CN116242299A - Aircraft engine rotor coaxiality stacking method based on five-offset axial measurement model - Google Patents
Aircraft engine rotor coaxiality stacking method based on five-offset axial measurement model Download PDFInfo
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- 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
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Abstract
The invention relates to an aircraft engine rotor coaxiality stacking method based on a five-offset axial measurement model. The invention relates to the technical field of coaxiality measurement, wherein an eccentric error causes the sampling angle to deviate during axial measurement of a cylindrical member during measurement, and the actual sampling angle deviation is determined; the sampling angle is shifted, and the actual angle offset is determined; according to the radius error of the measuring head, the radius of the measuring head affects 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 piece is the horizontal direction, a measuring error is introduced, so that a runout error appears on the surface of the measuring point, and the runout error offset and the contour offset error are determined; the inclination error of the measuring head supporting rod enables the error of the radius of the measuring head to influence the measurement of coaxiality, and a contour measurement model and an actual sampling angle are determined; and determining the error of the monopole rotor based on the contour measurement model, and evaluating the coaxiality of the multi-stage rotor.
Description
Technical Field
The invention relates to the technical field of coaxiality measurement, in particular to an aero-engine rotor coaxiality stacking method based on a five-offset axial measurement model.
Background
The core engine is used as a heart of the aeroengine, and the assembly quality of the core engine directly influences the performance of the aeroengine. The multi-stage rotor assembly quality testing device mainly comprises a multi-stage rotor stack, and coaxiality is a core parameter for testing the multi-stage rotor assembly quality. When the aero-engine is operated at a working speed, such as a common working speed of a civil engine, which is more than 12000rpm, imbalance response caused by coaxiality errors after the multi-stage rotor is assembled can be amplified, so that the engine vibrates, and the blades and the casing are in collision and abrasion. It is counted that more than 70% of faults of the aero-engine are caused by vibration, and about 20% of faults are caused by collision and grinding. Generally, the rubbing and vibration are caused by different axes after assembly. Therefore, the problem of the ultra-poor assembly coaxiality of the multistage rotor of the aero-engine is a core problem which restricts the performance of the engine.
The existing coaxiality measuring method is mainly a rotation axis method, and a plurality of systematic errors exist in the method, and the mutual coupling of the errors can obviously influence the coaxiality measuring precision. Therefore, the coaxiality measurement model is improved, the multisystem errors of the measurement model are effectively separated, and the method has important significance for improving ultra-precise measurement precision and realizing precise model engineering.
When facing to the coaxiality measurement method based on contact, the problem of inaccurate coaxiality measurement caused by five system error couplings of an eccentric error, a measuring head offset error, a measuring head radius error, a measuring head supporting rod inclination error and an inclination error in a device system is urgent to provide a coaxiality measurement model considering the system error of a measuring device, and a theoretical basis is provided for subsequent error separation.
Disclosure of Invention
The invention provides an aircraft engine rotor coaxiality stacking method based on a five-offset axial measurement model, which aims to overcome the defects of the prior art.
It is noted that relational terms such as first and second, and the like are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Moreover, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.
The invention provides an aircraft engine rotor coaxiality stacking method based on a five-offset axial measurement model, which provides the following technical scheme:
an aircraft engine rotor coaxiality stacking method based on a five-offset axial measurement model, the method comprising the steps of:
step 1: the eccentric error causes the sampling angle to deviate when the cylindrical member is axially measured during measurement, and the actual sampling angle deviation is determined;
step 2: when the measuring direction of the sensor deviates from the rotation direction in the measuring process, introducing a sensor side head offset error, offsetting the sampling angle, and determining the actual angle offset;
step 3: according to the radius error of the measuring head, during actual measurement, systematic errors such as eccentricity, inclination and the like can be mutually influenced with the radius of the measuring head, the radius of the measuring head influences the eccentric error, and the eccentric error is determined;
step 4: the measuring head support rod is parallel to the vertical direction, the contact direction of the measuring head and the measured piece is the horizontal direction, a measuring error is introduced, so that a runout error appears on the surface of the measuring point, and the runout error offset and the contour offset error are determined;
step 5: the inclination error of the measuring head supporting rod enables the error of the radius of the measuring head to influence the measurement of coaxiality, and a contour measurement model and an actual sampling angle are determined;
step 6: and determining the error of the monopole rotor based on the contour measurement model, and evaluating the coaxiality of the multi-stage rotor.
Preferably, the step 1 specifically includes:
the maximum value of concentricity errors of all levels of rotor measuring surfaces relative to a reference axis is the coaxiality error of the multi-level rotor, and the concentricity errors of all levels of rotors are 2 times of the eccentricity errors of the multi-level rotor, the coaxiality errors of the multi-level rotors can be measured and assembled and adjusted through the measurement and adjustment of the eccentricity errors, the eccentricity errors cause the sampling angle to deviate during the axial measurement of a cylindrical component during the measurement, and the actual sampling angle deviation is represented by the following steps:
wherein ,pj For initial eccentricity, alpha j For corresponding eccentric angle r 0j To fit radius phi ij For the actual sampling angle, θ ij Is an ideal sampling angle.
Preferably, the step 2 specifically includes:
when the measuring direction of the sensor deviates from the rotation direction in the measuring process, a sensor side head deviation error is introduced, so that the sampling angle is deviated, and the actual angle deviation is expressed by the following formula:
Δη i ＝sin -1 ((m j +p j sin(η ij -α j ))/r 0j )
wherein ,mj For measuring head offset, O 2j For instantaneous centre of rotation, Δθ, due to probe deflection ij Is the offset angle of each sampling point of the cross section.
Preferably, the step 3 specifically includes:
because the measuring head cannot be processed into a non-dimensional ideal point, a measuring head radius error is introduced, and during actual measurement, systematic errors such as eccentricity, inclination and the like can be mutually influenced with the measuring head radius, the measuring head radius influences the eccentric error, and the eccentric error is expressed by the following formula:
Δη j ＝sin -1 ((m j +p j sin(η ij -α j ))/(r 0j +Δl ij +r))。
preferably, the step 4 specifically includes:
the measuring head support rod is parallel to the vertical direction, the contact direction of the measuring head and a measured piece is the horizontal direction, the mechanical quick machining error and the contact force are inappropriately adjusted, the contact direction is difficult to keep horizontal, the measurement error is introduced, the surface of the measuring point is subjected to the jump error, and the jump error offset is represented by the following formula:
wherein ,
for the inclination angle of the measuring head supporting rod, AA is the ideal contact direction of the measuring head and the measured piece, and BB is the actual contact direction;
in actual measurement, the measured geometric axis and the measured rotation axis are difficult to ensure to coincide, and a tilt error is introduced, and the tilt error causes the profile measurement to deviate, and is expressed by the following formula:
wherein ,r0 Is the sampling radius, g is the geometrical axis tilt angle, b j Is the angle between the projection direction of the geometric axis on the measuring plane and the initial measuring direction.
Preferably, the step 5 specifically includes:
the measurement of coaxiality is affected by the error of the radius of the measuring head due to the inclination error of the measuring head supporting rod, and the final contour measurement model and the actual sampling angle are expressed by the following formula:
preferably, the step 6 specifically includes:
based on the contour measurement model, the error of the monopole rotor is obtained, and the error transfer rule of the stacking of the multistage rotors can be analyzed, so that the coaxiality of the multistage rotors is evaluated, the assembly error of the multistage rotors is synthesized by a positioning error and an orientation error, wherein the positioning error is represented by a translation matrix, the orientation error is represented by a rotation matrix, and thus, the cumulative eccentric error expression of the multistage rotors after stacking is determined, and the eccentric error of the nth stage of rotors is represented by the following expression:
trari is a transformation matrix between two rotor joint surfaces, traZi is an eccentric center of an ideal circle of a rotor, tracle is a translation transformation matrix with a rotor i reference surface being eccentric in clearance, tradzi is an eccentric translation transformation matrix caused by a rotor i reference surface machining error, traori is a rotation transformation matrix from a rotor i rotor reference surface to a rotation center of an assembly surface, and Rotxi is a rotation matrix of an i-th rotor reference surface around an X axis; rotyi is a rotation matrix of the ith rotor reference plane around the Y axis; qi is an ideal position vector of the circle center of the assembling surface of the ith rotor; dQi is a machining error vector of the circle center position of the assembling surface of the ith rotor; dQ' i is the i-th stage rotor clearance eccentric position vector; rotri is the rotation matrix of the ith stage rotor around the Z axis;
the center position vector of the assembled surface of the assembled nth-stage rotor is expressed by the following formula:
according to the standard definition of coaxiality, the coaxiality of the n-level rotor is obtained by the following formula:
based on the position vector of axial projection of the axial positions of the rotors at all stages, the largest double of the modes is the optimal coaxiality of the multi-stage hybrid matched rotor.
An aircraft engine rotor coaxiality stacking device based on a five-offset axial measurement model, the device comprising:
the actual sampling angle offset measuring module is used for measuring an axial measurement of the cylindrical component, and determining an actual sampling angle offset;
the actual angle measurement module is used for introducing a sensor side head offset error when the measurement direction of the sensor deviates from the rotation direction in the measurement process of the actual angle measurement module, offsetting the sampling angle and determining the actual angle offset;
the eccentric error module is used for determining the eccentric error according to the influence of the system errors such as eccentricity, inclination and the like on the radius of the measuring head during actual measurement and the influence of the radius of the measuring head on the eccentric error;
the error offset and contour offset error measuring module is used for measuring the offset of the measuring point, wherein the offset of the error and the contour offset error measuring module is parallel to the vertical direction of the measuring head supporting rod, the contact direction of the measuring head and the measured piece is the horizontal direction, and the measuring error is introduced, so that the surface of the measuring point has a runout error, and the runout error offset and the contour offset error are determined;
the inclination error of the measuring head supporting rod enables the error of the radius of the measuring head to influence the measurement of coaxiality, and a contour measurement model and an actual sampling angle are determined;
and the multistage rotor coaxiality evaluation module is used for determining the error of the monopole rotor based on the contour measurement model and evaluating the coaxiality of the multistage rotor.
A computer readable storage medium having stored thereon a computer program for execution by a processor for implementing an aircraft engine rotor coaxiality stacking method as based on a five-offset axial measurement model.
A computer device comprising a memory and a processor, the memory having a computer program stored therein, the processor executing an aircraft engine rotor coaxiality stacking method according to a five-offset axial measurement model when the processor runs the computer program stored in the memory.
The invention has the following beneficial effects:
aiming at the problem of inaccurate coaxiality measurement caused by five system error couplings of an eccentric error, a measuring head offset error, a measuring head radius error and a tilting error in the coaxiality measuring device, the invention provides a corresponding five system error measuring model which is used for separating the measuring error of the axial direction of a cylindrical member. On this basis, the method can guide the elimination of the error brought to the coaxiality during stacking.
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In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are needed in the description of the embodiments or the prior art will be briefly described, and it is obvious that the drawings in the description below are some embodiments of the present invention, and other drawings can be obtained according to the drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic diagram of eccentricity errors;
FIG. 2 is a schematic diagram of a stylus offset error;
FIG. 3 is a schematic diagram of a gauge head radius error;
FIG. 4 is a schematic view of the probe pin tilt error;
FIG. 5 is a diagram of tilt error;
FIG. 6 is a schematic diagram of a stacking model.
Detailed Description
The following description of the embodiments of the present invention will be made apparent and fully in view of the accompanying drawings, in which some, but not all embodiments of the invention are shown. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
In the description of the present invention, it should be noted that the directions or positional relationships indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the directions or positional relationships shown in the drawings, are merely for convenience of describing the present invention and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it should be noted that, unless explicitly specified and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be either fixedly connected, detachably connected, or integrally connected, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.
In addition, the technical features of the different embodiments of the present invention described below may be combined with each other as long as they do not collide with each other.
The present invention will be described in detail with reference to specific examples.
First embodiment:
according to the embodiments shown in fig. 1 to 6, the specific optimization technical scheme adopted by the present invention to solve the above technical problems is as follows: the invention relates to an aircraft engine rotor coaxiality stacking method based on a five-offset axial measurement model.
An aircraft engine rotor coaxiality stacking method based on a five-offset axial measurement model, the method comprising the steps of:
step 1: the eccentric error causes the sampling angle to deviate when the cylindrical member is axially measured during measurement, and the actual sampling angle deviation is determined;
step 2: when the measuring direction of the sensor deviates from the rotation direction in the measuring process, introducing a sensor side head offset error, offsetting the sampling angle, and determining the actual angle offset;
step 3: according to the radius error of the measuring head, during actual measurement, systematic errors such as eccentricity, inclination and the like can be mutually influenced with the radius of the measuring head, the radius of the measuring head influences the eccentric error, and the eccentric error is determined;
step 4: the measuring head support rod is parallel to the vertical direction, the contact direction of the measuring head and the measured piece is the horizontal direction, a measuring error is introduced, so that a runout error appears on the surface of the measuring point, and the runout error offset and the contour offset error are determined;
step 5: the inclination error of the measuring head supporting rod enables the error of the radius of the measuring head to influence the measurement of coaxiality, and a contour measurement model and an actual sampling angle are determined;
step 6: and determining the error of the monopole rotor based on the contour measurement model, and evaluating the coaxiality of the multi-stage rotor.
Specific embodiment II:
the second embodiment of the present application differs from the first embodiment only in that:
the step 1 specifically comprises the following steps:
the maximum value of concentricity errors of all levels of rotor measuring surfaces relative to a reference axis is the coaxiality error of the multi-level rotor, and the concentricity errors of all levels of rotors are 2 times of the eccentricity errors of the multi-level rotor, the coaxiality errors of the multi-level rotors can be measured and assembled and adjusted through the measurement and adjustment of the eccentricity errors, the eccentricity errors cause the sampling angle to deviate during the axial measurement of a cylindrical component during the measurement, and the actual sampling angle deviation is represented by the following steps:
wherein ,pj For initial eccentricity, alpha j For corresponding eccentric angle r 0j To fit radius phi ij For the actual sampling angle, θ ij Is an ideal sampling angle.
Third embodiment:
the difference between the third embodiment and the second embodiment of the present application is only that:
the step 2 specifically comprises the following steps:
when the measuring direction of the sensor deviates from the rotation direction in the measuring process, a sensor side head offset error is introduced, as shown in fig. 2, so that the sampling angle is offset, and the actual angle offset is expressed by the following formula:
Δη i ＝sin -1 ((m j +p j sin(η ij -α j ))/r 0j )
wherein ,mj For measuring head offset, O 2j For instantaneous centre of rotation, Δθ, due to probe deflection ij Is the offset angle of each sampling point of the cross section.
Fourth embodiment:
the fourth embodiment of the present application differs from the third embodiment only in that:
the step 3 specifically comprises the following steps:
because the measuring head cannot be processed into an ideal point without size, and a measuring head radius error is introduced, as shown in fig. 3, during actual measurement, systematic errors such as eccentricity, inclination and the like can be interacted with the measuring head radius, the measuring head radius has an influence on the eccentricity error, and the eccentricity error is expressed by the following formula:
Δη j ＝sin -1 ((m j +p j sin(η ij -α j ))/(r 0j +Δl ij +r))。
fifth embodiment:
the fifth embodiment differs from the fourth embodiment only in that:
the step 4 specifically comprises the following steps:
the measuring head support rod is parallel to the vertical direction, the contact direction of the measuring head and a measured piece is the horizontal direction, the mechanical quick machining error and the contact force are inappropriately adjusted, the contact direction is difficult to keep horizontal, as shown in fig. 4, the measurement error is introduced, the surface of the measuring point is subjected to the jump error, and the deviation of the jump error is represented by the following formula:
wherein ,
for the inclination angle of the measuring head supporting rod, AA is the ideal contact direction of the measuring head and the measured piece, and BB is the actual contact direction;
since in actual measurement, the measured geometric axis and the measured rotation axis are difficult to ensure to coincide, and a tilt error is introduced, as shown in fig. 5, the tilt error causes the profile measurement to deviate, and the tilt error is expressed by the following formula:
wherein ,r0 Is the sampling radius, g is the geometrical axis tilt angle, b j Is the angle between the projection direction of the geometric axis on the measuring plane and the initial measuring direction.
Specific embodiment six:
the difference between the sixth embodiment and the fifth embodiment of the present application is only that:
the step 5 specifically comprises the following steps:
the measurement of coaxiality is affected by the error of the radius of the measuring head due to the inclination error of the measuring head supporting rod, and the final contour measurement model and the actual sampling angle are expressed by the following formula:
specific embodiment seven:
the seventh embodiment of the present application differs from the sixth embodiment only in that:
the step 6 specifically comprises the following steps:
based on the contour measurement model, the error of the monopole rotor is obtained, and the error transfer rule of the stacking of the multistage rotors can be analyzed, so that the coaxiality of the multistage rotors is evaluated, the assembly error of the multistage rotors is synthesized by a positioning error and an orientation error, wherein the positioning error is represented by a translation matrix, the orientation error is represented by a rotation matrix, and thus, the cumulative eccentric error expression of the multistage rotors after stacking is determined, and the eccentric error of the nth stage of rotors is represented by the following expression:
trari is a transformation matrix between two rotor joint surfaces, traZi is an eccentric center of an ideal circle of a rotor, tracle is a translation transformation matrix with a rotor i reference surface being eccentric in clearance, tradzi is an eccentric translation transformation matrix caused by a rotor i reference surface machining error, traori is a rotation transformation matrix from a rotor i rotor reference surface to a rotation center of an assembly surface, and Rotxi is a rotation matrix of an i-th rotor reference surface around an X axis; rotyi is a rotation matrix of the ith rotor reference plane around the Y axis; qi is an ideal position vector of the circle center of the assembling surface of the ith rotor; dQi is a machining error vector of the circle center position of the assembling surface of the ith rotor; dQ' i is the i-th stage rotor clearance eccentric position vector; rotri is the rotation matrix of the ith stage rotor around the Z axis;
the center position vector of the assembled surface of the assembled nth-stage rotor is expressed by the following formula:
according to the standard definition of coaxiality, the coaxiality of the n-level rotor is obtained by the following formula:
based on the position vector of axial projection of the axial positions of the rotors at all stages, the largest double of the modes is the optimal coaxiality of the multi-stage hybrid matched rotor.
Specific embodiment eight:
the eighth embodiment of the present application differs from the seventh embodiment only in that:
the invention provides an aircraft engine rotor coaxiality stacking device based on a five-offset axial measurement model, which comprises:
the actual sampling angle offset measuring module is used for measuring an axial measurement of the cylindrical component, and determining an actual sampling angle offset;
the actual angle measurement module is used for introducing a sensor side head offset error when the measurement direction of the sensor deviates from the rotation direction in the measurement process of the actual angle measurement module, offsetting the sampling angle and determining the actual angle offset;
the eccentric error module is used for determining the eccentric error according to the influence of the system errors such as eccentricity, inclination and the like on the radius of the measuring head during actual measurement and the influence of the radius of the measuring head on the eccentric error;
the error offset and contour offset error measuring module is used for measuring the offset of the measuring point, wherein the offset of the error and the contour offset error measuring module is parallel to the vertical direction of the measuring head supporting rod, the contact direction of the measuring head and the measured piece is the horizontal direction, and the measuring error is introduced, so that the surface of the measuring point has a runout error, and the runout error offset and the contour offset error are determined;
the inclination error of the measuring head supporting rod enables the error of the radius of the measuring head to influence the measurement of coaxiality, and a contour measurement model and an actual sampling angle are determined;
and the multistage rotor coaxiality evaluation module is used for determining the error of the monopole rotor based on the contour measurement model and evaluating the coaxiality of the multistage rotor.
Specific embodiment nine:
embodiment nine of the present application differs from embodiment eight only in that:
the invention provides a computer readable storage medium having stored thereon a computer program for execution by a processor for implementing an aircraft engine rotor coaxiality stacking method based on a five-offset axial measurement model.
Specific embodiment ten:
the tenth embodiment differs from the ninth embodiment only in that:
the invention provides computer equipment, which comprises 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 aeroengine rotor coaxiality stacking method based on a five-offset axial measurement model.
Specific example eleven:
embodiment eleven of the present application differs from embodiment eleven only in that:
because the rotary main shaft has radial rotary errors, angular rotary errors and the like, even if the rotary precision is high, the rotary axis cannot be ensured to coincide with an ideal Z axis, and the adjustment platform has errors in the processing process and cannot ensure that the ideal position is reached in the rotor adjustment process, the eccentric errors can exist in the measurement process. According to the definition of the international standard on the coaxiality, the maximum value of the concentricity errors of the measuring surfaces of the rotors at each stage relative to the reference axis is the coaxiality error of the rotors at each stage, and the concentricity error of the rotors at each stage is 2 times of the eccentric error of the rotors at each stage, so that the coaxiality error measurement and the assembly adjustment of the rotors at each stage can be realized through the measurement and the adjustment of the eccentric error. As shown in fig. 1, the eccentricity error causes the sampling angle of the axial measurement of the cylindrical member to be shifted when the measurement is performed, and the actual sampling angle shift amount is expressed as follows:
wherein pj For initial eccentricity, alpha j For corresponding eccentric angle r 0j To fit radius phi ij For the actual sampling angle, θ ij Is an ideal sampling angle.
The single-stage rotor measuring model and the actual sampling angle are respectively
Based on the measurement model, a coaxiality error source can be obtained. Therefore, when the rotors are stacked, the errors of the single-stage rotors can be separated, error sources are eliminated step by step, coaxiality is evaluated according to a formula, and meanwhile, the assembly phases of the rotors at all stages are adjusted, so that the coaxiality is optimal.
In the description of the present specification, a description referring to terms "one embodiment," "some embodiments," "examples," "specific examples," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present invention. In this specification, schematic representations of the above terms are not necessarily directed to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or N embodiments or examples. Furthermore, the different embodiments or examples described in this specification and the features of the different embodiments or examples may be combined and combined by those skilled in the art without contradiction. Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "N" means at least two, for example, two, three, etc., unless specifically defined otherwise. Any process or method descriptions in flow charts or otherwise described herein may be understood as representing modules, segments, or portions of code which include one or more N executable instructions for implementing specific logical functions or steps of the process, and further implementations are included within the scope of the preferred embodiment of the present invention in which functions may be executed out of order from that shown or discussed, including substantially concurrently or in reverse order, depending on the functionality involved, as would be understood by those reasonably skilled in the art of the embodiments of the present invention. Logic and/or steps represented in the flowcharts or otherwise described herein, e.g., a ordered listing of executable instructions for implementing logical functions, can be embodied in any computer-readable medium for use by or in connection with an instruction execution system, apparatus, or device, such as a computer-based system, processor-containing system, or other system that can fetch the instructions from the instruction execution system, apparatus, or device and execute the instructions. For the purposes of this description, a "computer-readable medium" can be any means that can contain, store, communicate, propagate, or transport the program for use by or in connection with the instruction execution system, apparatus, or device. More specific examples (a non-exhaustive list) of the computer-readable medium would include the following: an electrical connection (electronic device) having one or N wires, a portable computer cartridge (magnetic device), a Random Access Memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical fiber device, and a portable compact disc read-only memory (CDROM). In addition, the computer readable medium may even be paper or other suitable medium on which the program is printed, as the program may be electronically captured, via, for instance, optical scanning of the paper or other medium, then compiled, interpreted or otherwise processed in a suitable manner, if necessary, and then stored in a computer memory. It is to be understood that portions of the present invention may be implemented in hardware, software, firmware, or a combination thereof. In the above-described embodiments, the N steps or methods may be implemented in software or firmware stored in a memory and executed by a suitable instruction execution system. As with the other embodiments, if implemented in hardware, may be implemented using any one or combination of the following techniques, as is well known in the art: discrete logic circuits having logic gates for implementing logic functions on data signals, application specific integrated circuits having suitable combinational logic gates, programmable Gate Arrays (PGAs), field Programmable Gate Arrays (FPGAs), and the like.
Those of ordinary skill in the art will appreciate that all or a portion of the steps carried out in the method of the above-described embodiments may be implemented by a program to instruct related hardware, where the program may be stored in a computer readable storage medium, and where the program, when executed, includes one or a combination of the steps of the method embodiments. In addition, each functional unit in the embodiments of the present invention may be integrated in one processing module, or each unit may exist alone physically, or two or more units may be integrated in one module. The integrated modules may be implemented in hardware or in software functional modules. The integrated modules may also be stored in a computer readable storage medium if implemented in the form of software functional modules and sold or used as a stand-alone product.
The above description is only a preferred implementation manner of the method for stacking the coaxiality of the aero-engine rotor based on the five-offset axial measurement model, and the protection scope of the method for stacking the coaxiality of the aero-engine rotor based on the five-offset axial measurement model is not limited to the above embodiments, and all technical solutions under the concept belong to the protection scope of the invention. It should be noted that modifications and variations can be made by those skilled in the art without departing from the principles of the present invention, which is also considered to be within the scope of the present invention.
Claims (10)
1. An aircraft engine rotor coaxiality stacking method based on a five-offset axial measurement model is characterized by comprising the following steps of: the method comprises the following steps:
step 1: the eccentric error causes the sampling angle to deviate when the cylindrical member is axially measured during measurement, and the actual sampling angle deviation is determined;
step 2: when the measuring direction of the sensor deviates from the rotation direction in the measuring process, introducing a sensor side head offset error, offsetting the sampling angle, and determining the actual angle offset;
step 3: according to the radius error of the measuring head, during actual measurement, systematic errors such as eccentricity, inclination and the like can be mutually influenced with the radius of the measuring head, the radius of the measuring head influences the eccentric error, and the eccentric error is determined;
step 4: the measuring head support rod is parallel to the vertical direction, the contact direction of the measuring head and the measured piece is the horizontal direction, a measuring error is introduced, so that a runout error appears on the surface of the measuring point, and the runout error offset and the contour offset error are determined;
step 5: the inclination error of the measuring head supporting rod enables the error of the radius of the measuring head to influence the measurement of coaxiality, and a contour measurement model and an actual sampling angle are determined;
step 6: and determining the error of the monopole rotor based on the contour measurement model, and evaluating the coaxiality of the multi-stage rotor.
2. The aircraft engine rotor coaxiality stacking method based on the five-offset axial measurement model, which is characterized by comprising the following steps of: the step 1 specifically comprises the following steps:
the maximum value of concentricity errors of all levels of rotor measuring surfaces relative to a reference axis is the coaxiality error of the multi-level rotor, and the concentricity errors of all levels of rotors are 2 times of the eccentricity errors of the multi-level rotor, the coaxiality errors of the multi-level rotors can be measured and assembled and adjusted through the measurement and adjustment of the eccentricity errors, the eccentricity errors cause the sampling angle to deviate during the axial measurement of a cylindrical component during the measurement, and the actual sampling angle deviation is represented by the following steps:
wherein ,pj For initial eccentricity, alpha j For corresponding eccentric angle r 0j To fit radius phi ij For the actual sampling angle, θ ij Is an ideal sampling angle.
3. The aircraft engine rotor coaxiality stacking method based on the five-offset axial measurement model is characterized by comprising the following steps of: the step 2 specifically comprises the following steps:
when the measuring direction of the sensor deviates from the rotation direction in the measuring process, a sensor side head deviation error is introduced, so that the sampling angle is deviated, and the actual angle deviation is expressed by the following formula:
Δη i ＝sin -1 ((m j +p j sin(η ij -α j ))/r 0j )
wherein ,mj For measuring head offset, O 2j For instantaneous centre of rotation, Δθ, due to probe deflection ij Is the offset angle of each sampling point of the cross section.
4. The aircraft engine rotor coaxiality stacking method based on the five-offset axial measurement model, which is characterized by comprising the following steps of: the step 3 specifically comprises the following steps:
because the measuring head cannot be processed into a non-dimensional ideal point, a measuring head radius error is introduced, and during actual measurement, systematic errors such as eccentricity, inclination and the like can be mutually influenced with the measuring head radius, the measuring head radius influences the eccentric error, and the eccentric error is expressed by the following formula:
Δη j ＝sin -1 ((m j +p j sin(η ij -α j ))/(r 0j +Δl ij +r))。
5. the aircraft engine rotor coaxiality stacking method based on the five-offset axial measurement model, which is disclosed by claim 4, is characterized by comprising the following steps of:
the step 4 specifically comprises the following steps:
the measuring head support rod is parallel to the vertical direction, the contact direction of the measuring head and a measured piece is the horizontal direction, the mechanical quick machining error and the contact force are inappropriately adjusted, the contact direction is difficult to keep horizontal, the measurement error is introduced, the surface of the measuring point is subjected to the jump error, and the jump error offset is represented by the following formula:
wherein ,
for the inclination angle of the measuring head supporting rod, AA is the ideal contact direction of the measuring head and the measured piece, and BB is the actual contact direction;
in actual measurement, the measured geometric axis and the measured rotation axis are difficult to ensure to coincide, and a tilt error is introduced, and the tilt error causes the profile measurement to deviate, and is expressed by the following formula:
wherein ,r0 Is the sampling radius, g is the geometrical axis tilt angle, b j Is the angle between the projection direction of the geometric axis on the measuring plane and the initial measuring direction.
6. The aircraft engine rotor coaxiality stacking method based on the five-offset axial measurement model, which is characterized by comprising the following steps of: the step 5 specifically comprises the following steps:
the measurement of coaxiality is affected by the error of the radius of the measuring head due to the inclination error of the measuring head supporting rod, and the final contour measurement model and the actual sampling angle are expressed by the following formula:
7. the aircraft engine rotor coaxiality stacking method based on the five-offset axial measurement model, which is characterized by comprising the following steps of: the step 6 specifically comprises the following steps:
based on the contour measurement model, the error of the monopole rotor is obtained, and the error transfer rule of the stacking of the multistage rotors can be analyzed, so that the coaxiality of the multistage rotors is evaluated, the assembly error of the multistage rotors is synthesized by a positioning error and an orientation error, wherein the positioning error is represented by a translation matrix, the orientation error is represented by a rotation matrix, and thus, the cumulative eccentric error expression of the multistage rotors after stacking is determined, and the eccentric error of the nth stage of rotors is represented by the following expression:
trari is a transformation matrix between two rotor joint surfaces, traZi is an eccentric center of an ideal circle of a rotor, tracle is a translation transformation matrix with a rotor i reference surface being eccentric in clearance, tradzi is an eccentric translation transformation matrix caused by a rotor i reference surface machining error, traori is a rotation transformation matrix from a rotor i rotor reference surface to a rotation center of an assembly surface, and Rotxi is a rotation matrix of an i-th rotor reference surface around an X axis; rotyi is a rotation matrix of the ith rotor reference plane around the Y axis; qi is an ideal position vector of the circle center of the assembling surface of the ith rotor; dQi is a machining error vector of the circle center position of the assembling surface of the ith rotor; dQ' i is the i-th stage rotor clearance eccentric position vector; rotri is the rotation matrix of the ith stage rotor around the Z axis;
the center position vector of the assembled surface of the assembled nth-stage rotor is expressed by the following formula:
according to the standard definition of coaxiality, the coaxiality of the n-level rotor is obtained by the following formula:
based on the position vector of axial projection of the axial positions of the rotors at all stages, the largest double of the modes is the optimal coaxiality of the multi-stage hybrid matched rotor.
8. An aeroengine rotor coaxiality stacking device based on a five-offset axial measurement model is characterized in that: the device comprises:
the actual sampling angle offset measuring module is used for measuring an axial measurement of the cylindrical component, and determining an actual sampling angle offset;
the actual angle measurement module is used for introducing a sensor side head offset error when the measurement direction of the sensor deviates from the rotation direction in the measurement process of the actual angle measurement module, offsetting the sampling angle and determining the actual angle offset;
the eccentric error module is used for determining the eccentric error according to the influence of the system errors such as eccentricity, inclination and the like on the radius of the measuring head during actual measurement and the influence of the radius of the measuring head on the eccentric error;
the error offset and contour offset error measuring module is used for measuring the offset of the measuring point, wherein the offset of the error and the contour offset error measuring module is parallel to the vertical direction of the measuring head supporting rod, the contact direction of the measuring head and the measured piece is the horizontal direction, and the measuring error is introduced, so that the surface of the measuring point has a runout error, and the runout error offset and the contour offset error are determined;
the inclination error of the measuring head supporting rod enables the error of the radius of the measuring head to influence the measurement of coaxiality, and a contour measurement model and an actual sampling angle are determined;
and the multistage rotor coaxiality evaluation module is used for determining the error of the monopole rotor based on the contour measurement model and evaluating the coaxiality of the multistage rotor.
9. A computer readable storage medium having stored thereon a computer program, the program being executed by a processor for implementing an aircraft engine rotor coaxiality stacking method based on a five-offset axial measurement model as claimed in claims 1-7.
10. A computer device comprising a memory and a processor, the memory having stored therein a computer program, which when executed by the processor performs an aircraft engine rotor coaxiality stacking method based on a five-bias axial measurement model as claimed in claims 1-7.
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