CN106768302A - A kind of critical vibration mode test method of aeroengine rotor - Google Patents
A kind of critical vibration mode test method of aeroengine rotor Download PDFInfo
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- CN106768302A CN106768302A CN201710068299.8A CN201710068299A CN106768302A CN 106768302 A CN106768302 A CN 106768302A CN 201710068299 A CN201710068299 A CN 201710068299A CN 106768302 A CN106768302 A CN 106768302A
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- blade
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- test method
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01H—MEASUREMENT OF MECHANICAL VIBRATIONS OR ULTRASONIC, SONIC OR INFRASONIC WAVES
- G01H17/00—Measuring mechanical vibrations or ultrasonic, sonic or infrasonic waves, not provided for in the preceding groups
Abstract
The invention discloses a kind of critical vibration mode test method of aeroengine rotor.The critical vibration mode test method of aeroengine rotor is comprised the following steps：Step 1：Multistage blade every grade blade just to perforate on casing position；Step 2：One index blade is set；Step 3：Under engine rotor critical speed, blade tip and casing gap width are recorded；Step 4：Obtain vibration peak；Step 5：Calculate the phase difference of the number of blade and index blade corresponding to the minimum value of gap；Step 6：For other grade blades, repeating said steps 3 to the step 5 can obtain the rotor vibration displacement peak value and phase difference of different grade blades；Step 7：The vibration vector figure of different rotor position is drawn out, by each vibration vector figure line, the vibration shape of the rotor under critical condition is obtained.The critical vibration mode test method of aeroengine rotor in the present invention, directly can obtain result in engine operation process by test.
Description
Technical field
The present invention relates to aeroengine rotor technical field, more particularly to a kind of critical vibration shape of aeroengine rotor
Method of testing.
Background technology
The vibration characteristics of rotor is also the basis of engine luggine test, analysis and fault diagnosis.But because engine turns
The complicated and particularity (rotor banding blade) of minor structure, and rotor is wrapped within casing completely, is led to not directly to rotor
Tested, the test of the critical rotor vibration shape cannot be realized always.
Way general at present is during engine test, using the vibrating sensor being installed on engine crankcase
Pickup vibration signal, by extracting the vibration amplitude of rotor power frequency, judges whether rotor occurs critical phenomena using amplitude change.
And to the critical corresponding vibration shape, then by being calculated, there is no actual test.
Thus, it is desirable to have a kind of technical scheme come overcome or at least mitigate prior art at least one drawbacks described above.
The content of the invention
Overcome or at least subtract it is an object of the invention to provide a kind of critical vibration mode test method of aeroengine rotor
At least one drawbacks described above of light prior art.
To achieve the above object, the present invention provides a kind of critical vibration mode test method of aeroengine rotor, the aviation
The critical vibration mode test method of engine rotor is comprised the following steps：
Step 1：Engine crankcase along the same angle of rotor axial, multistage blade every grade blade just to casing position
Upper perforate, the hole is used to install clearance test sensor；
Step 2：An index blade is set on any one grade blade of engine rotor；
Step 3：Tested with any one grade blade, under engine rotor critical speed, be with the index blade
Data record starting point, record rotor rotates a circle, blade tip when each blade is by clearance test sensor and casing gap
Value；
Step 4：In the blade tip that rotor rotates a circle with casing gap width, gap minimum value and spacing maxima are searched,
Rotor vibration displacement peak-to-peak value is obtained using gap minimum value and spacing maxima difference, rotor vibration displacement peak-to-peak value is removed
With 2, vibration peak is obtained；
Step 5：In the blade tip that rotor rotates a circle with casing gap width, the blade corresponding to the minimum value of gap is searched
Number, calculates its phase difference with index blade；
Step 6：For other grade blades, repeating said steps 3 to the step 5 can obtain turning for different grade blades
Sub- vibration displacement peak value and phase difference；
Step 7：On the basis of each phase difference for obtaining and each vibration displacement peak value, different rotor position is drawn out
Vibration vector figure, by each vibration vector figure line, obtain the vibration shape of the rotor under critical condition.
Preferably, the step 5 is calculated using equation below：
Wherein,
M is the number of blade, and n is the number of blade of rotor one-level；It is phase difference.
Preferably, the multistage blade is at least three-level.
Preferably, the index blade is marked in the following way：The blade tip of the index blade is than normal blade
Short, the blade tip of the index blade will be greater than other blade tips and casing gap with casing gap width in process of the test.
Preferably, in the step 3, at least 3 positions to be tested along rotor axial.
Preferably, the step 3 is tested using engine tip clearance test system.
Preferably, when being tested using engine tip clearance test system, sample frequency guarantees test to often
Individual blade.
The critical vibration mode test method of aeroengine rotor in the present invention, directly can lead in engine operation process
Cross test and obtain result, decomposed without engine or be additionally provided exciting force, real result is credible.The present invention has solved external
Whether the problem of casing and blade-carrying the rotor Improvement of The Experimental Modal Shape under critical speed, for checking result of calculation, judge resonance
It is harmful to provide direct foundation.
Brief description of the drawings
Fig. 1 is the schematic flow sheet of the critical vibration mode test method of aeroengine rotor according to an embodiment of the invention.
Fig. 2 is the rotor that is obtained of the critical vibration mode test method of aeroengine rotor shown in Fig. 1 under critical condition
The vibration shape schematic diagram.
Specific embodiment
To make the purpose, technical scheme and advantage of present invention implementation clearer, below in conjunction with the embodiment of the present invention
Accompanying drawing, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from start to finish or class
As label represent same or similar element or the element with same or like function.Described embodiment is the present invention
A part of embodiment, rather than whole embodiments.Embodiment below with reference to Description of Drawings is exemplary, it is intended to used
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiment in the present invention, ordinary skill people
The every other embodiment that member is obtained under the premise of creative work is not made, belongs to the scope of protection of the invention.Under
Face is described in detail with reference to accompanying drawing to embodiments of the invention.
In the description of the invention, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instruction such as "left", "right", " vertical ", " level ", " top ", " bottom " " interior ", " outward " are based on accompanying drawing institute
The orientation or position relationship for showing, are for only for ease of the description present invention and simplify description, rather than the dress for indicating or implying meaning
Put or element with specific orientation, with specific azimuth configuration and operation, therefore it is not intended that must be protected to the present invention
The limitation of scope.
Fig. 1 is the schematic flow sheet of the critical vibration mode test method of aeroengine rotor according to an embodiment of the invention.
Fig. 2 is the vibration shape of the rotor that is obtained of the critical vibration mode test method of aeroengine rotor shown in Fig. 1 under critical condition
Schematic diagram.
The critical vibration mode test method of aeroengine rotor as shown in Figure 1 is comprised the following steps：
Step 1：Engine crankcase along the same angle of rotor axial, multistage blade every grade blade just to casing position
Upper perforate, hole is used to install clearance test sensor；
Step 2：An index blade is set on any one grade blade of engine rotor；
Step 3：Tested with any one grade blade, under engine rotor critical speed, with index blade as data
Record start point, record rotor rotates a circle, blade tip when each blade is by clearance test sensor and casing gap width；
Step 4：In the blade tip that rotor rotates a circle with casing gap width, gap minimum value and spacing maxima are searched,
Rotor vibration displacement peak-to-peak value is obtained using gap minimum value and spacing maxima difference, rotor vibration displacement peak-to-peak value is removed
With 2, vibration peak is obtained；
Step 5：In the blade tip that rotor rotates a circle with casing gap width, the blade corresponding to the minimum value of gap is searched
Number, calculates its phase difference with index blade；
Step 6：For other grade blades, repeat step 3 to the step 5, the rotor that can obtain different grade blades shakes
Dynamic displacement peak value and phase difference；
Step 7：On the basis of each phase difference for obtaining and each vibration displacement peak value, different rotor position is drawn out
Vibration vector figure, by each vibration vector figure line, obtain the vibration shape of the rotor under critical condition.
The critical vibration mode test method of aeroengine rotor in the present invention, directly can lead in engine operation process
Cross test and obtain result, decomposed without engine or be additionally provided exciting force, real result is credible.The present invention has solved external
Whether the problem of casing and blade-carrying the rotor Improvement of The Experimental Modal Shape under critical speed, for checking result of calculation, judge resonance
It is harmful to provide direct foundation.
In the present embodiment, step 5 is calculated using equation below：
Wherein,
M is the number of blade, and n is the number of blade of rotor one-level；It is phase difference.
In the present embodiment, the multistage blade is at least three-level.
In the present embodiment, index blade is marked in the following way：The blade tip of index blade is shorter than normal blade,
The blade tip of the index blade will be greater than other blade tips and casing gap with casing gap width in process of the test.
In the present embodiment, in step 3, at least 3 positions to be tested along rotor axial.
In the present embodiment, step 3 is tested using engine tip clearance test system.
In the present embodiment, when being tested using engine tip clearance test system, sample frequency guarantees to survey
Try each blade.
The application is further elaborated by way of example below.It is understood that this is illustrated do not constitute to this
Any limitation of application.
There are fan propeller critical phenomena under 70% low pressure rotating speed, it is necessary to test its vibration shape in certain h type engine h,
To judge whether this critical is harmful to.
According to step 1, instrument connection at 3 is opened along the same angle of rotor axial in engine machine, 3 holes are just to 3 grade blades (certain type
Engine has 3 grade blades) center, clearance test sensor is at instrument connection.
According to step 2, certain grade blade of h type engine h fan 1 totally 23, by it is therein it is a piece of be replaced by index blade, its ratio
The blade of the short 2mm of normal blade.
According to step 3, engine tip clearance measuring system includes test probe, three layers of double shield metallic cable, extension
The parts such as cable, capacitance measurement module, and data sampling and processing system.The signal that test probe is picked up is by cable transmission
Capacitance measurement module, the signal after data collecting system collection capacitance measurement module conversion process are given, and is obtained by processing system
To required test value.
Engine peed stable under 70% low pressure rotating speed, with index blade by gap sensor when gap width be number
According to record start point (), the gap width of other 22 blades (totally 23 blades) is recorded successively at the 1st point；And the 2nd grade is recorded simultaneously
With the gap width of 3rd level blade.Concrete numerical value is as shown in table 1.
The clearance test data of table 1
According to step 4, for the 1st grade blade, blade tip and casing gap width are searched in table 1, A can be obtained1min=
0.16mm, A1max=1.77mm (except mark point gap width), then A1p-p=A1max—A1min=1.61mm, by vibration displacement
Peak-peak value (A1p-p) divided by 2, obtain vibration peak A1p=0.805mm.
According to step 5, because of the total n=23 pieces of rotor blade, gap minimum value A1minThe corresponding number of blade is m=4, root
According to formula
Then minimum clearance value blade and mark point phase difference
According to step 6, for the 2nd grade blade, can obtain：A2p=0.325mm,3rd level blade, can be with
Obtain：A3p=0.35mm,
According to step 7, with the phase difference for obtainingAnd the vibration displacement peak value (A for obtaining1p, A2p,
A3p) on the basis of, by each vibration vector figure line, then can obtain the vibration shape of the rotor under critical condition (referring to Fig. 2).By shaking
Type analysis, the engine rotor critical speed is that pitching is critical.
It is last it is to be noted that：The above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations.To the greatest extent
Pipe has been described in detail to the present invention with reference to the foregoing embodiments, it will be understood by those within the art that：It is still
Technical scheme described in foregoing embodiments can be modified, or which part technical characteristic is equally replaced
Change；And these modifications or replacement, do not make the essence of the essence disengaging various embodiments of the present invention technical scheme of appropriate technical solution
God and scope.
Claims (7)
1. a kind of critical vibration mode test method of aeroengine rotor, it is characterised in that the aeroengine rotor is critical to shake
Type method of testing is comprised the following steps：
Step 1：Engine crankcase along the same angle of rotor axial, multistage blade every grade blade just to being opened on casing position
Hole, the hole is used to install clearance test sensor；
Step 2：An index blade is set on any one grade blade of engine rotor；
Step 3：Tested with any one grade blade, under engine rotor critical speed, with the index blade as data
Record start point, record rotor rotates a circle, blade tip when each blade is by clearance test sensor and casing gap width；
Step 4：In the blade tip that rotor rotates a circle with casing gap width, gap minimum value and spacing maxima are searched, utilized
Gap minimum value obtains rotor vibration displacement peak-to-peak value with spacing maxima difference, by rotor vibration displacement peak-to-peak value divided by 2,
Obtain vibration peak；
Step 5：In the blade tip that rotor rotates a circle with casing gap width, the number of blade corresponding to the minimum value of gap, meter are searched
Calculate its phase difference with index blade；
Step 6：For other grade blades, repeating said steps 3 to the step 5, the rotor that can obtain different grade blades shakes
Dynamic displacement peak value and phase difference；
Step 7：On the basis of each phase difference for obtaining and each vibration displacement peak value, shaking for different rotor position is drawn out
Dynamic vector figure, by each vibration vector figure line, obtains the vibration shape of the rotor under critical condition.
2. the critical vibration mode test method of aeroengine rotor as claimed in claim 1, it is characterised in that the step 5 is adopted
Calculated with equation below：
Wherein,
M is the number of blade, and n is the number of blade of rotor one-level；It is phase difference.
3. the critical vibration mode test method of aeroengine rotor as claimed in claim 2, it is characterised in that the multistage blade
At least three-level.
4. the critical vibration mode test method of aeroengine rotor as claimed in claim 3, it is characterised in that the index blade
It is marked in the following way：The blade tip of the index blade is shorter than normal blade, the index blade in process of the test
Blade tip will be greater than other blade tips and casing gap with casing gap width.
5. the critical vibration mode test method of aeroengine rotor as claimed in claim 4, it is characterised in that in the step 3,
At least to test 3 positions along rotor axial.
6. the critical vibration mode test method of aeroengine rotor as claimed in claim 5, it is characterised in that the step 3 is adopted
Tested with engine tip clearance test system.
7. the critical vibration mode test method of aeroengine rotor as claimed in claim 6, it is characterised in that use engine leaf
When intercuspal space test system is tested, sample frequency guarantees test to each blade.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201710068299.8A CN106768302A (en) | 2017-02-08 | 2017-02-08 | A kind of critical vibration mode test method of aeroengine rotor |
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|---|---|---|---|
| CN201710068299.8A CN106768302A (en) | 2017-02-08 | 2017-02-08 | A kind of critical vibration mode test method of aeroengine rotor |
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ID=58955479
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111241609A (en) * | 2020-01-20 | 2020-06-05 | 西北工业大学 | Prediction method for blade tip clearance of rotor and stator assembly of aircraft engine |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1093803A (en) * | 1993-03-15 | 1994-10-19 | 南京航空航天大学 | The blade vibration monitoring method and system |
| CA2105274C (en) * | 1992-09-03 | 2005-08-02 | Michel Clement | Process and device for measuring operating turbine blade vibrations |
| CN102564698A (en) * | 2011-12-21 | 2012-07-11 | 浙江省电力试验研究院 | Multi-rotor joint vibration mode balancing method for single support shafting steam turbine generator unit |
| CN102735326A (en) * | 2011-04-14 | 2012-10-17 | 中国特种设备检测研究院 | Real-time on-line monitoring apparatus of blade vibration of flue gas turbine |
| CN102840968A (en) * | 2012-07-31 | 2012-12-26 | 沈阳黎明航空发动机(集团)有限责任公司 | Detection device and detection method for wide-range vibration amplitude of blade of aviation engine |
| JP5293406B2 (en) * | 2009-05-28 | 2013-09-18 | 株式会社Ｉｈｉ | Noncontact blade vibration measurement method for rotor blades |
| CN103364069A (en) * | 2012-04-05 | 2013-10-23 | 中国航空工业集团公司沈阳发动机设计研究所 | Non-contact rotating vane vibration testing method based on positioning without rotating speed |
| CN105547462A (en) * | 2015-12-16 | 2016-05-04 | 中国航空工业集团公司沈阳发动机设计研究所 | Radial vibration measuring method of engine rotor |
-
2017
- 2017-02-08 CN CN201710068299.8A patent/CN106768302A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA2105274C (en) * | 1992-09-03 | 2005-08-02 | Michel Clement | Process and device for measuring operating turbine blade vibrations |
| CN1093803A (en) * | 1993-03-15 | 1994-10-19 | 南京航空航天大学 | The blade vibration monitoring method and system |
| JP5293406B2 (en) * | 2009-05-28 | 2013-09-18 | 株式会社Ｉｈｉ | Noncontact blade vibration measurement method for rotor blades |
| CN102735326A (en) * | 2011-04-14 | 2012-10-17 | 中国特种设备检测研究院 | Real-time on-line monitoring apparatus of blade vibration of flue gas turbine |
| CN102564698A (en) * | 2011-12-21 | 2012-07-11 | 浙江省电力试验研究院 | Multi-rotor joint vibration mode balancing method for single support shafting steam turbine generator unit |
| CN103364069A (en) * | 2012-04-05 | 2013-10-23 | 中国航空工业集团公司沈阳发动机设计研究所 | Non-contact rotating vane vibration testing method based on positioning without rotating speed |
| CN102840968A (en) * | 2012-07-31 | 2012-12-26 | 沈阳黎明航空发动机(集团)有限责任公司 | Detection device and detection method for wide-range vibration amplitude of blade of aviation engine |
| CN105547462A (en) * | 2015-12-16 | 2016-05-04 | 中国航空工业集团公司沈阳发动机设计研究所 | Radial vibration measuring method of engine rotor |
Non-Patent Citations (2)
| Title |
|---|
| 刘习军 等: "《工程振动与测试技术》", 30 September 1999, 天津大学出版社 * |
| 李应红 等: "《航空涡轮风扇发动机试验技术与方法》", 31 December 2014, 上海交通大学出版社 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111241609A (en) * | 2020-01-20 | 2020-06-05 | 西北工业大学 | Prediction method for blade tip clearance of rotor and stator assembly of aircraft engine |
| CN111241609B (en) * | 2020-01-20 | 2022-04-01 | 西北工业大学 | Prediction method for blade tip clearance of rotor and stator assembly of aircraft engine |
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