CN117570909B - Rotor deformation identification method with connecting structure - Google Patents
Rotor deformation identification method with connecting structure Download PDFInfo
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- CN117570909B CN117570909B CN202410059138.2A CN202410059138A CN117570909B CN 117570909 B CN117570909 B CN 117570909B CN 202410059138 A CN202410059138 A CN 202410059138A CN 117570909 B CN117570909 B CN 117570909B
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- 238000000034 method Methods 0.000 title claims abstract description 12
- 238000006073 displacement reaction Methods 0.000 claims abstract description 26
- 239000013598 vector Substances 0.000 claims abstract description 11
- 238000013461 design Methods 0.000 abstract description 3
- 238000003745 diagnosis Methods 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 4
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000005284 excitation Effects 0.000 description 2
- 230000001154 acute effect Effects 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B21/00—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant
- G01B21/32—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant for measuring the deformation in a solid
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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
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
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- General Physics & Mathematics (AREA)
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
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Abstract
The invention belongs to the field of aeroengine fault diagnosis, and discloses a rotor deformation identification method with a connecting structure, which comprises the steps of firstly determining two sections to be tested on each continuous shaft section of a rotor, and arranging two displacement sensors on each section to be tested; then all displacement sensors are started, and the space positions of the axes of all sections and the rotating speed of the rotor at the moment t are recorded; then, calculating the space pointing vector and deflection angle of each continuous shaft section by combining displacement data of each continuous shaft section under quasi-static state; calculating the included angle between the space directional vectors of two adjacent continuous shaft sections; finally, according to deflection angle data and angular deformation data, judging the deformation degree of the rotor; compared with the prior art, the method and the device calculate the space direction and deflection angle of the typical shaft section and the angular deformation of the connecting structure through a non-contact means, establish a rotor system dynamics prediction model with the connecting structure, and realize the robustness design of the aeroengine rotor system.
Description
Technical Field
The invention belongs to the field of aeroengine fault diagnosis, and particularly relates to a rotor deformation identification method with a connecting structure.
Background
Aero gas turbine engines (aero engines for short) are representative of high-precision tip power equipment. The rotor structure system of the aeroengine is often formed by connecting and combining a large number of parts through various connecting structures (such as flange-bolts, rabbets, end teeth and the like). Under the combined action of a high-speed rotation working condition and a complex and changeable working environment, the connecting structure can be damaged, the angular deformation of the rotor is abrupt (discontinuous), the additional unbalanced excitation of the rotor is increased, the vibration of the whole machine is further increased, and the reliability and the safety of the aeroengine are threatened.
In order to fully study the influence of interface damage of a connection structure on a mesoscopic layer on the dynamic characteristics of a rotor system on a system layer, a rotor system dynamic prediction model with a connection structure is established, and verification or support of shafting spatial deformation and discontinuous angular deformation results of the connection structure on a local structure layer is required.
Therefore, how to identify the shaft of the rotor system with the connection structure, the angular deformation of the connection structure is a problem to be solved.
Disclosure of Invention
In order to solve the technical problems, the invention provides a rotor deformation identification method with a connecting structure, which solves the problems in the prior art, and adopts the following technical scheme:
a rotor deformation identification method with a connecting structure comprises the following steps:
step 1, determining two sections to be detected on each continuous shaft section of a rotor, wherein each section to be detected is provided with two displacement sensors;
step 2, starting all displacement sensors, driving the rotor to rotate, and recording the space positions of the axes of all sections at the moment t and the rotating speed of the rotor;
step 3, calculating the space directional vector and deflection angle of each continuous shaft section according to the two sections to be measured on the continuous shaft sections;
step 4, calculating the included angle between the space directional vectors of two adjacent continuous shaft sections, and taking the included angle as the angular deformation of the connecting structure at the position；
Step 5, according to deflection angle data of each continuous shaft section, angular deformation data of the connecting structureThe degree of deformation of the rotor is determined.
The invention has the following beneficial effects: the invention uses a non-contact method to measure the space position of the typical section of the rotor in a working state, calculates and obtains the space direction and deflection angle of the typical shaft section and the angular deformation of the connecting structure, thereby being beneficial to guiding and researching the influence of the interface damage of the connecting structure on the mesoscopic layer on the dynamic characteristics of the rotor system on the system layer, obtaining additional unbalanced excitation after the structural state of the rotor system is changed under complex load, establishing a rotor system dynamic prediction model with the connecting structure and finally realizing the design of the robustness of the rotor system of the aeroengine.
Drawings
FIG. 1 is a schematic overall flow diagram of the present invention;
FIG. 2 is a schematic diagram of a rotor station arrangement;
FIG. 3 is a sectional view of S-S in FIG. 2;
FIG. 4 is a cross-sectional view of R-R in FIG. 2;
FIG. 5 is a schematic diagram of a four-station deformation of the rotor;
FIG. 6 is a schematic diagram of a three-station rotor deformation;
FIG. 7 is an example of a set of connection structure angular deformations as a function of rotational speed;
in the figure, a rotor 10 with a connecting structure, an air compressor shaft section 11, a drum shaft section 12, a connecting structure 13, an initial phase point 15, a section A, B, C, D to be measured, a vertical measuring point A1 and a horizontal measuring point A2 of a displacement sensor, and a center point of the section to be measured、/>、/>、Instantaneous position of rotor axis of section to be measured>、/>、/>、/>。
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to fig. 1 to 7 in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, but not all embodiments, and technical means used in the embodiments are conventional means known to those skilled in the art unless specifically indicated.
Referring to fig. 1, a method for identifying deformation of a rotor with a connection structure includes the steps of:
step 1, 2 sections A, B and C, D to be measured are determined at different axial positions of each successive shaft section of the rotor 10, namely the compressor shaft section 11 and the drum shaft section 12, and each section to be measured is provided with 2 displacement sensors for monitoring the spatial position of the section to be measured. On the cross section R-R of the end of the rotor 10, 1 initial phase point 15 is defined. Radially outside the initial phase point 15, a phase sensor PH is arranged.
Referring to fig. 2, the continuous shaft section refers to a portion of the rotor 10 that is a continuous shaft body in the Z direction in the drawing, and this embodiment is exemplified by the compressor shaft section 11 and the drum shaft section 12. The X direction in fig. 2 is the vertical radial direction of the rotor 10, Y is the horizontal radial direction of the rotor, and Z is the axial direction of the rotor 10.
Preferably, 2 sensors of each section to be measured in the step 1 are orthogonally arranged. Taking a section A to be measured as an example, as shown in fig. 3, the section is provided with 2 displacement sensors, namely a vertical measuring point A1 and a horizontal measuring point A2, and the displacement of the section A in the vertical direction and the horizontal direction is respectively monitored.
Preferably, referring to fig. 2 and 4, the initial phase point in step 1 may be a key slot. When the initial phase point 15 is facing the phase sensor 15, the rotor is considered to rotate to zero phase.
Step 2:
firstly, the axial coordinates of the sections A, B and C, D to be measured are respectively recorded as, all displacement sensors are started, the rotor 10 is rotated in a quasi-static state, and the reading values of the displacement sensors in the X direction and the Y direction corresponding to the sections A, B, C, D to be measured when the rotor rotates to a zero phase are recorded as initial displacement values.
Preferably, the X-direction displacement sensor and the Y-direction displacement sensor of the quasi-static section A to be measured in the step 2 have the reading values of、/>The reading value of the displacement sensor in the X direction and the Y direction of the section B to be measured is +.>、/>The X-direction and Y-direction displacement sensor of the section C to be measured has a reading value of +.>、/>The reading value of the displacement sensor in the X direction and the Y direction of the section D to be measured is +.>、/>。
Then the rotor 10 is driven to rotate, the rotor deforms under the action of unbalanced centrifugal load, as shown in figure 5, the instantaneous position point of the axis of the rotor with the section to be measured、/>、/>、/>Deviation from the center point of the section to be measured->、/>、/>、/>And recording the rotating speed of the rotor at the time t and the reading values of the displacement sensors, and calculating the space position of the axis of the section.
Preferably, the X-direction displacement sensor and the Y-direction displacement sensor of the section A to be measured in the rotating state in the step 2 have the reading values of、/>The reading value of the displacement sensor in the X direction and the Y direction of the section B to be measured is +.>、/>The X-direction and Y-direction displacement sensor of the section C to be measured has a reading value of +.>、/>The reading value of the displacement sensor in the X direction and the Y direction of the section D to be measured is +.>、/>.
Preferably, in the step 2, the instantaneous axial position point of the section A, B, C, D to be measured of the rotor in the rotating state、/>、/>、/>The space coordinates are +.>、/>、/>、/>Wherein the coordinate of X, Y direction is calculated by the following formula
And 3, calculating the space orientation vector and deflection angle of each continuous shaft section according to the space positions of 2 sections to be measured of the shaft section.
Preferably, the spatial orientation vectors of the compressor shaft section 11, the drum shaft section 12、/>Calculated by the following formula
Preferably, the deflection angle of the compressor shaft section 11, the drum shaft section 12 is much smaller than the axial dimension of the rotor due to the lateral deflection of the rotor、/>Calculated by the following formula
Step 4, calculating the included angle (acute angle) between the space directional vectors of two adjacent continuous shaft sections, and taking the included angle as the angular deformation of the connecting structure。
Preferably, as shown in fig. 5, the angular deformation of the connection structure 13 between the compressor shaft section 11 and the drum shaft section 12 can be calculated using the cosine law
Preferably, if attention is paid only to abrupt characteristics or change trends of the angular deformation of the connection structure, the angular deformation of the connection structure is as shown in fig. 6Can be obtained by using the spatial positions of 3 sections to be measured, and the calculation formula is as follows
Step 5, according to the deflection angle data of the shaft section、/>And the number of angular deformations of the connection structure +.>And judging the deformation degree of the rotor, and recording the corresponding rotating speed so as to further analyze the working characteristics of the rotor.
In general, deformation values、/>And->The larger the rotor is, the easier the rotor is deformed, and if the rate of deformation along with the change of the rotating speed is extremely high, the abrupt change of the mechanical property of the rotor connecting structure under the specific rotating speed load is indicated.
For example, fig. 7 is an example of a set of connection structure angular deformations as a function of rotational speed. At around 7760RPM, the angular deformation of the connection structure suddenly increases, reaching an amplitude. The rotational speed continues to increase, and the amount of angular deformation decreases and stabilizes in the vicinity.
The above embodiments are only illustrative of the preferred embodiments of the present invention and are not intended to limit the scope of the present invention, and various modifications, variations, alterations, substitutions made by those skilled in the art to the technical solution of the present invention should fall within the protection scope defined by the claims of the present invention without departing from the spirit of the design of the present invention.
Claims (3)
1. The rotor deformation identification method with the connecting structure is characterized by comprising the following steps of:
step 1, determining two sections to be measured on each continuous shaft section of a rotor (10), wherein each section to be measured is provided with two displacement sensors;
step 2, starting all displacement sensors, driving the rotor (10) to rotate, and recording the space positions of the axes of all sections at the moment t and the rotating speed of the rotor (10);
step 3, calculating the space directional vector and deflection angle of each continuous shaft section according to the two sections to be measured on the continuous shaft sections;
step 4, calculating the included angle between the space directional vectors of two adjacent continuous shaft sections, and taking the included angle as the angular deformation of the connecting structure at the position；
Step 5, based on the deflection angle data of each continuous shaft section and the angular deformation data of the connecting structureJudging the deformation degree of the rotor;
in the step 1, the continuous shaft section comprises an air compressor shaft section (11) and a drum shaft section (12), and the section to be measured is positioned at different axial positions on the continuous shaft section;
wherein the section to be measured is divided into A, B, C, D, and the instantaneous axial position point of the section to be measured A, B, C, D is、/>、/>、/>The space coordinates are +.>、/>、/>、/>；
In the step 3, the spatial orientation vector of the compressor shaft section (11)The spatial orientation vector of the drum shaft section (12)>Calculated by the following formula:
；
in the step 4, the angular deformation is calculated by the following formula：
。
2. The method for recognizing deformation of rotor with connecting structure according to claim 1, wherein in step 1, two displacement sensors on each section to be measured are orthogonally distributed.
3. A method of identifying rotor deformations with connection according to claim 1, characterized in that in said step 3 the deflection angle of the compressor shaft section (11)Deflection angle of the drum shaft section (12)>Calculated by the following formula:
。
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| CN202410059138.2A CN117570909B (en) | 2024-01-16 | 2024-01-16 | Rotor deformation identification method with connecting structure |
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| CN202410059138.2A CN117570909B (en) | 2024-01-16 | 2024-01-16 | Rotor deformation identification method with connecting structure |
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| CN117570909B true CN117570909B (en) | 2024-04-12 |
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR19990039105A (en) * | 1997-11-10 | 1999-06-05 | 윤종용 | Method for measuring tuning response of rotating body considering initial deformation and balancing method of rotating body |
| CN106839968A (en) * | 2016-04-15 | 2017-06-13 | 南京航空航天大学 | Rotor space axis of bending test system and its method of testing |
| CN109117460A (en) * | 2018-09-12 | 2019-01-01 | 大连理工大学 | A method of survey calculation rotor is jumped based on end and assembles axis deviation |
| CN111993159A (en) * | 2020-08-27 | 2020-11-27 | 江苏科技大学 | In-place non-contact detection method for shaft workpieces |
| CN114021326A (en) * | 2021-10-28 | 2022-02-08 | 泰安航天特种车有限公司 | Method and system for analyzing vibration characteristics of helical bevel gear meshing system |
| CN115014728A (en) * | 2022-01-12 | 2022-09-06 | 沈阳航空航天大学 | Cross-coordinate system dynamic modeling method for rotor with misalignment of deflection angle and fault |
| CN116754134A (en) * | 2023-04-18 | 2023-09-15 | 北京航空航天大学 | Rotor imbalance state identification method based on test and simulation data fusion |
-
2024
- 2024-01-16 CN CN202410059138.2A patent/CN117570909B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR19990039105A (en) * | 1997-11-10 | 1999-06-05 | 윤종용 | Method for measuring tuning response of rotating body considering initial deformation and balancing method of rotating body |
| CN106839968A (en) * | 2016-04-15 | 2017-06-13 | 南京航空航天大学 | Rotor space axis of bending test system and its method of testing |
| CN109117460A (en) * | 2018-09-12 | 2019-01-01 | 大连理工大学 | A method of survey calculation rotor is jumped based on end and assembles axis deviation |
| CN111993159A (en) * | 2020-08-27 | 2020-11-27 | 江苏科技大学 | In-place non-contact detection method for shaft workpieces |
| CN114021326A (en) * | 2021-10-28 | 2022-02-08 | 泰安航天特种车有限公司 | Method and system for analyzing vibration characteristics of helical bevel gear meshing system |
| CN115014728A (en) * | 2022-01-12 | 2022-09-06 | 沈阳航空航天大学 | Cross-coordinate system dynamic modeling method for rotor with misalignment of deflection angle and fault |
| CN116754134A (en) * | 2023-04-18 | 2023-09-15 | 北京航空航天大学 | Rotor imbalance state identification method based on test and simulation data fusion |
Non-Patent Citations (3)
| Title |
|---|
| A Closed Loop Quality Control System Based on Online Measurement Technology for Aviation Complex Component Manufacturing;Chu, K. 等;2022 5th World Conference on Mechanical Engineering and Intelligent Manufacturing;20221231;661-667 * |
| 数字孪生驱动的转子装配及不平衡分布;吴法勇 等;北京航空航天大学学报;20231113;1-15 * |
| 横向裂纹对转子动力特性的影响;王娟 等;沈阳航空工业学院学报;20041031;第21卷(第5期);13-15 * |
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