Concentricity calculation and control method for bolt flange rotor connecting structure of aero-engine

Abstract

The invention discloses a concentricity calculation and control method of an aero-engine bolt flange rotor connection structure. The concentricity calculation under the condition of double-layer and multi-layer flange connection can be realized. The method comprises the following steps: firstly, confirming a connection form of a rotor, rotor part stages, a flange layer number, a centering mode of a connection structure and a fastening method; secondly, defining a coordinate system taking the center of the ball bearing as a coordinate origin O, and defining X, Y and Z directions; and then the necessary size and form and location tolerance of the part are obtained. And calculating the offset of the parts according to the geometrical relationship, and finally calculating the concentricity of the rotor through a formula. If the calculated concentricity of the rotor is too large during design, the size and tolerance can be adjusted to control the concentricity of the rotor. During assembly, the form and location tolerance of each rotor is measured, the angular position is analyzed, and the concentricity of the rotors is controlled to be at the minimum value through the dislocation assembly and stacking optimization technology.

Description

Technical Field

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

[0002] The bolt flange connection structure is one of the most widely used and common connection structures in the structural design of aircraft engines. Modern aircraft engines mostly adopt a dual-rotor structure, which has the characteristics of rolling bearing support, multi-stage wheel blades, complex excitation frequency, and severe working environment. With the continuous development of modern aircraft engine technology, aircraft engines with high thrust and high thrust-to-weight ratio are common, which has become an inevitable trend in the development of aircraft engines. Due to the limitations of mechanical processing technology, the most widely used rotor connection is still the bolt connection structure. Bolt connection has the advantages of 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 coincident 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 special structural characteristics of the aircraft engine rotor, if the concentricity deviation is large, on the one hand, the rotor rotation axis is skewed or bent, and on the other hand, the centroid deviation causes a large eccentricity of the center of mass, resulting in a large rotor imbalance. The above results may cause vibration problems in the aircraft engine rotor system during operation, affecting the stability of the rotor system.

[0005] Therefore, studying the calculation and control methods of the concentricity of the aero-engine bolt flange rotor connection structure, analyzing the rotor concentricity in advance, and optimizing the connection structure are of great significance and application value for 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 solution adopted by the present invention to solve the technical problem is as follows:

[0008] Step 1: 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 direction of the Y-axis is determined by 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 end face of the part, 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 ​​in the design stage and are measured values ​​after the part is processed;

[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 geometric tolerances u and t, forming 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 - After the rotors are stacked and assembled, 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;

[0021] b i - After the rotors are stacked and assembled, the angle between the center line of the i-th rotor and the theoretical center line caused by the parallelism deviation of the rear end surface of the i-1-th rotor;

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

[0023] k i - After the rotors are stacked and assembled, the concentricity of the rear end surface 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 stacked and 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, 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 may not be in the same phase limit or in 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 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;

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

[0038] The rotors of each stage are connected by bolt flanges, fastened by bolts and nuts, centered by flange stoppers, and the centering cylinder adopts interference fit; the front shaft neck of the compressor rotor is connected to the compressor first-stage rotor by two flanges and bolts and nuts, centered by the stoppers on the flange mating surface, and the stoppers adopt 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 stoppers on the mating surface of the flange, and the stoppers adopt interference fit;

[0039] The third and fourth stage rotors of the compressor are two-stage integrally connected rotors; the second stage rotor of the compressor is a structure with flange edges and bolt holes on the radial plate, and has two stoppers; the third and fourth stage rotors of the compressor, the fifth stage rotor of the compressor, and the rear shaft neck of the compressor rotor are connected through three layers of flanges, fastened by bolts and nuts, and centered by the stoppers on the matching surfaces of the flanges, and the stoppers adopt 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, which enables a computer to execute the above 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 executes 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, comprising 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 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 in the design stage, and reasonably allocate the dimensional tolerances of the parts based on the calculation results of the concentricity. There is no need to wait until the concentricity is found to be inappropriate after processing and assembly, and then to repair the parts again. This shortens the cycle and improves economic benefits. Secondly, by reasonably allocating the dimensional tolerances of the parts, it is no longer necessary to pursue the highest level of design and processing of the size of each part, which reduces the processing cost and improves the benefits. Finally, in the assembly stage, this method can provide a theoretical basis for staggered assembly, provide support and guidance for assembly work, and shorten the assembly cycle. BRIEF DESCRIPTION OF THE DRAWINGS

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

[0049] Figure 2 Schematic diagram of the rotor eccentricity 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 of the present invention;

[0051] Figure 4 is a 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 It is a schematic diagram of the concentricity of the rear end surface 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 surface of the i-th rotor of the present invention relative to the initial reference center O after superposition of various factors;

[0054] Figure 7 It is a schematic diagram of the geometric 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 connecting 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 rotor, 5-1 compressor third and fourth stage rotor front flange, 5-2 compressor first, second, third and fourth stage rotor connecting bolts and nuts, 5-3 compressor third and fourth stage rotor rear flange, 6 compressor fifth stage rotor, 6 -1 compressor five-stage rotor spoke flange, 7 compressor rotor rear shaft neck, 7-1 compressor rotor rear shaft neck front flange, 7-2 compressor three, four, and five-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 center line. DETAILED DESCRIPTION

[0057] The present invention is further described below in conjunction with the accompanying drawings and embodiments.

[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 the technical problem is:

[0060] A method for calculating and controlling the concentricity of a bolt flange rotor connection structure of an aircraft engine, wherein the rotor is composed of a multi-stage compressor and a turbine rotor, each stage of the rotor is connected by a bolt flange and centered by a stop. The method is characterized in that 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.

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

[0062] The rotors of each stage are connected by bolt flanges, fastened by bolts and nuts, centered by flange stoppers, and interference fit is adopted for the centering cylinder. The front shaft neck of the compressor rotor is connected to the compressor first-stage rotor by two flanges and bolts and nuts, centered by the stoppers on the flange mating surface, and interference fit is adopted for the stoppers. The compressor rotors, 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 stoppers on the mating surface of the flange, and interference fit is adopted for the stoppers. Among them, the compressor third- and fourth-stage rotors are two-stage integrally connected rotors; the compressor second-stage rotor is a structure with flange edges and bolt holes on the radial plate, and has two stoppers. The compressor third- and fourth-stage rotors, the compressor fifth-stage rotor, and the compressor rotor rear shaft necks are connected by three layers of flanges, fastened by bolts and nuts, centered by the stoppers on the mating surface of the flange, and interference fit is adopted for the stoppers. Among them, the compressor five-stage rotor is a structure with flange edges and bolt holes on the radial plate, and has two stoppers. The rear journal 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 matching surface of the flange, and the stoppers adopt an interference fit. The turbine rotor is connected to the rear journal of the turbine rotor through two layers of flanges, fastened by bolts and nuts, and centered by the stoppers on the matching surface of the flange, and the stoppers adopt 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 direction of the Y-axis 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 end face of the part, 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 ​​in the design stage and can be measured values ​​after the part is processed.

[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, i is a 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 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 of 180°|k i |Minimum.

[0078] When designing the rotor, the rotor concentricity k is calculated. i , to 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, since the connection structure is bolt flange connection, the rotor offset assembly angle is limited by the bolt hole spacing and angle, and it is difficult to meet the requirement that the shape and position tolerances of all parts are in the opposite phase of 180°. The only way is to measure and analyze the shape and position tolerances and angular position of each rotor in advance, and to ensure the rotor concentricity as much as possible through offset assembly and stacking optimization technology. i |The value is minimized, thereby reducing the vibration of the entire aircraft engine.

[0080] By accumulating the actual dimensions after processing and the concentricity dimensions after actual assembly, the relationship between the actual concentricity and the maximum concentricity calculated in the design phase can be measured to obtain the corresponding probability coefficient. In the design phase, the probability coefficient can be used to calculate the probability value of concentricity, thereby obtaining a value closer to the actual value.

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

[0082] Example:

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

[0084] The rotors of each stage are connected by bolt flanges, fixed by bolts and nuts, centered by flange stoppers, and interference fit is adopted for the centering cylinder. The front shaft neck 2 of the compressor rotor is connected to the compressor first-stage rotor 3 by two flanges 2-1 and 3-1, and bolts and nuts 3-2, centered by stoppers on the matching surfaces of flanges 2-1 and 3-1, and interference fit is adopted for the stoppers. The compressor rotors, the compressor first-stage rotor 3, the compressor second-stage rotor 4, and the compressor third- and fourth-stage rotors 5 are connected by three layers of flanges 3-3, 4-1, and 5-1, fastened by bolts and nuts 5-2, centered by stoppers on the matching surfaces of flanges 3-3, 4-1, and 5-1, and interference fit is adopted for the stoppers. Among them, the compressor third- and fourth-stage rotors 5 are integral rotors connected in two stages; the compressor second-stage rotor 4 is a structure with flange edges and bolt holes on the radial plate, and has two stoppers. The compressor three- and four-stage rotors 5, the compressor five-stage rotor 6, and the compressor rotor rear journal 7 are connected through three layers of flanges 5-3, 6-1, and 7-1, and are fastened by bolts and nuts 7-2. They are centered by the stoppers on the matching surfaces of flanges 5-3, 6-1, and 7-1, and the stoppers are interference fit. Among them, the compressor five-stage rotor 6 is a structure with flange edges and bolt holes on the radial plate, and has two stoppers. The compressor rotor rear journal 7 is connected to the turbine rotor 8 through two layers of flanges 7-3 and 8-1, and are fastened by bolts and nuts 8-2. They are centered by the stoppers on the matching surfaces of flanges 7-3 and 8-1, and the stoppers are interference fit. The turbine rotor 8 is connected to the turbine rotor rear journal 9 through two layers of flanges 8-3 and 9-1, and are fastened by bolts and nuts 8-4. They are centered by the stoppers on the matching surfaces of flanges 8-3 and 9-1, and the stoppers are interference fit.

[0085] Determine the coordinate system of the rotor, set the theoretical center of the front bearing as the coordinate origin O, set the theoretical center line of the rotor as the X-axis, the direction of the rear bearing as the positive direction of the X-axis, and the vertical upward direction as the positive direction of the Z-axis. Determine the direction of the Y-axis by the right-hand rule. Set L as the axial distance between the front and rear end faces of a single rotor part, D as the diameter of the end face of a single rotor part, u as the concentricity of the end face of a single rotor part relative to the reference end face, and t as the parallelism of a single rotor part relative to the reference end face. L, D, u, and t are part design values ​​in the design stage, and can be measured values ​​after the parts are processed.

[0086] After the rotors of each level are assembled, the concentricity of the entire rotor deviates from the theoretical center due to the superposition and accumulation of the geometric 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, i is a 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 of 180°|k i |Minimum.

[0097] When the rotor is designed, the rotor concentricity k is calculated. i , to 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 offset assembly and stacking optimization technology. i | value is the smallest. When assembling the rotor, since the connection structure is bolt flange connection, the rotor offset assembly angle is limited by the bolt hole spacing and angle, and it is difficult to meet the requirement that the shape and position tolerances of all parts are in the opposite phase of 180°. We can only measure and analyze the shape and position tolerances and angular position of each rotor in advance, and use offset assembly and stacking optimization technology to ensure the 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 processing and the concentricity dimensions after actual assembly, the relationship between the actual concentricity and the maximum concentricity calculated in the design phase can be measured to obtain the corresponding probability coefficient. In the design phase, the probability coefficient can be used to calculate the probability value of concentricity, thereby obtaining a value closer to the actual value.

[0100] The rotor shown in the present invention comprises 8 parts, and the size tolerance of each part is 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 another number, the calculation method is the same as that in the above implementation.

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 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 direction of the Y-axis is determined by 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 end face of the part, 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 ​​in the design stage and are measured values ​​after the part is processed; 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 geometric tolerances u and t, 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 - After the rotors are stacked and assembled, 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; b i - After the rotors are stacked and assembled, the angle between the center line of the i-th rotor and the theoretical center line caused by the parallelism deviation of the rear end surface of the i-1-th rotor; g i -After the rotors are assembled, the rear end face of the i-th rotor is parallel to the center of its front end face due to the deviation of the parallelism of the rear end face of the i-1th rotor. i Concentricity; k i - After the rotors are stacked and assembled, the concentricity of the rear end surface 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 stacked and 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, 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 may not be in the same phase limit or in different angular positions; u i and t i is a vector parameter, rotor concentricity k i About U i and t i The vector and 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 concentricity calculation and control method 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 concentricity calculation and control method 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 and roller bearings; The rotors of each stage are connected by bolt flanges, fastened by bolts and nuts, centered by flange stoppers, and the centering cylinder adopts interference fit; the front shaft neck of the compressor rotor is connected to the compressor first-stage rotor by two flanges and bolts and nuts, centered by the stoppers on the flange mating surface, and the stoppers adopt 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 stoppers on the mating surface of the flange, and the stoppers adopt interference fit; The third and fourth stage rotors of the compressor are two-stage integrally connected rotors; the second stage rotor of the compressor is a structure with flange edges and bolt holes on the radial plate, and has two stoppers; the third and fourth stage rotors of the compressor, the fifth stage rotor of the compressor, and the rear shaft neck of the compressor rotor are connected through three layers of flanges, fastened by bolts and nuts, and centered by the stoppers on the matching surfaces of the flanges, and the stoppers adopt 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. A computer program, characterized in that The computer program enables a computer to execute the method according to any one of claims 1 to 3.

5. 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 executes the method as claimed in any one of claims 1 to 3.

6. 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.

7. 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 a method as claimed in any one of claims 1 to 3.

8. 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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