CN108036911A - A kind of experimental rig for measuring turbine rotor blade damping vibration attenuation effect - Google Patents
A kind of experimental rig for measuring turbine rotor blade damping vibration attenuation effect Download PDFInfo
- Publication number
- CN108036911A CN108036911A CN201711332859.2A CN201711332859A CN108036911A CN 108036911 A CN108036911 A CN 108036911A CN 201711332859 A CN201711332859 A CN 201711332859A CN 108036911 A CN108036911 A CN 108036911A
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- turbine rotor
- rotor blade
- blade
- damping
- fixture
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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
-
- 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
-
- 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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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The invention discloses a kind of experimental rig for measuring turbine rotor blade damping vibration attenuation effect, belong to turbine rotor blade experimental technique field.The experimental rig includes the first load maintainer for applying centrifugal load to the blade-section of the turbine rotor blade, second load maintainer of centrifugal load is applied to the damping portion of the turbine rotor blade, the vibrating mechanism of vibration is provided, clamp the fixture of blade and measure the acceleration transducer of vibrating effect, it is separate during loading work that the loading device can ensure that two sets of load maintainers perform, coupling phenomenon does not occur, the damping measurement under its working status can be solved the problems, such as existing turbine rotor blade, technical support is provided for the design and research of engine movable vane damping, for engine health, the research of reliability provides guarantee.
Description
Technical field
The invention belongs to turbine rotor blade experimental technique field, and in particular to a kind of measurement turbine rotor blade damping vibration attenuation effect
Experimental rig.
Background technology
More severe based on turbine rotor blade working environment, suffered aerodynamic force and unstable excitation load are larger, to keep away
Exempt from blade because forced vibration causes to resonate, using the method for increase damping, reach the mesh for suppressing paddle response, reducing vibration stress
, therefore, it is necessary to study blade in the case of by centrifugal force, influence of the damping block to blade vibration characteristic, that is, need research to hinder
The effectiveness in vibration suppression of Buddhist nun's block.
Existing turbine rotor blade damping vibration attenuation effect test can only fix loading device on the ground, hammered into shape or swashed using power
Device shake into row energization, can not be installed on high-frequency vibrating table, therefore turbine rotor blade and the service load and work of damping can not be simulated
Make the stress under state, with the measurement turbine rotor blade damping of existing test method can not avoid power hammer into shape or vibrator it is additional
The influence of quality and additional stiffness to test result, and cannot more be met the turbine rotor blade damping effect of actual working state
Fruit, is unfavorable for the design and research of the damping of engine turbine movable vane.
The content of the invention
To solve the above-mentioned problems, the present invention provides it is a kind of measure turbine rotor blade damping vibration attenuation effect experimental rig,
Including applying the first load maintainer of centrifugal load, the damper portion to the turbine rotor blade to the blade-section of the turbine rotor blade
Give plus the second load maintainer of centrifugal load, the vibrating mechanism of offer vibration, the fixture of clamping blade and measurement vibration are imitated
The acceleration transducer of fruit, wherein,
Fixture, is fixed on vibrating mechanism, including the cavity volume that is limited by cylinder cap and is arranged on the cylinder cap one
Five fir-tree type tongue-and-grooves of side, the tenon of blade are gripped by the tongue-and-groove；
First load maintainer, is arranged in the cavity volume of the fixture, and passes through cylinder cap to pass through to extension at the tenon of blade
Jacking block is held out against in the end of tenon；
Second load maintainer, including preceding elastic string, one end of the preceding elastic string is connected on the damping block of blade, another
End is connected on portal frame front column, the side of the front column direction as damping block to portal frame centrifugal force suffered by blade
To；
Vibrating mechanism, including the high-frequency vibrating table being connected with the fixture, to provide dither to the fixture；
Acceleration transducer, is arranged on Blade measuring point.
Preferably, the fixture is hydraulic cylinder structure, and the first load maintainer in it is hydraulic loading device, the liquid
Press the front end setting of loading device fluted, accommodate one end of the jacking block, the other end apical grafting tenon of jacking block.
Preferably, second load maintainer further includes rear elastic string, and one end of the rear elastic string is connected to fixture
On, the other end is connected on portal frame rear column, and front column and the rear column of the portal frame are separately positioned on the both sides of fixture.
Preferably, the preceding elastic string on rear elastic string with being provided with bottle gouard moved by hands, to provide suffered by the damping block
Centrifugal force.
Preferably, the preceding elastic string on rear elastic string with being provided with clump weight, to provide suffered by the damping block
Centrifugal force.
Preferably, the preceding elastic string on rear elastic string with setting force sensor.
Preferably, the preceding elastic string connects the damping block by steel wire rope.
It is an advantage of the invention that：It is separate during loading work that the loading device can ensure that two sets of load maintainers perform, no
Generation coupling phenomenon, the damping measurement under its working status can be solved the problems, such as existing turbine rotor blade, is hindered for engine movable vane
The design and research of Buddhist nun provides technical support, and guarantee is provided for the research of engine health, reliability.
Brief description of the drawings
Fig. 1 is the structure according to a preferred embodiment of the experimental rig of present invention measurement turbine rotor blade damping vibration attenuation effect
Top view.
Fig. 2 is the front view of embodiment illustrated in fig. 1 of the present invention.
Fig. 3 is the position relationship schematic diagram between the first load maintainer and blade of embodiment illustrated in fig. 1 of the present invention.
Wherein, 1 is blade, and 1-1 is blade, and 1-2 is damping block, and 1-3 is tenon；
2 be the second load maintainer, and 2-1 is preceding elastic string, and 2-2 is rear elastic string, and 2-3 is force snesor；
3 be portal frame；
4 be fixture, and 4-1 is cylinder cap, and 4-2 is tongue-and-groove；
5 be group section, and 6 be high-frequency vibrating table, and 7 be the first load maintainer, and 8 be jacking block.
Embodiment
To make the purpose, technical scheme and advantage that the present invention is implemented clearer, below in conjunction with the embodiment of the present invention
Attached drawing, the technical solution in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label represent same or similar element or there is same or like element.Described embodiment is the present invention
Part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to uses
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiments of the present invention, ordinary skill people
Member's all other embodiments obtained without creative efforts, belong to the scope of protection of the invention.Under
Face is described in detail the embodiment of the present invention with reference to attached drawing.
In the description of the present 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 ", " outer " is based on attached drawing institutes
The orientation or position relationship shown, is for only for ease of the description present invention and simplifies description, rather than instruction or the dress for implying meaning
Put or element there must be specific orientation, with specific azimuth configuration and operation, therefore it is not intended that the present invention is protected
The limitation of scope.
The present invention is further explained below in conjunction with the accompanying drawings, below in the description of attached drawing, before left side is, such as preceding rubber
Leather rope 2-1, the front column of portal frame；After right side is, such as rear elastic string 2-2, the rear column of portal frame etc..
It is main to include to the whirlpool with reference to figure 1- Fig. 3, the experimental rig of present invention measurement turbine rotor blade damping vibration attenuation effect
The blade-section for taking turns movable vane applies the first load maintainer of centrifugal load, the damping portion to the turbine rotor blade applies centrifugation and carries
The second load maintainer of lotus, the vibrating mechanism that vibration is provided, the fixture for clamping blade and the acceleration biography for measuring vibrating effect
Sensor, it is described separately below
With reference to figure 1 and Fig. 2, fixture 4 is fixed on vibrating mechanism, including by the cylinder cap 4-1 cavity volumes limited and
Five fir-tree type tongue-and-groove 4-2 of the cylinder cap 4-1 sides are arranged on, the tenon 1-3 of blade 1 is gripped by the tongue-and-groove 4-2,
The structure of blade refers to Fig. 3.
It should be noted that according to blade and damping block mounting condition, in fixture while design can install five blades
Fir-tree type tongue-and-groove (completely the same with true turbine disk design parameter), although experiment only carries out vibration simulation to middle blade,
As shown in Figure 1 or 2, but five blade installations of design can preferably simulate truth, such as take into account intermediate blade
The factors such as the vibration effect by surrounding vanes.
In the present embodiment, the first load maintainer 7, is arranged in the cavity volume of the fixture 4, and passes through cylinder cap 4-1 to blade
Tenon 1-3 at extend, with reference to figure 3, it is held out against in the end of tenon 1-3 by jacking block 8.In the present embodiment, the first loading machine
Structure can be with individualism, can also be as a part for fixture, such as the fixture 4 is hydraulic cylinder structure, and first in it adds
Mounted mechanism 7 is hydraulic loading device, and the front end setting of the hydraulic loading device is fluted, accommodates one end of the jacking block 8, pushes up
The other end apical grafting tenon 1-3 of block 8.
In the present embodiment, the second load maintainer 2 includes preceding elastic string 2-1, rear elastic string 2-2 and force snesor 2-3, its
In, one end of the preceding elastic string 2-1 is connected on the damping block 1-2 of blade, and the other end is connected on 3 front column of portal frame,
The direction of the front column direction as damping block 1-2 to portal frame 3 centrifugal force suffered by blade.It is understood that to rubber
Leather rope applies pulling force, you can the forward centrifugal force that simulation blade is subject to.
In the present embodiment, rear elastic string 2-2 one end is connected on fixture 4, and the other end is connected on 3 rear column of portal frame,
The front column of the portal frame 3 is separately positioned on the both sides of fixture 4 with rear column, and referring to Fig. 1 or Fig. 2, it is used for trimming moment.
In the present embodiment, vibrating mechanism includes the high-frequency vibrating table 6 being connected with the fixture 4, to provide the fixture
Dither.
Described device further includes acceleration transducer, is arranged on Blade measuring point.
Specifically, the measuring process that the present invention damps is as follows：Fixture 4 is installed on high-frequency vibrating table 6 by group section 5,
Encouraged using high-frequency vibrating table 6, acceleration transducer 8 is arranged in measurement point, ensure that the signal acquisition of each measuring point is synchronous, with
Afterwards by signal-data processing, frequency response data are obtained, obtain the data such as the intrinsic frequency, the vibration shape, damping of model.
In the present embodiment, manual/electric calabash is provided with the preceding elastic string 2-1 and rear elastic string 2-2 of the second load maintainer 2
Reed, to provide the centrifugal force suffered by the damping block 1-2, in alternate embodiment, can also use clump weight, with described in offer
Centrifugal force suffered by damping block 1-2.
In the present embodiment, force sensor 2-3 is set on the preceding elastic string 2-1 and rear elastic string 2-2.It is appreciated that
It is before being tested, according to centrifugal force calculation formula, to determine the simulation centrifugal force load of blade 1-1 and damping block 1-2, into
And vane stress situation is reflected by force snesor etc., easy to be precisely controlled.
In order to preferably connect damping block, steel wire rope generally is extended with the end of preceding elastic string 2-1, is connected by steel wire rope
Meet the damping block 1-2.
In the present embodiment, vane simulated 7 working method of centrifugal force load applying mechanism：Hydraulic loading device promotes blade,
Simulation centrifugal force is delivered on fixture 4, and fixture 4 is subject to the active force with vane simulated centrifugal force equidirectional, to balance this work
Firmly, fixture 4 is arranged to hydraulic cylinder structure, inside installation hydraulic loading device.Path of Force Transfer is hydraulic loading device → blade
→ tongue-and-groove → fixture (installation blade face) → fixture side → cylinder cap.
Damping block simulates centrifugal force load applying mechanism working method：Preceding elastic string 2-1 pulls damping block 1-2, damping block
1-2 is transferred force on fixture 4, the rubber rope device 2-2 after the setting of 4 other end of fixture, is fixedly arranged at the rear column of portal frame 3
On, make fixture 4 make a concerted effort in the horizontal direction/resultant moment is zero.Path of Force Transfer is preceding rubber rope device 2-1 → damping block 1-2 → leaf
1 → fixture of piece 4 → rear elastic string 2-1.
It is an advantage of the invention that：It is separate during loading work that the loading device can ensure that two sets of load maintainers perform, no
Generation coupling phenomenon, the damping measurement under its working status can be solved the problems, such as existing turbine rotor blade, is hindered for engine movable vane
The design and research of Buddhist nun provides technical support, and guarantee is provided for the research of engine health, reliability.
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 is with reference to the foregoing embodiments described in detail the present invention, it will be understood by those of ordinary skill in the art that：It is still
It can modify to the technical solution described in foregoing embodiments, or which part technical characteristic is equally replaced
Change；And these modifications or replacement, the essence of appropriate technical solution is departed from the essence of various embodiments of the present invention technical solution
God and scope.
Claims (7)
1. a kind of experimental rig for measuring turbine rotor blade damping vibration attenuation effect, it is characterised in that including to the turbine rotor blade
First load maintainer of blade-section application centrifugal load, the damping portion to the turbine rotor blade apply the second of centrifugal load
Load maintainer, the vibrating mechanism that vibration is provided, the fixture for clamping blade and the acceleration transducer for measuring vibrating effect, its
In,
Fixture (4), is fixed on vibrating mechanism, including the cavity volume that is limited by cylinder cap (4-1) and is arranged on the cylinder
Five fir-tree type tongue-and-grooves (4-2) of (4-1) side are covered, the tenon (1-3) of blade (1) is gripped by the tongue-and-groove (4-2)；
First load maintainer (7), is arranged in the cavity volume of the fixture (4), and passes through tenon (1- of the cylinder cap (4-1) to blade
3) place extends, and is held out against by jacking block (8) in the end of tenon (1-3)；
Second load maintainer (2), including preceding elastic string (2-1), one end of the preceding elastic string (2-1) are connected to the damping of blade
On block (1-2), the other end is connected on portal frame (3) front column, the front column by damping block (1-2) to portal frame (3)
Direction is the direction of centrifugal force suffered by blade；
Vibrating mechanism, including the high-frequency vibrating table (6) being connected with the fixture (4), to provide dither to the fixture；
Acceleration transducer, is arranged on Blade measuring point.
2. the experimental rig of measurement turbine rotor blade damping vibration attenuation effect as claimed in claim 1, it is characterised in that the fixture
(4) it is hydraulic cylinder structure, the first load maintainer (7) in it is hydraulic loading device, and the front end of the hydraulic loading device is set
Groove is equipped with, accommodates one end of the jacking block (8), the other end apical grafting tenon (1-3) of jacking block (8).
3. the experimental rig of measurement turbine rotor blade damping vibration attenuation effect as claimed in claim 1, it is characterised in that described second
Load maintainer (2) further includes rear elastic string (2-2), and one end of the rear elastic string (2-2) is connected on fixture (4), the other end
It is connected on portal frame (3) rear column, front column and the rear column of the portal frame (3) are separately positioned on the both sides of fixture (4).
4. the experimental rig of measurement turbine rotor blade damping vibration attenuation effect as claimed in claim 3, it is characterised in that the preceding rubber
Leather rope (2-1) on rear elastic string (2-2) with being provided with bottle gouard moved by hands, to provide the centrifugal force suffered by the damping block (1-2).
5. the experimental rig of measurement turbine rotor blade damping vibration attenuation effect as claimed in claim 3, it is characterised in that the preceding rubber
Leather rope (2-1) on rear elastic string (2-2) with being provided with clump weight, to provide the centrifugal force suffered by the damping block (1-2).
6. the experimental rig of turbine rotor blade damping vibration attenuation effect is measured as described in claim 4 or 5, it is characterised in that described
Preceding elastic string (2-1) is with setting force sensor (2-3) on rear elastic string (2-2).
7. the experimental rig of measurement turbine rotor blade damping vibration attenuation effect as claimed in claim 1, it is characterised in that the preceding rubber
Leather rope (2-1) connects the damping block (1-2) by steel wire rope.
Priority Applications (1)
| 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 |
Applications Claiming Priority (1)
| 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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| CN108036911A true CN108036911A (en) | 2018-05-15 |
| CN108036911B CN108036911B (en) | 2020-04-28 |
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|---|---|---|---|
| CN201711332859.2A Active CN108036911B (en) | 2017-12-13 | 2017-12-13 | Test device for measuring damping vibration attenuation effect of turbine movable blade |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111006950A (en) * | 2019-12-23 | 2020-04-14 | 北京航空航天大学 | Turbine joggle joint structure photoelastic experiment loading device |
| CN113639950A (en) * | 2021-09-10 | 2021-11-12 | 西北工业大学 | Single-rod drawing type vibration table testing device and testing method for representing centrifugal force |
| CN114275187A (en) * | 2021-04-26 | 2022-04-05 | 北京强度环境研究所 | Vibration-static force-excitation three-comprehensive test device |
| CN117074005A (en) * | 2023-10-11 | 2023-11-17 | 江苏阿莫斯燃气轮机有限公司 | Vibration testing device for blade damper of gas turbine |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101308057A (en) * | 2008-06-06 | 2008-11-19 | 北京航空航天大学 | Vibration damping test device possessing dry damping structure vane |
| 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 |
| CN102954887A (en) * | 2012-11-08 | 2013-03-06 | 中国航空工业集团公司沈阳发动机设计研究所 | Testing device for measuring damping effect of working blades of high-pressure turbine |
| 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 |
| 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 |
-
2017
- 2017-12-13 CN CN201711332859.2A patent/CN108036911B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101308057A (en) * | 2008-06-06 | 2008-11-19 | 北京航空航天大学 | Vibration damping test device possessing dry damping structure vane |
| 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 |
| CN102954887A (en) * | 2012-11-08 | 2013-03-06 | 中国航空工业集团公司沈阳发动机设计研究所 | Testing device for measuring damping effect of working blades of high-pressure turbine |
| CN104062104A (en) * | 2013-03-19 | 2014-09-24 | 徐可君 | Cyclic test device for fatigue of aeroengine compressor blade |
| 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 |
| 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 |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111006950A (en) * | 2019-12-23 | 2020-04-14 | 北京航空航天大学 | Turbine joggle joint structure photoelastic experiment loading device |
| CN111006950B (en) * | 2019-12-23 | 2020-09-15 | 北京航空航天大学 | Turbine joggle joint structure photoelastic experiment loading device |
| CN114275187A (en) * | 2021-04-26 | 2022-04-05 | 北京强度环境研究所 | Vibration-static force-excitation three-comprehensive test 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 |
| CN113639950A (en) * | 2021-09-10 | 2021-11-12 | 西北工业大学 | Single-rod drawing type vibration table testing device and testing method for representing centrifugal force |
| 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 |
| CN117074005A (en) * | 2023-10-11 | 2023-11-17 | 江苏阿莫斯燃气轮机有限公司 | Vibration testing device for blade damper of gas turbine |
| 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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