CN102156035B - Turbine blade vibration characteristic testing and measuring device with shroud damping block and blade root wedged damping block - Google Patents
Turbine blade vibration characteristic testing and measuring device with shroud damping block and blade root wedged damping block Download PDFInfo
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- CN102156035B CN102156035B CN201110072247A CN201110072247A CN102156035B CN 102156035 B CN102156035 B CN 102156035B CN 201110072247 A CN201110072247 A CN 201110072247A CN 201110072247 A CN201110072247 A CN 201110072247A CN 102156035 B CN102156035 B CN 102156035B
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Abstract
The invention discloses a turbine blade vibration characteristic testing and measuring device with a shroud damping block and a blade root wedged damping block. The device comprises a test foundation rack, a blade root contact surface pressure load applying mechanism, a centrifugal force applying mechanism for the blade root wedged damping block and the shroud damping block, an exciting force applying mechanism and a vibration parameter measuring mechanism, wherein the blade root contact surface pressure load applying mechanism applies pressure load to the blade root contact surface, and the applied pressure load is measured by a standard test piece adhered with a strain gauge; corresponding centrifugal force load is applied to the blade root wedged damping block and the shroud damping block by utilizing a steel wire pulley structure, and the applied centrifugal force of the damping block is measured by adopting a static force sensor; a vibration exciter is connected with a blade body part of the blade and applies an exciting force to the blade; and the measured vibration parameter corresponds to the vibration displacement response of the blade, the vibration displacement response of the blade is measured by a displacement transducer, and a force signal and a displacement signal are detected through a force sensor and the displacement transducer.
Description
Technical field
The present invention relates to the turbine blade measurement mechanism, be specifically related to a kind of turbine blade vibration attribute testing measurement mechanism with shroud damping block and blade root wedge shape damping block.
Background technology
Steam turbine is widely used in importances such as generating, industrial power and boats and ships in national economy is produced, and the safe reliability of its key equipment blade is the important assurance of Steam Turbine safe operation.Blade receives the effect of pulse pneumatic power at work and produces vibration, and the operation practical experience shows that the damage of blade is to be caused by blade vibration fatigue mostly.Dry damping structure owing to simple in structure, not be widely used in the turbine blade design by temperature limitation to reduce its vibration stress.Because the strong nonlinearity characteristic of dry-friction damping; Be difficult to describe with a kind of general model; Need study it through test; So be necessary the influence research experiment of dry damping structure to actual turbine blade damping behavior, so that necessary foundation is provided for further effectively utilizing and developing turbine blade with corresponding dry damping structure.
Summary of the invention
The purpose of this invention is to provide and a kind ofly can obtain the damping vibration attenuation characteristic of damping block, for further developing the turbine blade vibration attribute testing measurement mechanism that turbine blade with corresponding damping structure lays the foundation with shroud damping block and blade root wedge shape damping block to blade through measuring.
For achieving the above object; The technical scheme that the present invention adopts is: comprise the experimental basis stand of being made up of testing table base plate and testing table side plate; The experimental basis stand is fixed on the basic platform, and testing table side plate inboard is provided with boss, on the testing table base plate, is placed with hydraulic jack; Hydraulic jack is provided with the standard specimen that posts foil gauge that is used for gaging pressure load; The exert pressure blade root jacking block of load of blade root is placed on the upper surface of standard specimen, and race is placed on the upper end of blade root jacking block, thereby is fixed on the boss in the testing table side plate through each side place hydraulic jack race is made progress jack-up at the race lower surface; Blade is inserted in the race; Push rod inserts in the space of race and blade root bottom, and the push rod both sides apply radial pull simulation its suffered centrifugal force through the wireline pulley screw-rod structure forward and backward with being installed in the testing table side plate outside to blade root wedge shape damping block through the wire rope tractive, on the shroud damping block, are equipped with through hole; This through hole of steel wire penetrating applies radial pull simulation shroud damping block centrifugal force through the wireline pulley screw-rod structure middle with being installed in the testing table side plate outside to it; The static force sensor that is used to measure value of thrust all is installed on wire rope, and the vanes threaded rod links to each other with vibrator, on threaded rod, near the blade surface place dynamic force sensor that exciting force is measured is installed; Blade vibration response measurement mechanism comprises support and displacement transducer; Support is fixed on and keeps static on the basic platform, and displacement transducer is rack-mount, and keeps the measuring distance of 1mm between displacement transducer and the blade surface.
Be provided with cushion block between hydraulic jack of the present invention and the standard specimen.
The present invention can obtain the damping vibration attenuation characteristic of damping block to turbine blade under the more consistent situation of the force-bearing situation that guarantees blade and damping block and actual state, for further utilizing and developing corresponding damping structure turbine blade necessary foundation is provided.
Description of drawings
Fig. 1 is the turbine blade structural representation with shroud damping block and blade root wedge shape damping block;
Fig. 2 is an experimental basis horse structure synoptic diagram;
Fig. 3 is that root of blade interface pressure load applies and the measuring mechanism synoptic diagram;
Fig. 4 is that blade root wedge shape damping block and shroud damping block centrifugal force load apply and the measuring mechanism synoptic diagram;
Fig. 5 is that exciting force applies and measuring mechanism and blade vibration displacement response measuring mechanism synoptic diagram;
Code name implication among the figure: 1-testing table base plate; 2-testing table side plate; The 3-hydraulic jack; The hydraulic jack of 4-both sides; The 5-cushion block; 6-posts the standard specimen of foil gauge; 7-blade root jacking block; The 8-blade; The 9-race; The 10-push rod; The 11-wireline pulley; 12-static force sensor; The 13-screw-rod structure, 14-support, 15-displacement transducer, 16-threaded rod; 17-dynamic force sensor, 18-vibrator, 19-neckband, 20-blade part, 21-leaf root part, 22-shroud damping block, 23-blade root wedge shape damping block.
Embodiment
Below in conjunction with accompanying drawing the present invention is done further explain.
Referring to Fig. 1, at first the structure of damping vane 8 in the test is introduced.Blade 8 is made up of leaf root part 21, blade part 20 and neckband 19, also comprises blade root wedge shape damping block 23 and shroud damping block 22, and blade root wedge shape damping block 23 is placed in the cavity that the blade root platform side of adjacent two blades forms; Shroud damping block 22 is placed in the cavity of adjacent two blade shroud band sides formation; During work, under action of centrifugal force, blade root wedge shape damping block 23 tightly touch with shroud damping block 22 and blade root platform side and shroud side; Under the effect of steam flow excitation power; Produce the relative slippage of microcosmic or macroscopic view between blade and the damping block, thereby the dissipates vibration energy produces the damping vibration attenuation effect.
The present invention is intended to the test that makes an experiment of the damped vibration characteristic with damping block structured turbine blade, obtains the damped vibration characteristic of damping block to blade.Based on this purpose; Designed the test battery proving installation; This device comprises that experimental basis stand, root of blade surface of contact load apply with measuring mechanism, blade root wedge shape damping block and shroud damping block centrifugal force and applies and measuring mechanism, and exciting force applies, measuring mechanism and blade vibration displacement response measuring mechanism.
With reference to Fig. 2, the experimental basis stand is made up of testing table base plate 1 and testing table side plate 2, and the two is connected as a single entity through welding.Testing table base plate 1 is used to place all the other test units; Testing table side plate 2 inboard boss are used for fixing race 9, and the forward and backward and middle screw-rod structure 13 in testing table side plate 2 outsides is respectively applied for the centrifugal force load that applies blade root wedge shape damping block 23 and shroud damping block 22.
With reference to Fig. 3, root of blade interface pressure load applies hydraulic jack 4, cushion block 5, standard specimen 6, jacking block 7, blade 8 and the race 9 that comprises hydraulic jack 3, both sides with measuring mechanism.Hydraulic jack 3 is placed on testing table base plate 1 central authorities; Cushion block 5 is placed on the upper surface of hydraulic jack 3; The standard specimen that posts foil gauge 6 that is used for gaging pressure load is placed in the cushion block 5 upper surface corresponding groove; The exert pressure blade root jacking block 7 of load of leaf root part 21 is placed on the upper surface of standard specimen 6; Thereby the hydraulic jack 4 through the left and right sides is fixed in race 9 jack-up on the boss in the testing table side plate 2; Three blades 8 are inserted in the race 9 that is fixed on testing table side plate 2 inner convex platforms; Blade root jacking block 7 under the effect of hydraulic jack 3 to blade root 21 bottom section imposed loads; Make pressure load be delivered on the corresponding surface of contact of blade root 21 surface of contact and race 9, thereby realize applying of root of blade pressure load, and measure institute's applied pressure load through the standard specimen 6 that posts foil gauge.
With reference to Fig. 4, blade root wedge shape damping block and shroud damping block centrifugal force apply with measuring mechanism and comprise push rod 10, wireline pulley 11, static force sensor 12, screw-rod structure 13.In order to apply the simulation centrifugal force load of blade root wedge shape damping block; Push rod 10 is inserted in the space of race 9 bottom blade root; Push rod 10 both sides are through the wire rope tractive; Apply radial pull with the forward and backward screw-rod structure that is fixed on testing table side plate 2 outsides 13 and 11 pairs of blade root wedge shapes of wireline pulley damping block and simulate damping block centrifugal force, value of thrust measures through the static force sensor 12 on the wire rope; In order to apply shroud damping block simulation centrifugal force load; Directly on shroud damping block 22, get through the hole; Wire rope is worn in this through hole; Middle screw rod structure 13 through the wireline pulley 11 and testing table side plate 2 outsides applies radial pull to it and simulates shroud damping block centrifugal force again, and value of thrust measures through the static force sensor 12 on the wire rope.
After having applied blade root pressure load and each damping block centrifugal force load, can apply exciting force and arrange the blade displacement response measuring device blade.With reference to Fig. 5; Centrifugal force applies with measuring mechanism and comprises vibrator 18, threaded rod 16 and dynamic force sensor 17; Through threaded rod 16 vibrator 18 and blade 8 are coupled together, on threaded rod 16, be connected with 17 pairs of exciting forces of dynamic force sensor and measure near blade 8 surfaces; Blade vibration response measurement mechanism comprises support 14 and displacement transducer 15; Support 14 is fixed on and keeps static on the basic platform; Displacement transducer 15 is installed on the support 14, keeps the measuring distance of 1mm between adjustment support 14 top offset sensors 15 and blade 8 surfaces.
Apply the exciting force of certain amplitude and frequency at last through 18 pairs of blades 8 of vibrator; And the displacement transducer on the employing support 15 is measured the vibration displacement response of blade; Thereby obtain to have the damped vibration characteristic of shroud damping block and blade root wedge shape damping block turbine blade, necessary foundation is provided for further utilizing and developing corresponding damping structure turbine blade.
Claims (2)
1. turbine blade vibration attribute testing measurement mechanism with shroud damping block and blade root wedge shape damping block; It is characterized in that: comprise the experimental basis stand of forming by testing table base plate (1) and testing table side plate (2); The experimental basis stand is fixed on the basic platform; Testing table side plate (2) inboard is provided with boss, on testing table base plate (1), is placed with testing table hydraulic jack (3), and hydraulic jack (3) is provided with the standard specimen that posts foil gauge (6) that is used for gaging pressure load; The exert pressure blade root jacking block (7) of load of blade root is placed on the upper surface of standard specimen (6); Race (9) is placed on the upper end of blade root jacking block (7), through each side place at race (9) lower surface a hydraulic jack (4) with race (9) thus upwards jack-up is fixed on the boss in the testing table side plate (2), blade is inserted in the race (9); Push rod (10) inserts in the space of race (9) bottom blade root; Push rod (10) both sides are through the wire rope tractive, through wireline pulley (11) be installed in forward and backward screw-rod structure (13) outside the testing table side plate (2), blade root wedge shape damping block (23) is applied radial pull; Simulate its suffered centrifugal force; On shroud damping block (22), be equipped with through hole, middle screw-rod structure (13) applies radial pull simulation shroud damping block centrifugal force to it to this through hole of steel wire penetrating through wireline pulley (11) with outside being installed in testing table side plate (2), and the static force sensor (12) that is used to measure value of thrust all is installed on wire rope; Blade (8) links to each other with vibrator (18) through threaded rod (16); Upward near blade (8) surface the dynamic force sensor (17) that exciting force is measured is installed in threaded rod (16), blade vibration response measurement mechanism comprises support (14) and displacement transducer (15), and support (14) is fixed on and keeps static on the basic platform; Displacement transducer (15) is installed on the support (14), and keeps the measuring distance of 1mm between displacement transducer (15) and blade (8) surface.
2. the turbine blade vibration attribute testing measurement mechanism with shroud damping block and blade root wedge shape damping block according to claim 1 is characterized in that: be provided with cushion block (5) between described testing table hydraulic jack (3) and the standard specimen (6).
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| Application Number | Priority Date | Filing Date | Title |
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| CN201110072247A CN102156035B (en) | 2011-03-24 | 2011-03-24 | Turbine blade vibration characteristic testing and measuring device with shroud damping block and blade root wedged damping block |
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| CN201110072247A CN102156035B (en) | 2011-03-24 | 2011-03-24 | Turbine blade vibration characteristic testing and measuring device with shroud damping block and blade root wedged damping block |
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| CN102156035A CN102156035A (en) | 2011-08-17 |
| CN102156035B true CN102156035B (en) | 2012-09-05 |
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| CN201110072247A Expired - Fee Related CN102156035B (en) | 2011-03-24 | 2011-03-24 | Turbine blade vibration characteristic testing and measuring device with shroud damping block and blade root wedged damping block |
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Cited By (1)
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| FR3079929A1 (en) * | 2018-04-10 | 2019-10-11 | Safran Aircraft Engines | VIBRATORY TEST DEVICE FOR TURBINE MACHINE BLADES. |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1589166A1 (en) * | 1999-08-03 | 2005-10-26 | Imad H. Mualla | A device for damping movements of structural elements and a bracing system |
| CN200979484Y (en) * | 2006-10-14 | 2007-11-21 | 合肥工业大学 | A dynamic stress experimental unit with adjustable static load position |
| CN101122541A (en) * | 2007-08-03 | 2008-02-13 | 东方电气集团东方汽轮机有限公司 | Turbine blade vibration test method and device |
| CN101349170A (en) * | 2008-09-13 | 2009-01-21 | 东方电气集团东方汽轮机有限公司 | Damp structure of steam turbine cover band |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SE9602380L (en) * | 1996-06-17 | 1997-11-10 | Gustav Ingmar Johnson | Reference scale for calibration of wind tunnel scales |
-
2011
- 2011-03-24 CN CN201110072247A patent/CN102156035B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1589166A1 (en) * | 1999-08-03 | 2005-10-26 | Imad H. Mualla | A device for damping movements of structural elements and a bracing system |
| CN200979484Y (en) * | 2006-10-14 | 2007-11-21 | 合肥工业大学 | A dynamic stress experimental unit with adjustable static load position |
| CN101122541A (en) * | 2007-08-03 | 2008-02-13 | 东方电气集团东方汽轮机有限公司 | Turbine blade vibration test method and device |
| CN101349170A (en) * | 2008-09-13 | 2009-01-21 | 东方电气集团东方汽轮机有限公司 | Damp structure of steam turbine cover band |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR3079929A1 (en) * | 2018-04-10 | 2019-10-11 | Safran Aircraft Engines | VIBRATORY TEST DEVICE FOR TURBINE MACHINE BLADES. |
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