CN114720075A - Turbine blade flange damping test system - Google Patents
Turbine blade flange damping test system Download PDFInfo
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- CN114720075A CN114720075A CN202210345053.1A CN202210345053A CN114720075A CN 114720075 A CN114720075 A CN 114720075A CN 202210345053 A CN202210345053 A CN 202210345053A CN 114720075 A CN114720075 A CN 114720075A
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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
- G01M7/025—Measuring arrangements
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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
- G01M7/027—Specimen mounting arrangements, e.g. table head adapters
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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
- G01M7/04—Monodirectional test stands
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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
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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Abstract
The application provides a turbine blade flange damping test system, which comprises a vibration table, a fixed clamp, a clamping clamp, a turbine blade, a flange damper, a strain gauge, an acceleration sensor, a steel cable, a fixed pulley, a force sensor, a ball hinge support, a lever and a weight, wherein the clamping clamp is provided with a tongue-and-groove structure matched with the shape of a tenon of the turbine blade, the turbine blade is assembled and installed in the tongue-and-groove structure of the clamping clamp through the tenon, the turbine blade, the clamping clamp, the fixed clamp and the vibration table are combined into a rigid body, the flange damper is arranged at the joint of adjacent turbine blade flanges and connected with the steel cable, the other end of the steel cable is connected with the force sensor through the fixed pulley and further connected to the lever, one end of the lever is fixed on the ball hinge support, the weight is hung at the other end of the lever, thereby realizing the loading of a simulated centrifugal force, the surface of a blade body of the turbine blade to be tested is pasted with the strain gauge, an acceleration sensor is mounted at a tip position relative to the turbine blade.
Description
Technical Field
The application belongs to the technical field of aero-engine design, and particularly relates to a turbine blade flange damping test system.
Background
In a gas turbine engine structure, turbine blades are in a complex working environment of fluid-solid-thermal coupling, and have high requirements on strength and service life. The excitation factors of the turbine blade under the unsteady flow field are related to a casing, a stator blade, a support plate and the like, and harmful vibration is easily induced to cause high cycle fatigue failure of the turbine blade. The turbine blade is generally provided with a longer extension root due to the cooling requirement, on one hand, the structure enables the cantilever of the turbine blade to be lengthened and weakened, and the failure is easy to be induced, and on the other hand, the feasibility of designing the edge plate damper at the position is improved due to the sufficient space. The edge plate damper can effectively reduce the vibration response of the turbine blade, but due to the complex contact state and the load environment of the edge plate damper, the simulation precision of the damping effect of the edge plate damper is always greatly limited, and the structural design mainly depends on engineering experience.
Due to the new requirements of turbine blade vibration reduction, a new platform damper scheme is urgently needed to reduce the turbine blade vibration response and improve the high cycle fatigue resistance of the blade. Therefore, a turbine blade edge plate damping effect testing system which is low in cost, high in precision and easy to realize is urgently needed to support the structural design of the edge plate damper.
In the prior art, for example, patent No. cn201710070743.x discloses a vibration reduction test device for a turbine blade with a flange damper structure, and patent No. CN201910964045.3 discloses a vibration magnetic vibration-induced modeling test device for a rotary damping blade, but the two flange dampers have the following disadvantages:
1) in the vibration reduction test device, the load is loaded by a spring, the simulated centrifugal force fluctuates along with the amplitude and is inconsistent with the actual working state of the turbine blade edge plate damper, so that the result deviation is caused;
2) in the vibration damping test device, a real blade cannot be installed on a mortise simulation piece, the contact state of a flange plate damper and a blade extension root cannot be simulated, and the structural damping state and the damping state of the flange plate damper are inconsistent with the real working state of a turbine blade, so that the result deviation is caused;
3) in the vibration damping test device, a real turbine blade cannot be adopted, so that the vibration response of the blade in different damping states cannot be tested;
4) the rotary damping excitation device needs a complete turbine disc and blades, and the cost is too high;
5) the rotary damping excitation device is influenced by an electric initiator and an excitation source, the excitation force adjusting range is narrow, and the vibration response of the blade cannot be accurately measured at multiple points.
Disclosure of Invention
It is an object of the present application to provide a turbine blade platform damping test system to address or mitigate at least one of the problems of the background art.
The technical scheme of the application is as follows: the utility model provides a turbine blade flange damping test system, test system includes shaking table, mounting fixture, centre gripping anchor clamps, turbine blade, flange attenuator, foil gage, acceleration sensor, cable wire, fixed pulley, force transducer, ball hinge support, lever, weight, dynamic stress test system and acceleration test system, wherein:
the vibration table provides power required by vibration of the edge plate damper, and the fixed clamp is fixed with the vibration table through a fixed bolt;
the side edge of the fixed clamp is provided with a notch, and the clamping clamp is fixedly arranged at the notch of the fixed clamp through a self-locking bolt;
a mortise structure matched with the shape of the tenon of the turbine blade is arranged on the clamping fixture;
the turbine blade is assembled and installed in a mortise structure of the clamping fixture through a tenon, the clamping fixture is deformed through the pretightening force of the self-locking bolt, the turbine blade is clamped, and therefore the turbine blade, the clamping fixture, the fixed fixture and the vibrating table are combined into a rigid body;
the platform comprises a platform body, a platform hinge support, a platform and a platform, wherein the platform body is provided with a platform, the platform damper is arranged at the joint of adjacent turbine blade platforms, the platform body is connected with a steel cable, the platform damper is connected with the platform, the platform body is connected with a steel cable, the other end of the steel cable is connected with a fixed pulley, one end of the platform hinge support, one end of the platform is fixed pulley, one end of the platform is fixed on the platform hinge support, and is fixed pulley, and is fixed on the platform hinge support, and is fixed pulley, the platform hinge support, the platform body is connected with a weight, the platform, so that the platform is hung with a weight, the platform body, so as to realize the platform, so as to simulate the loading of the platform, so as to realize the loading of the platform, so as to simulate the platform, so as to realize the platform, the loading of the platform, so as to realize the platform, the loading of the platform to realize the platform to simulate centrifugal force loading of the platform, so as to realize the platform, the platform to realize loading of the platform, to realize the loading of the platform, so as to realize the loading of the platform;
the method comprises the following steps that a strain gauge is attached to the surface of a blade body of a turbine blade to be tested, the strain gauge is connected to a dynamic stress testing system through a cable, and a stress measurement value of the strain gauge is obtained through the dynamic stress testing system;
and an acceleration sensor is arranged at the position of the blade tip relative to the turbine blade and is connected with an acceleration testing system through a cable, so that the monitoring on the vibration stress and the vibration response of the turbine blade is realized.
Furthermore, the tail end of each mortise structure is provided with an elastic groove communicated with the mortise structure, and the clamping fixture forms an elastic clamping structure for clamping the turbine blade through the elastic groove.
Further, the edge plate damper and the steel cable are fixed in a welding mode.
Furthermore, a plurality of strain gauges are attached along the blade body direction of the turbine blade.
Furthermore, the number of the mortise structures arranged on the clamping fixture is three or more.
Further, when the number of the mortise structures on the clamping fixture is three or more, the turbine blades in the middle position or the non-edge position among the turbine blades matched with the mortise structures form a turbine blade to be tested, the weight-loaded flange dampers are positioned on two sides of the turbine blade to be tested, and the acceleration sensor corresponds to the tip position of the turbine blade to be tested.
Compared with the prior art, the damping test system has the following advantages:
1) by adopting a loading force mode of weight loading and lever amplification, the load is constant and has no fluctuation (the load is always equal to the weight gravity), the centrifugal force of the edge plate damper can be effectively simulated, and the method is easy to realize;
2) the clamping fixture with a real mortise structure and a real turbine blade are adopted, the contact state of the edge plate damper and the turbine blade is consistent with the real using environment, and the test simulation precision is high;
3) the real turbine blade is adopted, and the dynamic stress test system and the acceleration test system are adopted to measure the vibration response and the vibration stress level of the blade, so that quantitative damping effect data can be obtained, and the data reliability is high;
4) the clamping fixture for simulating the turbine disc is used, the complete turbine disc is not needed, the turbine blade can be continuously used after the test, and the cost is low;
5) the vibration table is used as an excitation source, the adjustment range of the excitation force is wide, the test equipment is not limited, and more test data can be obtained.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.
FIG. 1 is a schematic view of an exemplary turbine blade of the present application.
FIG. 2 is a schematic view of a turbine bucket platform damping test system of the present application.
FIG. 3 is a schematic view of a turbine blade in an engaged state.
Reference numerals:
1-vibration table
2-stationary fixture
3-self-locking bolt
4-clamping fixture
5-turbine blade
6-edge plate damper
7-strain gauge
8-acceleration sensor
9-Steel rope
10-fixed pulley
11-force sensor
12-ball hinge support
13-Lever
14-weight
15-dynamic stress test system
16-acceleration test system
17-fixing bolt
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.
In order to solve the problems that the simulation of the load environment of a damping test device in the prior art is inaccurate, the simulation of the contact state is not real, and the test of real turbine blades cannot be carried out, the invention provides a novel turbine blade flange damping test system.
Referring to fig. 1, which is a schematic view of a typical turbine blade structure, a lower end of a blade body of the turbine blade 1 is provided with a flange 11, a lower end of the flange 11 is provided with a tongue 12 and a tenon, the tenon is used for matching with a mortise 21 of a wheel disc 2, and the tongue 12 is used for connecting the blade body and the tenon. Platform dampers are typically located at platform 11 locations to reduce turbine blade vibrational response and improve blade resistance to high cycle fatigue.
As shown in FIG. 2, in order to verify the turbine blade damping effect test with the platform damper, the turbine blade platform damping test system provided by the application mainly comprises the following components: the device comprises a vibration table 1, a fixing clamp 2, a clamping clamp 4, a turbine blade 5, a flange plate damper 6, a strain gauge 7, an acceleration sensor 8, a steel cable 9, a fixed pulley 10, a force sensor 11, a ball hinge support 12, a lever 13, a weight 14, a dynamic stress testing system 15 and an acceleration testing system 16.
The vibration table 1 provides power required by the vibration of the edge plate damper 6, and the fixing clamp 2 is fixed with the vibration table 1 through a fixing bolt 17.
The side of mounting fixture 2 is equipped with the breach, and centre gripping anchor clamps 4 pass through the fixed breach department that sets up at mounting fixture 2 of self-locking bolt 3.
The clamping fixture 4 is provided with a mortise structure matched with the shape of the turbine blade tenon, and the tail end of each mortise structure is provided with an elastic groove 41 communicated with the mortise structure.
The tenon of the turbine blade 5 is assembled with the mortise structure of the clamping fixture 4, the clamping fixture 4 is deformed through the pretightening force of the self-locking bolt 3, the turbine blade 5 is clamped, and the turbine blade 5, the clamping fixture 4, the fixing fixture 2 and the vibration table 1 are combined into a rigid body.
The blade surface of the turbine blade 5 to be tested is attached with a strain gage 7, preferably a plurality of strain gages, in the direction of the blade body of the turbine blade. The strain gauge 7 is connected by a cable to a dynamic stress testing system 15, and a stress measurement value of the strain gauge 7 can be obtained by the dynamic stress testing system 15. An acceleration sensor 8 for measuring the blade tip movement is arranged near the blade tip of the turbine blade 5, and the acceleration sensor 8 is connected with an acceleration testing system 16 through a cable, so that the monitoring of the vibration stress and the vibration response of the turbine blade is realized.
In the preferred embodiment of the present application, the number of the mortise structure on the holding jig 4 is three or more, so that the number of the turbine blades 5 matched with the mortise structure is three or more, and among the three or more turbine blades 5, the turbine blade 5 in the middle position or the non-edge position constitutes the object to be measured, and the platform dampers 6 on both sides of the turbine blade 5 to be measured are loaded by the structure such as the wire rope 9. Meanwhile, the strain gauge 7 is adhered to the turbine blade 5 to be measured, and the acceleration sensor 8 is aligned with the tip position of the turbine blade 5 to be measured.
When the test system works, firstly, the test system is installed according to the assembly relation of the components; and then calculating the centrifugal force according to the rotating speed of the turbine blade 5 to obtain the centrifugal force, and selecting a proper number of weights 14 to realize the contact pressure simulation of the flange damper 6 and the flange contact surface of the turbine blade 5. The turbine blade 5 is subjected to a vibratory excitation by the vibration table 1 and the excitation force and frequency are recorded. The dynamic stress test system 15 measures the dynamic stress distribution of the turbine blade 5 through the strain gauge 7, and the acceleration test system 16 measures the response information of the turbine blade 5 from the blade tip to the acceleration/speed/displacement and the like through the acceleration sensor 8, so that the vibration response quantitative relation test of the edge plate damper 6 and the turbine blade 5 is realized.
Compared with the prior art, the damping test system has the following advantages:
1) by adopting a loading force mode of weight loading and lever amplification, the load is constant and has no fluctuation (the load is always equal to the weight gravity), the centrifugal force of the edge plate damper can be effectively simulated, and the method is easy to realize;
2) the clamping fixture with a real mortise structure and a real turbine blade are adopted, the contact state of the edge plate damper and the turbine blade is consistent with the real using environment, and the test simulation precision is high;
3) the real turbine blade is adopted, and the dynamic stress test system and the acceleration test system are adopted to measure the vibration response and the vibration stress level of the blade, so that quantitative damping effect data can be obtained, and the data reliability is high;
4) the clamping fixture for simulating the turbine disc is used, the complete turbine disc is not needed, the turbine blade can be continuously used after the test, and the cost is low;
5) the vibration table is used as an excitation source, the adjustment range of the excitation force is wide, the test equipment is not limited, and more test data can be obtained.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (6)
1. The utility model provides a turbine blade flange damping test system, its characterized in that, test system includes shaking table, mounting fixture, centre gripping anchor clamps, turbine blade, flange attenuator, foil gage, acceleration sensor, cable wire, fixed pulley, force transducer, ball hinge support, lever, weight, dynamic stress test system and acceleration test system, wherein:
the vibration table provides power required by vibration of the edge plate damper, and the fixed clamp is fixed with the vibration table through a fixed bolt;
the side edge of the fixed clamp is provided with a notch, and the clamping clamp is fixedly arranged at the notch of the fixed clamp through a self-locking bolt;
the clamping fixture is provided with a mortise structure matched with the shape of the tenon of the turbine blade;
the turbine blade is assembled in a mortise structure of the clamping fixture through a tenon, the clamping fixture is deformed through the pretightening force of the self-locking bolt, and the turbine blade is clamped, so that the turbine blade, the clamping fixture, the fixed fixture and the vibrating table are combined into a rigid body;
the platform comprises a platform body, a platform hinge support, a platform and a platform, wherein the platform body is provided with a platform, the platform damper is arranged at the joint of adjacent turbine blade platforms, the platform body is connected with a steel cable, the platform damper is connected with the platform, the platform body is connected with a steel cable, the other end of the steel cable is connected with a fixed pulley, one end of the platform hinge support, one end of the platform is fixed pulley, one end of the platform is fixed on the platform hinge support, and is fixed pulley, and is fixed on the platform hinge support, and is fixed pulley, the platform hinge support, the platform body is connected with a weight, the platform, so that the platform is hung with a weight, the platform body, so as to realize the platform, so as to simulate the loading of the platform, so as to realize the loading of the platform, so as to simulate the platform, so as to realize the platform, the loading of the platform, so as to realize the platform, the loading of the platform to realize the platform to simulate centrifugal force loading of the platform, so as to realize the platform, the platform to realize loading of the platform, to realize the loading of the platform, so as to realize the loading of the platform;
the method comprises the following steps that a strain gauge is attached to the surface of a blade body of a turbine blade to be tested, the strain gauge is connected to a dynamic stress testing system through a cable, and a stress measurement value of the strain gauge is obtained through the dynamic stress testing system;
and an acceleration sensor is arranged at the position of the blade tip relative to the turbine blade and is connected with an acceleration testing system through a cable, so that the monitoring on the vibration stress and the vibration response of the turbine blade is realized.
2. The turbine blade platform damping test system of claim 1, wherein a distal end of each said tongue and groove structure defines a resilient slot in communication with said tongue and groove structure, whereby said clamping fixture defines a resilient clamping structure for clamping a turbine blade.
3. The turbine bucket platform damping test system of claim 1 wherein said platform dampers are secured to steel cables by welding.
4. The turbine blade platform damping test system of claim 1, wherein a plurality of said strain gages are attached along a blade body of a turbine blade.
5. The turbine bucket platform damping test system of claim 1 wherein three or more tongue and groove structures are provided on said clamp fixture.
6. A turbine blade platform damping test system according to claim 5, wherein when there are three or more tongue and groove structures on the clamping fixture, the turbine blades in the middle position or the non-edge position among the turbine blades fitted with the tongue and groove structures constitute the turbine blade under test, the platform dampers loaded by weights are located on both sides of the turbine blade under test, and the acceleration sensor corresponds to the tip position of the turbine blade under test.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210345053.1A CN114720075A (en) | 2022-03-31 | 2022-03-31 | Turbine blade flange damping test system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210345053.1A CN114720075A (en) | 2022-03-31 | 2022-03-31 | Turbine blade flange damping test system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114720075A true CN114720075A (en) | 2022-07-08 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210345053.1A Pending CN114720075A (en) | 2022-03-31 | 2022-03-31 | Turbine blade flange damping test system |
Country Status (1)
| Country | Link |
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| CN (1) | CN114720075A (en) |
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2022
- 2022-03-31 CN CN202210345053.1A patent/CN114720075A/en active Pending
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