CN108036911B - Test device for measuring damping vibration attenuation effect of turbine movable blade - Google Patents
Test device for measuring damping vibration attenuation effect of turbine movable blade Download PDFInfo
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- CN108036911B CN108036911B CN201711332859.2A CN201711332859A CN108036911B CN 108036911 B CN108036911 B CN 108036911B CN 201711332859 A CN201711332859 A CN 201711332859A CN 108036911 B CN108036911 B CN 108036911B
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- 238000013016 damping Methods 0.000 title claims abstract description 59
- 230000000694 effects Effects 0.000 title claims abstract description 21
- 238000012360 testing method Methods 0.000 title claims abstract description 21
- 230000007246 mechanism Effects 0.000 claims abstract description 39
- 230000001133 acceleration Effects 0.000 claims abstract description 8
- 229910000831 Steel Inorganic materials 0.000 claims description 4
- 239000010959 steel Substances 0.000 claims description 4
- 238000010521 absorption reaction Methods 0.000 claims 6
- 230000035939 shock Effects 0.000 claims 6
- 238000011160 research Methods 0.000 abstract description 7
- 238000013461 design Methods 0.000 abstract description 6
- 238000005259 measurement Methods 0.000 abstract description 4
- 230000008878 coupling Effects 0.000 abstract description 3
- 238000010168 coupling process Methods 0.000 abstract description 3
- 238000005859 coupling reaction Methods 0.000 abstract description 3
- 230000005540 biological transmission Effects 0.000 description 2
- 230000005284 excitation Effects 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 230000004044 response Effects 0.000 description 2
- 238000004088 simulation Methods 0.000 description 2
- 238000004364 calculation method Methods 0.000 description 1
- 238000010586 diagram 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
- 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
- G01M13/00—Testing of machine parts
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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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Abstract
The invention discloses a test device for measuring damping vibration attenuation effects of turbine movable blades, and belongs to the technical field of turbine movable blade tests. The test device comprises a first loading mechanism for applying centrifugal load to a blade part of the turbine movable blade, a second loading mechanism for applying centrifugal load to a damping part of the turbine movable blade, a vibration mechanism for providing vibration, a clamp for clamping the blade and an acceleration sensor for measuring vibration effect, and can ensure that the two sets of loading mechanisms are mutually independent when performing loading work and do not generate coupling phenomenon, solve the problem of damping measurement of the existing turbine movable blade in a working state, provide technical support for design and research of the damping of the movable blade of the engine and provide guarantee for research of the safety and reliability of the engine.
Description
Technical Field
The invention belongs to the technical field of turbine movable blade tests, and particularly relates to a test device for measuring damping and vibration attenuation effects of turbine movable blades.
Background
Based on the fact that the working environment of the turbine movable blade is severe, the aerodynamic force and the unstable excitation load are large, in order to avoid the blade from resonating due to forced vibration, a damping increasing method is adopted, the purposes of restraining blade response and reducing vibration stress are achieved, and therefore the influence of the damping block on the vibration characteristic of the blade under the condition that the blade is subjected to centrifugal force needs to be researched, namely the vibration damping effect of the damping block needs to be researched.
The existing turbine movable blade damping vibration attenuation effect test can only fix a loading device on the ground, adopts a force hammer or a vibration exciter to excite, and cannot be installed on a high-frequency vibration table, so that the working load and the stress state of the turbine movable blade and the damping can not be simulated, the influence of the additional mass and the additional rigidity of the force hammer or the vibration exciter on a test result can not be avoided by measuring the turbine movable blade damping by using the existing test method, the turbine movable blade damping effect which is more consistent with the actual working state can not be obtained, and the design and the research of the engine turbine movable blade damping are not facilitated.
Disclosure of Invention
In order to solve the above problems, the present invention provides a test device for measuring a damping and vibration-damping effect of a turbine rotor blade, comprising a first loading mechanism for applying a centrifugal load to a blade portion of the turbine rotor blade, a second loading mechanism for applying a centrifugal load to a damping portion of the turbine rotor blade, a vibration mechanism for providing vibration, a jig for holding the blade, and an acceleration sensor for measuring a vibration effect,
the fixture is fixedly arranged on the vibration mechanism and comprises a containing cavity defined by a cylinder cover and five fir-shaped mortises arranged on one side of the cylinder cover, and tenons of the blades are clamped and fixed by the mortises;
the first loading mechanism is arranged in the containing cavity of the clamp, penetrates through the cylinder cover to extend to the tenon of the blade, and is tightly propped against the end part of the tenon through the jacking block;
the second loading mechanism comprises a front rubber rope, one end of the front rubber rope is connected to the damping block of the blade, the other end of the front rubber rope is connected to the front upright post of the portal frame, and the direction from the damping block to the front upright post of the portal frame is the direction of the centrifugal force applied to the blade;
a vibration mechanism comprising a high-frequency vibration table connected with the clamp to provide high-frequency vibration to the clamp;
and the acceleration sensor is arranged on the blade measuring point.
Preferably, the clamp is of a hydraulic cylinder structure, the first loading mechanism in the clamp is a hydraulic loading device, a groove is formed in the front end of the hydraulic loading device, one end of the ejector block is accommodated, and the other end of the ejector block abuts against the tenon.
Preferably, the second loading mechanism further comprises a rear rubber rope, one end of the rear rubber rope is connected to the fixture, the other end of the rear rubber rope is connected to a rear upright post of the portal frame, and the front upright post and the rear upright post of the portal frame are respectively arranged on two sides of the fixture.
Preferably, hand-operated hoists are arranged on the front rubber rope and the rear rubber rope to provide centrifugal force to the damping block.
Preferably, the front rubber rope and the rear rubber rope are provided with balancing weights to provide centrifugal force to the damping block.
Preferably, force sensors are arranged on the front rubber rope and the rear rubber rope.
Preferably, the front rubber rope is connected with the damping block through a steel wire rope.
The invention has the advantages that: the loading device can ensure that two sets of loading mechanisms are mutually independent when executing loading work, do not generate coupling phenomenon, can solve the problem of damping measurement of the existing turbine movable blades in the working state, provides technical support for the design and research of the damping of the movable blades of the engine, and provides guarantee for the research of the safety and the reliability of the engine.
Drawings
FIG. 1 is a structural plan view of a preferred embodiment of a test device for measuring damping and vibration attenuation effects of turbine blades according to the invention.
Fig. 2 is a front view of the embodiment of the invention shown in fig. 1.
FIG. 3 is a schematic diagram illustrating a position relationship between the first loading mechanism and the blade according to the embodiment of the invention shown in FIG. 1.
Wherein, 1 is a blade, 1-1 is a blade body, 1-2 is a damping block, and 1-3 is a tenon;
2 is a second loading mechanism, 2-1 is a front rubber rope, 2-2 is a rear rubber rope, and 2-3 is a force sensor;
3 is a portal frame;
4 is a clamp, 4-1 is a cylinder cover, and 4-2 is a tongue-and-groove;
5 is a switching section, 6 is a high-frequency vibration table, 7 is a first loading mechanism, and 8 is a top block.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, but not all embodiments of the invention. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention. 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. Embodiments of the present invention will be described in detail below with reference to the accompanying drawings.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present invention and for simplifying the description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the scope of the present invention.
The invention is further explained with reference to the drawings, wherein the left side of the description of the drawings is the front side, such as a front rubber rope 2-1 and a front upright post of a portal frame; the right side is the back, such as the back rubber rope 2-2, the back column of the portal frame, etc.
Referring to fig. 1-3, the testing device for measuring the damping and vibration attenuation effects of the turbine moving blade of the present invention mainly comprises a first loading mechanism for applying a centrifugal load to the blade portion of the turbine moving blade, a second loading mechanism for applying a centrifugal load to the damping portion of the turbine moving blade, a vibration mechanism for providing vibration, a clamp for clamping the blade, and an acceleration sensor for measuring the vibration effects, and the following description describes each of them
Referring to fig. 1 and 2, the fixture 4 is fixedly arranged on the vibration mechanism and comprises a cavity defined by a cylinder cover 4-1 and five fir-tree type mortises 4-2 arranged on one side of the cylinder cover 4-1, tenons 1-3 of the blade 1 are clamped and fixed by the mortises 4-2, and the structure of the blade can refer to fig. 3.
It should be noted that, according to the installation conditions of the blade and the damping block, a fir-tree-shaped mortise (completely consistent with the design parameters of a real turbine disk) capable of installing five blades is designed at one side of the fixture, and although the test only performs vibration simulation on the middle blade, as shown in fig. 1 or fig. 2, the design of the five blade installation can better simulate the real situation, for example, considering the influence of the vibration of the surrounding blades on the middle blade.
In this embodiment, the first loading mechanism 7 is disposed in the cavity of the fixture 4, and extends through the cylinder cover 4-1 to the tenon 1-3 of the blade, and referring to fig. 3, it is tightly pressed against the end of the tenon 1-3 by the top block 8. In this embodiment, the first loading mechanism may exist alone or may be a part of the fixture, for example, the fixture 4 is a hydraulic cylinder structure, the first loading mechanism 7 therein is a hydraulic loading device, a groove is provided at a front end of the hydraulic loading device, the groove accommodates one end of the ejector block 8, and the other end of the ejector block 8 abuts against the tenon 1-3.
In this embodiment, the second loading mechanism 2 includes a front rubber rope 2-1, a rear rubber rope 2-2 and a force sensor 2-3, wherein one end of the front rubber rope 2-1 is connected to the damping block 1-2 of the blade, the other end is connected to a front column of the portal frame 3, and a direction from the damping block 1-2 to the front column of the portal frame 3 is a direction of a centrifugal force applied to the blade. It will be appreciated that the application of tension to the bungee cord simulates the forward centrifugal force experienced by the blade.
In this embodiment, one end of the rear rubber rope 2-2 is connected to the clamp 4, and the other end is connected to the rear pillar of the portal frame 3, and the front pillar and the rear pillar of the portal frame 3 are respectively disposed on two sides of the clamp 4, as shown in fig. 1 or fig. 2, and are used for balancing torque.
In this embodiment, the vibration mechanism comprises a dither table 6 connected to the jig 4 to provide dither to the jig.
The device further comprises an acceleration sensor arranged at the blade measuring point.
Specifically, the damping measurement steps of the invention are as follows: the fixture 4 is installed on a high-frequency vibration table 6 through a switching section 5, the high-frequency vibration table 6 is adopted for excitation, an acceleration sensor is arranged on a measuring point, the signal acquisition synchronization of each measuring point is guaranteed, then, signal data are processed, frequency response data are obtained, and data such as the natural frequency, the vibration mode and the damping of the model are obtained.
In this embodiment, the front rubber rope 2-1 and the rear rubber rope 2-2 of the second loading mechanism 2 are provided with manual/electric hoists to provide the centrifugal force applied to the damping block 1-2, and in an alternative embodiment, a counterweight may be used to provide the centrifugal force applied to the damping block 1-2.
In this embodiment, the force sensors 2-3 are arranged on the front rubber rope 2-1 and the rear rubber rope 2-2. It can be understood that before the test, the simulated centrifugal force loads of the blade body 1-1 and the damping block 1-2 are determined according to a centrifugal force calculation formula, and then the stress condition of the blade is reflected through a force sensor and the like, so that the accurate control is facilitated.
For better connection of the damping block, a steel wire rope is generally extended at the end of the front rubber rope 2-1, and the damping block 1-2 is connected through the steel wire rope.
In this embodiment, the blade simulation centrifugal force load application mechanism 7 operates in the following manner: the hydraulic loading device pushes the blades, the simulated centrifugal force is transmitted to the clamp 4, the clamp 4 is subjected to acting force in the same direction as the blade simulated centrifugal force, in order to balance the acting force, the clamp 4 is of a hydraulic cylinder structure, and the hydraulic loading device is installed inside the hydraulic loading device. The force transmission path is a hydraulic loading device → the blade → the mortise → the clamp (mounting blade surface) → the side surface of the clamp → the cylinder cover.
The damping block simulates the working mode of a centrifugal force load applying mechanism: the front rubber rope 2-1 pulls the damping block 1-2, the damping block 1-2 transmits force to the clamp 4, the rear rubber rope device 2-2 is arranged at the other end of the clamp 4 and fixedly connected to the rear upright post of the portal frame 3, and the resultant force/resultant moment of the clamp 4 in the horizontal direction is zero. The force transmission path is the front rubber rope device 2-1 → the damping block 1-2 → the leaf 1 → the clamp 4 → the rear rubber rope 2-1.
The invention has the advantages that: the loading device can ensure that two sets of loading mechanisms are mutually independent when executing loading work, do not generate coupling phenomenon, can solve the problem of damping measurement of the existing turbine movable blades in the working state, provides technical support for the design and research of the damping of the movable blades of the engine, and provides guarantee for the research of the safety and the reliability of the engine.
Finally, it should be pointed out that: the above examples are only for illustrating the technical solutions of the present invention, and are not limited thereto. Although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.
Claims (7)
1. A test device for measuring the damping and vibration attenuation effects of turbine moving blades is characterized by comprising a first loading mechanism for applying centrifugal load to the blade part of the turbine moving blades, a second loading mechanism for applying centrifugal load to the damping part of the turbine moving blades, a vibration mechanism for providing vibration, a clamp for clamping the blades and an acceleration sensor for measuring the vibration effects,
the fixture (4) is fixedly arranged on the vibration mechanism and comprises a containing cavity defined by a cylinder cover (4-1) and five fir-shaped mortises (4-2) arranged on one side of the cylinder cover (4-1), and tenons (1-3) of the blade (1) are clamped and fixed by the mortises (4-2);
the first loading mechanism (7) is arranged in the containing cavity of the clamp (4), extends to the tenon (1-3) of the blade through the cylinder cover (4-1), and is tightly propped at the end part of the tenon (1-3) through a jacking block (8);
the second loading mechanism (2) comprises a front rubber rope (2-1), one end of the front rubber rope (2-1) is connected to the damping block (1-2) of the blade, the other end of the front rubber rope is connected to a front upright post of the portal frame (3), and the direction from the damping block (1-2) to the front upright post of the portal frame (3) is the direction of the centrifugal force applied to the blade;
a vibration mechanism comprising a high frequency vibration table (6) connected to the clamp (4) to provide high frequency vibration to the clamp;
and the acceleration sensor is arranged on the blade measuring point.
2. The test device for measuring the damping and shock absorption effects of the turbine movable blades as claimed in claim 1, wherein the clamp (4) is of a hydraulic cylinder structure, the first loading mechanism (7) in the clamp is of a hydraulic loading device, a groove is formed in the front end of the hydraulic loading device, one end of the ejector block (8) is accommodated, and the other end of the ejector block (8) abuts against the tenon (1-3).
3. The test device for measuring the damping and shock absorption effects of the turbine moving blades as claimed in claim 1, wherein the second loading mechanism (2) further comprises a rear rubber rope (2-2), one end of the rear rubber rope (2-2) is connected to the clamp (4), the other end of the rear rubber rope is connected to a rear upright of the portal frame (3), and a front upright and the rear upright of the portal frame (3) are respectively arranged on two sides of the clamp (4).
4. The test device for measuring the damping and shock absorption effects of the turbine moving blades as claimed in claim 3, wherein hand-operated hoists are arranged on the front rubber rope (2-1) and the rear rubber rope (2-2) to provide the centrifugal force applied to the damping blocks (1-2).
5. The test device for measuring the damping and shock absorption effects of the turbine moving blades as claimed in claim 3, wherein balancing weights are arranged on the front rubber rope (2-1) and the rear rubber rope (2-2) to provide the centrifugal force applied to the damping block (1-2).
6. The test device for measuring damping and shock absorption effects of the turbine bucket according to claim 4 or 5, wherein force sensors (2-3) are arranged on the front rubber rope (2-1) and the rear rubber rope (2-2).
7. The test device for measuring the damping and shock absorption effects of the turbine moving blades as claimed in claim 1, wherein the front rubber rope (2-1) is connected with the damping block (1-2) through a steel wire rope.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711332859.2A CN108036911B (en) | 2017-12-13 | 2017-12-13 | Test device for measuring damping vibration attenuation effect of turbine movable blade |
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| CN201711332859.2A CN108036911B (en) | 2017-12-13 | 2017-12-13 | Test device for measuring damping vibration attenuation effect of turbine movable blade |
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| CN108036911A CN108036911A (en) | 2018-05-15 |
| CN108036911B true CN108036911B (en) | 2020-04-28 |
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Families Citing this family (5)
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| CN111006950B (en) * | 2019-12-23 | 2020-09-15 | 北京航空航天大学 | A turbo tenon structure photoelastic experimental loading device |
| CN114275187B (en) * | 2021-04-26 | 2024-02-13 | 北京强度环境研究所 | Vibration-static force-excitation three-combination test device |
| CN113639950B (en) * | 2021-09-10 | 2023-11-28 | 西北工业大学 | Single-rod drawing type vibration table testing device and testing method for representing centrifugal force |
| CN114720075B (en) * | 2022-03-31 | 2024-10-18 | 中国航发沈阳发动机研究所 | Turbine blade edge plate damping test system |
| CN117074005B (en) * | 2023-10-11 | 2023-12-19 | 江苏阿莫斯燃气轮机有限公司 | Vibration testing device for blade damper of gas turbine |
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| CN103743556A (en) * | 2013-12-20 | 2014-04-23 | 西安交通大学 | Testing apparatus for steam turbine blade with shroud ring and boss lashing wire structures |
| CN104062104A (en) * | 2013-03-19 | 2014-09-24 | 徐可君 | Cyclic test device for fatigue of aeroengine compressor blade |
| CN105571802A (en) * | 2016-02-01 | 2016-05-11 | 苏州长菱测试技术有限公司 | Testing method and testing device for blade pretightening force |
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2017
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| CN101308057A (en) * | 2008-06-06 | 2008-11-19 | 北京航空航天大学 | Vibration reduction test device for blades with dry friction damping structure |
| CN102156035A (en) * | 2011-03-24 | 2011-08-17 | 西安交通大学 | Turbine blade vibration characteristic testing and measuring device with shroud damping block and blade root wedged damping block |
| RU2494365C1 (en) * | 2012-03-27 | 2013-09-27 | Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова" | Loading device for investigation of end damping of oscillations of fan blades of gas-turbine engine on vibration test rig |
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