CN115112081A - Aircraft engine rotor assembly phase optimization method and matching method - Google Patents
Aircraft engine rotor assembly phase optimization method and matching method Download PDFInfo
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B21/00—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant
- G01B21/22—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant for measuring angles or tapers; for testing the alignment of axes
- G01B21/24—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant for measuring angles or tapers; for testing the alignment of axes for testing alignment of axes
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B21/00—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant
- G01B21/02—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant for measuring length, width, or thickness
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M1/00—Testing static or dynamic balance of machines or structures
- G01M1/14—Determining imbalance
- G01M1/16—Determining imbalance by oscillating or rotating the body to be tested
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
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Abstract
The invention discloses an aircraft engine rotor assembly phase optimization method and a matching method, wherein the aircraft engine rotor assembly phase optimization method comprises the following steps: obtaining the axial length of a compressor rotor, the front-end eccentric quantity and the front-end eccentric phase of the compressor rotor, the axial length of a turbine rotor, and the rear-end eccentric quantity and the rear-end eccentric phase of the turbine rotor; obtaining the relation between the eccentricity of the combined surface of the high-pressure combined rotor and the assembling phase angle according to a mathematical model; and adjusting the assembling phase angle according to the requirement of the eccentricity of the combined surface of the high-pressure combined rotor. A mathematical model is established according to the size characteristics of the compressor rotor and the turbine rotor, so that the relation between the joint surface of the high-pressure combined rotor and the assembling phase angle is established, the eccentricity or the range interval of the jumping value at the joint surface of the combined rotor assembled by the compressor rotor and the turbine rotor can be rapidly evaluated according to the relation, the optimal assembling phase angle can be given, the actual assembling work can be effectively guided, and the assembling efficiency is improved.
Description
Technical Field
The application belongs to the field of aero-engines, and particularly relates to an aero-engine rotor assembling phase optimization method and an aero-engine rotor matching method.
Background
The factors causing the vibration of the whole engine are many, and the magnitude of the unbalance of the rotor and the distribution state of the unbalance inside the rotor are one of the key factors. The most direct and important factor influencing the unbalance of the rotor is the assembling quality of the rotor. Generally speaking, the straighter a rotor is loaded, the smaller its runout in the axial direction means the smaller the degree of deviation of the disks/drums etc. of the stages inside the rotor assembly from the rotation axis, and thus the smaller the initial unbalance amount of the rotor assembly, and the control of the runout of the rotor is one of the important means for controlling the initial unbalance amount of the rotor. The high-pressure combined rotor of the civil turbofan birotor aeroengine consists of a high-pressure compressor maintenance unit body rotor (a compressor rotor for short) and a high-pressure turbine maintenance unit body rotor (a turbine rotor for short), the high-pressure combined rotor shows a change trend of an increasingly slender structure along with the release of more new types of aeroengine products, and the influence of the self-pulsation change of the maintenance unit body rotor, particularly the pulsation value of the middle joint of the combined rotor, on the straightness of the combined rotor is more sensitive. This aspect can result in a higher requirement for the accuracy of rotor runout in the repair unit, which tends to further increase the accuracy of manufacturing the rotor components and the accuracy of assembling the rotor assembly, but this can result in a decrease in part manufacturing yield and rotor assembly efficiency. On the other hand, in the prior art, the jump of the middle joint of the high-pressure combined rotor is difficult to be rapidly estimated, which hinders the development progress of scientific research engine rotors and the improvement of the batch production qualification rate of model engine rotors.
Disclosure of Invention
The invention provides an aircraft engine rotor assembly phase optimization method and an assembly method, aiming at overcoming the defects that an assembly method in the prior art is difficult to meet the requirement of rotor runout precision and is difficult to quickly predict the runout of a middle joint of a high-pressure combined rotor.
The invention solves the technical problems through the following technical scheme:
an aircraft engine rotor assembly phase optimization method comprises the following steps:
obtaining the axial length of a compressor rotor, the front-end eccentric quantity and the front-end eccentric phase of the compressor rotor, the axial length of a turbine rotor, and the rear-end eccentric quantity and the rear-end eccentric phase of the turbine rotor;
obtaining the relation between the eccentricity of the combined surface of the high-pressure combined rotor and the assembling phase angle according to a mathematical model;
and adjusting the assembling phase angle according to the requirement of the eccentricity of the combined surface of the high-pressure combined rotor.
According to the scheme, a mathematical model is established according to the size characteristics of the compressor rotor and the turbine rotor, the relation between the joint surface of the high-pressure combined rotor and the assembling phase angle is established through the mathematical model, the eccentricity or the range of the beating value at the joint surface of the combined rotor assembled by the compressor rotor and the turbine rotor can be rapidly evaluated according to the relation, the optimal assembling phase angle can be given, the actual assembling work is effectively guided, and the assembling efficiency is improved.
Preferably, the obtaining of the axial length of the compressor rotor, the front end eccentric amount and the front end eccentric phase of the compressor rotor, the axial length of the turbine rotor, and the rear end eccentric amount and the rear end eccentric phase of the turbine rotor includes:
measuring to obtain a run-out value of the front end bearing journal when the matching seam allowance at the rear end combining surface of the compressor rotor is taken as a reference;
and fitting the front-end eccentricity and the front-end eccentric phase of the compressor rotor by a least square method.
Preferably, the obtaining of the axial length of the compressor rotor, the front end eccentric amount and the front end eccentric phase of the compressor rotor, the axial length of the turbine rotor, and the rear end eccentric amount and the rear end eccentric phase of the turbine rotor includes:
measuring to obtain a runout value of the rear end bearing journal when the matching spigot at the front end combining surface of the turbine rotor is taken as a reference;
and fitting the rear-end eccentric quantity and the rear-end eccentric phase of the turbine rotor by a least square method.
Preferably, the formula of the mathematical model is:
wherein:
s is the eccentricity of the joint surface of the high-pressure combined rotor;
L 1 is the axial length of the compressor rotor;
P 1 the front end eccentricity of the compressor rotor is measured;
L 2 is the axial length of the turbine rotor;
P 2 is the amount of eccentricity at the rear end of the turbine rotor;
theta is the assembly phase angle.
Preferably, according to the formula, a relation curve of the eccentricity of the joint surface of the high-pressure combined rotor and the assembling phase angle is obtained.
An aircraft engine rotor matching method, comprising:
providing m compressor rotors and n turbine rotors, wherein m and n are integers which are more than or equal to one;
measuring to obtain the axial length of each compressor rotor, the front-end eccentricity and the front-end eccentricity phase of each compressor rotor, the axial length of each turbine rotor, and the rear-end eccentricity phase of each turbine rotor;
combining the compressor rotor and the turbine rotor in pairs to obtain m multiplied by n groups of rotor combinations;
obtaining the relation between the eccentricity of the high-pressure combined rotor joint surface in each group of rotor combination and the assembly phase angle by using the aero-engine rotor assembly phase optimization method;
screening all rotor combinations which can meet the requirement of the eccentricity of the junction surface of the high-pressure combined rotor;
and selecting a rotor combination according to the optimization target to complete rotor matching.
In the scheme, all combinations of the compressor rotors and the turbine rotors are substituted into the mathematical model to obtain the relation between the eccentricity of the high-pressure combination rotor junction surfaces and the assembly phase angle in all the rotor combinations, and the corresponding rotor combination is selected according to an optimization target.
Preferably, the selecting a rotor combination according to the optimization objective to complete rotor matching includes:
if the optimization target is to obtain the matching modes of the rotor combinations with the largest number of the eccentricity requirements capable of meeting the high-pressure combination rotor junction surfaces in the m compressor rotors and the n turbine rotors, all the matching modes are listed, the number of the rotor combinations capable of meeting the eccentricity requirements of the high-pressure combination rotor junction surfaces in each matching mode is obtained, and the matching mode of the rotor combinations with the largest number of the eccentricity requirements capable of meeting the high-pressure combination rotor junction surfaces is selected.
Preferably, the selecting a rotor combination according to the optimization objective to complete rotor matching includes:
if the optimization target is to obtain the rotor combination with the minimum eccentricity of the high-pressure combination rotor combination surface, calculating the minimum eccentricity of the high-pressure combination rotor combination surface which can be reached in each rotor combination, and selecting the rotor combination which can reach the minimum eccentricity.
The positive progress effects of the invention are as follows: the method for optimizing the assembly phase of the rotor of the aero-engine can quickly evaluate the eccentric amount or the range of the runout value at the combined rotor joint surface assembled by the compressor rotor and the turbine rotor, can provide the optimal assembly phase angle, effectively guides the actual assembly work and improves the assembly efficiency. The aeroengine rotor matching method can be used for matching and screening two high-pressure maintenance unit body rotors in the mass production of engines, and improves the assembly qualification rate. The optimization method is more reasonable and is closer to the actual requirement of the high-pressure combined rotor of the engine.
Drawings
Fig. 1A and 1B are schematic diagrams illustrating a butt-joint assembly state of the high-pressure combined rotor.
Fig. 2A and 2B are schematic views of the assembled state of the compressor rotor and the turbine rotor at different assembling phases.
FIG. 3 is a schematic view of the geometrical relationship of the compressor rotor axis and the turbine rotor axis in a high pressure combined rotor.
FIG. 4 is a flow chart of a method for optimizing an aircraft engine rotor assembly phase according to an embodiment of the invention.
Fig. 5 is a diagram illustrating a way of evaluating the runout of the compressor rotor in the aircraft engine rotor assembly phase optimization method according to an embodiment of the present invention.
FIG. 6 shows a turbine rotor runout evaluation method in the aircraft engine rotor assembly phase optimization method according to an embodiment of the invention.
Fig. 7 is a graph plotting the relationship between the eccentricity of the joint surface of the high-pressure combined rotor and the assembly phase angle according to the method for optimizing the assembly phase of the aircraft engine rotor in one embodiment of the present invention.
FIG. 8 is a flow chart of a method for matching an aircraft engine rotor according to an embodiment of the invention.
Description of the reference numerals
Turbine rotor axis of rotation 21
High-pressure combined rotor 3
True axis of rotation 31
Detailed Description
The invention is further illustrated by the following examples, which are not intended to limit the scope of the invention.
In order to ensure the rotor assembly quality, different jumping control measures are respectively adopted at different assembly stages of the engine. The part is adorned the stage and is carried out run-out control to two maintenance unit body rotors alone, and the requirement of beating to the compressor rotor does: and taking two cylindrical surfaces or one cylindrical surface plus one shaft shoulder end surface on the front end shaft neck of the compressor rotor as a reference, wherein the end surface runout and the cylindrical surface radial runout at the rear end stop of the labyrinth plate are required to be less than or equal to a certain value R1. The runout requirements for the turbine rotor are: the end face and the cylindrical surface at the front end drum shaft spigot of the turbine rotor are taken as references, and the cylindrical surface and the shaft shoulder end face runout at the rear end bearing journal are required to be less than or equal to a certain value R2. In the final assembly stage, the jumping requirement of the high-pressure combined rotor is as follows: taking the cylindrical surfaces at the bearing journals at the two ends of the combined rotor as a combined reference, the jumping of the center of the grate plate at the middle combined part or the jumping of the outer cylindrical surface at the front end of the drum shaft is required to be less than or equal to a certain value R3.
The above method has two problems: firstly, the possible runout value range of the combined rotor cannot be estimated quickly, and the optimal butt joint phase of the two maintenance unit body rotors which can meet the runout requirement of the combined rotor cannot be identified directly; second, the rotor runout value does not reflect the true state of the rotor and may mislead the assembly process. For example, when perpendicularity errors or concentricity errors exist among measuring references, in the process of measuring and aligning the references through jumping, unimportant measuring delay errors are generated under the influence of the structural characteristics of the rotor, and the false phenomenon that the rotor jumps unqualified is caused.
The embodiment provides a rotor assembly phase optimization method, which can effectively solve the problem of run-out delay errors caused by errors among measurement references, can also realize quick prediction of the run-out range of a combined rotor, and realizes efficient matching of a rotor in a maintenance unit.
As shown in fig. 1A, the compressor rotor 1 and the turbine rotor 2 of the high-pressure combined rotor 3 form a new actual rotation axis 31 (as shown in fig. 1B) after the compressor rotor 1 and the turbine rotor 2 are combined, that is, the high-pressure combined rotor 3 rotates around the actual rotation axis 31, due to the influence of rotor runout, the eccentricity of the junction surface of the high-pressure combined rotor 3 is denoted as S, which is defined as the distance from the center of the middle junction of the high-pressure combined rotor to the actual rotation axis, and when the roundness error of the part is not considered, the runout value is 2 times of the eccentricity S.
Generally, the selectable assembly phase of two rotors connected by bolts is equal to the number of bolt holes, and the jumping size at the combined rotor joint surface is different when the rotors are butted at different phases. The bolt holes are generally equally spaced circumferentially, so that the step value for adjusting the assembly phase angle is 360 °/i when the number of bolt holes is i, where i is a positive integer greater than 1.
In order to quickly predict the runout at the joint surface of the high-pressure combined rotor and find the optimal runout combination, an angle can be converted to analyze the runout characteristics of the combined rotor. Considering by taking the joint surface of the high-pressure combined rotor 3 as a reference, as shown in fig. 2A, when the compressor rotor and the turbine rotor are in a certain assembling phase, the eccentricity S of the joint surface of the high-pressure combined rotor is large, and when the turbine rotor 2 is rotated to be in other assembling phases, as shown in fig. 2B, the eccentricity S of the joint surface of the high-pressure combined rotor is reduced.
As shown in fig. 3, X, Y, Z in the figure are coordinate axes perpendicular to each other, point O is an intersection of the three coordinate axes, the joint surface of the high-pressure combined rotor 3 is first adjusted to the YOZ plane in fig. 4, and the compressor rotor axis 11 in the high-pressure combined rotor 3 is adjusted to the XOZ plane, in which case the turbine rotor axis 21 may be oriented at any angle in space. This expression is also to be understood equivalently: the high-pressure combined rotor 3 is formed by taking the joint surfaces of two maintenance unit rotors (namely a compressor rotor 1 and a turbine rotor 2) as reference, and butting and assembling the eccentricities at the bearing journal at the other end of each rotor after staggering a certain phase angle. A relational expression between the eccentricity S of the combined rotor and related parameters of the compressor rotor and the turbine rotor can be quickly obtained according to the space geometric relationship, and the relational expression is as follows:
wherein: s is the eccentricity of the joint surface of the high-pressure combined rotor; l is 1 To pressurize gasAxial length of the rotor; p 1 The front end eccentricity of the compressor rotor is measured; l is 2 Is the axial length of the turbine rotor; p 2 Is the amount of eccentricity at the rear end of the turbine rotor; theta is an assembly phase angle, and the value range of theta is 0-360 degrees.
And in quick evaluation, the 2-time S value can be used as the radial runout value of the combined surface of the high-pressure combined rotor.
As shown in fig. 4, the present embodiment provides a method for optimizing an aircraft engine rotor assembly phase, where the method for optimizing the aircraft engine rotor assembly phase includes:
obtaining axial length L of compressor rotor 1 Front end eccentricity P of compressor rotor 1 And the front end eccentric phase and the axial length L of the turbine rotor 2 Rear end eccentricity P of turbine rotor 2 And a rear end eccentric phase;
obtaining the relation between the eccentricity S of the combined surface of the high-pressure combined rotor and the assembling phase angle theta according to a mathematical model;
and adjusting the assembling phase angle theta according to the requirement of the eccentricity S of the combined surface of the high-pressure combined rotor.
In the embodiment, a mathematical model is established according to the size characteristics of the compressor rotor 1 and the turbine rotor 2, the relation between the joint surface of the high-pressure combined rotor and the assembling phase angle theta is established through the mathematical model, the eccentricity or the range interval of the jumping value at the joint surface of the combined rotor assembled by the compressor rotor 1 and the turbine rotor 2 can be rapidly evaluated according to the relation, the optimal assembling phase angle can be given, the actual assembling work can be effectively guided, and the assembling efficiency is improved. And if the actual bolt hole distribution cannot reach the optimal assembly phase, selecting the assembly phase closest to the optimal assembly phase.
The principle of measuring the front end eccentricity and the front end eccentricity phase of the compressor rotor 1 is shown in fig. 5, specifically, the run-out value of the front end bearing journal is measured when the rear end joint face of the compressor rotor 1 is matched with the spigot as the reference, and the front end eccentricity P of the compressor rotor 1 is fitted by the least square method 1 And a front end eccentric phase. The front end eccentricity can also be considered approximately as 0.5 run outThe value is obtained.
Similarly, the principle of measuring the rear-end eccentricity and the rear-end eccentric phase of the turbine rotor 2 is shown in fig. 6, the runout value of the turbine rotor 2 at the rear-end bearing journal is measured by taking the fitting spigot at the front-end joint surface as the reference, and the rear-end eccentricity P of the turbine rotor 2 is fitted by the least square method 2 And a rear end eccentric phase. The back end eccentricity can also be considered approximately 0.5 run out values.
The optimization method of the embodiment optimizes the evaluation mode of the compressor rotor runout at the partial installation stage to meet the requirement of the eccentric amount at the front end bearing journal by taking the outer spigot 12 at the rear end joint surface as a reference; meanwhile, the evaluation mode of the turbine rotor runout is optimized to meet the requirement of the eccentric amount of the rear end bearing journal by taking the inner spigot 22 at the front end joint surface as a reference.
According to the formula (1), a relation curve (as shown in fig. 7) between the eccentricity of the high-pressure combined rotor joint surface and the assembling phase angle is obtained, and according to the relation curve, the range of the eccentricity S of the high-pressure combined rotor joint surface can be quickly and intuitively obtained, and the optimal assembling phase angle theta can be obtained.
The embodiment also provides an aircraft engine rotor assembling method, when a plurality of compressor rotors (such as m rotors) and a plurality of turbine rotors (such as n rotors) are assembled, wherein m and n are integers which are more than or equal to one. If m is larger than or equal to n, at most n high-pressure combined rotors meeting the requirements can be paired.
As shown in fig. 8, the method for matching an aircraft engine rotor according to the embodiment includes:
providing m compressor rotors and n turbine rotors, wherein m and n are integers which are more than or equal to one;
combining the compressor rotor 1 and the turbine rotor 2 in pairs to obtain m multiplied by n groups of rotor combinations;
obtaining the relation between the eccentricity of the high-pressure combined rotor joint surface in each group of rotor combination and the assembly phase angle by using the aero-engine rotor assembly phase optimization method;
screening out all rotor combinations which can meet the requirement of the eccentricity of the combining surface of the high-pressure combined rotor;
and selecting a rotor combination according to the optimization target to complete rotor matching.
In the scheme, all combinations of the compressor rotors and the turbine rotors are substituted into the mathematical model, namely formula (1), so that the relation between the eccentricity of the high-pressure combination rotor combination surfaces and the assembly phase angle in all rotor combinations is obtained, and the corresponding rotor combination is selected according to an optimization target.
If the optimization target is that in m compressor rotors and n turbine rotors, the matching mode of the rotor combination with the largest number of the rotor combinations which can meet the requirement of the eccentricity of the high-pressure combined rotor junction surface is obtained, all the matching modes are listed, the number of the combinations which can be successfully matched with each compressor rotor is found, the compressor rotors are sequenced according to the sequence of the number of the combinations from small to large (when m is less than or equal to n, the compressor rotors are sequenced according to the condition of the turbine rotors, and the m combination rotors can be successfully matched at most), then the compressor rotors and the turbine rotors are sequentially matched, wherein the butt joint phase of the compressor rotors and the turbine rotors is executed according to the theta angle corresponding to the eccentricity S (the runout value is 2 times the S value) which meets the requirement of the pair of the combination rotors, and the rotor matching is completed.
Therefore, when the requirement of the eccentricity or the radial runout value at the middle joint surface of the high-pressure combined rotor is given, the matching method of the embodiment can be used for quickly matching the batch maintenance unit body rotors.
If the optimization target is to obtain the rotor combination with the minimum eccentricity of the high-pressure combination rotor combination surface, calculating the minimum eccentricity of the high-pressure combination rotor combination surface which can be reached in each rotor combination, and selecting the rotor combination which can reach the minimum eccentricity.
While specific embodiments of the invention have been described above, it will be appreciated by those skilled in the art that this is by way of example only, and that the scope of the invention is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the spirit and scope of the invention, and these changes and modifications are within the scope of the invention.
Claims (8)
1. The aircraft engine rotor assembly phase optimization method is characterized by comprising the following steps:
obtaining the axial length of a compressor rotor, the front-end eccentric quantity and the front-end eccentric phase of the compressor rotor, the axial length of a turbine rotor, and the rear-end eccentric quantity and the rear-end eccentric phase of the turbine rotor;
obtaining the relation between the eccentricity of the combined surface of the high-pressure combined rotor and the assembling phase angle according to a mathematical model;
and adjusting the assembling phase angle according to the requirement of the eccentricity of the combined surface of the high-pressure combined rotor.
2. The aircraft engine rotor assembly phase optimization method of claim 1, wherein the obtaining of the axial length of the compressor rotor, the front end eccentricity and the front end eccentricity phase of the compressor rotor, the axial length of the turbine rotor, the rear end eccentricity and the rear end eccentricity phase of the turbine rotor comprises:
measuring to obtain a run-out value of the front end bearing journal when the matching seam allowance at the rear end combining surface of the compressor rotor is taken as a reference;
and fitting the front-end eccentric quantity and the rear-end eccentric phase of the compressor rotor by a least square method.
3. The aircraft engine rotor assembly phase optimization method of claim 1, wherein the obtaining of the axial length of the compressor rotor, the front end eccentricity and the front end eccentricity phase of the compressor rotor, the axial length of the turbine rotor, the rear end eccentricity and the rear end eccentricity phase of the turbine rotor comprises:
measuring to obtain a runout value of the rear end bearing journal when the matching spigot at the front end combining surface of the turbine rotor is taken as a reference;
and fitting the rear-end eccentric quantity and the front-end eccentric phase of the turbine rotor by a least square method.
4. The aircraft engine rotor assembly phase optimization method of claim 1,
the formula of the mathematical model is as follows:
wherein:
s is the eccentricity of the combined surface of the high-pressure combined rotor;
L 1 is the axial length of the compressor rotor;
P 1 the front end eccentricity of the compressor rotor is measured;
L 2 is the axial length of the turbine rotor;
P 2 is the amount of eccentricity at the rear end of the turbine rotor;
theta is the assembly phase angle.
5. The aircraft engine rotor assembly phase optimization method of claim 4, wherein a relation curve of the eccentricity of the high-pressure combined rotor joint surface and the assembly phase angle is obtained according to the formula.
6. An aircraft engine rotor matching method is characterized by comprising the following steps:
providing m compressor rotors and n turbine rotors, wherein m and n are integers which are more than or equal to one;
combining the compressor rotor and the turbine rotor in pairs to obtain m multiplied by n groups of rotor combinations;
obtaining the relation between the eccentricity of the joint surface of the high-pressure combined rotor in each group of rotor combination and the assembly phase angle by using the aircraft engine rotor assembly phase optimization method of any one of claims 1 to 4;
screening out all rotor combinations which can meet the requirement of the eccentricity of the combining surface of the high-pressure combined rotor;
and selecting a rotor combination according to the optimization target to complete rotor matching.
7. An aircraft engine rotor assembly method according to claim 6, wherein said selecting a rotor combination based on optimization objectives, completing rotor assembly comprises:
if the optimization target is to obtain the matching modes of the rotor combinations with the largest number of the eccentricity requirements capable of meeting the high-pressure combination rotor junction surfaces in the m compressor rotors and the n turbine rotors, all the matching modes are listed, the number of the rotor combinations capable of meeting the eccentricity requirements of the high-pressure combination rotor junction surfaces in each matching mode is obtained, and the matching mode of the rotor combinations with the largest number of the eccentricity requirements capable of meeting the high-pressure combination rotor junction surfaces is selected.
8. An aircraft engine rotor assembly method according to claim 6, wherein said selecting a rotor combination based on optimization objectives, completing rotor assembly comprises:
if the optimization target is to obtain the rotor combination with the minimum eccentricity of the high-pressure combination rotor combination surface, calculating the minimum eccentricity of the high-pressure combination rotor combination surface which can be reached in each rotor combination, and selecting the rotor combination which can reach the minimum eccentricity.
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| CN115673704A (en) * | 2022-10-10 | 2023-02-03 | 哈尔滨工业大学 | Multi-stage large-scale high-speed rotation equipment assembling system and method based on virtual reality guidance, computer equipment and storage medium |
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| CN115673704A (en) * | 2022-10-10 | 2023-02-03 | 哈尔滨工业大学 | Multi-stage large-scale high-speed rotation equipment assembling system and method based on virtual reality guidance, computer equipment and storage medium |
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