CN113588277A - Vibration measuring device for multi-size outline rotor of engine and digital twinning method thereof - Google Patents
Vibration measuring device for multi-size outline rotor of engine and digital twinning method thereof Download PDFInfo
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- CN113588277A CN113588277A CN202110913743.8A CN202110913743A CN113588277A CN 113588277 A CN113588277 A CN 113588277A CN 202110913743 A CN202110913743 A CN 202110913743A CN 113588277 A CN113588277 A CN 113588277A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B11/00—Measuring arrangements characterised by the use of optical techniques
- G01B11/02—Measuring arrangements characterised by the use of optical techniques for measuring length, width or thickness
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01H—MEASUREMENT OF MECHANICAL VIBRATIONS OR ULTRASONIC, SONIC OR INFRASONIC WAVES
- G01H1/00—Measuring characteristics of vibrations in solids by using direct conduction to the detector
- G01H1/003—Measuring characteristics of vibrations in solids by using direct conduction to the detector of rotating machines
- G01H1/006—Measuring characteristics of vibrations in solids by using direct conduction to the detector of rotating machines of the rotor of turbo machines
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Abstract
The invention relates to a vibration measuring device for a multi-size outline rotor of an engine and a digital twinning method thereof, wherein the device comprises a vibration measuring component and a data acquisition component; the vibration measurement assembly comprises an upright post, a beam structure, a three-degree-of-freedom sensor bracket adjusting mechanism and a base; the data acquisition component comprises a test computer, an LMS test system, an infrared displacement sensor, a rotary encoder and USBCAN equipment. The invention can solve the problems of complicated repeated distance and angle debugging, incapability of realizing small-distance intensive arrangement of infrared displacement sensors in the axial direction of a rotor due to the volume limitation of the magnetic gauge stand in the existing vibration measurement technology, measurement error caused by inaccurate arrangement of the magnetic gauge stand in the existing vibration measurement technology, difficult positioning of small-angle deviation or small-distance deviation generated when the magnetic gauge stand is finally locked and the like. And the digital twin technology is applied to the test of the rotor of the aircraft engine, so that the advancement of the rotor vibration measuring technology of the aircraft engine is improved.
Description
Technical Field
The invention relates to the technical field of aero-engine testing, in particular to a vibration measuring device for a multi-size outline rotor of an engine and a digital twinning method thereof.
Background
The existing vibration measurement technology is mainly a vibration measurement device composed of a distance regulator, an infrared displacement sensor fixer and the like, and a vibration measurement system can be formed by the infrared distance infrared displacement sensor and a data acquisition unit, and is widely applied to occasions of vibration tests of machine tool rotating shafts and engine rotors or other rotating machines. A conventional distance adjuster generally includes a magnetic base and a fixing bolt, and is disclosed in patent document CN 104776987A. The existing vibration measuring device is mainly characterized in that a magnetic gauge stand is fixed on a base, a slide rail is fixed on the magnetic gauge stand through bolts, a sensor support is fixed at the appointed position of the slide rail through two bolts, an infrared displacement sensor is fixed on the sensor support through a screw, and the infrared displacement sensor measuring head and the axis of a measured rotor are located on the same horizontal plane by adjusting the position of the sensor support on each distance adjuster. A plurality of magnetic gauge stands can be arranged in the existing vibration measuring device at the same time, the thickness of each magnetic gauge stand is 50mm, and the distance between two infrared displacement sensors is 100 mm.
Firstly, the magnetic gauge stand in the traditional vibration measurement technology cannot realize small-space dense arrangement in the axial direction of the rotor due to self volume limitation, and when the adjacent space of required measurement points is smaller than the self thickness of the magnetic gauge stand, the specified test requirement is difficult to be completed by adopting the vibration measurement technology. The thickness of the magnetic gauge stand is 50mm, and when the distance between the required measuring points is less than 50mm, the requirements that the two vibration measuring devices are on a straight line parallel to the axis of the rotor and the measuring head is perpendicular to the measured object and the like are met, the situation that the test cannot be accurately finished can be generated, and the requirements are common requirements which need to be met in the test of the rotor of the aero-engine. Secondly, although the existing vibration measurement technology generally has the advantages of multiple degrees of freedom, flexibility and the like, the characteristic is not very suitable for the engine rotor with unique vibration measurement requirements, and even some unnecessary defects are generated. At present, most aeroengine rotors have similar outline characteristics, and meanwhile, test measuring points are often only distributed on a horizontal plane or a vertical plane coplanar with the axis of the rotor, so that the multi-degree-of-freedom and flexibility characteristics of the traditional vibration measurement technology are not important when the aeroengine rotors are used, but various problems can be caused by excessive degrees of freedom and flexibility, such as the problem of measurement errors caused by inaccurate arrangement of a magnetic gauge stand in the existing vibration measurement technology, the problem of positioning difficulty caused by small-angle deviation or small-distance deviation easily generated when the magnetic gauge stand is finally locked, and the translational degree of freedom along X, Y, Z and the rotational degree of freedom around a Z axis exist. Thirdly, under the condition that the number of the measuring points to be arranged is large, a plurality of vibration measuring devices need to be arranged at the same time in the existing vibration measuring technology, and further the problem of complex repeated distance and angle debugging is caused. Obviously, when the number of the measuring points N is large, a large amount of time is consumed in debugging, the progress of test debugging is greatly influenced, the progress of the whole test is influenced, and further vibration characteristic analysis is not facilitated. And a large number of infrared displacement sensor measuring points are often arranged in the vibration test of the aeroengine, and if the traditional vibration measurement technology is adopted, a large amount of time is wasted only in the test debugging stage, so that the test efficiency is greatly reduced, and the development progress of the engine is even further influenced. The existing vibration measurement technology is usually limited to the acquisition of displacement signal data, the characteristics of stress distribution or deformation cloud charts and the like of vibration measurement objects in the test process cannot be directly obtained, and the higher requirements of the advanced test technology in the high-quality development work of an aircraft engine cannot be met.
Therefore, the existing vibration measurement technologies all have certain defects and shortcomings, and whether the existing vibration measurement technologies can produce good technical effects in practical application is still to be further discussed.
Disclosure of Invention
In view of the above problems, an object of the present invention is to provide a vibration measuring device for a rotor having a multi-size outer contour of an engine. Through changing sensor support structural design among the technique of testing vibration, solve repeated debugging distance, loaded down with trivial details of angle, current technique of testing vibration can't realize the closely spaced infrared ray displacement sensor of arranging of underspaced on the rotor axial direction because magnetic gauge stand self volume restriction, the measurement error problem that inaccurate results in was put to magnetic gauge stand among the current technique of testing vibration and the magnetic gauge stand finally when locking the emergence small-angle skew or the difficult scheduling problem of location of small distance skew.
Another object of the present invention is to provide a digital twinning method for a multi-sized profile rotor of an engine. The deformation cloud chart of the rotor in the testing process is obtained in real time through interaction of sensor data and computer simulation software, the digital twin technology is applied to the test of the rotor of the aero-engine, and the advancement of the rotor vibration measuring technology of the aero-engine is improved.
The technical scheme adopted by the invention is as follows:
the invention provides a vibration measuring device for a multi-size outline rotor of an engine and a digital twinning method thereof, wherein the device comprises a vibration measuring component and a data acquisition component;
the vibration measurement assembly comprises an upright post, a beam structure, a three-degree-of-freedom sensor bracket adjusting mechanism and a base; the three-degree-of-freedom sensor support adjusting mechanisms are respectively arranged on the inner surface of the stand column on one side and the lower surface of the beam structure;
the three-degree-of-freedom sensor support adjusting mechanism comprises an X-direction guide rail, a Y-direction guide rail, a Z-direction guide rail, a sensor support and an infrared displacement sensor; the X-direction guide rails are arranged on the upper side and the lower side of the middle part of the inner surface of the upright post and on the left side and the right side of the middle part of the lower surface of the cross beam structure at intervals, the Z-direction guide rails are arranged between the two X-direction guide rails at intervals, and the X-direction guide rails and the Z-direction guide rails form a # -shaped structure; one end of the Y-direction guide rail is connected with the middle part of the Z-direction guide rail; the sensor bracket is arranged between the upper surfaces of the other ends of the two Y-direction guide rails, and the infrared displacement sensors are respectively and uniformly arranged along the X-direction guide rails and are connected with the sensor bracket;
the data acquisition assembly is connected with the sensor bracket.
Further, the sensor bracket comprises a sensor integration plate sliding block, a sensor integration plate and a sensor switching fixing plate; the sensor integrated board sliding blocks are respectively arranged on the upper surface of the end part of the guide rail in the Y direction, the sensor integrated board is arranged on the upper surface of the sensor integrated board sliding blocks, the sensor switching fixing plates are respectively and uniformly arranged on the upper surface of the sensor integrated board in the transverse direction, and the infrared displacement sensors are respectively and correspondingly arranged on one side of each sensor switching fixing plate.
Further, the sensor switching fixing plate comprises a base and a thin-wall plate; the thin-wall plate is vertically fixed on one side of the base, and the base is fixedly connected with the corresponding position of the upper surface of the sensor integration plate.
Further, the data acquisition assembly comprises a test computer, an LMS test system, a rotary encoder and USBCAN equipment; the testing computer is connected with an LMS testing system through a network cable, the LMS testing system is connected with an infrared displacement sensor through a front end connecting line, the rotary encoder is fixed at the end of the rotor shaft and transmits signals to the USBCAN equipment through a CAN local area network, and the USBCAN equipment further transmits the signals to a testing computer network protocol, namely to the testing computer.
Further, the upright column comprises an upright column bottom plate, a corner support, an upright column section bar and an upright column end plate; the upright post bottom plate is fixed on the base, the bottom of the upright post sectional material is fixed on the upright post bottom plate through a corner support, and the upright post end face plate is fixed at the top end of the upright post sectional material.
The method comprises the following steps:
s1, extracting rotor speed data in real time; fixing a rotary encoder to the shaft end of the rotor, and when the rotor rotates, the rotary encoder rotates along with the rotor and obtains real-time rotating speed data of the rotor;
s2, intermediately converting the rotating speed data; the rotary encoder transmits the speed signal to USBCAN equipment through a local area network CAN, and the USBCAN serves as a signal transmission medium to prepare for transmission to a test computer in the next step;
s3, receiving a rotation speed signal of the test computer; the USBCAN equipment further transmits the speed signal to the test computer through a corresponding matching network protocol;
s4, leading in a speed signal; after the test computer obtains the speed signal, setting the signal data as the rotation driving speed of the rotor in the ADAMS to realize the consistency of the rotation speed of the ADAMS and the rotation speed of the rotor in the entity space;
s5, setting software; after the rotor is set to rotate and drive, all parts in the ADAMS are subjected to flexible processing, and each part is divided into grids to prepare for obtaining a deformed cloud picture; then, performing kinematic simulation analysis on the rotor system to obtain a deformation cloud picture of the rotor system changing along with the rotating speed, and extracting corresponding real-time acceleration and speed curves of different nodes;
s6, analyzing results; according to the deformation cloud picture of the rotor system changing along with the rotating speed and the corresponding acceleration and speed curve obtained in the last step, the maximum deformation of each part of the rotor system is observed in real time, and the rotor system in the physical space is analyzed in real time, protected from damage and evaluated in reliability;
s7, optimizing the structure; and further optimizing the rotor system structure according to the real-time analysis, damage protection, reliability evaluation and the like of the rotor system in the last step, and pertinently enhancing the structural strength of the rotor to reduce the maximum deformation displacement.
Compared with the prior art, the invention has the following beneficial effects:
1. according to the vibration measuring device for the multi-size outline rotor of the engine, the sensor integrated plate structure reflecting the integration idea is designed, so that the simultaneous arrangement of the single-sensor bracket and the multiple infrared displacement sensors is realized, and the time consumption problem of repeated debugging is solved. Compared with the prior art, the scheme of the invention only needs to use the sensor integration board as a reference when debugging the testing distance, angle and the like, when the relative position relationship between the sensor integration board and the measuring points is accurate, the position relationship between each infrared displacement sensor and the corresponding measuring point can simultaneously meet the requirements, thereby avoiding the repeated adjustment of the position relationship between a plurality of infrared displacement sensors and the measuring points, solving the time-consuming problem of repeated debugging and greatly accelerating the overall progress of the test;
2. by designing a thin-wall type sensor switching fixing plate and combining a sensor integration plate, the axial small-interval dense arrangement meeting the test requirement of an aircraft engine rotor is realized, and the interference problem is solved; compared with the prior art, the magnetic gauge stand which is originally responsible for the position adjusting function of the sensor bracket in the scheme of the invention occupies a larger space, the axial small-distance arrangement of the infrared displacement sensor is realized under the condition of avoiding interference, and the minimum measuring point distance which can be realized is changed from 50mm to 38 mm;
3. by designing X, Y, Z three-degree-of-freedom sensor support adjusting mechanism, the limitation on the degree of freedom of the infrared displacement sensor is realized, and the problem of inaccurate positioning and clamping is solved. Compared with the prior art, the scheme of the invention ensures that the position adjustment of the infrared displacement sensor is completely finished by the X, Y, Z guide rail of the adjusting mechanism, and the spatial freedom degree of the measuring head of the infrared displacement sensor is only limited to three translational freedom degrees, thereby solving the problem of inaccurate positioning and clamping caused by excessive flexibility and freedom degrees of the sensor bracket;
4. the invention provides a digital twinning method for a multi-size outline rotor of an engine, which realizes real-time interaction of an aircraft engine rotor in an entity space and a virtual space by establishing a univariate digital twinning model based on ADAMS and solves the problem that the current vibration measurement technology cannot meet advanced test requirements. Compared with the prior art, the vibration measurement technology of the scheme of the invention has more advanced innovation, and can obtain the displacement signal of the rotor and obtain the deformation cloud picture of the rotor on a computer in real time.
Drawings
FIG. 1 is a schematic overall structure diagram of a vibration measuring device for a multi-size profile rotor of an engine, which is provided by the invention;
FIG. 2 is a schematic structural view of the sensor board and the sensor adapter plate of FIG. 1;
FIG. 3 is a schematic diagram of a sensor plate configuration for a real engine profile;
FIG. 4 is a schematic diagram of a test scenario for a different profile rotor;
FIG. 5 is a schematic view of a portion of the enlarged structure of FIG. 1;
FIG. 6 is a flow chart of a digital twinning method implementation;
FIG. 7 is a schematic diagram of a time consuming comparison of a conventional test protocol to the present invention;
FIG. 8 is a schematic diagram of the comparison of the degree of freedom of a conventional test scheme and the vibration measuring device of the present invention;
FIG. 9 is a virtual space rotor drive speed curve;
FIG. 10 is a cloud of rotor deformation at different times as a function of rotational speed in virtual space.
Wherein, the reference numbers: 1-a column bottom plate; 2-corner brace; 3-column section bar; 4-sensor integrated board slider; 5-a sensor integrated board; 6-a sensor switching fixing plate; 61-a base; 62-thin walled plate; 7-infrared displacement sensor; 8-column end panels; 9-a beam structure; a 10-Z-direction guide rail; 11-X direction guide rails; a 12-Y directional guide rail; 13-a base; 14-test computer; 15-LMS test system.
Detailed Description
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
It should be noted that in the description of the present invention, the terms "upper", "lower", "top", "bottom", "one side", "the other side", "left", "right", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of describing the present invention and simplifying the description, but do not mean that a device or an element must have a specific orientation, be configured and operated in a specific orientation.
Referring to fig. 1 to 10, a specific structure of an embodiment of a vibration measuring device for a multi-size profile rotor of an engine and a digital twinning method thereof according to the present invention is shown. The device comprises a vibration measurement component and a data acquisition component;
as shown in fig. 1 and 2, the vibration measurement assembly includes an upright post, a beam structure 9, a three-degree-of-freedom sensor support adjustment mechanism, and a base 13; the upright comprises an upright bottom plate 1, a corner support 2, an upright section bar 3 and an upright end plate 8; the upright post bottom plate 1 is fixed on the base 13, the bottom of the upright post sectional material 3 is fixed on the upright post bottom plate 1 through the angle brace 2, and the upright post end panel 8 is fixed at the top end of the upright post sectional material; the upright columns are symmetrically arranged on the left side and the right side of the upper surface of the base 13 in pairs, namely four upright columns are arranged in a rectangular shape and serve as a main body supporting structure of the vibration measuring assembly; the beam structure 9 is arranged between the upper parts of the upright columns on the two sides, and the distance between the beam structure 9 and the top ends of the upright columns is 100 mm; the three-degree-of-freedom sensor support adjusting mechanisms are respectively arranged on the inner surface of the stand column on one side and the lower surface of the beam structure 9.
The three-degree-of-freedom sensor support adjusting mechanism comprises an X-direction guide rail 11, a Y-direction guide rail 12, a Z-direction guide rail 10, a sensor support and an infrared displacement sensor 7; the X-direction guide rails 11 are arranged on the upper side and the lower side of the middle part of the inner surface of the upright post and the left side and the right side of the middle part of the lower surface of the cross beam structure 9 at intervals, and the X-direction guide rails 11 are connected with the upright post and the cross beam structure 9 through bolts; the Z-direction guide rails 10 are connected between the two X-direction guide rails 11 at certain intervals through bolts, and the two X-direction guide rails 11 and the two Z-direction guide rails 10 form a # -shaped structure; one end of the Y-direction guide rail 11 is connected with the middle part of the Z-direction guide rail 10 through a bolt and is vertical to the Z-direction guide rail 10; the sensor support is arranged between the upper surfaces of the other ends of the two Y-direction guide rails 12, and the infrared displacement sensors 7 are respectively and uniformly arranged along the direction of the X-direction guide rails 11 and are connected with the sensor support. Wherein, each guide rail and the beam structure 9 are processed by section bars.
The sensor bracket comprises a sensor integration plate sliding block 4, a sensor integration plate 5 and a sensor transfer fixing plate 6; the sensor integration plate sliding blocks 4 are respectively connected to the upper surfaces of the end parts of the two Y-direction guide rails 12 through bolts, the sensor integration plates 5 are connected to the upper surfaces of the sensor integration plate sliding blocks 4 through bolts, the sensor transfer fixing plates 6 are respectively and uniformly arranged on the upper surfaces of the sensor integration plates 5 in the transverse direction through bolts, and the infrared displacement sensors 7 are respectively and correspondingly installed on one side of each sensor transfer fixing plate 6 through screws; in this embodiment, the sensor adapter fixing plate 6 includes a base 61 and a thin-wall plate 62; the thin-wall plate 62 is vertically fixed on one side of the base 61, the base 61 is fixedly connected with the corresponding position of the upper surface of the sensor integration plate 5, and the infrared displacement sensors 7 are correspondingly installed on one side of the thin-wall plate 62 through screws respectively.
The data acquisition assembly comprises a test computer 14, an LMS test system 15, a rotary encoder and USBCAN equipment, which are not shown in the figure; the testing computer is connected with an LMS testing system 15 through a network cable, the LMS testing system 15 is connected with the infrared displacement sensor 7 through a front end connecting wire, the rotary encoder is fixed at the end of the rotor shaft and transmits signals to the USBCAN equipment through a CAN local area network, and the USBCAN equipment further transmits the signals to a testing computer network protocol, namely to the testing computer 14.
As for how to realize the simultaneous arrangement of a single sensor bracket and a plurality of infrared displacement sensors and solve the time-consuming problem of repeated debugging, the scheme of the invention is completed by designing a sensor integrated board 5 which embodies the integration idea, as shown in figure 3, a plurality of infrared displacement sensors 7 are simultaneously arranged on the sensor integrated board 5 which is punched according to the relative position relationship which is appointed in advance, and the positioning reference of all the infrared displacement sensors 7 is synchronous with the sensor integrated board 5, thus, the debugging work of testing distance, angle and the like only needs to take the sensor integrated board 5 as the reference, when the relative position relationship between the sensor integrated board 5 and the measuring points is accurate, the position relationship between each infrared displacement sensor 7 and the corresponding measuring point can simultaneously meet the requirement, and the repeated adjustment of the position relationship between a plurality of infrared displacement sensors and the measuring points is avoided, the problem of consuming time of repeated debugging is solved. As shown in fig. 4, two different test schemes are shown, and the integrated board structure not only has the advantage of fast debugging, but also has the characteristics of flexibility in testing, universality and the like. When the mutual position relations among the infrared ray displacement sensors and between the infrared ray displacement sensors and the measuring points are required to be adjusted as shown in the drawing, only a sensor integrated board meeting the distance requirement of the drawing is needed to be designed and all the infrared ray displacement sensors are fixedly installed, then the distance between one infrared ray displacement sensor and the measuring point is adjusted to meet the requirement by taking the sensor integrated board as a reference, and the position of each infrared ray displacement sensor does not need to be repeatedly adjusted to meet the requirement.
The scheme of the invention is completed by designing a thin-wall type sensor switching fixing plate 6 and combining a sensor integration plate 5, and fixing an infrared displacement sensor 7 on the thin-wall type sensor switching fixing plate 6 through a screw, because the structure of the sensor integration plate 5 realizes the linkage debugging function of multiple infrared displacement sensors accurately meeting the specified position relation, the large space occupied by a magnetic gauge stand which is in charge of the position adjusting function of a sensor bracket in the traditional vibration measurement technology is saved, and the axial small-distance arrangement of the infrared displacement sensors is realized under the condition of avoiding interference.
The scheme of the invention is implemented by designing X, Y, Z three-degree-of-freedom sensor support adjusting mechanisms, so that the position adjustment of the infrared displacement sensor is completely implemented by X, Y, Z guide rails of the adjusting mechanisms, and as long as the three-degree-of-freedom sensor support adjusting mechanisms move accurately and reliably, spatial movement except X, Y, Z three translational degrees of freedom is not generated, namely, the spatial degree of freedom of a measuring head of the infrared displacement sensor is only limited to three translational degrees of freedom, so that the problem of inaccurate positioning and clamping caused by excessive flexibility and excessive degrees of freedom of the sensor support is solved, and the sensor degree of freedom in the vibration measurement technology is X, Y, Z three translational degrees of freedom, as shown in fig. 5.
A digital twinning method for a multi-size profile rotor of an engine, the method comprising the steps of:
s1, extracting rotor speed data in real time; fixing a rotary encoder to the shaft end of the rotor, and when the rotor rotates, the rotary encoder rotates along with the rotor and obtains real-time rotating speed data of the rotor;
s2, intermediately converting the rotating speed data; the rotary encoder transmits the speed signal to USBCAN equipment through a local area network CAN, and the USBCAN serves as a signal transmission medium to prepare for transmission to a test computer in the next step;
s3, receiving a rotation speed signal of the test computer; the USBCAN equipment further transmits the speed signal to the test computer through a corresponding matching network protocol;
s4, leading in a speed signal; after the test computer obtains the speed signal, setting the signal data as the rotation driving speed of the rotor in the ADAMS to realize the consistency of the rotation speed of the ADAMS and the rotation speed of the rotor in the entity space;
s5, setting software; after the rotor is set to rotate and drive, all parts in the ADAMS are subjected to flexible processing, and each part is divided into grids to prepare for obtaining a deformed cloud picture; then, performing kinematic simulation analysis on the rotor system to obtain a deformation cloud picture of the rotor system changing along with the rotating speed, and extracting corresponding real-time acceleration and speed curves of different nodes;
s6, analyzing results; according to the deformation cloud picture of the rotor system changing along with the rotating speed and the corresponding acceleration and speed curve obtained in the last step, the maximum deformation of each part of the rotor system is observed in real time, and the rotor system in the physical space is analyzed in real time, protected from damage and evaluated in reliability;
s7, optimizing the structure; and further optimizing the rotor system structure according to the real-time analysis, damage protection, reliability evaluation and the like of the rotor system in the last step, and pertinently enhancing the structural strength of the rotor to reduce the maximum deformation displacement.
The scheme of the invention is completed by establishing an ADAMS-based univariate digital twin model, and in terms of the entity space, a Rotary encoder (Rotary encoder) is supposed to be adopted to obtain the rotating speed of the test rotor, the rotating speed data is transmitted to USBCAN equipment through a control local area network (CAN), and then the data is transmitted to a network protocol (WebSocket) on a test computer 14 through a USB interface on the computer, and the processed data is connected to an ADAMS flexible body kinematics simulation module; in the aspect of virtual space of an ADAMS-based flexible body kinematics simulation module, rotor rotating speed data obtained from an entity space is used as a rotor driving rotating speed in the virtual space, and finally a deformation cloud picture of the whole rotor model is obtained in real time. Meanwhile, the deformed cloud picture of the virtual space can also be used as a basis for real-time analysis, damage protection and reliability evaluation of the rotor in the physical space, so that a closed loop circulation of the whole virtual space and the physical space is formed, and a circulation flow chart is shown in fig. 6.
The above-mentioned embodiments are merely illustrative of the preferred embodiments of the present invention, and do not limit the scope of the present invention, and various modifications and improvements of the technical solution of the present invention by those skilled in the art should fall within the protection scope defined by the claims of the present invention without departing from the spirit of the present invention.
Claims (6)
1. The utility model provides a device that shakes of surveying to many sizes profile rotor of engine which characterized in that: the device comprises a vibration measurement component and a data acquisition component;
the vibration measurement assembly comprises an upright post, a beam structure, a three-degree-of-freedom sensor bracket adjusting mechanism and a base; the three-degree-of-freedom sensor support adjusting mechanisms are respectively arranged on the inner surface of the stand column on one side and the lower surface of the beam structure;
the three-degree-of-freedom sensor support adjusting mechanism comprises an X-direction guide rail, a Y-direction guide rail, a Z-direction guide rail, a sensor support and an infrared displacement sensor; the X-direction guide rails are arranged on the upper side and the lower side of the middle part of the inner surface of the upright post and on the left side and the right side of the middle part of the lower surface of the cross beam structure at intervals, the Z-direction guide rails are arranged between the two X-direction guide rails at intervals, and the X-direction guide rails and the Z-direction guide rails form a # -shaped structure; one end of the Y-direction guide rail is connected with the middle part of the Z-direction guide rail; the sensor bracket is arranged between the upper surfaces of the other ends of the two Y-direction guide rails, and the infrared displacement sensors are respectively and uniformly arranged along the X-direction guide rails and are connected with the sensor bracket;
the data acquisition assembly is connected with the sensor bracket.
2. The vibration measuring device for the multi-size profile rotor of the engine as claimed in claim 1, wherein: the sensor bracket comprises a sensor integration plate sliding block, a sensor integration plate and a sensor switching fixing plate; the sensor integrated board sliding blocks are respectively arranged on the upper surface of the end part of the guide rail in the Y direction, the sensor integrated board is arranged on the upper surface of the sensor integrated board sliding blocks, the sensor switching fixing plates are respectively and uniformly arranged on the upper surface of the sensor integrated board in the transverse direction, and the infrared displacement sensors are respectively and correspondingly arranged on one side of each sensor switching fixing plate.
3. The vibration measuring device for the multi-size profile rotor of the engine as claimed in claim 2, wherein: the sensor switching fixing plate comprises a base and a thin-wall plate; the thin-wall plate is vertically fixed on one side of the base, and the base is fixedly connected with the corresponding position of the upper surface of the sensor integration plate.
4. The vibration measuring device for the multi-size profile rotor of the engine as claimed in claim 2, wherein: the data acquisition component comprises a test computer, an LMS test system, a rotary encoder and USBCAN equipment; the testing computer is connected with an LMS testing system through a network cable, the LMS testing system is connected with an infrared displacement sensor through a front end connecting line, the rotary encoder is fixed at the end of the rotor shaft and transmits signals to the USBCAN equipment through a CAN local area network, and the USBCAN equipment further transmits the signals to a testing computer network protocol, namely to the testing computer.
5. The vibration measuring device for the multi-size profile rotor of the engine as claimed in claim 1, wherein: the upright column comprises an upright column bottom plate, a corner support, an upright column section bar and an upright column end plate; the upright post bottom plate is fixed on the base, the bottom of the upright post sectional material is fixed on the upright post bottom plate through a corner support, and the upright post end face plate is fixed at the top end of the upright post sectional material.
6. A digital twinning method for a multi-sized profile rotor of an engine using the apparatus of claim 4, wherein the method comprises the steps of:
s1, extracting rotor speed data in real time; fixing a rotary encoder to the shaft end of the rotor, and when the rotor rotates, the rotary encoder rotates along with the rotor and obtains real-time rotating speed data of the rotor;
s2, intermediately converting the rotating speed data; the rotary encoder transmits the speed signal to USBCAN equipment through a local area network CAN, and the USBCAN serves as a signal transmission medium to prepare for transmission to a test computer in the next step;
s3, receiving a rotation speed signal of the test computer; the USBCAN equipment further transmits the speed signal to the test computer through a corresponding matching network protocol;
s4, leading in a speed signal; after the test computer obtains the speed signal, setting the signal data as the rotation driving speed of the rotor in the ADAMS to realize the consistency of the rotation speed of the ADAMS and the rotation speed of the rotor in the entity space;
s5, setting software; after the rotor is set to rotate and drive, all parts in the ADAMS are subjected to flexible processing, and each part is divided into grids to prepare for obtaining a deformed cloud picture; then, performing kinematic simulation analysis on the rotor system to obtain a deformation cloud picture of the rotor system changing along with the rotating speed, and extracting corresponding real-time acceleration and speed curves of different nodes;
s6, analyzing results; according to the deformation cloud picture of the rotor system changing along with the rotating speed and the corresponding acceleration and speed curve obtained in the last step, the maximum deformation of each part of the rotor system is observed in real time, and the rotor system in the physical space is analyzed in real time, protected from damage and evaluated in reliability;
s7, optimizing the structure; and further optimizing the rotor system structure according to the real-time analysis, damage protection, reliability evaluation and the like of the rotor system in the last step, and pertinently enhancing the structural strength of the rotor to reduce the maximum deformation displacement.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110913743.8A CN113588277B (en) | 2021-08-10 | 2021-08-10 | Vibration measuring device for multi-size outline rotor of engine and digital twinning method thereof |
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| CN114813155A (en) * | 2022-06-27 | 2022-07-29 | 中国航发四川燃气涡轮研究院 | Engine exhaust vector angle measurement and tail flame monitoring system |
| CN115091265A (en) * | 2022-06-08 | 2022-09-23 | 安庆帝伯格茨活塞环有限公司 | Piston ring deviation detection equipment and detection method |
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