CN114577398A - High-speed balancing method for output shaft assembly of power turbine rotor - Google Patents
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- CN114577398A CN114577398A CN202210183775.1A CN202210183775A CN114577398A CN 114577398 A CN114577398 A CN 114577398A CN 202210183775 A CN202210183775 A CN 202210183775A CN 114577398 A CN114577398 A CN 114577398A
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- 238000000034 method Methods 0.000 title claims abstract description 46
- 238000012360 testing method Methods 0.000 claims abstract description 30
- 230000000630 rising effect Effects 0.000 claims description 6
- 230000000694 effects Effects 0.000 abstract description 6
- 230000035945 sensitivity Effects 0.000 abstract description 3
- 235000012149 noodles Nutrition 0.000 description 6
- 238000005259 measurement Methods 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 238000012545 processing Methods 0.000 description 3
- 238000005452 bending Methods 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M1/00—Testing static or dynamic balance of machines or structures
- G01M1/14—Determining imbalance
- G01M1/16—Determining imbalance by oscillating or rotating the body to be tested
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M1/00—Testing static or dynamic balance of machines or structures
- G01M1/30—Compensating imbalance
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M1/00—Testing static or dynamic balance of machines or structures
- G01M1/30—Compensating imbalance
- G01M1/32—Compensating imbalance by adding material to the body to be tested, e.g. by correcting-weights
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M1/00—Testing static or dynamic balance of machines or structures
- G01M1/30—Compensating imbalance
- G01M1/34—Compensating imbalance by removing material from the body to be tested, e.g. from the tread of tyres
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M1/00—Testing static or dynamic balance of machines or structures
- G01M1/30—Compensating imbalance
- G01M1/36—Compensating imbalance by adjusting position of masses built-in the body to be tested
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/20—Hydro energy
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Abstract
The invention discloses a high-speed balancing method for an output shaft assembly of a power turbine rotor, which belongs to the technical field of high-speed dynamic balance and comprises the following steps: carrying out a high-speed test on the power turbine rotor, and testing the initial deflection and the phase thereof; then, changing the mass of the power turbine rotor; wherein the high-speed test is performed on a high-speed dynamic balance device; the initial deflection is a dynamic deflection value generated in the process that the center position of the power turbine rotor is tested to rise to the rated rotating speed, and the phase position is a position generating flexible deformation. According to the invention, the influence coefficient of the balance weight on the power turbine rotor is calculated, and the high-speed dynamic balance is realized by removing materials from the power turbine rotor, so that the technical problems of low accuracy and low sensitivity in a high-speed dynamic balance method in the prior art are solved, and the technical effect of accurately and effectively maintaining the high-speed dynamic balance of the power turbine rotor is realized.
Description
Technical Field
The invention relates to the technical field of high-speed dynamic balance, in particular to a high-speed balancing method for an output shaft assembly of a power turbine rotor.
Background
The current mainstream high-speed dynamic balance method comprises a vibration mode balance method and an influence coefficient method. The vibration mode balancing method is to balance the rotor in order according to the vibration mode of the rotor, and the balance results of the rotor in a low-speed state and a high-speed state are not influenced mutually. The influence coefficient rule is to obtain the mass and phase of the balance weight needed by the rotor system to reach balance by comparing the flexible deformation of the rotor when the balance weight is applied with the flexible deformation of the rotor when the balance weight is not applied.
However, when the vibration mode balance method is adopted, when the influence of system damping is large, the vibration mode is not easy to be measured accurately, and the effectiveness is reduced; in addition, when the method is used for shafting balance, a single vibration mode is not easy to obtain near the critical rotating speed. When the influence coefficient method is adopted, the times of balance starting at high rotating speed are more; especially in the case of a high-order mode, the sensitivity is reduced.
Disclosure of Invention
In order to solve the problems, the invention provides a high-speed balancing method for an output shaft assembly of a power turbine rotor, which comprises the following steps: carrying out a high-speed test on the power turbine rotor, and testing the initial deflection and the phase thereof; then, changing the mass of the power turbine rotor; wherein the high-speed test is performed on a high-speed dynamic balance device; the initial deflection is a dynamic deflection value generated in the process that the center position of the power turbine rotor is tested to rise to the rated rotating speed, and the phase position is a position generating flexible deformation; wherein, the initial flexibility value is measured to be X, and the phase is measured to be Y; the position for changing the mass of the power turbine rotor is the center position of the turbine rotor, and the position for changing the mass m of the power turbine rotor is as follows: (X-275 μm)/140 μm ═ r … q, where r is the quotient and q is the remainder;
m＝0.1×(r+1)g。
optionally, the manner of varying the power turbine rotor mass comprises: the material removal process is performed at a power turbine rotor center position Y, the material removal having a mass m.
Optionally, the manner of varying the power turbine rotor mass further comprises: and adding a counterweight at the central position Z of the power turbine rotor, wherein the included angle between the position Z and the position Y is 180 degrees, and the mass of the added counterweight is m.
Optionally, the means for reducing weight includes manual grinding, manual filing, and mechanical grinding.
Optionally, the thickness of the material removal process does not exceed 1.5 mm.
Optionally, the process of testing the initial deflection and the phase thereof is to test the dynamic deflection value and the phase thereof generated during the process of the central position of the rotor of the power turbine rising from 300rpm to 20900 rpm.
By adopting the technical scheme, the invention mainly has the following technical effects:
the technical problems of low accuracy and low sensitivity in a high-speed dynamic balancing method in the prior art are solved by calculating the influence coefficient of the balance weight on the power turbine rotor and removing materials from the power turbine rotor to realize high-speed dynamic balancing, and the technical effect of accurately and effectively keeping the high-speed dynamic balancing of the power turbine rotor is realized.
Drawings
FIG. 1 is a schematic view of a power turbine rotor assembly according to the present invention;
FIG. 2 is a bode diagram of a high speed dynamic balance front deflection value curve according to the present invention;
FIG. 3 is a Bode diagram of a deflection value curve after high-speed dynamic balancing according to the present invention;
FIG. 4 is a Nyquist plot of the high speed dynamic balancing front deflection value curve of the present invention;
FIG. 5 is a schematic diagram of dynamic balance deduplication in the present invention.
Wherein the reference numerals have the following meanings:
1. a power turbine rotor; 2. a left swing frame; 3. a right swing frame;
A. a power input direction; B. boss No. 1; C. no. 2 boss; D. no. 3 boss; E. no. 1 dynamic deflection measuring surface; F. number 2 dynamic deflection measuring surface; G. no. 3 dynamic deflection measuring surface;
101. measuring a face deflection value curve by No. 1; 102. measuring a face deflection value curve by No. 2; 103. and No. 3 measuring the curve of the face flexibility value.
Detailed Description
In order to make the technical solutions of the present invention better understood, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the specification of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Reference herein to "an embodiment" means that a particular feature, structure, or characteristic described in connection with the embodiment can be included in at least one embodiment of the invention. The appearances of the phrase in various places in the specification are not necessarily all referring to the same embodiment, nor are separate or alternative embodiments mutually exclusive of other embodiments. It is explicitly and implicitly understood by one skilled in the art that the embodiments described herein can be combined with other embodiments.
The invention provides a high-speed balancing method for an output shaft assembly of a power turbine rotor, which is carried out on a power turbine rotor of a turboshaft-X engine in a preferred embodiment, wherein the power turbine rotor of the turboshaft-X engine belongs to a typical flexible rotor, flexible deformation is generated due to unbalanced mass centrifugal force during high-speed rotation, and the deformation degree is changed along with the change of the rotating speed. It should be particularly noted that, in the present embodiment, the phase refers to a position where the flexible deformation is generated on the rotor, for example, but not limited to, the highest position in the vertical direction in the free state before the rotor rotates may be a reference line, and the phase is an included angle between the reference line and the position where the flexible deformation is generated.
The main balancing steps are as follows:
(a) carrying out a high-speed test on the power turbine rotor, and testing the initial deflection and the phase thereof;
in the step, the initial deflection and the phase position of the power turbine rotor are tested by arranging the power turbine rotor on high-speed dynamic balance equipment for testing. Wherein, the high-speed dynamic balance equipment has mature application cases.
In some preferred embodiments of the present invention, the rated operating speed of the power turbine rotor is 20900rpm, and therefore, the specific process of testing the initial deflection and the phase thereof in the present invention is to record the dynamic deflection value generated during the process of the rotor rising from 300rpm to 20900 rpm.
(b) Removing materials from the power turbine rotor;
in this step, the power turbine rotor is subjected to a material removal treatment to reduce the weight;
the following further illustrates the principles of material removal processing of a power turbine rotor to achieve high speed balancing of a power turbine rotor output shaft assembly:
specifically, referring to FIG. 1, FIG. 1 is a schematic view of a power turbine rotor assembly;
wherein, the two ends of the power turbine rotor 1 are respectively arranged on the left swing frame 2 and the right swing frame 3. Wherein, A is the direction of power input, B, C and D correspond to the boss position on the power turbine rotor 1 respectively, E, F and G correspond to the dynamic deflection measuring surface position of B, C and D respectively;
specifically, B is the boss No. 1 on the power turbine rotor 1, C is the boss No. 2 on the power turbine rotor 1, D is the boss No. 3 on the power turbine rotor 1, and the dynamic deflection measuring surface No. 1E corresponding to the boss No. 1, the dynamic deflection measuring surface No. 2F corresponding to the boss No. 2, and the dynamic deflection measuring surface No. 3G corresponding to the boss No. 3.
In the specific setting position of the boss, the setting position of the boss No. 1 is close to the left swing frame 2, the setting position of the boss No. 2 is the central position of the power turbine rotor 1, and the setting position of the boss No. 3 is close to the right swing frame 3.
Referring further to table 1, table 1 shows the effect of the location and weight of the counterweights applied to the No. 1-No. 3 bosses of the power turbine rotor 1 on the maximum dynamic deflection of the rotor.
TABLE 1 influence of position and weight of applied weights on maximum dynamic deflection of rotor
Through the analysis of the data in the table, further, according to the analysis of the test result of the No. 2 measuring surface, after the No. 2 boss applies the counterweight at the position corresponding to the original state phase, the influence of the counterweight on the deflection value and the phase is multiplied, wherein the corresponding specific positions are as follows: the angle between the point where the counterweight is applied and the phase is 180 °, i.e. 329 ° + 149 ° +180 °.
Specifically, as can be seen from table 1, when no counterweight is applied, the initial dynamic deflection of the No. 2 measuring surface is 458 μm/149 ° through a high-speed dynamic balance equipment test;
further, a weight of 0.1g was applied at 329 °, and the measured face dynamic deflection of No. 2 was 318 μm/148 ° by a power-on test;
the influence coefficient of 0.1g of balance weight on the deflection value of the No. 2 measuring surface is obtained through calculation:
x＝(458μm-318μm)
the deflection coefficient was found to be 140 μm.
And the influence coefficient of the 0.1g counterweight on the phase of the No. 2 measuring surface is calculated as follows:
T＝(149°-145°)
it is further found that the phase coefficient T is 4 °.
Therefore, the coefficient of influence of the 0.1g weight on the No. 2 measuring surface was 140 μm 4 °.
And analyzing the test results: the boss No. 1 is close to the left swing frame 2, the boss No. 3 is close to the right swing frame 3, the boss No. 1 and the boss No. 3 are insensitive to reaction when the counter weights with the mass increasing are applied due to the limitation of the left swing frame 2 and the right swing frame 3, and the maximum dynamic deflection of the measuring surface of the boss No. 2 is decreased gradually when the counter weights with the mass increasing are applied to the boss No. 2, so that the application of the counter weights on the boss No. 2 is the best balancing method.
However, it should be noted that, when a weight of 0.2g is applied to 329 °, the dynamic deflection of the No. 2 measuring surface is 178 μm/140 ° by the start-up test, and it is found by calculation that when the weight applied to the No. 2 boss is changed from 0.1g to 0.2g, the change value of the dynamic deflection is 140 μm · 5 °, that is, the change value of the dynamic phase coefficient is T ═ 5 °, and therefore, there is a difference from the influence coefficient of the 0.1g weight on the No. 2 measuring surface being 140 μm · 4 °, and the test result is analyzed, and the difference is caused by an error between the actual test value of the dynamic deflection change value and the theoretical value.
Further, the high-speed balance test process specification of the power turbine rotor stipulates that: the maximum flexibility value is not more than 275 mu m in the process of starting to rise to the rated working rotating speed (20900rpm), and the flexibility value is not more than 50 mu m under the rated working rotating speed (20900rpm), namely the high-speed balance test is qualified.
Therefore, the mass of the balance weight is changed according to the influence coefficient of the 0.1g balance weight on the No. 2 measuring surface of 140 mu m & lt 4 & gt, so that the maximum flexibility value of the power turbine rotor is not more than 275 mu m in the process of rising from 300rpm to rated working rotating speed (20900rpm), and the flexibility value of the power turbine rotor is not more than 50 mu m under the rated working rotating speed (20900rpm), and the high-speed balance of the output shaft assembly of the power turbine rotor can be realized.
It should be noted that, in the present embodiment, the power turbine rotor weight is added at a position corresponding to the phase of the original state in consideration of the inconvenience (for example, the weight may be dropped during high-speed operation). Therefore, the mode of removing materials in phase is adopted in the invention to realize high-speed balance of the output shaft assembly of the power turbine rotor, and the included angle between the position for removing the materials and the position for adding the balance weight is 180 degrees, so that high-speed dynamic balance is realized.
In summary, in some embodiments of the invention, the power turbine rotor is disposed on the high-speed dynamic balance device to test the initial deflection and the phase thereof, specifically, the dynamic deflection value generated in the process of increasing from 300rpm to 20900rpm at the central position of the power turbine rotor is tested; the power turbine rotor is subjected to a material removal treatment at a specific location, and the material removal treatment is performed at a phase.
The specific mass of material removed is further illustrated below:
in a high-speed test of a power turbine rotor, measuring that the initial deflection is X and the phase position is Y;
the calculation mode of the removed material mass is as follows:
(X-275 μm)/140 μm r … q, where r is the quotient and q is the remainder,
the mass m of the material removal process at the phase position is: m is 0.1 × (r +1) g.
It should be noted that r +1 is provided to solve the problem that when a remainder q exists, if only (0.1 × r) g is removed, the existence of the remainder q will make the maximum deflection value after the material removal processing greater than 275 μm, and therefore, the mass m of the material removal processing at the phase in the present invention is: m is 0.1 × (r +1) g.
That is, the balance effect, i.e. the final balance, can be achieved by directly removing 0.1 x (r +1) g of the balance weight at the Y position of the No. 2 measuring surface.
Of course, a balance can also be achieved by applying 0.1 × (r +1) g of weight at Z, where the angle between Z and Y is 180 °.
For example: the original state of the No. 2 measuring surface was 458 μm/149 °,
the balance of (458-.
In a preferred embodiment of the present invention, the material removal process includes manual grinding, manual filing and mechanical grinding.
In a preferred embodiment of the invention, the thickness of the material removal treatment site of boss No. 2 is no more than 1.5mm to avoid affecting the performance of the power turbine rotor itself.
The balance effect of the high-speed balance method for the output shaft assembly of the power turbine rotor provided by the invention is further described as follows:
referring to fig. 2 and table 2, fig. 2 is a nyquist plot of the high-speed dynamic balance forward deflection value curve, which records the dynamic deflection value generated during the process of the rotor rising from 300rpm to 20900 rpm; table 2 shows the initial flexural deformations and phases measured for each measurement plane at 7000rpm, 12000rpm and 20900rpm of the rotor before high speed rotation equilibrium. Wherein 101 is a bending value curve of a No. 1 measuring surface; 102 is a No. 2 measurement face deflection value curve; 103 is the curve of the measured face deflection value No. 3.
TABLE 2 initial flexural deformation and phase
| Rotational speed | No. 1 measuring noodle | No. 2 measuring noodle | No. 3 measuring noodle |
| 7000rpm | 153μm/207° | 153μm/222° | 137μm/221° |
| 12000rpm | 395μm/149° | 395μm/153° | 210μm/159° |
| 20900rpm | 42.5μm/298° | 23.5μm/309° | 17.7μm/333° |
As can be seen from the analysis of the test result in fig. 2, the flexural deformation of the rotor is maximum at the second-order critical speed during the period from the start of the operation to the working speed. The second-order critical rotation speed refers to a rotation speed at which the vibration value is maximum during the process of increasing the rotor from 300rpm to 20900rpm, and it can be further seen from fig. 2 that the second-order critical rotation speed is approximately within the interval of 12000rpm to 13000 rpm.
Referring to fig. 2, the rotor has the largest dynamic deflection when crossing the first and second critical rotation speeds, so that a rotation speed needs to be selected as the interval rotation speed before crossing the step, specifically 70% to 90% of the step rotation speed.
In a preferred embodiment of the present invention, the two rotation speeds of 7000rpm and 12000rpm adopted in table 2 are interval rotation speeds set according to first-order and second-order critical rotation speeds, and the setting is to prevent the rotor from increasing too fast during high-speed balancing and being unable to control the dynamic deflection. In addition, 20900rpm is the rated speed of the rotor under normal engine operation.
Referring further to fig. 2, the deformation at the second order rotational speed is significantly greater than the first order, while the rotor flexural deformation is smaller at its operating rotational speed. Therefore, the unbalance of the rotor is tested and corrected at the two rotating speeds of the second-order critical rotating speed and the working rotating speed of the rotor, and the rotor can be safely used in the whole working range only by ensuring the safe use at the two rotating speeds of the second-order critical rotating speed and the working rotating speed of the rotor.
Referring to fig. 3 and table 3, fig. 3 is a nyquist plot of the deflection value curve after high-speed dynamic balancing, which records the dynamic deflection value generated during the process of the rotor rising from 300rpm to 20900 rpm; table 3 shows the initial flexural deformations and phases measured for the respective measurement surfaces after the high-speed dynamic balancing when the rotor rotation speed is 7000rpm, 12000rpm, and 20900 rpm.
TABLE 3 post balance flexural deformation and phase
| Rotational speed | No. 1 measuring noodle | No. 2 measuring noodle | No. 3 measuring noodle |
| 7000rpm | 85.7um/140° | 102um/164° | 93.5um/162° |
| 12000rpm | 259um/43° | 248um/48° | 152um/56° |
| 20900rpm | 8.42um/169° | 7.33um/214° | 6.69um/192° |
Referring to fig. 3 and table 3, after the high-speed dynamic balance is performed, the peak value of the flexural deformation is reduced from about 395 μm to about 259 μm, and is 8.42 μm at the rated operating speed, and the flexural value meets the expected result (the maximum flexural value is not greater than 275 μm during the process from starting to increasing to the rated operating speed, and the flexural value is not greater than 50 μm at the rated operating speed). Wherein 101 is a bending value curve of a No. 1 measuring surface; 102 is a No. 2 measurement face deflection value curve; 103 is the curve of the measured face deflection value No. 3.
In conclusion, the high-speed balancing method of the output shaft assembly of the power turbine rotor provided by the invention can meet the requirements of the high-speed balancing test process after the power turbine rotor is dynamically balanced at high speed,
finally, it should be noted that: the embodiment of the present invention is disclosed only as a preferred embodiment of the present invention, which is only used for illustrating the technical solutions of the present invention and not for limiting the same; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those skilled in the art; the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the spirit and scope of the technical solutions of the embodiments of the present invention.
Claims (6)
1. A method of high speed balancing of a power turbine rotor output shaft assembly, comprising:
carrying out a high-speed test on the power turbine rotor, and testing the initial deflection and the phase thereof; then, changing the mass of the power turbine rotor;
wherein the high-speed test is performed on a high-speed dynamic balance device;
the initial deflection is a dynamic deflection value generated in the process that the center position of the power turbine rotor is tested to rise to the rated rotating speed, and the phase position is a position generating flexible deformation; wherein, the initial flexibility value is measured to be X, and the phase is measured to be Y;
the position for changing the mass of the power turbine rotor is the center position of the turbine rotor, and the position for changing the mass m of the power turbine rotor is as follows:
(X-275 μm)/140 μm ═ r … q, where r is the quotient and q is the remainder;
m＝0.1×(r+1)g。
2. the power turbine rotor output shaft assembly high speed balancing method of claim 1, wherein said manner of varying the power turbine rotor mass comprises:
the material removal process is performed at a power turbine rotor center position Y, the material removal having a mass m.
3. The power turbine rotor output shaft assembly high speed balancing method of claim 1, wherein said manner of varying the power turbine rotor mass further comprises:
and adding a counterweight at the central position Z of the power turbine rotor, wherein the included angle between the position Z and the position Y is 180 degrees, and the mass of the added counterweight is m.
4. The method of claim 2, wherein the means for reducing weight includes manual grinding, manual filing, and mechanical grinding.
5. The power turbine rotor output shaft assembly high speed balancing method of claim 2, wherein the removed material treatment is no more than 1.5mm thick.
6. The method as claimed in claim 1, wherein the step of testing the initial deflection and the phase thereof is to test the value of the dynamic deflection and the phase thereof generated during the process of the central position of the power turbine rotor rising from 300rpm to 20900 rpm.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20220003118A1 (en) * | 2018-10-02 | 2022-01-06 | Datatechnic | Method for balancing the out-of-balance of a shaft/wheel assembly |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104634509A (en) * | 2015-03-04 | 2015-05-20 | 大唐长春第二热电有限责任公司 | Method for acquiring dynamic balance coefficient of rotor |
| CN105890843A (en) * | 2016-04-18 | 2016-08-24 | 神华集团有限责任公司 | Dynamic balance method and dynamic balance device |
| CN110646141A (en) * | 2019-09-24 | 2020-01-03 | 华能(大连)热电有限责任公司 | Office software-based rotary machine on-site dynamic balance calculation and adjustment method |
-
2022
- 2022-02-28 CN CN202210183775.1A patent/CN114577398A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104634509A (en) * | 2015-03-04 | 2015-05-20 | 大唐长春第二热电有限责任公司 | Method for acquiring dynamic balance coefficient of rotor |
| CN105890843A (en) * | 2016-04-18 | 2016-08-24 | 神华集团有限责任公司 | Dynamic balance method and dynamic balance device |
| CN110646141A (en) * | 2019-09-24 | 2020-01-03 | 华能(大连)热电有限责任公司 | Office software-based rotary machine on-site dynamic balance calculation and adjustment method |
Non-Patent Citations (7)
| Title |
|---|
| 邓旺群 等: "对转发动机模拟低压转子高速动平衡试验研究", 燃气涡轮试验与研究, vol. 23, no. 04, 30 November 2010 (2010-11-30), pages 5 - 9 * |
| 邓旺群, 高德平: "应用于小发柔性转子的高速动平衡技术", 燃气涡轮试验与研究, no. 02, 30 May 2003 (2003-05-30), pages 30 - 37 * |
| 邓旺群;聂卫健;徐友良;袁胜;刘文魁;: "涡扇发动机高速柔性转子振动故障分析及平衡技术研究", 燃气涡轮试验与研究, no. 01, 15 February 2018 (2018-02-15), pages 24 - 58 * |
| 邓旺群;高德平;: "悬臂柔性转子动力特性及高速动平衡试验", 航空动力学报, no. 03, 30 June 2006 (2006-06-30), pages 556 - 562 * |
| 邓旺群;高德平;郭飞跃;: "航空发动机动力涡轮单元体高速动平衡试验研究", 机械强度, no. 03, 15 June 2007 (2007-06-15), pages 380 - 386 * |
| 邬立建: "影响系数法在现场动平衡中的应用", 冶金动力, no. 01, 25 February 2005 (2005-02-25), pages 55 - 60 * |
| 黄峰;: "刚性转子现场动平衡技术分析", 装备维修技术, no. 02, 13 June 2019 (2019-06-13), pages 157 - 159 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20220003118A1 (en) * | 2018-10-02 | 2022-01-06 | Datatechnic | Method for balancing the out-of-balance of a shaft/wheel assembly |
| US11788414B2 (en) * | 2018-10-02 | 2023-10-17 | Datatechnic | Method for balancing the out-of-balance of a shaft/wheel assembly |
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