CN112985721A - Device and method for detecting vibration characteristics of turbine rotor blade - Google Patents
Device and method for detecting vibration characteristics of turbine rotor blade Download PDFInfo
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- CN112985721A CN112985721A CN201911289238.XA CN201911289238A CN112985721A CN 112985721 A CN112985721 A CN 112985721A CN 201911289238 A CN201911289238 A CN 201911289238A CN 112985721 A CN112985721 A CN 112985721A
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- 238000000034 method Methods 0.000 title claims abstract description 14
- 238000001514 detection method Methods 0.000 claims abstract description 26
- 239000012530 fluid Substances 0.000 claims abstract description 19
- 230000005540 biological transmission Effects 0.000 claims abstract description 3
- 230000005284 excitation Effects 0.000 claims description 24
- 238000005259 measurement Methods 0.000 claims description 5
- 238000007689 inspection Methods 0.000 claims 1
- 238000012360 testing method Methods 0.000 description 27
- 238000013016 damping Methods 0.000 description 9
- 238000010998 test method Methods 0.000 description 5
- 230000008859 change Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 238000007599 discharging Methods 0.000 description 3
- 239000007788 liquid Substances 0.000 description 2
- 238000011084 recovery Methods 0.000 description 2
- 239000000243 solution Substances 0.000 description 2
- 238000005507 spraying Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000011010 flushing procedure Methods 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000010606 normalization Methods 0.000 description 1
- 230000000737 periodic effect Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000005086 pumping Methods 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 230000004083 survival effect Effects 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
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
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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
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- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Measurement Of Mechanical Vibrations Or Ultrasonic Waves (AREA)
Abstract
The invention relates to a device and a method for detecting the vibration characteristics of a turbine rotor blade, wherein the detection device comprises: a vacuum chamber (13) for accommodating the turbine rotor (1); the driving part (2) is configured to be in transmission connection with a blade disc (5) of the turbine rotor (1) so as to drive the turbine rotor (1) to rotate; at least one nozzle (4) arranged in the vacuum chamber (13) and configured to eject a fluid towards blades (6) mounted on the bladed disc (5) in order to excite the blades (6) into vibration; the measuring part (3) comprises a strain gauge (11) arranged in a vacuum chamber (13) to detect the vibration characteristic of the blade (6), so that the problem of large detection result error caused by large difference between the state of the detected blade and the working state of the detected blade mounted on an engine in the related art is solved.
Description
Technical Field
The invention relates to the field of aeroengine detection, in particular to a device and a method for detecting vibration characteristics of a turbine rotor blade.
Background
Turbine rotor blades of aircraft engines are subjected to very high temperatures, aerodynamic pressures and centrifugal forces during operation. Turbine blades often fail in high cycle fatigue due to excessive vibrational stresses during engine operation, resulting in loss of thrust from the engine. At present, tests on two aspects are generally carried out, so that unacceptable vibration stress of the high-pressure turbine rotor blade in the working process is avoided, and high-cycle fatigue fracture of the blade is prevented. On one hand, in the test, the high-pressure turbine blade is fixed by adopting an independent clamp, the vibration characteristic of the high-pressure turbine rotor blade when the root is fixed is measured, the blade is subjected to vibration excitation through a vibration table or a vibration exciter, and the limit of the vibration stress which can be born by the high-pressure turbine blade is measured; on the other hand, in the core machine or engine complete machine test, the actual vibration stress of the high-pressure turbine rotor blade is measured and compared with the vibration stress limit, and the fact that the actual vibration stress is far smaller than the vibration stress limit is guaranteed. The former test is a vibration test of a single turbine blade, the mounting structure and rigidity of the blade are usually far different from the actual condition of an engine during the test, and the error of the measurement result of the vibration characteristic is large; in the latter test, because the test is carried out on a core machine or a complete machine, the structural factor limitation is large, and the number of positions which can be measured is small. The environmental temperature and the centrifugal force of the working state are high, the survival rate of the high-temperature strain gauge is very low, and the available data is little.
Disclosure of Invention
The invention aims to provide a device and a method for detecting the vibration characteristic of a turbine rotor blade, so as to solve the problem that the detection result error is large due to the fact that the difference between the state of the detected blade and the working state of the detected blade installed on an engine is large in the related art.
According to an aspect of an embodiment of the present invention, there is provided a turbine rotor blade vibration characteristic detecting apparatus including:
the vacuum bin is used for accommodating the turbine rotor;
the driving part is configured to be in transmission connection with a blade disc of the turbine rotor so as to drive the turbine rotor to rotate;
at least one nozzle disposed in the vacuum chamber and configured to eject fluid toward the blades mounted on the blade disc to excite the blades to vibrate;
and the measuring part comprises a strain gauge arranged in the vacuum chamber so as to detect the vibration characteristic of the blade.
In some embodiments, the plurality of nozzles are arranged side-by-side along a circumference of the vacuum chamber.
In some embodiments of the present invention, the,
the number of the nozzles arranged side by side in the circumferential direction of the vacuum bin is adjustable; or
The number of the nozzles in the working state in the plurality of nozzles arranged side by side in the circumferential direction of the vacuum chamber is adjustable.
In some embodiments of the present invention, the,
the nozzles are detachably arranged in the vacuum chamber, so that the number of the nozzles can be adjusted; or
The detection device also includes a plurality of valves disposed in one-to-one correspondence with the nozzles, the valves communicating with the respective nozzles.
In some embodiments, the driving part includes:
the driving motor is arranged at the outer side of the vacuum bin;
and the connecting shaft is connected with the driving motor and extends to the inside of the vacuum cabin so as to be connected with the turbine rotor.
In some embodiments, the measuring part further comprises:
the cable is connected with the strain gauge and rotates along with the connecting shaft;
and the sliding ring electricity-leading device is sleeved on the connecting shaft and comprises a fixed part and a moving part which is connected with the cable and rotates along with the cable, and the fixed part is electrically connected with the moving part.
In some embodiments, the detection device further comprises a signal processor connected with the fixed part of the slip ring current lead through a cable.
In some embodiments, the injection volume of the nozzle is adjustable to adjust the excitation force to the blade.
According to another aspect of the present invention, there is also provided a method of detecting a vibrational characteristic of a turbine rotor blade, the method comprising:
assembling a turbine rotor, including mounting blades on a blisk;
placing a turbine rotor in a vacuum bin;
driving the turbine rotor to rotate;
ejecting fluid to the blades to excite the blades to vibrate;
a vibration characteristic parameter of the blade is detected.
In some embodiments, assembling the turbine rotor includes connecting together the multiple stage blisks and mounting a blade on each stage blisk.
In some embodiments, the detection method further comprises adjusting a vibration frequency of the excitation blade, the adjusting the vibration frequency of the excitation blade comprising:
adjusting the rotation speed of the turbine rotor;
the number of nozzles, which are arranged along the circumferential direction of the turbine rotor and eject fluid to the blades, is adjusted.
In some embodiments, adjusting the frequency of vibration exciting the blades includes adjusting the frequency of vibration of the blades of different stages of the turbine rotor to be different.
By applying the technical scheme of the invention, the blade to be detected is arranged on the blade disc to form the turbine rotor and is driven by the driving part to rotate, so that the state of the blade to be detected is close to the normal working state of the blade to be detected, and the problem of larger detection result error caused by larger difference between the state of the blade to be detected and the working state of the blade to be detected arranged on an engine in the related technology is solved.
Other features of the present invention and advantages thereof will become apparent from the following detailed description of exemplary embodiments thereof, which proceeds with reference to the accompanying drawings.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the related art, the drawings needed to be used in the description of the embodiments or the related art will be briefly introduced below, it is obvious that the drawings in the following description are only 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.
FIG. 1 illustrates a schematic structural view of a device for detecting vibration characteristics of turbine rotor blades in accordance with an embodiment of the present invention;
FIG. 2 illustrates a close-up view of a turbine rotor blade of an embodiment of the present invention;
FIG. 3 illustrates a vibration characteristic parameter map of a blade detected by a detecting device of an embodiment of the present invention;
FIG. 4 is a schematic diagram showing the relationship between time, frequency and amplitude of a blade in a rotating state detected by a detecting device according to an embodiment of the present invention, and the thickness of a black line represents the amplitude;
FIG. 5 shows a schematic view of the mounting position of the damping on the blade of an embodiment of the invention;
FIG. 6 shows a comparison of damping versus strain on a blade of an embodiment of the present invention.
In the figure:
1. a turbine rotor; 2. a drive section; 3. a measuring section; 4. a nozzle; 5. a leaf disc; 6. a blade; 7. a drive motor; 8. a bearing; 9. a connecting shaft; 10. a slip ring current lead; 11. a strain gauge; 12. a signal processor; 13. a vacuum bin; 14. damping; 20. a pump; 201. a recovery pipeline; 202. a delivery line.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments 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. The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the invention, its application, or uses. 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.
Fig. 1 shows a schematic configuration diagram of a device for detecting vibration characteristics of a turbine rotor blade according to an embodiment of the present invention. FIG. 2 illustrates a close-up view of a turbine rotor blade of an embodiment of the present invention.
As shown in fig. 1 and 2, the device for detecting the vibration characteristics of the turbine rotor blade of the present embodiment includes a vacuum chamber 13 for housing the turbine rotor 1, a driving portion 2 for driving the turbine rotor 1 to rotate and controlling the rotation speed of the turbine rotor 1, at least one nozzle 4 provided in the vacuum chamber 13, and a measuring portion 3 configured to measure the vibration characteristics of the blade 6.
The turbine rotor 1 includes a blisk 5 and a plurality of blades 6 connected to the blisk 5 by a dovetail structure. A plurality of blades 6 are arranged along the circumferential direction of the blisk 5. The turbine rotor 1 includes multiple stages of turbine rotors arranged side by side in the axial direction, each of which includes a blisk 5 and a plurality of blades 6 mounted on the blisk 5.
As shown in FIG. 5, in some embodiments, a damper 14 is also provided below the platform of the blades 6 when the turbine rotor 1 is being tested.
The nozzles 4 provided in the vacuum chamber 13 eject fluid toward the blades 6 of the turbine rotor 1 to excite the blades 6 to vibrate. In this embodiment, the fluid ejected from the nozzle 4 is oil.
The measurement unit 3 includes a strain gauge 11 provided in a vacuum chamber 13 and a signal processor 12 electrically connected to the strain gauge 11. As shown in fig. 2, strain gauges 11 are attached to the blade 6 to acquire vibration information of the blade 6, the strain gauges 11 transmit electric signals representing the vibration information to a signal processor 12, and the signal processor 12 converts the electric signals into strain data.
In some embodiments, to facilitate a clear measurement of the vibrational stress of the blade 6, strain gauges 11 are affixed to the bottom of the suction side of the blade 6.
In this embodiment, the blade 6 to be measured is mounted on the blade disc 5 to form the turbine rotor 1, and is driven by the driving part 2 to rotate, so that the state of the blade 6 to be measured is close to the normal working state thereof, which is beneficial to improving the problem that the difference between the state of the blade 6 to be measured and the working state thereof mounted on the engine in the related art is large, which results in a large error of the detection result.
The turbine rotor 1 comprises a plurality of stages of blade discs 5 which are connected together, blades 6 are connected to each stage of blade disc 5, the installation form of the blades is consistent with the real state of an engine, and the driving part 2 drives the turbine rotor 1 to rotate at a high speed to simulate the centrifugal force applied to the blades 6 in the working state of the engine during testing. The turbine rotor 1 to be tested is placed in the vacuum bin 13, and the vacuum bin 13 is vacuumized during rotation, so that heat generated by friction between the turbine rotor 1 and air is avoided.
Further, the blade 6 to be measured and the blade disc 5 are placed in the vacuum chamber 13, which improves the problem that the life and detection accuracy of the strain gauge 11 are affected by a large amount of heat generated by friction between the blade 6 rotating at a high speed and air in the related art.
A plurality of nozzles 4 are arranged side by side along the circumferential direction in the vacuum chamber 13. After the turbine rotor 1 is placed in the vacuum chamber 13, the plurality of nozzles 4 are arranged side by side along the circumferential direction of the turbine rotor 1. When the vibration characteristics of the blades 6 are detected, at least some of the nozzles 4 continuously discharge the fluid, and the blades 6 of the turbine rotor 1 are excited once per one nozzle 4 discharging the fluid, so that the number of times the blades 6 are excited per unit time can be adjusted by adjusting the number of revolutions of the turbine rotor 1 or the number of nozzles 4 discharging the fluid toward the blades 6 in the circumferential direction of the turbine rotor 1, thereby adjusting the excitation frequency of the blades 6.
The nozzles 4 are uniformly arranged on the inner wall surface of the vacuum chamber 13 in the circumferential direction, and provide periodic exciting force by spraying fluid onto the rotating blade 6, and the exciting frequency of the blade 6 satisfies the formula: the exciting frequency is the rotating speed multiplied by the number of the nozzles.
The ejection volume of the nozzle 4 is adjustable to adjust the exciting force to the vane 6. The nozzle 4 controls the excitation size of the vane 6 by the mass sprayed per second, and the nozzle 4 controls the excitation position and area of the vane 6 by adjusting the shape of the oil sprayed.
At least one nozzle 4 is provided in the circumferential direction of each stage of the disk 5 to excite the blades 6 mounted on the corresponding disk 5 to vibrate. By controlling the number of the nozzles 4 in the circumferential direction of each stage of the blade disc 5, different blade excitation frequencies of different stages at the same rotating speed can be realized. The nozzle 4 takes pressure as a judgment standard, the minimum pressure of the liquid sprayed out from the nozzle 4 in a cone is required to be ensured, and then oil pressure calibration is carried out. The oil pressure is set according to the test requirements.
In some embodiments, the nozzles 4 are removably mounted in the vacuum silo 13 so as to adjust the number of nozzles 4 arranged along the circumference of the turbine rotor 1.
In other embodiments, the detection device further includes a plurality of valves disposed in one-to-one correspondence with the nozzles 4, the valves communicating with the respective nozzles 4 to control whether the respective nozzles 4 eject the fluid, and the number of nozzles ejecting the fluid is adjustable by controlling opening and closing of the valves, thereby adjusting the excitation frequency of the vanes 6.
The detection device further comprises a pump 20 for supplying fluid to the nozzle 4 and a delivery line 202 connected between the pump 20 and the nozzle 4. The detection device further comprises a recovery line 201 for discharging the fluid inside the vacuum chamber 13.
As shown in fig. 1, the driving part 2 includes a driving motor 7 provided outside the vacuum chamber 13 and a connecting shaft 9 connected to the driving motor 7. The connecting shaft 9 is connected with the driving motor 7 and extends to the inside of the vacuum chamber 13 to connect the turbine rotor 1.
The detection device also comprises a bearing 8 sleeved on the connecting shaft 9. The bearing 8 forms a fulcrum for supporting the mounting of the connecting shaft 9. The fulcrum limits the vertical and horizontal displacement of the connecting shaft 9 through the bearing 8, thereby indirectly suspending the turbine rotor 1 in the vacuum chamber 13.
In some embodiments, the vacuum chamber 13 is cylindrical. The vacuum chamber 13 is coaxial with the connecting shaft 9. When the turbine rotor 1 is mounted on the connecting shaft 9, the turbine rotor 1 is coaxial with the vacuum chamber.
As shown in fig. 1, the measurement section 3 further includes a cable and slip ring current lead 10. The cable is connected with the strain gauge 11 and rotates along with the connecting shaft 9; and the slip ring electricity-leading device 10 is sleeved on the connecting shaft 9, the slip ring electricity-leading device 10 comprises a fixed part and a moving part which is connected with the cable and rotates along with the cable, and the fixed part is electrically connected with the moving part. The slip ring electricity leading device 10 is fixed on the ground through a fulcrum.
The detection device further comprises a signal processor 12 connected with the fixed part of the slip ring current lead 10 through a cable.
According to another aspect of the present invention, the present embodiment further provides a method for detecting vibration characteristics of a turbine rotor blade, the method comprising:
assembling the turbine rotor 1, including mounting the blades 6 on the blisk 5;
placing the turbine rotor 1 in a vacuum silo 13;
driving the turbine rotor 1 to rotate;
ejecting fluid to the blades 6 to excite the blades 6 to vibrate;
the vibration characteristic parameters of the blade 6 are detected.
Assembling the turbine rotor 1 includes connecting together the multiple stage blisks 5 and mounting a blade 6 on each stage blisk 5.
The detection method further comprises adjusting the vibration frequency of the excitation blade 6, wherein adjusting the vibration frequency of the excitation blade 6 comprises:
adjusting the rotation speed of the turbine rotor 1; or
The number of nozzles 4 arranged in the circumferential direction of the turbine rotor 1, which eject fluid to the blades 6, is adjusted.
The steps of detecting the vibration characteristics of the turbine rotor blades are as follows:
1. the strain gauge 11 is adhered to the measured blade 6, the strain gauge 11 is connected to the slip ring current lead device 10 through a lead, an electric signal on the turbine rotor in a rotating state is transmitted to the static signal processor 12 through the slip ring current lead device 10, and the voltage data is converted into strain data through the signal processor 12.
2. The rotor turbine rotor 1 is placed in the vacuum chamber 13, and the air in the vacuum chamber 13 is extracted to reduce the internal pressure to 100Pa or less. The purpose of the vacuum pumping is to prevent the heat generated by the friction between the rotor rotating at high speed and air during the test.
3. The rotating speed of the turbine rotor is slowly increased to a test rotating speed through the driving motor 7, the turbine rotor stays at the test rotating speed, and time domain data of strain are recorded through the signal processor 12 and stored in the storage device.
4. The nozzle 4 is opened, the oil liquid ejection quality is set to a certain fixed value, and the time domain data and the frequency domain data of the strain are recorded by the signal processor 12 and stored in the storage device.
5. Because the natural frequency of the blade has certain dispersibility, the rotating speed of the turbine rotor 1 is changed by adjusting the driving motor 7, so that the rotating speed slowly rises and falls in the upper rotating speed band and the lower rotating speed band of the test rotating speed, and the time domain data and the frequency domain data of the strain are recorded by the signal processor 12 and stored in the storage device.
6. And (5) adjusting the oil spraying quality of the nozzle 4 to be another fixed value, changing the excitation magnitude of the blade 6, and repeating the test of the step 5.
7. Stopping data recording of the signal processor 12, closing the nozzle 4, reducing the rotating speed of the turbine rotor to 0, flushing air into the vacuum bin 13, opening the vacuum bin, removing the turbine rotor 1, and checking whether the turbine rotor 1 is damaged.
The raw data recorded by the strain signal processor 12 is time domain data of strain change with time, as shown in fig. 3, wherein the abscissa is time, the ordinate is strain magnitude, and the curve in the graph represents the change of strain magnitude measured by the strain gauge on the blade with time. The strain data recorded by the signal processor 12 is processed by fourier transform to be in the form of a frequency domain as shown in fig. 4, fig. 4 being a three-dimensional data graph with the abscissa representing time of the turbine rotor, the ordinate representing vibration frequency of the blade, and the thickness of the black line in the graph representing the magnitude of strain. Fig. 4 represents vibration characteristic information of the blade in a rotating state, such as damping, natural frequency and the like, and meanwhile, whether the blade generates obvious resonance in a test rotating speed range can be judged. FIG. 5 represents a schematic view of the under platform damper 14 position of blade 6. FIG. 6 is a schematic diagram of the effect of blade strain without damping and with different mass damping, with no damping and different damping masses on the abscissa, and mass normalization. The ordinate is strain, normalized to strain.
The technical problem solved by the embodiment is as follows:
1. since the connection structure of the blade 6 and the blade disc 5 has a great influence on the vibration characteristics, the actual conditions of the blade 6 and the engine are greatly different, and therefore, the test object must contain a blade-blade disc assembly;
2. the centrifugal force can change the rigidity distribution of the blade, the centrifugal force of the blade can be considered in the vibration characteristic test method, and the blade is tested in a rotating state in the embodiment;
3. the vibration excitation source under the working environment of the engine is wide, the vibration excitation source is as low as about 200Hz of the rotor fundamental frequency, the excitation frequency caused by the front blade 6 and the rear blade 6 is as high as about 10000Hz, and the excitation frequency of the blade by the vibration characteristic testing method can at least cover 500 Hz-20000 Hz.
4. The excitation frequencies required by different stages of blades of a multi-stage turbine rotor during testing are different, and different excitation frequencies are required to be given to different stages of blades at the same rotating speed;
5. since the vibration characteristics of the blades under different excitation forces are different, the test method must be able to adjust the magnitude of the excitation force.
The test method solves the difficulty of realizing vibration excitation on the blade with higher rigidity in a high-speed rotation state and the difficulty of acquiring test data from time to time on the vibration response in the rotation state. The invention discloses a vibration characteristic test system of a multistage turbine blade-vane disk in a high-speed rotation state; a method for turbine blade excitation and testing in a rotating state is established. The test method can directly obtain the blade vibration characteristics, the blade frequency and the like of the real rotor system at the working state of the engine at normal temperature. The test data acquired by the method can be used for designing the blade, and the measured strain value can be used for designing the damping device.
The test can consider the rigidity change of each point of the blade under the action of centrifugal force, and obtain the real blade frequency.
The number of the nozzles is adjusted through different excitation frequencies of different stages of blades, and the test method can test the vibration test of a single-stage rotor system. And is suitable for vibration testing of multi-stage rotor systems
The present invention is not limited to the above exemplary embodiments, and any modifications, equivalent replacements, improvements, etc. within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (12)
1. An apparatus for detecting a vibrational characteristic of a turbine rotor blade, comprising:
a vacuum chamber (13) for accommodating the turbine rotor (1);
the driving part (2) is configured to be in transmission connection with a blade disc (5) of the turbine rotor (1) so as to drive the turbine rotor (1) to rotate;
at least one nozzle (4) arranged in the vacuum chamber (13) and configured to eject a fluid towards blades (6) mounted on the bladed disc (5) in order to excite the blades (6) into vibration;
a measuring part (3) comprising a strain gauge (11) arranged in a vacuum chamber (13) for detecting the vibration characteristics of the blade (6).
2. The detection device according to claim 1, characterized in that a plurality of nozzles (4) are arranged side by side along the circumference of the vacuum chamber (13).
3. The detection apparatus according to claim 1,
the number of the nozzles (4) arranged side by side in the circumferential direction of the vacuum bin (13) is adjustable; or
The number of the nozzles (4) in the working state in the plurality of nozzles (4) arranged side by side in the circumferential direction of the vacuum chamber (13) is adjustable.
4. The detection apparatus according to claim 3,
the nozzles (4) are detachably mounted on the vacuum chamber (13) so as to adjust the number of the nozzles (4); or
The detection device further comprises a plurality of valves arranged in one-to-one correspondence with the nozzles (4), the valves being in communication with the respective nozzles (4).
5. The detection device according to claim 1, wherein the drive portion (2) comprises:
the driving motor (7) is arranged on the outer side of the vacuum bin (13);
the connecting shaft (9) is connected with the driving motor (7) and extends to the interior of the vacuum bin (13) so as to be connected with the turbine rotor (1).
6. The detection device according to claim 5, wherein the measurement portion (3) further comprises:
the cable is connected with the strain gauge (11) and rotates along with the connecting shaft (9);
and the slip ring electricity-leading device (10) is sleeved on the connecting shaft (9), the slip ring electricity-leading device (10) comprises a fixed part and a moving part which is connected with the cable and rotates along with the cable, and the fixed part is electrically connected with the moving part.
7. The detection device according to claim 6, further comprising a signal processor (12) connected by a cable to a stationary part of the slip ring current lead (10).
8. The detection device according to claim 1, wherein the ejection volume of the nozzle (4) is adjustable to adjust the excitation force to the blade (6).
9. A method of detecting a vibrational characteristic of a turbine rotor blade, comprising:
assembling a turbine rotor (1) comprising mounting blades (6) on a blisk (5);
-placing the turbine rotor (1) in a vacuum chamber (13);
driving the turbine rotor (1) to rotate;
-ejecting a fluid towards the blade (6) to excite the blade (6) to vibrate;
the vibration characteristic parameters of the blade (6) are detected.
10. The inspection method according to claim 9, wherein assembling the turbine rotor (1) comprises connecting together a plurality of stages of blisks (5) and mounting a blade (6) on each stage of blisk (5).
11. The detection method according to claim 9, further comprising adjusting a vibration frequency exciting the blade (6), the adjusting the vibration frequency exciting the blade (6) comprising:
-adjusting the rotational speed of the turbine rotor (1);
adjusting the number of nozzles (4) arranged in the circumferential direction of the turbine rotor (1) that eject fluid toward the blades (6).
12. The detection method according to claim 11, wherein said adjusting the vibration frequency exciting the blades (6) comprises adjusting the vibration frequency of the blades of the turbine rotor of different stages to be different.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201911289238.XA CN112985721A (en) | 2019-12-13 | 2019-12-13 | Device and method for detecting vibration characteristics of turbine rotor blade |
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| CN201911289238.XA CN112985721A (en) | 2019-12-13 | 2019-12-13 | Device and method for detecting vibration characteristics of turbine rotor blade |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2022267611A1 (en) * | 2021-06-23 | 2022-12-29 | 中国航发商用航空发动机有限责任公司 | Vibration excitation device and oil-injection vibration excitation system |
| DE102022133376A1 (en) | 2022-12-15 | 2024-06-20 | MTU Aero Engines AG | METHOD FOR MEASURING A COMPONENT |
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| US20100286934A1 (en) * | 2007-04-03 | 2010-11-11 | Arnold Kuehhorn | Method for determining blade mistuning on integrally manufactured rotor wheels |
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2019
- 2019-12-13 CN CN201911289238.XA patent/CN112985721A/en active Pending
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|---|---|---|---|---|
| JPH07128198A (en) * | 1993-10-29 | 1995-05-19 | Mitsubishi Heavy Ind Ltd | Exciter for testing vibration and rotation of wing |
| JPH112586A (en) * | 1997-06-11 | 1999-01-06 | Mitsubishi Heavy Ind Ltd | Blade shaker used in rotational vibration test |
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| WO2022267611A1 (en) * | 2021-06-23 | 2022-12-29 | 中国航发商用航空发动机有限责任公司 | Vibration excitation device and oil-injection vibration excitation system |
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