous advancement of modern aircraft engine technology, high-thrust and high-thrust-to-weight ratio aircraft engines are becoming increasingly common, becoming an inevitable trend in aircraft engine development. Due to limitations in machining processes, bolted connections remain the most widely used rotor connection. Bolted connections offer advantages such as simple structure, strong operability, easy installation, and good connection rigidity.

[0003] The bolted flange rotor connection structure is a discontinuous structure. Theoretically, the center of the rotor component is a straight line coinciding with the rotating axis. In reality, due to the existence of dimensional tolerances and form and position tolerances of the connection structure, the center line of the actual rotor is offset from the theoretical center line, that is, the concentricity of the rotor is not zero.

[0004] Due to the unique structural characteristics of aircraft engine rotors, large concentricity deviations can lead to deflection or bending of the rotor axis. Furthermore, the centroid deviation causes a large eccentricity of the center of mass, resulting in large rotor imbalance. These consequences can cause vibration in the aircraft engine rotor system during operation, impacting its stability.

[0005] Therefore, studying the calculation and control methods of the concentricity of the bolt flange rotor connection structure of an aero-engine, analyzing the rotor concentricity in advance, and optimizing the connection structure are of great significance and application value in reducing the vibration of the entire aero-engine and ensuring the stable operation of the engine. Summary of the Invention

[0006] In order to overcome the shortcomings of the prior art, the present invention provides a method for calculating and controlling the concentricity of an aircraft engine bolt flange rotor connection structure, which can realize the concentricity calculation in the case of double-layer and multi-layer flange connections. First, confirm the connection form of the rotor, the number of rotor parts, the number of flange layers, the centering method of the connection structure, and the fastening method. Secondly, define a coordinate system with the center of the ball bearing as the coordinate origin O, and define the X, Y, and Z directions. Then obtain the necessary dimensions and form and position tolerances of the parts. Calculate the part offset based on the geometric relationship, and finally calculate the rotor concentricity through a formula. If the calculated rotor concentricity is too large during design, the size and tolerance can be adjusted to control the rotor concentricity. During assembly, measure the form and position tolerance of each rotor, analyze the angular position, and control the rotor concentricity to the minimum value through staggered assembly and stacking optimization technology.

[0007] The technical solutions adopted by the present invention to solve the technical problems are as follows:

[0008] Step 1: Assume that the theoretical center of the front bearing is the coordinate origin O, the theoretical centerline of the rotor is the X-axis, the direction of the rear bearing is the positive direction of the X-axis, and the vertical upward direction is the positive direction of the Z-axis. Determine the direction of the Y-axis using the right-hand rule; L is the axial distance between the front and rear end faces of the part, D is the diameter of the part end face, u is the concentricity of the end face of a single rotor part relative to the reference plane, and t is the parallelism of a single rotor part relative to the reference end face; L, D, u, and t are part design values ​​during the design phase and are measured values ​​after the part is machined;

[0009] Step 2: After the rotors at all levels are assembled, the concentricity of the entire rotor deviates from the theoretical center coordinate origin O due to the superposition and accumulation of form and position tolerances u and t, resulting in concentricity eccentricity. The rotor concentricity calculation method is as follows:

[0010] g i =L i *sinb i

[0011] b i =a i-1

[0012] sina i-1 =t i-1 / D i-1

[0013] g i =L i *t i-1 / D i-1

[0014] g i Convert to XY coordinate system as G i =L i *t i-1 / D i-1 +k i-1

[0015] u i Convert to XY coordinate system as U i =u i +k i-1

[0016] H i =k i-1 *(1+L i / (L1+L2+…+L i-1 ))

[0017] k i =G i +H i +U i

[0018] k i =k i-1 *(3+L i / (L1+L2+…+L i-1 ))+L i *t i-1 / D i-1 +u i

[0019] The variables are defined as follows:

[0020] a i-1 - The angle between the rear end face and the front end face of the i-1th rotor caused by the parallelism deviation of the rear end face of the i-1th rotor after the rotors are stacked and assembled;

[0021] b i -The angle between the centerline of the i-th rotor and the theoretical centerline caused by the parallelism deviation of the rear end face of the i-1-th rotor after the rotors are stacked and assembled;

[0022] g i -After the rotors are assembled, the rear end face of the i-1th rotor is parallel to the center of its front end face, causing the deviation of the rear end face of the i-1th rotor to be parallel to the center of its front end face, i Concentricity;

[0023] k i - After the rotors are assembled, the concentricity of the rear end face of the i-th rotor relative to the initial reference center O of the entire rotor;

[0024] k i-1 - After the rotors are stacked and assembled, the concentricity of the rear end surface of the i-1th rotor relative to the initial reference center O of the entire rotor;

[0025] u i - the concentricity of the rear end face of the i-th rotor relative to its front end face reference;

[0026] ti-1 - Parallelism of the rear end face of the i-1th rotor relative to the front end face reference;

[0027] L i -The axial distance between the front and rear end faces of the i-th rotor;

[0028] D i-1 -The diameter of the end face of the i-1th rotor;

[0029] G i -G i Convert to YOZ coordinate system and convert to concentricity relative to O;

[0030] H i - After the rotors are assembled, the concentricity of the rear end face of the i-th rotor relative to the initial reference center O of the entire rotor caused by the concentricity deviation of the previous rotor;

[0031] U i -will u i Convert to YOZ coordinate system and convert to concentricity relative to O;

[0032] Step 3: When u i , t i , L i 、D i When k is the design value, the obtained k i is the maximum value;

[0033] Step 4: When u i , t i , L i 、D i When it is the measured value after the part is processed, u i and t i It is possible that they are not in the same phase limit or at different angular positions; u i and t i is a vector parameter, rotor concentricity k i About U i and t i The vector sum formula of ;

[0034] When u i and t i At the same phase angle, concentricity |k i | Maximum; Concentricity at opposite phase angles 180° apart |k i |Minimum.

[0035] Preferably, the rotor is designed by calculating the rotor concentricity k i , judge the rotor concentricity k i The influence on rotor dynamics and rotor stability, if the concentricity k iIf it is greater than the set value, the size and tolerance can be adjusted to reduce the concentricity.

[0036] Preferably, the rotor is composed of a multi-stage compressor and turbine rotor, each stage of the rotor is connected by a bolt flange and centered by a stop; the rotor is composed of a compressor rotor front journal, a compressor first-stage rotor, a compressor second-stage rotor, a compressor third- and fourth-stage rotor, a compressor fifth-stage rotor, a compressor rotor rear journal, a turbine rotor, and a turbine rotor rear journal;

[0037] The entire rotor is supported on ball bearings and roller bearings;

[0038] The rotors at each stage are connected by bolt flanges, fastened by bolts and nuts, centered by the flange stop, and the centering cylindrical surface adopts an interference fit; the front shaft neck of the compressor rotor and the compressor first-stage rotor are connected by two flanges and bolts and nuts, centered by the stop on the flange mating surface, and the stop adopts an interference fit; the compressor rotor, the compressor first-stage rotor, the compressor second-stage rotor, and the compressor third and fourth-stage rotors are connected by three layers of flanges, fastened by bolts and nuts, centered by the stop on the mating surface of the flange, and the stop adopts an interference fit;

[0039] The third and fourth stage compressor rotors are two integrally connected rotors; the second stage compressor rotor is a structure with flange edges and bolt holes on the spoke plate, and has two stoppers; the third and fourth stage compressor rotors, the fifth stage compressor rotor, and the rear shaft journal of the compressor rotor are connected through three layers of flanges, fastened with bolts and nuts, and centered by the stoppers on the mating surfaces of the flanges, which adopt an interference fit;

[0040] The five-stage compressor rotor is a structure with flange edges and bolt holes on the spoke plate, and has two stoppers; the rear shaft neck of the compressor rotor is connected to the turbine rotor through two layers of flanges, fastened by bolts and nuts, and centered by the stoppers on the mating surfaces of the flanges, and the stoppers adopt an interference fit; the turbine rotor is connected to the rear shaft neck of the turbine rotor through two layers of flanges, fastened by bolts and nuts, and centered by the stoppers on the mating surfaces of the flanges, and the stoppers adopt an interference fit.

[0041] A computer program causes a computer to execute the above-mentioned concentricity calculation and control method.

[0042] An electronic device comprises: a processor and a memory; the memory is used to store a computer program, and the processor is used to execute the computer program stored in the memory, so that the electronic device performs the above-mentioned concentricity calculation and control method.

[0043] A computer-readable storage medium stores a computer program, which implements the above-mentioned concentricity calculation and control method when executed by a processor.

[0044] A chip includes: a processor for calling and running a computer program from a memory, so that a device equipped with the chip executes the above-mentioned concentricity calculation and control method.

[0045] A computer program product includes a computer storage medium storing a computer program, wherein the computer program includes instructions executable by at least one processor, and when the instructions are executed by the at least one processor, the above-mentioned concentricity calculation and control method is implemented.

[0046] The beneficial effects of the present invention are as follows:

[0047] First, the present invention can evaluate the concentricity of the rotor during the design phase and, based on the calculated concentricity, rationally allocate the dimensional tolerances of the parts. This eliminates the need to wait until after processing and assembly to discover that the concentricity is not appropriate and then re-adjust the parts. This shortens the cycle time and improves economic benefits. Secondly, by rationally allocating the dimensional tolerances of the parts, it is no longer necessary to pursue the highest level of design and processing for each part, thus reducing processing costs and increasing profits. Finally, during the assembly phase, this method can provide a theoretical basis for staggered assembly, offering support and guidance for assembly work and shortening the assembly cycle. BRIEF DESCRIPTION OF THE DRAWINGS

[0048] Figure 1 This is a schematic diagram of the rotor connection structure of the present invention;

[0049] Figure 2 This is a schematic diagram of the rotor non-concentricity of the rotor connection structure of the present invention;

[0050] Figure 3 Schematic diagram showing the effect of the parallelism of the rear end surface of the i-1th rotor on the concentricity of the i-th rotor according to the present invention;

[0051] Figure 4 Schematic diagram of the concentricity of the rear end face of the i-th rotor relative to the front end face reference of the present invention;

[0052] Figure 5 Schematic diagram of the concentricity of the rear end face of the i-th rotor relative to the initial reference center O of the entire rotor caused by the concentricity deviation of the previous rotor in the present invention;

[0053] Figure 6 Schematic diagram of the concentricity of the rear end face of the i-th rotor relative to the initial reference center O after superposition of various factors;

[0054] Figure 7 It is a schematic diagram of the form and position tolerance of each part of the present invention.

[0055] Description of reference numerals:

[0056] 1 ball bearing, 2 compressor rotor front journal, 2-1 compressor rotor front journal flange, 3 compressor first stage rotor, 3-1 compressor first stage rotor front flange, 3-2 rotor front journal and first stage rotor connection bolts and nuts, 3-3 compressor first stage rotor rear flange, 4 compressor second stage rotor, 4-1 compressor second stage rotor spoke flange, 5 compressor third and fourth stage rotors, 5-1 compressor third and fourth stage rotor front flange, 5-2 compressor first, second, third and fourth stage rotor connection bolts and nuts, 5-3 compressor third and fourth stage rotor rear flange, 6 compressor fifth stage rotor, 6 -1 compressor fifth-stage rotor spoke flange, 7 compressor rotor rear shaft neck, 7-1 compressor rotor rear shaft neck front flange, 7-2 compressor third, fourth, and fifth-stage rotors and rear shaft neck connecting bolts and nuts, 7-3 compressor rotor rear shaft neck rear flange, 8 turbine rotor, 8-1 turbine rotor front flange, 8-2 compressor rotor rear shaft neck and turbine rotor front flange connecting bolts and nuts, 8-3 turbine rotor rear flange, 8-4 turbine rotor rear flange and turbine rotor rear shaft neck connecting bolts and nuts, 9 turbine rotor rear shaft neck, 10 roller bearing, 11 rotor centerline. DETAILED DESCRIPTION

[0057] The present invention will be further described below with reference to the accompanying drawings and examples.

[0058] The purpose of the present invention is to provide a method for calculating and controlling the concentricity of an aircraft engine bolt flange rotor connection structure, which can realize the calculation and control of the rotor concentricity at the beginning of aircraft engine design and provide support for structural optimization design; it also provides an optimization basis for controlling the rotor concentricity during aircraft engine rotor assembly.

[0059] The technical solution adopted by the present invention to solve its technical problems is:

[0060] A method for calculating and controlling the concentricity of a bolted flange rotor connection structure for an aircraft engine is disclosed. The rotor comprises a multi-stage compressor and turbine rotor, each stage of which is connected via a bolted flange and centered via a stop. The method is characterized in that the rotor comprises a compressor rotor front journal, a compressor first-stage rotor, a compressor second-stage rotor, compressor third- and fourth-stage rotors, a compressor fifth-stage rotor, a compressor rotor rear journal, a turbine rotor, and a turbine rotor rear journal.

[0061] The entire rotor is supported on ball and roller bearings.

[0062] Each rotor stage is connected via bolted flanges, secured with bolts and nuts, and centered using flange stoppers. The centering cylinder utilizes an interference fit. The front shaft journal of the compressor rotor is connected to the first-stage compressor rotor via two flanges and bolts and nuts. The stoppers are centered using the stoppers on the flange mating surfaces, which utilize an interference fit. The first-stage compressor rotor, the second-stage compressor rotor, and the third- and fourth-stage compressor rotors are connected via three layers of flanges, secured with bolts and nuts, and centered using the stoppers on the flange mating surfaces, which utilize an interference fit. The third- and fourth-stage compressor rotors are integrally connected, while the second-stage compressor rotor features flange edges and bolt holes on the spokes, along with two stoppers. The third- and fourth-stage compressor rotors, the fifth-stage compressor rotor, and the rear shaft journal of the compressor rotor are connected via three layers of flanges, secured with bolts and nuts, and centered using the stoppers on the flange mating surfaces, which utilize an interference fit. The five-stage compressor rotor features a flanged, bolt-hole-enclosed spoke with two stoppers. The compressor rotor's rear journal is connected to the turbine rotor via two flanges, secured with bolts and nuts. The stoppers are centered on the flange's mating surfaces, employing an interference fit. The turbine rotor is also connected to the turbine rotor's rear journal via two flanges, secured with bolts and nuts. The stoppers are centered on the flange's mating surfaces, employing an interference fit.

[0063] Assume that the theoretical center of the front bearing is the coordinate origin O, the theoretical center line of the rotor is the X-axis, the direction of the rear bearing is the positive direction of the X-axis, the vertical upward direction is the positive direction of the Z-axis, and the Y-axis direction is determined by the right-hand rule.

[0064] L is the axial distance between the front and rear end faces of the part, D is the diameter of the part end face, u is the concentricity of the end face of a single rotor part relative to the reference plane, and t is the parallelism of a single rotor part relative to the reference end face. L, D, u, and t are design values ​​during the design phase and can be measured after the part is manufactured.

[0065] After the rotors at all levels are assembled, the concentricity of the entire rotor deviates from the theoretical center coordinate origin O due to the superposition and accumulation of form and position tolerances u and t, resulting in concentricity eccentricity. Figure 3 、 Figure 4 、 Figure 5 This is the eccentricity principle diagram. The rotor concentricity calculation method is as follows:

[0066] g i =L i *sinb i

[0067] b i =a i-1

[0068] sina i-1 =t i-1 / D i-1

[0069] g i =L i *t i-1 / D i-1

[0070] g i Convert to XY coordinate system as G i =L i *t i-1 / D i-1 +k i-1

[0071] u i Convert to XY coordinate system as U i =u i +k i-1

[0072] H i =k i-1 *(1+L i / (L1+L2+…+L i-1 ))

[0073] k i =G i +H i +U i

[0074] k i =k i-1 *(3+L i / (L1+L2+…+L i-1 ))+L i *t i-1 / D i-1 +u i

[0075] Among them, u i , t i , L i 、D i It is a known value, which can be the geometric tolerance given during design or the measured value after processing.

[0076] When u i , t i , L i 、D i When k is the design value, the obtained k i is the maximum value. i , t i , L i 、D i When it is the measured value after the part is processed, u i and t i It is possible that they are not in the same phase limit, different angular positions, u i and ti is a vector parameter. Rotor concentricity k i About U i and t i The vector and formula of .

[0077] When u i and t i At the same phase angle, concentricity |k i |Max. Concentricity at opposite phase angles 180°|k i |Minimum.

[0078] When designing the rotor, the rotor concentricity k is calculated. i , judge its influence on rotor dynamics and rotor stability, if the concentricity k i If it is too large, the size and tolerance can be adjusted to reduce the concentricity.

[0079] During rotor assembly, due to the bolted flange connection, the rotor offset assembly angle is limited by the bolt hole spacing and angle, making it difficult to ensure that all parts are 180° in opposite phase within their form and position tolerances. This can only be achieved by measuring and analyzing the form and position tolerances and angular position of each rotor in advance, and using offset assembly and stacking optimization techniques to ensure rotor concentricity as much as possible. i |The value is minimized, thereby reducing the vibration of the entire aircraft engine.

[0080] By accumulating the actual dimensions after machining and the concentricity dimensions after actual assembly, we can calculate the relationship between the actual concentricity and the maximum concentricity calculated during the design phase, and obtain the corresponding probability coefficient. During the design phase, we can apply the probability coefficient to calculate the probability value of concentricity, thereby obtaining a value closer to reality.

[0081] When the number of parts making up the entire rotor changes, the above rotor concentricity calculation formula and control method are still applicable.

[0082] Example:

[0083] An aircraft engine bolted flange rotor connection structure consists of a multi-stage compressor and turbine rotor. The rotors between each stage are connected by bolted flanges and centered by stoppers. The rotors consist of a compressor rotor front journal 2, a compressor stage 1 rotor 3, a compressor stage 2 rotor 4, compressor stage 3 and 4 rotors 5, a compressor stage 5 rotor 6, a compressor rotor rear journal 7, a turbine rotor 8, and a turbine rotor rear journal 9. The entire rotor is supported by two bearings: a ball bearing 1 and a roller bearing 10.

[0084] Each rotor stage is connected via bolted flanges, secured with bolts and nuts, and centered via flange stoppers, with an interference fit on the centering cylinder. The compressor rotor front journal 2 is connected to the compressor stage 1 rotor 3 via two flanges 2-1 and 3-1, as well as bolts and nuts 3-2. The stoppers are centered via the mating surfaces of flanges 2-1 and 3-1, with an interference fit. The compressor rotors, the compressor stage 1 rotor 3, the compressor stage 2 rotor 4, and the compressor stage 3 and 4 rotors 5, are connected via three layers of flanges 3-3, 4-1, and 5-1, secured with bolts and nuts 5-2, and centered via the stoppers on the mating surfaces of flanges 3-3, 4-1, and 5-1, with an interference fit. The compressor stage 3 and 4 rotors 5 are integral rotors connected in two stages; the compressor stage 2 rotor 4 is a structure with flange edges and bolt holes on the spoke plate, and has two stoppers. The compressor stage 3 and 4 rotors 5, the compressor stage 5 rotor 6, and the compressor rotor rear journal 7 are connected via three flanges 5-3, 6-1, and 7-1, secured by bolts and nuts 7-2. The flanges 5-3, 6-1, and 7-1 are used for centering, and the flanges 6-1 and 7-1 have an interference fit. The compressor stage 5 rotor 6 has a flanged plate with bolt holes and two flanges. The compressor rotor rear journal 7 is connected to the turbine rotor 8 via two flanges 7-3 and 8-1, secured by bolts and nuts 8-2, and the flanges 7-3 and 8-1 have an interference fit for centering. The turbine rotor 8 is connected to the turbine rotor rear journal 9 via two flanges 8-3 and 9-1, secured by bolts and nuts 8-4, and the flanges 8-3 and 9-1 have an interference fit for centering.

[0085] Determine the rotor's coordinate system, assuming the theoretical center of the front bearing as the coordinate origin, O, the theoretical centerline of the rotor as the X-axis, the direction of the rear bearing as the positive X-axis, and the vertically upward direction as the positive Z-axis. Use the right-hand rule to determine the Y-axis direction. Let L be the axial distance between the front and rear end faces of a single rotor component, D be the diameter of the end face of a single rotor component, u be the concentricity of the end face of a single rotor component relative to the reference end face, and t be the parallelism of a single rotor component relative to the reference end face. L, D, u, and t are part design values ​​during the design phase and can be measured values ​​after part processing.

[0086] After the rotors at all levels are assembled, the concentricity of the entire rotor deviates from the theoretical center due to the superposition and accumulation of form and position tolerances u and t, resulting in concentricity eccentricity. Figure 3 、 Figure 4 、 Figure 5 This is the eccentricity principle diagram. The rotor concentricity calculation method is as follows:

[0087] g i =L i *sinb i

[0088] bi =a i-1

[0089] sina i-1 =t i-1 / D i-1

[0090] g i =L i *t i-1 / D i-1

[0091] g i Convert to XY coordinate system as G i =L i *t i-1 / D i-1 +k i-1

[0092] u i Convert to XY coordinate system as U i =u i +k i-1

[0093] H i =k i-1 *(1+L i / (L1+L2+…+L i-1 ))

[0094] k i =G i +H i +U i

[0095] k i =k i-1 *(3+L i / (L1+L2+…+L i-1 ))+L i *t i-1 / D i-1 +u i

[0096] When u i , t i , L i 、D i When k is the design value, the obtained k i is the maximum value. i , t i , L i 、D i When it is the measured value after the part is processed, u i and t i It is possible that they are not in the same phase limit, different angular positions, u i and ti is a vector parameter. Rotor concentricity k i About U i and t i The vector sum formula. When u i and t i At the same phase angle, concentricity |k i |Max. Concentricity at opposite phase angles 180°|k i |Minimum.

[0097] When the rotor is designed, the rotor concentricity k is calculated. i , judge its influence on rotor dynamics and rotor stability, if the concentricity k i If it is too large, the concentricity can be controlled by adjusting the size, tolerance or structure.

[0098] When assembling the rotor, the shape and position tolerances of each rotor should be measured in advance, the angular position should be analyzed, and the rotor concentricity should be ensured through staggered assembly and stacking optimization technology. i | value is minimal. During rotor assembly, due to the bolted flange connection structure, the rotor offset assembly angle is limited by the bolt hole spacing and angle, making it difficult to ensure that all components are 180° opposite in phase within their form and position tolerances. This can only be achieved by measuring and analyzing the form and position tolerances and angular position of each rotor in advance, and using offset assembly and stacking optimization techniques to ensure rotor concentricity |k as much as possible. i |The value is minimized, thereby reducing the vibration of the entire aircraft engine.

[0099] By accumulating the actual dimensions after machining and the concentricity dimensions after actual assembly, we can calculate the relationship between the actual concentricity and the maximum concentricity calculated during the design phase, and obtain the corresponding probability coefficient. During the design phase, we can apply the probability coefficient to calculate the probability value of concentricity, thereby obtaining a value closer to reality.

[0100] The rotor shown in the present invention comprises 8 parts, and the size tolerances of each part are shown in Figure 7 The specific calculation process is as follows:

[0101] 1) k1 = u1

[0102] t1=0

[0103] 2) G2 = L2 * t1 / D1 + u1 = u1

[0104] U2=u2+u1

[0105] H2=k1*(1+L2 / L1)

[0106] k2=G i +H i +U i

[0107] k2=u1*(3+L2 / L1)+u2

[0108] 3)k3=k2*(3+L3 / (L1+L2))+L3*t2 / D2+u3

[0109] k3=(u1*(3+L2 / L1)+u2)*(3+L3 / (L1+L2))+L3*t2 / D2+u3

[0110] …

[0111] 8) k8 = G8 + H8 + U8

[0112] k8=k7*(3+L8 / (L1+L2+…+L7))+L8*t7 / D7+u8

[0113] When the number of parts constituting the entire rotor is not equal to 8 but is other numbers, the calculation method is the same as that in the above embodiment.

Claims

1. A method for calculating and controlling the concentricity of an aircraft engine bolt flange rotor connection structure, characterized in that: The steps include: Step 1: Assume that the theoretical center of the front bearing is the coordinate origin O, the theoretical centerline of the rotor is the X-axis, the direction of the rear bearing is the positive direction of the X-axis, and the vertical upward direction is the positive direction of the Z-axis. Determine the direction of the Y-axis using the right-hand rule; L is the axial distance between the front and rear end faces of the part, D is the diameter of the part end face, u is the concentricity of the end face of a single rotor part relative to the reference plane, and t is the parallelism of a single rotor part relative to the reference end face; L, D, u, and t are part design values ​​during the design phase and are measured values ​​after the part is machined; Step 2: After the rotors at all levels are assembled, due to the shape and position tolerance u u and t t The cumulative superposition of the entire rotor concentricity deviates from the theoretical center coordinate origin O, forming concentricity eccentricity. The rotor concentricity calculation method is as follows: g i =L i *symbol i b i =a i-1 that i-1 =t i-1 / D i-1 g i =L i *t i-1 / D i-1 g i Convert to XY coordinate system as G i =L i *t i-1 / D i-1 +k i-1 u i Convert to XY coordinate system as U i =u i +k i-1 H i =k i-1 *(1+L i / (L1+L2+…+L i-1 )) k i =G i +H i +U i k i =k i-1 *(3+L i / (L1+L2+…+L i-1 ))+L i *t i-1 / D i-1 +u i The variables are defined as follows: a i-1 - The angle between the rear end face and the front end face of the i-1th rotor caused by the parallelism deviation of the rear end face of the i-1th rotor after the rotors are stacked and assembled; b i -The angle between the centerline of the i-th rotor and the theoretical centerline caused by the parallelism deviation of the rear end face of the i-1-th rotor after the rotors are stacked and assembled; g i -After the rotors are assembled, the rear end face of the i-1th rotor is parallel to the center of its front end face, causing the deviation of the rear end face of the i-1th rotor to be parallel to the center of its front end face, i Concentricity; k i - After the rotors are assembled, the concentricity of the rear end face of the i-th rotor relative to the initial reference center O of the entire rotor; k i-1 - After the rotors are stacked and assembled, the concentricity of the rear end surface of the i-1th rotor relative to the initial reference center O of the entire rotor; u i - the concentricity of the rear end face of the i-th rotor relative to its front end face reference; t i-1 - Parallelism of the rear end face of the i-1th rotor relative to the front end face reference; L i -The axial distance between the front and rear end faces of the i-th rotor; D i-1 -The diameter of the end face of the i-1th rotor; G i -G i Convert to YOZ coordinate system and convert to concentricity relative to O; H i - After the rotors are assembled, the concentricity of the rear end face of the i-th rotor relative to the initial reference center O of the entire rotor caused by the concentricity deviation of the previous rotor; U i -will u i Convert to YOZ coordinate system and convert to concentricity relative to O; Step 3: When u i , t i , L i 、D i When k is the design value, the obtained k i is the maximum value; Step 4: When u i , t i , L i 、D i When it is the measured value after the part is processed, u i and t i It is possible that they are not in the same phase limit or at different angular positions; u i and t i is a vector parameter, rotor concentricity k i About U i and t i The vector sum formula of ; When u i and t i At the same phase angle, concentricity |k i | Maximum; Concentricity at opposite phase angles 180° apart |k i |Minimum.

2. The method for calculating and controlling the concentricity of an aircraft engine bolt flange rotor connection structure according to claim 1, characterized in that: The rotor is designed by calculating the rotor concentricity k i , judge the rotor concentricity k i The influence on rotor dynamics and rotor stability, if the concentricity k i If it is greater than the set value, the size and tolerance can be adjusted to reduce the concentricity.

3. The method for calculating and controlling the concentricity of an aircraft engine bolt flange rotor connection structure according to claim 1, characterized in that: The rotor is composed of a multi-stage compressor and turbine rotor, each stage of the rotor is connected by a bolt flange and centered by a stopper; the rotor is composed of a compressor rotor front journal, a compressor first-stage rotor, a compressor second-stage rotor, a compressor third- and fourth-stage rotor, a compressor fifth-stage rotor, a compressor rotor rear journal, a turbine rotor, and a turbine rotor rear journal; The entire rotor is supported on ball bearings and roller bearings; The rotors at each stage are connected by bolt flanges, fastened by bolts and nuts, centered by the flange stop, and the centering cylindrical surface adopts an interference fit; the front shaft neck of the compressor rotor and the compressor first-stage rotor are connected by two flanges and bolts and nuts, centered by the stop on the flange mating surface, and the stop adopts an interference fit; the compressor rotor, the compressor first-stage rotor, the compressor second-stage rotor, and the compressor third and fourth-stage rotors are connected by three layers of flanges, fastened by bolts and nuts, centered by the stop on the mating surface of the flange, and the stop adopts an interference fit; The third and fourth stage compressor rotors are two integrally connected rotors; the second stage compressor rotor is a structure with flange edges and bolt holes on the spoke plate, and has two stoppers; the third and fourth stage compressor rotors, the fifth stage compressor rotor, and the rear shaft journal of the compressor rotor are connected through three layers of flanges, fastened with bolts and nuts, and centered by the stoppers on the mating surfaces of the flanges, which adopt an interference fit; The five-stage compressor rotor is a structure with flange edges and bolt holes on the spoke plate, and has two stoppers; the rear shaft neck of the compressor rotor is connected to the turbine rotor through two layers of flanges, fastened by bolts and nuts, and centered by the stoppers on the mating surfaces of the flanges, and the stoppers adopt an interference fit; the turbine rotor is connected to the rear shaft neck of the turbine rotor through two layers of flanges, fastened by bolts and nuts, and centered by the stoppers on the mating surfaces of the flanges, and the stoppers adopt an interference fit.

4. An electronic device, characterized in that: include: processor and memory; The memory is used to store a computer program, and the processor is used to execute the computer program stored in the memory, so that the electronic device performs the method according to any one of claims 1 to 3.

5. A computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by a processor, the method according to any one of claims 1 to 3 is implemented.

6. A chip, characterized in that: include: A processor, configured to call and run a computer program from a memory, so that a device equipped with the chip executes the method according to any one of claims 1 to 3.

7. A computer program product, characterized in that The computer program product comprises a computer storage medium storing a computer program, wherein the computer program comprises instructions executable by at least one processor, and when the instructions are executed by the at least one processor, the method according to any one of claims 1 to 3 is implemented.

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