Engine rotor unbalance amount estimation method, electronic device, and medium

Abstract

The application discloses an engine rotor unbalance amount estimation method, an electronic device and a medium, and relates to the technical field of engine rotor balancing, and can effectively solve the problem of whether a simulation rotor is still usable due to changes in various indexes or damage in long-term use of the simulation rotor, provide data support, and can be used for carrying out estimation on an unbalance amount of an aero-engine combined rotor adopting a simulation balancing process, so that the quality and reliability of rotor balancing are improved.

Description

Technical Field

[0001] This invention relates to the field of engine technology, and in particular to a method, electronic device and medium for predicting rotor imbalance of an aero-engine. Background Technology

[0002] The design of high-bypass turbofan aero engines has continuously broken through the limitations of earlier models in terms of thrust-to-weight ratio, rotor speed, turbine inlet temperature, and fuel consumption, pursuing higher reliability, economy, and maintainability. To facilitate assembly, disassembly, troubleshooting, and maintenance, the engine structure increasingly adopts a modular maintenance unit design.

[0003] Simulated balancing is one of the main dynamic balancing processes currently used for engine rotors. Taking the high-pressure rotor of a dual-rotor aero-engine as an example, the high-pressure combined rotor consists of a high-pressure compressor maintenance unit rotor and a high-pressure turbine maintenance unit rotor. The simulated balancing process involves using a simulated rotor to replace the real rotor and assembling it with another rotor for dynamic balancing. The two real rotors, after being balanced, can be directly assembled without further combined balancing. On the one hand, it can solve the problem in traditional combined balancing processes where the combined rotor's balancing correction surface overlaps with the component rotor's balancing correction surface, causing the combined rotor balancing to disrupt the component rotor's balance state and violate the step-by-step balancing principle. It can meet the design requirements for the dynamic balancing of the combined rotor components. On the other hand, it can avoid repeated assembly, which would cause unnecessary workload, enabling rapid selection and replacement of rotors and rapid troubleshooting of unit faults, fully meeting the needs of mass production and unit maintainability of engines.

[0004] In engine simulation balancing, the key factor affecting rotor balance quality is the simulated rotor. Due to limitations in manufacturing processes and the influence of the actual assembly state of the engine rotor, the quality characteristics of the simulated rotor cannot be exactly the same as all actual rotors. From the perspective of balancing tooling requirements, the simulated rotor tooling should have higher geometric accuracy than the engine rotor. This creates a very high manufacturing precision requirement for the simulated rotor, leading to increased manufacturing cycle and cost. Therefore, when facing questions such as to what extent the quality and geometric characteristic deviations of the simulated rotor need to be controlled to meet the dynamic balancing requirements of the actual engine rotor, and whether the simulated rotor can still be used when the actual rotor configuration is slightly modified, the estimation of the initial imbalance of the engine assembly rotor caused by the deviation of the simulated rotor is of great practical significance. However, current technology cannot effectively estimate the rotor imbalance, resulting in reduced rotor balancing quality and reliability. Summary of the Invention

[0005] The technical problem to be solved by the present invention is to overcome the defect in the prior art that it is impossible to effectively predict the rotor imbalance, which leads to a reduction in the quality and reliability of rotor balance, and to provide a method, electronic device and medium for predicting engine rotor imbalance.

[0006] The present invention solves the above-mentioned technical problems through the following technical solution:

[0007] According to one embodiment, a method for predicting engine rotor imbalance is provided, comprising:

[0008] Establish simplified representations of simulated engine rotors and actual engine rotors;

[0009] Based on the simplified expression, a prediction model for the unbalance of the engine rotor using simulated balancing technology is established;

[0010] Based on the prediction model, the influence of the actual deviation of the simulated rotor on the balance quality of the engine rotor using the simulated balancing process is quantitatively evaluated and output. The actual deviation includes at least one of weight deviation, center of mass position deviation, moment of inertia deviation, and geometric tolerance deviation.

[0011] Optionally, the step of establishing a predictive model for engine rotor imbalance using a simulated balancing process includes:

[0012] Establish a model for predicting the unbalance of an actual high-pressure compressor rotor using a simulated balancing process.

[0013] Optionally, the step of establishing a predictive model for engine rotor imbalance using a simulated balancing process includes:

[0014] A model for predicting the unbalance of an actual high-pressure turbine rotor using a simulated balancing process is established.

[0015] Optionally, the step of establishing a predictive model for engine rotor imbalance using a simulated balancing process includes:

[0016] A model for predicting the initial imbalance of a high-pressure combined rotor using a simulated balancing process was established.

[0017] Optionally, after establishing the prediction model, the method further includes:

[0018] Based on the prediction model, the influence of end runout at the actual engine rotor mating surface on the initial imbalance of the combined rotor is quantitatively assessed and output.

[0019] Optionally, after establishing the prediction model, the method further includes:

[0020] Based on the prediction model, the influence of simulated engine rotor runout deviation on the displacement compensation balance in the single engine rotor displacement balancing is quantitatively evaluated and output.

[0021] Optionally, it also includes:

[0022] Based on the predicted model, at least one design specification requirement for the simulated engine rotor is output to optimize the simulated engine rotor.

[0023] Optionally, the at least one design specification requirement information includes at least one of the following: allowable range of weight deviation, allowable range of center of mass position deviation, allowable range of moment of inertia deviation, and allowable range of runout tolerance.

[0024] According to another embodiment, an electronic device is provided, including a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the engine rotor imbalance prediction method as described above.

[0025] According to another embodiment, a computer-readable storage medium is provided having a computer program stored thereon, which, when executed by a processor, implements the engine rotor imbalance estimation method as described above.

[0026] Based on common knowledge in the field, the preferred conditions described can be combined arbitrarily to obtain various preferred embodiments of the present invention.

[0027] The positive and progressive effects of this invention are as follows:

[0028] The present invention provides a method, electronic equipment, and medium for predicting unbalance in aero-engine rotors. Based on a prediction model, it quantitatively assesses the impact of actual deviations in the simulated rotor on the balance quality of engine rotors using simulated balancing technology. Furthermore, combining the degree of influence of simulated rotor deviations with the balance requirements of aero-engine rotors, it proposes and optimizes various design parameters of the simulated rotor. This method effectively addresses the question of whether a simulated rotor remains usable after long-term use due to changes in various parameters or damage, providing data support for predicting the unbalance of combined rotors in aero-engines using simulated balancing technology, thereby improving the quality and reliability of rotor balancing. Attached Figure Description

[0029] The features and advantages of the present invention will be better understood after reading the following detailed description of embodiments of the present disclosure in conjunction with the accompanying drawings. In the drawings, components are not necessarily drawn to scale, and components having similar related properties or features may have the same or similar reference numerals.

[0030] Figure 1 This is a schematic diagram of the overall process of the engine rotor imbalance prediction method according to a preferred embodiment of the present invention.

[0031] Figure 2 This is a schematic diagram of the prediction calculation process of the engine rotor imbalance prediction method according to a preferred embodiment of the present invention.

[0032] Figure 3a A simplified schematic diagram of the high-pressure compressor rotor.

[0033] Figure 3b A simplified schematic diagram of the high-pressure turbine rotor.

[0034] Figure 3c A simplified schematic diagram of a high-pressure compressor rotor.

[0035] Figure 3d A simplified schematic diagram of a high-pressure turbine rotor.

[0036] Figure 3e A simplified model diagram simulating a high-pressure compressor rotor.

[0037] Figure 3f A simplified model diagram for simulating a high-pressure turbine rotor.

[0038] Figure 4a This is a schematic diagram showing the actual high-pressure compressor rotor at 0° position and the simulated high-pressure turbine rotor docking together.

[0039] Figure 4b This is a schematic diagram showing the actual high-pressure compressor rotor at 180° position and the simulated high-pressure turbine rotor docking together.

[0040] Figure 5 This diagram illustrates the remaining imbalance of an actual high-pressure compressor rotor after it has been balanced and corrected.

[0041] Figure 6a This is a schematic diagram simulating the docking of a high-pressure compressor rotor with an actual high-pressure turbine rotor at the 0° position.

[0042] Figure 6b This is a schematic diagram simulating the docking of a high-pressure compressor rotor with an actual high-pressure turbine rotor at a 180° position.

[0043] Figure 7 This is a schematic diagram illustrating the remaining imbalance of an actual high-pressure turbine rotor after balancing and correction.

[0044] Figure 8 This is a schematic diagram of the actual high-voltage combined rotor connection.

[0045] Figure 9 This is a schematic diagram of an electronic device for implementing an engine rotor imbalance prediction method according to another preferred embodiment of the present invention. Detailed Implementation

[0046] The present invention will be further illustrated by way of embodiments below, but the present invention is not limited to the scope of the embodiments described herein.

[0047] To overcome the aforementioned deficiencies, this embodiment provides a method for predicting engine rotor imbalance, comprising: establishing simplified expressions for simulated engine rotors and actual engine rotors; establishing a prediction model for engine rotor imbalance using simulated balancing processes based on the simplified expressions; and quantitatively evaluating and outputting the impact of actual deviations of the simulated rotors on the balance quality of engine rotors using simulated balancing processes based on the prediction model, wherein the actual deviations include at least one of weight deviation, center of mass position deviation, moment of inertia deviation, and geometric tolerance deviation.

[0048] In this embodiment, the method can effectively solve the problem of whether the simulated rotor is still usable due to changes or damage to various indicators during long-term use, providing data support and enabling the estimation of the imbalance of the combined rotor of the aero-engine using the simulation balancing process, thereby improving the quality and reliability of rotor balancing.

[0049] Specifically, as an example, such as Figure 1 As shown, the engine rotor imbalance prediction method provided in this embodiment mainly includes the following steps:

[0050] Step 101: Establish simplified representations of the simulated engine rotor and the actual engine rotor.

[0051] In this step, simplified representations of the simulated rotor and the actual rotor are established, including features such as unbalance, runout tolerance, and quality characteristic deviation.

[0052] Specifically, the simplified form of the actual rotor entity is as follows: Figure 3a , Figure 3b , Figure 3c , Figure 3d , Figure 3e and Figure 3f As shown in the diagram. OXYZ is a rectangular coordinate system, with O being the rotor's center of mass. The plane formed by the rotor's center of mass inertial axis and the normal to the end face at the rotor's mating surface is placed within the XOZ plane, and the center of mass inertial axis is coaxial with OX. The rotor's unbalance vector is represented by the static unbalance vector passing through the center of mass and the corresponding even unbalance vector. At this point, the static and even unbalance vectors passing through the center of mass on the rotor are located within the YOZ plane and may point in any direction in space. This simplification is applied to the simulated rotor, assuming the simulated rotor has weight, center of mass position, moment of inertia deviation, and runout tolerances. The relevant symbols are explained in Table 1 below.

[0053] Table 1: Explanation of Simplified Rotor Symbols

[0054]

[0055]

[0056] The rules are as follows: 1) Static unbalance is positive along the positive direction of the coordinate axis and negative along the negative direction; 2) Even unbalance is positive counterclockwise and negative clockwise in the coordinate plane. When balancing the actual high-pressure compressor rotor with the simulated high-pressure turbine rotor, and vice versa, the classic "indexing balancing method" from rigid rotor balancing theory is used to eliminate balancing fixture errors and installation errors. Here, a conventional 180° indexing balancing method is used (the analysis method for indexing balancing at other angles follows the same logic).

[0057] Step 102: Establish a rotor imbalance prediction model.

[0058] As an optional implementation, in this step, based on geometric algebra theory and the law of balance vector synthesis, an unbalance prediction model for the actual high-pressure compressor rotor using a simulated balancing process is established.

[0059] Specifically, the schematic diagram of the rotor state when the actual high-pressure compressor rotor adopts simulated balance is shown below. Figure 4a and Figure 4b As shown. First, the unbalance of the actual high-pressure compressor rotor when it is docked with the simulated high-pressure turbine rotor at the 0° position is obtained; second, the unbalance of the actual high-pressure compressor rotor when it is docked with the simulated high-pressure turbine rotor at the 180° position is obtained; third, the first two are added together to obtain twice the displacement compensation balance amount required in the balancing process (see the following expression (1)); fourth, the first two are subtracted to obtain twice the actual high-pressure compressor rotor correction unbalance amount (see the following expression (2)). The displacement compensation balance amount and the correction unbalance amount are described separately in the XOY plane and the XOZ plane (the same applies below).

[0060] According to geometric algebra theory and the law of equilibrium vector composition, we can obtain

[0061] Expression (1) is as follows:

[0062] XOY noodles,

[0063]

[0064] XOZ noodles,

[0065]

[0066] in,

[0067] U TB =[m1L1L A +(m2+Δm T (L4-ΔL) T )L B ]Δ T

[0068] M TB =[ΔJ1L A +(m2+Δm T (L4-ΔL) T )L B (L2+L3+ΔL T )-(ΔJ2+ΔJ T )L B ]Δ T

[0069]

[0070]

[0071] Expression (2) is as follows:

[0072] XOY noodles,

[0073] XOZ noodles,

[0074] in,

[0075] U 1B =[m1L1L A +(m2+Δm T (L4-ΔL) T )L B ]Δ1

[0076] M 1B =[ΔJ1L A +(m2+Δm T (L4-ΔL) T )L B (L2+L3+ΔL T )-(ΔJ2+ΔJ T )L B ]Δ1

[0077] γ - represents the angle (°) between the plane formed by the inertial axis of the simulated high-pressure turbine rotor's center of mass and the normals to the end faces at the joint surfaces of the two rotors, and the XOZ plane. It reflects the staggered joint of the two rotors at a certain angle.

[0078] After balancing the actual high-pressure compressor rotor according to expression (2), the remaining unbalance on the rotor is as shown in expression (3) below. Figure 5 As shown.

[0079] Considering that it is impossible for a real high-pressure compressor rotor to be completely balanced, there must be a residual static imbalance U within the balance tolerance range. 1per and the remaining even imbalance M 1per .

[0080] Expression (3) is as follows:

[0081] XOY noodles,

[0082] XOZ noodles,

[0083] As an optional implementation, in this step, based on geometric algebra theory and the law of balance vector synthesis, an unbalance prediction model for actual high-pressure turbine rotors using simulated balancing process is established.

[0084] Specifically, the schematic diagram of the rotor state when the actual high-pressure turbine rotor is subjected to simulated balancing is as follows: Figure 6a and Figure 6b As shown. First, the unbalance of the actual high-pressure turbine rotor when the simulated high-pressure compressor rotor and the actual high-pressure turbine rotor are combined and docked at the 0° position is obtained; second, the unbalance of the actual high-pressure turbine rotor when the simulated high-pressure compressor rotor and the actual high-pressure turbine rotor are combined and docked at the 180° position is obtained; third, the two are added together to obtain twice the displacement compensation balance amount required in the balancing process (see the following expression (4)); fourth, the two are subtracted to obtain twice the actual high-pressure turbine rotor correction unbalance amount (see the following expression (5)).

[0085] According to geometric algebra theory and the law of equilibrium vector composition, we can obtain

[0086] Expression (4) is as follows:

[0087] XOY noodles,

[0088]

[0089] XOZ noodles,

[0090]

[0091] in,

[0092] U CB =[m2L4L B +(m1+Δm C (L1+ΔL) C )L A ]Δ C

[0093] M CB =[-ΔJ2L B -(m1+Δm C (L1+ΔL) C )L A (L2+L3-ΔL C )+(ΔJ1+ΔJ C)L A ]Δ C

[0094] Expression (5) is as follows:

[0095] XOY noodles,

[0096] XOZ noodles,

[0097] in,

[0098] U 2B =[m2L4L B +(m1+Δm C (L1+ΔL) C )L A ]Δ2

[0099] M 2B =[-ΔJ2L B -(m1+Δm C (L1+ΔL) C )L A (L2+L3-ΔL C )+(ΔJ1+ΔJ C )L A ]Δ2

[0100] δ represents the angle (°) between the plane formed by the center of mass inertial axis of the simulated high-pressure compressor rotor and the normals to the end faces at the joint surfaces of the two rotors, and the XOZ plane. It reflects the staggered joint of the two rotors at a certain angle.

[0101] After balancing the actual high-pressure turbine rotor according to expression (5), the remaining unbalance on the rotor is as shown in expression (6) and Figure 7 As shown. Considering that a real high-pressure turbine rotor cannot be perfectly balanced, there must be a residual static imbalance U within the balance tolerance range. 2per and the remaining even imbalance M 2per .

[0102] Expression (6) is as follows:

[0103] XOY noodles,

[0104] XOZ noodles,

[0105] As an optional implementation, in this step, based on geometric algebra theory and the law of balance vector synthesis, a model for predicting the initial unbalance of a high-pressure combined rotor using simulated balancing technology is established.

[0106] Specifically, the actual high-pressure compressor rotor and the actual high-pressure turbine rotor, after simulated balance correction, are assembled at an arbitrary angle η. A schematic diagram of the high-pressure combined rotor docking state is shown below. Figure 8 As shown.

[0107] According to geometric algebra theory and the law of balance vector synthesis, and combining expressions (3) and (6), the initial unbalance of the high-pressure combined rotor on the intermediate joint surface can be obtained as expression (7).

[0108] Expression (7) is as follows:

[0109] XOY noodles,

[0110]

[0111] XOZ noodles,

[0112]

[0113] As can be seen from expression (7), the initial imbalance of the combined rotor comes from two factors: one is the combined rotor imbalance caused by the simulated rotor deviation, and the other is the combined rotor imbalance caused by the remaining imbalance after the individual rotor is balanced and corrected.

[0114] Step 103: Quantitatively assess the degree of impact on rotor balance quality.

[0115] As an optional implementation, in this step, based on the prediction model, the influence of simulated rotor deviations (weight deviation, center of mass position deviation, and moment of inertia deviation) on the initial imbalance of the combined rotor can be quantitatively analyzed.

[0116] As an optional implementation, in this step, based on the prediction model, the degree of influence of the end runout at the actual rotor mating surface on the initial imbalance of the combined rotor can be quantitatively analyzed.

[0117] As an optional implementation, in this step, the influence of simulated rotor runout deviation on the rotation compensation balance in a single rotor rotation balance can be quantitatively analyzed based on the prediction model.

[0118] Step 104: Output the design specifications of the simulated rotor for optimization.

[0119] In this step, the design parameters of the simulated rotor are proposed and optimized by combining the influence of the simulated rotor deviation and the balance requirements of the aero-engine rotor.

[0120] After executing step 104, you can return to step 102 to optimize the prediction model. Based on the prediction model in step 102, you can propose more reasonable technical indicators for simulating the rotor from the perspective of meeting the engine rotor balance requirements, including allowable ranges for weight deviation, center of mass position deviation, moment of inertia deviation, runout tolerance, etc.

[0121] refer to Figure 2 As shown, the following uses the high-pressure rotor simulation balancing of a dual-rotor aero-engine as an example to explain the process of predicting the initial imbalance of the combined rotor (the imbalance prediction of other rotors can be deduced by analogy).

[0122] 1. Measure the actual high-pressure compressor rotor weight m1, the axial distance L1 from the rotor's center of mass to the front support center, the axial distance L2 from the rotor's center of mass to the rear joint surface, and the diameter and moment of inertia ΔJ. 1d With polar rotational inertia ΔJ 1p And the joint surface end jump Δ1 and the diameter D at the joint surface, and calculate ΔJ1=ΔJ 1d -ΔJ 1p (In the preliminary analysis, the weight, center of gravity position, and moment of inertia parameters can also be obtained from the theoretical data in the three-dimensional model of the high-pressure compressor rotor.)

[0123] 2. The actual weight m2 of the high-pressure turbine rotor, the axial distance L3 from the rotor's center of mass to the front end mating surface, the axial distance L4 from the rotor's center of mass to the rear end support center, and the diameter and moment of inertia ΔJ were measured. 2d With polar rotational inertia ΔJ 2p And the joint surface end jump Δ2, and calculate ΔJ2=ΔJ 2d -ΔJ 2p (In the preliminary analysis, the weight, center of mass position, and moment of inertia parameters can also be obtained using theoretical data from the three-dimensional model of the high-pressure turbine rotor.)

[0124] 3. The following parameters were measured to obtain the simulated high-pressure compressor rotor weight, axial distance from the rotor's center of mass to the front support center, diameter moment of inertia, pole moment of inertia, and end runout Δ at the mating surface: C .

[0125] 4. Calculate Δm C =Simulated high-pressure compressor rotor weight - m1,

[0126] ΔL C =Axial distance from the simulated rotor's center of mass to the front support center - L1,

[0127] ΔJ C = Difference between the diameter rotational inertia and the pole rotational inertia of the simulated high-pressure compressor rotor -ΔJ1.

[0128] 5. The following parameters were measured: the weight of the simulated high-pressure turbine rotor, the axial distance from the rotor's center of mass to the front end mating surface, the diameter moment of inertia and the pole moment of inertia, and the end jump Δ at the mating surface. T .

[0129] 6. Calculate Δm T =Simulated high-pressure turbine rotor weight - m2

[0130] ΔL T =Axial distance from the simulated rotor's center of mass to the front end mating surface - L3

[0131] ΔJ T = Difference between the diameter rotational inertia and the pole rotational inertia of the simulated high-pressure turbine rotor -ΔJ2.

[0132] 7. Calculate L according to expression (1) A and L B .

[0133] 8. After balancing and correcting the actual high-pressure compressor rotor, the remaining static imbalance U is measured. 1per and the remaining even imbalance M 1per and the corresponding angle θ 1per and

[0134] 9. After balancing and correcting the actual high-pressure turbine rotor, its remaining static imbalance U is measured. 2per and the remaining even imbalance M 2per and the corresponding angle θ 2per and

[0135] 10. Given the docking angle η between the actual high-pressure compressor rotor and the actual high-pressure turbine rotor.

[0136] 11. Substituting the above values ​​into expression (7), the initial imbalance of the high-pressure combined rotor at the intermediate joint surface using the simulated balancing process can be obtained.

[0137] 12. If we assume that the remaining unbalance of the actual high-pressure compressor rotor and the actual high-pressure turbine rotor after balancing and correction is 0, the initial unbalance of the high-pressure combined rotor caused only by the simulated rotor deviation can be calculated according to expression (7). Furthermore, the sensitivity of each deviation and runout parameter to the initial unbalance of the high-pressure combined rotor can be analyzed.

[0138] This embodiment takes the high-pressure rotor of a dual-rotor aero-engine as an example to establish a method for predicting the initial imbalance of a high-pressure combined rotor using a simulated balancing process. This method is also applicable to other rotors, and can be adjusted and selected according to the actual situation.

[0139] The engine rotor imbalance prediction method provided in this embodiment has the following main advantages:

[0140] 1) This embodiment can be used to predict the initial imbalance of the combined rotor of an aero-engine using a simulated balancing process, thereby improving the quality and reliability of rotor balancing.

[0141] 2) This embodiment can effectively and quantitatively assess the impact of simulated rotor deviations (weight deviation, center of mass position deviation, moment of inertia deviation, and geometric tolerance deviation) on the balance mass of aero-engine rotors.

[0142] 3) This embodiment can formulate reasonable technical specifications for the simulated rotor from the perspective of meeting the actual use requirements of aero-engine rotors, avoiding the problems of increased costs, longer manufacturing cycles, and high maintenance requirements caused by endlessly improving the various technical specifications of the simulated rotor.

[0143] 4) This embodiment can be used to evaluate simulated rotors that have been in long-term use, so as to help plan the use, maintenance and scrapping of simulated rotors in advance.

[0144] Figure 9 This is a schematic diagram of an electronic device according to another embodiment of the present invention. The electronic device includes a memory, a processor, and a computer program stored in the memory and executable on the processor. When the processor executes the program, it implements the engine rotor imbalance prediction method as described in the above embodiment. Figure 9 The electronic device 30 shown is merely an example and should not impose any limitation on the functionality and scope of use of the embodiments of the present invention.

[0145] like Figure 9 As shown, the electronic device 30 can be manifested as a general-purpose computing device, such as a server device. The components of the electronic device 30 may include, but are not limited to: at least one processor 31, at least one memory 32, and a bus 33 connecting different system components (including memory 32 and processor 31).

[0146] Bus 33 includes a data bus, an address bus, and a control bus.

[0147] The memory 32 may include volatile memory, such as random access memory (RAM) 321 and / or cache memory 322, and may further include read-only memory (ROM) 323.

[0148] The memory 32 may also include a program / utility 325 having a set (at least one) of program modules 324, including but not limited to: an operating system, one or more application programs, other program modules, and program data, each or some combination of these examples may include an implementation of a network environment.

[0149] The processor 31 executes various functional applications and data processing by running computer programs stored in the memory 32, such as the engine rotor imbalance prediction method of the present invention as described in the above embodiment.

[0150] Electronic device 30 can also communicate with one or more external devices 34 (e.g., keyboard, pointing device, etc.). This communication can be performed via input / output (I / O) interface 35. Furthermore, the model-generating device 30 can also communicate with one or more networks (e.g., local area network (LAN), wide area network (WAN), and / or public networks, such as the Internet) via network adapter 36. Figure 9 As shown, network adapter 36 communicates with other modules of the model-generated device 30 via bus 33. It should be understood that, although not shown in the figure, other hardware and / or software modules can be used in conjunction with the model-generated device 30, including but not limited to: microcode, device drivers, redundant processors, external disk drive arrays, RAID (disk array) systems, tape drives, and data backup storage systems.

[0151] It should be noted that although several units / modules or sub-units / modules of the electronic device have been mentioned in the detailed description above, this division is merely exemplary and not mandatory. In fact, according to embodiments of the present invention, the features and functions of two or more units / modules described above can be embodied in one unit / module. Conversely, the features and functions of one unit / module described above can be further divided and embodied by multiple units / modules.

[0152] This embodiment also provides a computer-readable storage medium storing a computer program thereon, which, when executed by a processor, implements the steps in the engine rotor imbalance prediction method as described in the above embodiment.

[0153] The readable storage medium may be more specifically adopted, including but not limited to: portable disk, hard disk, random access memory, read-only memory, erasable programmable read-only memory, optical storage device, magnetic storage device, or any suitable combination thereof.

[0154] In a possible implementation, the present invention can also be implemented as a program product comprising program code that, when the program product is run on a terminal device, causes the terminal device to perform the steps in the engine rotor imbalance prediction method as described in the above embodiments.

[0155] The program code for executing the present invention can be written in any combination of one or more programming languages. The program code can be executed entirely on the user device, partially on the user device, as a standalone software package, partially on the user device and partially on a remote device, or entirely on a remote device.

[0156] While specific embodiments of the present invention have been described above, those skilled in the art should understand that these are merely illustrative examples, and the scope of protection of the present invention is defined by the appended claims. Those skilled in the art can make various changes or modifications to these embodiments without departing from the principles and essence of the present invention, but all such changes and modifications fall within the scope of protection of the present invention.

Claims

1. A method for predicting engine rotor imbalance, characterized in that, The method comprises the following steps: establishing a simplified expression mode of a simulation engine rotor and an actual engine rotor; establishing a prediction model of an unbalance amount of the engine rotor adopting a simulation balancing process according to the simplified expression mode; quantitatively evaluating an influence degree of an actual deviation of the simulation rotor on a balancing quality of the engine rotor adopting the simulation balancing process and outputting the influence degree according to the prediction model, the actual deviation comprising at least one of a weight deviation, a center of mass position deviation, a moment of inertia deviation and a geometric tolerance deviation; wherein the step of establishing the prediction model of the unbalance amount of the engine rotor adopting the simulation balancing process comprises: establishing a prediction model of an unbalance amount of an actual high-pressure compressor rotor adopting the simulation balancing process: obtaining an actual high-pressure compressor rotor unbalance amount when a 0° position of the actual high-pressure compressor rotor is combined with a simulation high-pressure turbine rotor, obtaining an actual high-pressure compressor rotor unbalance amount when a 180° position of the actual high-pressure compressor rotor is combined with the simulation high-pressure turbine rotor, adding the two actual high-pressure compressor rotor unbalance amounts to obtain a 2-fold required indexing compensation balance amount in a balancing process, subtracting the two actual high-pressure compressor rotor unbalance amounts to obtain a 2-fold actual high-pressure compressor rotor correction unbalance amount, and obtaining a simulation balancing corrected actual high-pressure compressor rotor residual unbalance amount according to the required indexing compensation balance amount and the actual high-pressure compressor rotor correction unbalance amount; establishing a prediction model of an unbalance amount of an actual high-pressure turbine rotor adopting the simulation balancing process: obtaining an actual high-pressure turbine rotor unbalance amount when a simulation high-pressure compressor rotor is combined with a 0° position of the actual high-pressure turbine rotor, obtaining an actual high-pressure turbine rotor unbalance amount when the simulation high-pressure compressor rotor is combined with a 180° position of the actual high-pressure turbine rotor, adding the two actual high-pressure turbine rotor unbalance amounts to obtain a 2-fold required indexing compensation balance amount in a balancing process, subtracting the two actual high-pressure turbine rotor unbalance amounts to obtain a 2-fold actual high-pressure turbine rotor correction unbalance amount, and obtaining a simulation balancing corrected actual high-pressure turbine rotor residual unbalance amount according to the required indexing compensation balance amount and the actual high-pressure turbine rotor correction unbalance amount; establishing a prediction model of an initial unbalance amount of a high-pressure combined rotor adopting the simulation balancing process: obtaining an initial unbalance amount of the high-pressure combined rotor on an intermediate joint surface according to the actual high-pressure compressor rotor residual unbalance amount and the actual high-pressure turbine rotor residual unbalance amount.

2. The method of claim 1, wherein, After the prediction model is established, the method further comprises: quantitatively evaluating an influence degree of an end runout at a joint surface of an actual engine rotor on the initial unbalance amount of the combined rotor and outputting the influence degree according to the prediction model.

3. The method of claim 1, wherein, After the prediction model is established, the method further comprises: quantitatively evaluating an influence degree of a runout deviation of a simulation engine rotor in single engine rotor indexing balancing on an indexing compensation balance amount and outputting the influence degree according to the prediction model.

4. The method of claim 1, wherein, Further comprising: outputting at least one design index requirement information of the simulation engine rotor to optimize the simulation engine rotor according to the prediction model.

5. The method of claim 4, wherein, The at least one design index requirement information includes at least one of a weight deviation allowable range, a mass center position deviation allowable range, a moment of inertia deviation allowable range, and a runout tolerance allowable range.

6. An electronic device comprising a memory, a processor, and a computer program stored on the memory and executable on the processor, characterized in that, The processor, when executing the computer program, implements the engine rotor unbalance amount estimation method according to any one of claims 1-5.

7. A computer readable storage medium having stored thereon a computer program, characterized in that The computer program, when executed by the processor, implements the engine rotor unbalance amount estimation method according to any one of claims 1-5.

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