Aero-engine rotor coaxiality stacking method based on five-bias axial measurement model

Abstract

The application is a kind of aviation engine rotor coaxiality stacking method based on five bias axial measurement model. The application relates to the technical field of coaxiality measurement. The eccentric error causes the sampling angle deviation when the cylindrical component is axially measured, and the actual sampling angle deviation is determined. The sampling angle deviation is determined. According to the error of the measuring head radius, the measuring head radius has an impact on the eccentric error, and the eccentric error is determined. The measuring head support rod is parallel to the vertical direction, the contact direction of the measuring head and the measured member is the horizontal direction, the measurement error is introduced, the runout error of the surface of the measuring point appears, the runout error deviation and the profile deviation error are determined. The inclination error of the measuring head support rod makes the error of the measuring head radius have an impact on the measurement of the coaxiality, and the profile measurement model and the actual sampling angle are determined. Based on the profile measurement model, the error of the single-pole rotor is determined, and the coaxiality of the multi-stage rotor is evaluated.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of coaxiality measurement, and is a method for stacking the coaxiality of an aero-engine rotor based on a five-bias axial measurement model. BACKGROUND

[0002] The core engine is the heart of the aero-engine, and the assembly quality thereof directly affects the performance of the aero-engine. The core engine is mainly composed of a plurality of stacked rotors, and the coaxiality is a core parameter for checking the assembly quality of the plurality of rotors. When the aero-engine is working at a working speed, for example, the working speed of a civil engine can be up to 12000 rpm or more, the unbalance response caused by the coaxiality error of the plurality of rotors after assembly will be amplified, resulting in engine vibration and causing the blades and the casing to collide and rub. According to statistics, more than 70% of the failures of the aero-engine are caused by vibration, and about 20% of the failures are caused by collision and rubbing. Generally speaking, the occurrence of collision and vibration is caused by factors such as different shafts after assembly. Therefore, the problem of the coaxiality error of the plurality of rotors after assembly of the aero-engine is a core problem that restricts the performance of the engine.

[0003] At present, the method for measuring the coaxiality mainly uses the rotary axis method, and this method has a plurality of system errors, and these errors are coupled with each other, which will significantly affect the measurement accuracy of the coaxiality. Therefore, it is of great significance to improve the coaxiality measurement model and effectively separate the plurality of system errors of the measurement model, so as to improve the ultra-precision measurement accuracy and realize the precision model engineering.

[0004] When facing the coaxiality measurement method based on the contact type, the five system errors of the device system, i.e., eccentric error, probe offset error, probe radius error, probe support rod tilt error and tilt error, are coupled to cause the problem of inaccurate coaxiality measurement, and therefore it is urgent to propose a coaxiality measurement model considering the system errors of the measurement device, so as to provide a theoretical basis for subsequent error separation. SUMMARY

[0005] The present application provides a method for stacking the coaxiality of an aero-engine rotor based on a five-bias axial measurement model.

[0006] It should be noted that, in this text, relational terms such as first and second are used merely to distinguish one entity or action from another, and do not necessarily require or imply that there is any such actual relationship or order between these entities or actions. Moreover, the terms "include", "contain" or any other variants thereof are intended to cover non-exclusive inclusion, so that the process, method, article or device including a series of elements not only includes those elements, but also includes other elements not explicitly listed or inherent to such process, method, article or device.

[0007] The application provides an aero-engine rotor coaxiality stacking method based on a five-bias axial measurement model.

[0008] An aero-engine rotor coaxiality stacking method based on a five-bias axial measurement model, the method comprising the following steps:

[0009] Step 1: Eccentric error causes the sampling angle to deviate during the axial measurement of a cylindrical component, and the actual sampling angle deviation is determined.

[0010] Step 2: When the measurement direction of the sensor deviates from the rotation direction during the measurement process, the sensor side head deviation error is introduced, the sampling angle deviates, and the actual angle deviation is determined.

[0011] Step 3: According to the probe radius error, the eccentricity, tilt and other system errors will interact with the probe radius during actual measurement, the probe radius has an impact on the eccentricity error, and the eccentricity error is determined.

[0012] Step 4: The probe support rod is parallel to the vertical direction, the contact direction of the probe and the measured member is the horizontal direction, the measurement error is introduced, the runout error occurs on the surface of the measured point, and the runout error deviation and the profile deviation error are determined.

[0013] Step 5: The tilt error of the probe support rod causes the error of the probe radius to have an impact on the measurement of the coaxiality, and the profile measurement model and the actual sampling angle are determined.

[0014] Step 6: Based on the profile measurement model, the error of the single-pole rotor is determined, and the coaxiality of the multi-stage rotor is evaluated.

[0015] Preferably, the step 1 is specifically:

[0016] The maximum concentricity error of the measurement surface of each stage rotor relative to the reference axis is the multi-stage rotor coaxiality error, and the concentricity error of each stage rotor is twice the eccentricity error, so that the multi-stage rotor coaxiality error measurement and assembly adjustment can be realized through the measurement and adjustment of the eccentricity error. Eccentric error causes the sampling angle to deviate during the axial measurement of a cylindrical component, and the actual sampling angle deviation is determined by the following formula:

[0017]

[0018] Wherein, p j is the initial eccentricity, α j is the corresponding eccentric angle, r 0j is the fitting radius, φ ij is the actual sampling angle, θ ij is the ideal sampling angle.

[0019] Preferably, the step 2 is specifically:

[0020] When the measurement direction of the sensor deviates from the rotation direction during the measurement, a sensor side head offset error is introduced, which causes the sampling angle to deviate, and the actual angle deviation is represented by the following formula:

[0021] Δη i = sin -1 ((m j +p j sin(η ij -α j )) / r 0j )

[0022] Wherein, m j is the head offset, O 2j is the instantaneous rotation center generated by the head offset, and Δθ ij is the offset angle of each sampling point in the cross section.

[0023] Preferably, the step 3 is specifically:

[0024] Since the measuring head cannot be processed into a dimensionless ideal point, the head radius error is introduced, and during actual measurement, the system errors such as eccentricity and inclination will interact with the head radius. The head radius has an impact on the eccentricity error, and the eccentricity error is represented by the following formula:

[0025] Δη j = sin -1 ((m j +p j sin(η ij -α j )) / (r 0j +Δl ij +r)).

[0026] Preferably, the step 4 is specifically:

[0027] The head support rod is parallel to the vertical direction, and the contact direction of the head and the measured member is horizontal. The improper adjustment of the mechanical fast processing error and the contact force makes it difficult to keep the contact direction horizontal, introduces measurement error, and causes the surface of the measurement point to appear jumping error. The jumping error deviation is represented by the following formula:

[0028]

[0029] Wherein, is the inclination angle of the head support rod, AA is the ideal contact direction of the head and the measured member, and BB is the actual contact direction.

[0030] Since the measured geometric axis and the measurement rotation axis are difficult to coincide in actual measurement, an inclination error is introduced, which causes the profile measurement to deviate. The inclination error is represented by the following formula:

[0031]

[0032] wherein r0 is the sampling radius, g is the geometric axis tilt angle, b j is the angle between the projection direction of the geometric axis on the measurement plane and the initial measurement direction.

[0033] Preferably, the step 5 is specifically:

[0034] Due to the tilt error of the stylus stem, the error of the probe radius has an impact on the measurement of the coaxiality, and the final profile measurement model and the actual sampling angle are represented by the following formula:

[0035]

[0036] Preferably, the step 6 is specifically:

[0037] Based on the profile measurement model, the error of the single-pole rotor is obtained, and the error transmission law of the multi-stage rotor stack can be analyzed to evaluate the coaxiality of the multi-stage rotor. The assembly error of the multi-stage rotor is composed of a positioning error and an orientation error, wherein the positioning error is represented by a translation matrix, and the orientation error is represented by a rotation matrix. Thus, the cumulative eccentric error expression of the multi-stage rotor stack is determined, and the eccentric error of the nth stage rotor is represented by the following formula:

[0038]

[0039] wherein Trari is the transformation matrix between the two-stage rotor joint surfaces, TraZi is the eccentricity of the ideal center of the rotor, Tracle is the translation transformation matrix of the eccentricity of the rotor i reference surface gap, Tradzi is the eccentricity translation transformation matrix caused by the machining error of the rotor i reference surface, Traori is the rotation transformation matrix of the rotor i rotor reference surface to the assembly surface rotation center, Rotxi is the rotation matrix of the i-th stage rotor reference surface around the X-axis; Rotyi is the rotation matrix of the i-th stage rotor reference surface around the Y-axis; Qi is the ideal position vector of the i-th stage rotor assembly surface center; dQi is the machining error vector of the i-th stage rotor assembly surface center position; dQ'i is the gap eccentric position vector of the i-th stage rotor; Rotri is the rotation matrix of the i-th stage rotor around the Z-axis.

[0040] The position vector of the assembly surface center of the n-th stage rotor after assembly is represented by the following formula:

[0041]

[0042] According to the standard definition of the coaxiality, the coaxiality of the n-stage rotor is represented by the following formula:

[0043]

[0044] Based on the position vector of the axial projection of the position of the rotor shaft at each level, the maximum modulus is twice the optimal coaxiality of the multi-stage mixed fit rotor.

[0045] A five-bias axial measurement model-based aero-engine rotor coaxiality stacking device, the device comprises:

[0046] An actual sampling angle offset measurement module, which determines the actual sampling angle offset when the sampling angle is offset during the axial measurement of the cylindrical member caused by the eccentric error during measurement.

[0047] An actual angle measurement module, which determines the actual angle offset when the measurement direction of the sensor deviates from the rotation direction during the measurement process, introduces the sensor side head offset error, and the sampling angle is offset.

[0048] An eccentric error module, which determines the eccentric error according to the probe radius error, the eccentricity, the tilt and other system errors during actual measurement, and the probe radius influences the eccentric error.

[0049] An error offset and profile offset error measurement module, which determines the runout error offset and profile offset error when the probe support rod is parallel to the vertical direction, the contact direction of the probe and the measured member is horizontal, introduces measurement error, and makes the surface of the measurement point appear runout error.

[0050] The tilt error of the probe support rod influences the measurement of the coaxiality caused by the error of the probe radius, and the profile measurement model and the actual sampling angle are determined.

[0051] A multi-stage rotor coaxiality evaluation module, which determines the error of a single-pole rotor based on the profile measurement model, and evaluates the coaxiality of a multi-stage rotor.

[0052] A computer readable storage medium having a computer program stored thereon, the program being executed by a processor to implement a five-bias axial measurement model-based aero-engine rotor coaxiality stacking method.

[0053] A computer device comprising a memory and a processor, the memory storing a computer program, and when the processor runs the computer program stored in the memory, the processor executes a five-bias axial measurement model-based aero-engine rotor coaxiality stacking method.

[0054] The present application has the following beneficial effects:

[0055] The present application aims at the problem that the coaxiality measurement is not accurate due to the coupling of five system errors of eccentric error, probe offset error, probe radius error and tilt error in the coaxiality measurement device, and proposes a corresponding five system error measurement model for separating the measurement error of the axial cylindrical component. On this basis, the error caused by the coaxiality during stacking can be eliminated. BRIEF DESCRIPTION OF DRAWINGS

[0056] In order to more clearly illustrate the technical solutions in the specific embodiments or the prior art, the drawings needed to be used in the specific embodiments or the prior art description will be briefly introduced. Obviously, the drawings in the following description are some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative labor.

[0057] Figure 1 It is an eccentric error schematic diagram;

[0058] Figure 2 It is a probe offset error schematic diagram;

[0059] Figure 3 It is a probe radius error schematic diagram;

[0060] Figure 4 It is a probe support rod tilt error schematic diagram;

[0061] Figure 5 It is a tilt error schematic diagram;

[0062] Figure 6 It is a stacking model schematic diagram. DETAILED DESCRIPTION

[0063] The technical solutions of the present application will be described clearly and completely below in combination with the drawings. Obviously, the described embodiments are some of the embodiments of the present application, not all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor are within the protection scope of the present application.

[0064] In the description of the present application, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer" and the like indicate the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application. In addition, the terms "first", "second", "third" are only for the purpose of description, and cannot be understood as indicating or implying relative importance.

[0065] In the description of the present application, it should be noted that unless otherwise explicitly specified and limited, the terms "mounting", "connection", "connecting" should be understood in a broad sense, for example, can be fixed connection, can also be detachable connection, or integrally connected; can be mechanical connection, can also be electrical connection; can be directly connected, can also be indirectly connected through an intermediate medium, can be the communication inside two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0066] In addition, the technical features involved in the different embodiments of the application described below can be combined with each other as long as there is no conflict between them.

[0067] The present application is described in detail below in conjunction with specific embodiments. Embodiment I:

[0069] According to Figures 1 to 6 The specific optimization technical scheme adopted by the present application to solve the above technical problems is: the present application relates to a method for stacking the coaxiality of an aero-engine rotor based on a five-bias axial measurement model.

[0070] A method for stacking the coaxiality of an aero-engine rotor based on a five-bias axial measurement model, the method comprising the following steps:

[0071] Step 1: The eccentric error causes the sampling angle to deviate during the axial measurement of the cylindrical member during measurement, and the actual sampling angle deviation is determined;

[0072] Step 2: When the measurement direction of the sensor deviates from the rotation direction during the measurement process, the sensor side head deviation error is introduced, the sampling angle deviates, and the actual angle deviation is determined;

[0073] Step 3: According to the probe radius error, during actual measurement, the eccentricity, tilt and other system errors will interact with the probe radius, and the probe radius will affect the eccentricity error, and the eccentricity error is determined;

[0074] Step 4: The probe support rod is parallel to the vertical direction, the contact direction of the probe and the measured member is horizontal, the measurement error is introduced, the runout error occurs on the surface of the measurement point, and the runout error deviation and the profile deviation error are determined;

[0075] Step 5: The tilt error of the probe support rod causes the error of the probe radius to affect the measurement of the coaxiality, and the profile measurement model and the actual sampling angle are determined;

[0076] Step 6: Based on the profile measurement model, the error of the single-pole rotor is determined, and the coaxiality of the multi-stage rotor is evaluated. Embodiment II:

[0078] The difference between the embodiment two and the embodiment one of the present application is only that:

[0079] The step 1 is specifically:

[0080] The maximum value of the concentricity error of the rotor measuring surface of each level relative to the reference axis is the coaxiality error of the multi-stage rotor, and the concentricity error of each rotor is twice the eccentricity error, so the coaxiality error of the multi-stage rotor can be measured and assembled by measuring and adjusting the eccentricity error. The eccentricity error causes the sampling angle to deviate when measuring the axial direction of the cylindrical member, and the actual sampling angle deviation is represented by the following formula:

[0081]

[0082] Wherein, p j is the initial eccentricity, α j is the corresponding eccentric angle, r 0j is the fitting radius, φ ij is the actual sampling angle, θ ij is the ideal sampling angle. Specific embodiment three:

[0084] The difference between the embodiment three and the embodiment two of the present application is only that:

[0085] The step 2 is specifically:

[0086] When the measurement direction of the sensor deviates from the rotation direction during the measurement process, the sensor side head offset error is introduced, as shown in Figure 2 , which causes the sampling angle to deviate, and the actual angle deviation is represented by the following formula:

[0087] Δη i = sin -1 ((m j +p j sin(η ij -α j )) / r 0j )

[0088] Wherein, m j is the head offset, O 2j is the instantaneous rotation center generated by the head offset, and Δθ ij is the offset angle of each sampling point in the cross section. Specific embodiment four:

[0090] The difference between the embodiment four and the embodiment three of the present application is only that:

[0091] The step 3 is specifically:

[0092] Since the measuring head cannot be machined into an ideal point without size, the head radius error is introduced, as shown inFigure 3 As shown, in actual measurement, system errors such as eccentricity and inclination will interact with the probe radius, the probe radius has an impact on the eccentricity error, and the eccentricity error is represented by the following formula:

[0093] Δη j = sin -1 ((m j +p j sin(η ij -α j )) / (r 0j +Δl ij +r))。 Specific embodiment five:

[0095] The difference between the embodiment five and the embodiment four is only that:

[0096] The step 4 is specifically:

[0097] The probe support rod is parallel to the vertical direction, the contact direction of the probe and the measured member is horizontal, and improper adjustment of the mechanical fast processing error and the contact force makes it difficult to keep the contact direction horizontal, such as Figure 4 As shown, the measurement error is introduced, which causes the runout error of the measurement point surface, and the runout error offset is represented by the following formula:

[0098]

[0099] Wherein, is the inclination angle of the probe support rod, AA is the ideal contact direction of the probe and the measured member, and BB is the actual contact direction;

[0100] Due to the fact that the measured geometric axis and the measurement rotation axis are difficult to coincide in actual measurement, an inclination error is introduced, such as Figure 5 As shown, the inclination error causes the profile measurement to deviate, and the inclination error is represented by the following formula:

[0101]

[0102] Wherein, r0 is the sampling radius, g is the inclination angle of the geometric axis, and b j is the angle between the projection direction of the geometric axis on the measurement plane and the initial measurement direction. Specific embodiment six:

[0104] The difference between the embodiment six and the embodiment five is only that:

[0105] The step 5 is specifically:

[0106] Due to the inclination error of the probe support rod, the error of the probe radius has an impact on the coaxiality measurement, and the final profile measurement model and the actual sampling angle are represented by the following formula:

[0107] Specific embodiment seven:

[0109] The difference between the embodiment seven and the embodiment six is only that:

[0110] The step 6 is specifically:

[0111] Based on the contour measurement model, the error of the single-pole rotor is obtained, and the error transmission law of the multi-stage rotor stack can be analyzed to evaluate the coaxiality of the multi-stage rotor. The assembly error of the multi-stage rotor is composed of a positioning error and an orientation error, wherein the positioning error is represented by a translation matrix, and the orientation error is represented by a rotation matrix. Thus, the cumulative eccentric error expression of the multi-stage rotor stack is determined, and the eccentric error of the nth stage rotor is represented by the following formula:

[0112]

[0113] Wherein, Trari is the transformation matrix between the two-stage rotor joint surfaces, TraZi is the eccentricity of the ideal center of the rotor, Tracle is the translation transformation matrix of the eccentricity of the gap reference surface of the rotor i, Tradzi is the eccentricity translation transformation matrix caused by the machining error of the reference surface of the rotor i, Traori is the rotation transformation matrix of the rotor i reference surface to the assembly surface rotation center, Rotxi is the rotation matrix of the i-th stage rotor reference surface around the X-axis; Rotyi is the rotation matrix of the i-th stage rotor reference surface around the Y-axis; Qi is the ideal position vector of the center of the i-th stage rotor assembly surface; dQi is the machining error vector of the center position of the i-th stage rotor assembly surface; dQ'i is the gap eccentric position vector of the i-th stage rotor; Rotri is the rotation matrix of the i-th stage rotor around the Z-axis;

[0114] The center position vector of the assembly surface of the nth stage rotor after assembly is represented by the following formula:

[0115]

[0116] According to the standard definition of the coaxiality, the coaxiality of the n-stage rotor is represented by the following formula:

[0117]

[0118] Based on the position vector of the axial projection of the center position of each stage rotor, the maximum modulus of twice is the optimal coaxiality of the multi-stage mixed fit rotor. Specific embodiment eight:

[0120] The difference between the embodiment eight and the embodiment seven is only that:

[0121] The application provides an aero-engine rotor coaxiality stacking device based on a five-bias axial measurement model, and the device comprises:

[0122] An actual sampling angle offset amount measurement module is used to determine an actual sampling angle offset amount when a sampling angle is offset during axial measurement of a cylindrical member caused by eccentric error during measurement.

[0123] An actual angle measurement module is used to determine an actual angle offset amount when a measurement direction of a sensor deviates from a rotation direction during measurement, a sensor side head offset error is introduced, and a sampling angle is offset.

[0124] An eccentric error module is used to determine eccentric error according to a probe radius error, and the eccentric error, tilt and other system errors are influenced by the probe radius during actual measurement, the probe radius influences the eccentric error.

[0125] An error offset amount and profile offset error measurement module is used to determine a runout error offset amount and a profile offset error when a probe support rod is parallel to the vertical direction, a contact direction of the probe and the measured member is the horizontal direction, a measurement error is introduced, and a runout error is generated on the surface of a measurement point.

[0126] A tilt error of the probe support rod influences the measurement of the coaxiality caused by the error of the probe radius, and a profile measurement model and an actual sampling angle are determined.

[0127] A multi-stage rotor coaxiality evaluation module is used to determine the error of a single-pole rotor based on the profile measurement model, and the coaxiality of the multi-stage rotor is evaluated. Specific embodiment nine:

[0129] The difference between the embodiment nine and the embodiment eight is only that:

[0130] The application provides a computer readable storage medium, which stores a computer program, and the program is executed by a processor to implement an aero-engine rotor coaxiality stacking method based on a five-bias axial measurement model. Specific embodiment ten:

[0132] The difference between the embodiment ten and the embodiment nine is only that:

[0133] The application provides a computer device, which comprises a memory and a processor, and the memory stores a computer program, and when the processor runs the computer program stored in the memory, the processor executes an aero-engine rotor coaxiality stacking method based on a five-bias axial measurement model. Specific embodiment eleven:

[0135] The difference between the embodiment eleven and the embodiment ten is only that:

[0136] Since the rotary main shaft has radial rotation error, angular rotation error, etc., even if the rotation accuracy is high, the rotary axis cannot be guaranteed to coincide with the ideal Z axis, and the adjustment platform has errors in the machining process, and the ideal position cannot be guaranteed in the rotor adjustment process, so there will be eccentric error in measurement. According to the definition of coaxiality in international standards, the maximum concentricity error of each rotor measurement surface relative to the reference axis is the multi-stage rotor coaxiality error, and the concentricity error of each rotor is twice the eccentric error, so the measurement and adjustment of the eccentric error can realize the measurement and assembly adjustment of the multi-stage rotor coaxiality error. As shown in the figure, the eccentric error will cause the sampling angle to deviate when measuring the axial measurement of the cylindrical member, and the actual sampling angle deviation is expressed as follows: Figure 1

[0137]

[0138] Where p j is the initial eccentricity, α j is the corresponding eccentric angle, r 0j is the fitting radius, φ ij is the actual sampling angle, and θ ij is the ideal sampling angle.

[0139] The single-stage rotor measurement model and the actual sampling angle are respectively

[0140]

[0141]

[0142] Based on the above measurement model, the coaxiality error source can be obtained. Therefore, when the multi-stage rotor is stacked, the error of the single-stage rotor can be separated first, the error source can be gradually eliminated, and the coaxiality can be evaluated according to the formula, and the assembly phase of each stage of rotor is adjusted to make the coaxiality optimal.

[0143] ​In the description of the specification, the description of the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" and the like means that the specific features, structures, materials or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present application. In the specification, the illustrative description of the above terms does not necessarily refer to the same embodiment or example. Also, the specific features, structures, materials or characteristics described can be combined in any appropriate manner in any one or N embodiments or examples. In addition, the person skilled in the art can combine and combine the different embodiments or examples described in the specification and the features of the different embodiments or examples, without contradiction. In addition, the terms "first", "second" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance or implicitly indicating the number of indicated technical features. Therefore, the features limited by "first", "second" can explicitly or implicitly include at least one of the features. In the description of the present application, the meaning of "N" is at least two, for example, two, three, etc., unless otherwise specifically limited. Any process or method described in the flowchart or otherwise described herein can be understood as representing a module, fragment or part of code including one or more executable instructions for implementing custom logic functions or processes, and the scope of the preferred embodiments of the present application includes additional implementations in which the functions can be performed in the order shown or discussed, including in a substantially simultaneous manner or in reverse order according to the functions involved, which should be understood by the person skilled in the art. The embodiments of the present application. In the flowchart or otherwise described herein, logic and / or steps, for example, can be considered as a list of executable instructions for implementing logical functions, which can be embodied in any computer readable medium for use by an instruction execution system, device or apparatus, such as a computer based system, a system including a processor or other system that can fetch and execute instructions from the instruction execution system, device or apparatus. For the purpose of the present specification, "computer readable medium" can be any device that can contain, store, communicate, propagate or transport programs for use by an instruction execution system, device or apparatus or in conjunction with these instruction execution systems, devices or apparatus. More specific examples (non-exhaustive list) of computer readable medium include the following: electrical connections having one or N wires (electronic devices), portable computer diskette (magnetic devices), random access memory (RAM), read only memory (ROM), erasable programmable read only memory (EPROM or flash memory), fiber optic devices, and portable compact disc read only memory (CD ROM).Additionally, a computer readable medium can be paper or other comparable effectively on which the program is printed as there are no media, since, for example, through optical scanning of the paper or other medium, the program can then be edited, interpreted or otherwise processed in such a manner that it can be stored in the computer memory so that, as a result, it is executed by a computer. It should be understood that parts of the present application can be implemented in hardware, software, firmware or a combination thereof. In the above embodiments, the N steps or methods can be implemented by software or firmware stored in the memory and executed by a suitable instruction execution system. As in another embodiment, if implemented in hardware, any of the following technologies known in the art or their combinations can be used: discrete logic circuit with logic gate circuit for implementing logic functions on data signals, application specific integrated circuit with suitable combination logic gate circuit, programmable gate array (PGA), field programmable gate array (FPGA) and the like.

[0144] Those skilled in the art can understand that all or part of the steps carried out by the above-mentioned embodiment methods can be completed by programs instructing relevant hardware, and the programs can be stored in a computer readable storage medium. When the programs are executed, one or a combination of the steps of the method embodiments is included. In addition, each functional unit in each embodiment of the present application can be integrated in one processing module, or each unit can exist physically independently, or two or more units can be integrated in one module. The integrated module can be realized in the form of hardware or in the form of a software functional module. When the integrated module is realized in the form of a software functional module and sold or used as an independent product, it can also be stored in a computer readable storage medium.

[0145] The above is only a preferred embodiment of the aero-engine rotor coaxiality stacking method based on the five-bias axial measurement model, and the protection scope of the aero-engine rotor coaxiality stacking method based on the five-bias axial measurement model is not limited to the above-mentioned embodiments. Any technical solution belonging to the idea belongs to the protection scope of the present application. It should be pointed out that for those skilled in the art, some improvements and changes without departing from the principles of the present application should be considered as the protection scope of the present application.

Claims

1. An aeroengine rotor coaxiality stacking method based on a five-bias axial measurement model, characterized in that: The method comprises the following steps: Step 1: eccentric error causes the sampling angle to deviate during the axial measurement of the cylindrical component, and the actual sampling angle deviation is determined; Step 2: when the measurement direction of the sensor deviates from the rotation direction during the measurement process, the sensor side head deviation error is introduced, the sampling angle deviates, and the actual angle deviation is determined; Step 3: according to the probe radius error, the eccentricity and the inclination system error will interact with the probe radius during the actual measurement, the probe radius has an influence on the eccentricity error, and the eccentricity error is determined; Step 4: the probe support rod is parallel to the vertical direction, the contact direction of the probe and the measured member is horizontal, the measurement error is introduced, the runout error occurs on the surface of the measured point, and the runout error deviation and the profile deviation error are determined; Step 5: the inclination error of the probe support rod causes the error of the probe radius to have an influence on the measurement of the coaxiality, and the profile measurement model and the actual sampling angle are determined; Step 6: based on the profile measurement model, the error of the single-pole rotor is determined, and the coaxiality of the multi-stage rotor is evaluated.

2. The method for aero-engine rotor coaxiality stacking based on five-bias axial measurement model according to claim 1, characterized in that: The step 1 is specifically: The maximum concentricity error of the measurement surface of each stage rotor relative to the reference axis is the coaxiality error of the multi-stage rotor, and the concentricity error of each stage rotor is twice the eccentricity error, so that the measurement and adjustment of the coaxiality error of the multi-stage rotor can be realized through the measurement and adjustment of the eccentricity error, the eccentricity error causes the sampling angle to deviate during the axial measurement of the cylindrical component, and the actual sampling angle deviation is represented by the following formula: where p j is the initial eccentricity, a j is the corresponding eccentric angle, r 0j is the fitting radius, φ ij is the actual sampling angle, and θ ij is the ideal sampling angle.

3. The method for stacking coaxiality of aero-engine rotors based on a five-offset axial measurement model according to claim 2, characterized in that: The step 2 is specifically: When the measurement direction of the sensor deviates from the rotation direction during the measurement process, the sensor side head deviation error is introduced, the sampling angle deviates, and the actual angle deviation is represented by the following formula: Δη i = sin -1 ((m j +p j sin(η ij -α j )) / r 0j ) Wherein, m j is the probe offset, O 2j is the instantaneous center of rotation resulting from the probe offset, Δθ ij is the offset angle of each sampling point of the cross section.

4. The method of claim 3, wherein: the five-bias axial measurement model is based on a five-bias axial measurement model of the form: ###0001### where: ###0002### and ###0003### are the measured values of the five-bias axial measurement model; and ###0004### are the true values of the five-bias axial measurement model. The step 3 is specifically: Since the probe cannot be processed into an ideal point without size, the probe radius error is introduced, the eccentricity, inclination and other system errors will interact with the probe radius during the actual measurement, the probe radius has an influence on the eccentricity error, and the eccentricity error is represented by the following formula: Δη j = sin -1 ((m j +p j sin(η ij -α j )) / (r 0j +Δl ij +r)) 5. The aviation engine rotor coaxiality stacking method based on the five-bias axial measurement model according to claim 4, characterized in that: The step 4 is specifically: The probe support rod is parallel to the vertical direction, the contact direction of the probe and the measured member is horizontal, the mechanical fast processing error and the improper contact force adjustment make it difficult to keep the contact direction horizontal, the measurement error is introduced, the runout error occurs on the surface of the measured point, and the runout error deviation is represented by the following formula: wherein, is the inclination angle of the probe support bar, AA is the ideal contact direction of the probe and the measured object, and BB is the actual contact direction. Since the measured geometric axis and the measurement rotation axis cannot be guaranteed to coincide in the actual measurement, the inclination error is introduced, the inclination error causes the profile measurement to deviate, and the inclination error is represented by the following formula: where g is the geometric axis tilt angle, b j is the angle between the projection direction of the geometric axis on the measurement plane and the initial measurement direction.

6. The method of claim 5, wherein: the five-bias axial measurement model is based on a five-bias axial measurement model of the form: ###0002### where: ###0003### and ###0004### are the measured values of the five-bias axial measurement model; and ###0005### are the true values of the five-bias axial measurement model. The step 5 is specifically: Since the inclination error of the probe support rod causes the error of the probe radius to have an influence on the measurement of the coaxiality, the final profile measurement model and the actual sampling angle are represented by the following formula:

7. The method of claim 6, wherein the method is a method of aeroengine rotor coaxiality stack-up based on a five-bias axial measurement model. The step 6 is specifically: Based on the profile measurement model, the error of the single-pole rotor is obtained, and the error transmission law of the multi-stage rotor stack can be analyzed to evaluate the coaxiality of the multi-stage rotor. The assembly error of the multi-stage rotor is composed of positioning error and orientation error, wherein the positioning error is represented by a translation matrix, and the orientation error is represented by a rotation matrix. Thus, the cumulative eccentric error expression of the multi-stage rotor stack is determined, and the eccentric error of the nth stage rotor is represented by the following formula: Wherein, Trari is the transformation matrix between the two-stage rotor joint surfaces, TraZi is the eccentricity of the ideal center of the rotor, Tracle is the translation transformation matrix of the eccentricity of the reference surface gap of the rotor i, Tradzi is the eccentricity translation transformation matrix caused by the machining error of the reference surface of the rotor i, Traori is the rotation transformation matrix of the rotor i rotor reference surface to the assembly surface rotation center, Rotxi is the rotation matrix of the i-th stage rotor reference surface around the X-axis; Rotyi is the rotation matrix of the i-th stage rotor reference surface around the Y-axis; Qi is the ideal position vector of the center of the i-th stage rotor assembly surface; dQi is the machining error vector of the center position of the i-th stage rotor assembly surface; dQ'i is the gap eccentric position vector of the i-th stage rotor; Rotri is the rotation matrix of the i-th stage rotor around the Z-axis; The center position vector of the assembly surface of the n-th stage rotor after assembly is represented by the following formula: According to the standard definition of coaxiality, the coaxiality of the n-stage rotor is represented by the following formula: Based on the position vector of the axial projection of the center position of each stage rotor, the maximum modulus is twice the optimal coaxiality of the multi-stage mixed fit rotor.

8. An aeroengine rotor coaxiality stacking device based on a five-bias axial measurement model, characterized by: The device comprises: An actual sampling angle offset measurement module, which determines the actual sampling angle offset when the sampling angle of the cylindrical member is offset during axial measurement of the eccentric error during measurement; An actual angle measurement module, which determines the actual angle offset when the measurement direction of the sensor deviates from the rotation direction during the measurement process, introduces the sensor side head offset error, and offsets the sampling angle; An eccentric error module, which determines the eccentric error according to the probe radius error, the actual measurement, the system errors such as eccentricity and inclination, and the influence of the probe radius on the eccentric error; An error offset and profile offset error measurement module, which determines the runout error offset and profile offset error when the probe support rod is parallel to the vertical direction, the contact direction of the probe and the measured member is horizontal, and measurement error is introduced, so that the surface of the measurement point appears runout error; The inclination error of the probe support rod causes the error of the probe radius to affect the measurement of the coaxiality, and the profile measurement model and the actual sampling angle are determined; A multi-stage rotor coaxiality evaluation module, which determines the error of the single-pole rotor based on the profile measurement model, and evaluates the coaxiality of the multi-stage rotor.

9. A computer readable storage medium having stored thereon a computer program, characterized in that, The program is executed by a processor to implement a five-bias axial measurement model-based aero-engine rotor coaxiality stacking method according to any one of claims 1-7.

10. A computer device, comprising: The application relates to a computer readable storage medium, comprising a memory and a processor, wherein the memory stores a computer program, and when the processor runs the computer program stored in the memory, the processor executes an aero-engine rotor coaxiality stacking method based on a five-bias axial measurement model.

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