CN108194035B - Device and method for suppressing vortex-induced vibration of marine riser - Google Patents
Device and method for suppressing vortex-induced vibration of marine riser Download PDFInfo
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- CN108194035B CN108194035B CN201810100604.1A CN201810100604A CN108194035B CN 108194035 B CN108194035 B CN 108194035B CN 201810100604 A CN201810100604 A CN 201810100604A CN 108194035 B CN108194035 B CN 108194035B
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- 230000001629 suppression Effects 0.000 claims abstract description 48
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- 230000000452 restraining effect Effects 0.000 claims description 10
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- 229910000831 Steel Inorganic materials 0.000 claims description 5
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- 230000005764 inhibitory process Effects 0.000 description 7
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Classifications
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- E—FIXED CONSTRUCTIONS
- E21—EARTH OR ROCK DRILLING; MINING
- E21B—EARTH OR ROCK DRILLING; OBTAINING OIL, GAS, WATER, SOLUBLE OR MELTABLE MATERIALS OR A SLURRY OF MINERALS FROM WELLS
- E21B17/00—Drilling rods or pipes; Flexible drill strings; Kellies; Drill collars; Sucker rods; Cables; Casings; Tubings
- E21B17/01—Risers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
- F15D—FLUID DYNAMICS, i.e. METHODS OR MEANS FOR INFLUENCING THE FLOW OF GASES OR LIQUIDS
- F15D1/00—Influencing flow of fluids
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Abstract
The invention discloses a rear body arrangement tail wing type rotary vortex-induced vibration suppression device which comprises a suppression device and two rotary units, wherein the suppression device is sleeved on a vertical pipe, the two ends of the suppression device are fixedly connected with the rotary units respectively, and the rotary units are clamped on the vertical pipe. The device is provided with the closed rotating unit, is suitable for different ocean current directions, and can avoid the problems of foreign matter entering, corrosion and rust reduction and the like. The rotary unit is of a planetary gear type design, and the planetary gear type design is characterized by stable rotary motion and strong shock resistance and vibration capacity. Meanwhile, hemispherical pits are formed in the curved surface of the sleeve, and CFD verification proves that the device has a better inhibiting effect than a vortex-induced vibration inhibiting device in the prior art.
Description
Technical Field
The invention belongs to the technical field of vortex-induced vibration suppression of marine risers, relates to a vortex-induced vibration suppression device, and particularly relates to a vortex-induced vibration suppression device of a marine riser.
Background
With the increasing exploitation strength of ocean oil and gas resources, deep water oil and gas exploitation has become a future trend, and an ocean riser is a component of ocean oil and gas drilling and exploitation and is an important component for connecting a floating drilling platform and a submarine production system. The marine riser is in a severe underwater environment and is stressed in complex manner. When wave current flows through the vertical pipe, periodical vortex shedding is generated at the tail part of the marine vertical pipe, the shedding of the vortex changes the stress distribution on the surface of the vertical pipe, periodic vortex-induced vibration is initiated, and great damage is caused to the vertical pipe. The reduction of the vortex-induced vibration of the marine riser has very important significance for the exploitation of marine oil.
The prior vortex-induced vibration device has the following defects:
1. most of the published prior devices belong to structural theoretical designs, and the effect of the published prior devices is not verified by CFD numerical simulation or by live experiments conforming to actual marine environment parameters (such as different Reynolds number ranges and different incoming flow angles).
2. The prior device generally interferes with the flow field near the vertical pipe to destroy and delay the formation and development of vortex, and the boundary layer fluid of the vertical pipe or the sleeve on the vertical pipe is not researched and utilized, because the boundary layer is much weaker than the vortex, the transverse stress disturbance of the vertical pipe can be reduced by expanding the shear layer and delaying the formation of the vortex.
The disclosed vortex-induced vibration suppression device has the disadvantage that the wake stability is not considered for the suppression of vortex-induced vibration, as disclosed in patent number US6685394B1 entitled "suppression of vortex-induced vibration by a partially perforated shroud" and method of use (Partial shroud with perforating for VIV suppression and method of using); the vortex-induced vibration suppression device disclosed in US9534618B1, entitled "fairing device with multiple members (Faring bodies with multiple parts)", has the disadvantage of not taking into account disturbances to incoming flow nor being able to rotate according to different incoming flow directions.
Disclosure of Invention
The invention aims to overcome the problems and defects of the prior art, mainly aims at the problem of vortex-induced vibration, realizes the suppression of vortex-induced vibration in different incoming flow directions, reduces fatigue damage to a vertical pipe, and provides a detachable rear body arrangement tail wing type rotary marine vertical pipe vortex-induced vibration suppression device with reliable performance.
In order to achieve the purpose, the invention adopts the following technical scheme:
a rear body arrangement tail wing type rotary vortex-induced vibration suppression device comprises a suppression device 2 and two rotary units 3 which are sleeved on a vertical pipe 1, wherein two ends of the suppression device 2 are fixedly connected with one rotary unit 3 respectively, and the rotary units 3 are clamped on the vertical pipe 1.
Further, the suppressing device 2 is composed of a sleeve 2-1, at least two connectors 2-2 and a rear body tail fin 2-3. Wherein the sleeve 2-1 is of a circular tube structure, and the connecting body 2-2 is of a columnar body. The section of the rear tail fin 2-3 is V-shaped, and the V-shaped openings are symmetrically distributed at the downstream side in the incoming flow direction of the vertical pipe 1 and face to the downstream side. The connecting body 2-2 is positioned between the sleeve 2-1 and the rear body tail wing 2-3, one end of the connecting body is fixedly connected with the sleeve 2-1, and the other end of the connecting body is fixedly connected with the rear body tail wing 2-3.
Further, the rotating unit 3 is of a planetary gear type structure and comprises a central wheel 3-2, at least 4 planetary wheels 3-3, an outer ring 3-4, two semicircular cover plates 3-1 and a bottom plate 3-2-2. The central wheel 3-2, the planet wheel 3-3 and the outer ring 3-4 are distributed from inside to outside in a 'inner, middle and outer' mode and are meshed and connected through gear teeth respectively arranged. Meanwhile, a circular bottom plate 3-2-2 is designed at the bottom of the rotary unit 3, the bottom plate 3-2-2 is fixedly connected with the central wheel 3-2, and two semicircular cover plates 3-1 are arranged at the upper part of the rotary unit 3 in a mirror image involution manner and are fixedly connected with the central wheel 3-2. So that the rotating unit 3 forms a closed structure. The rotating unit 3 is clamped to the riser 1. And meanwhile, the outer ring 3-4 of the rotary unit 3 is fixed at two ends of the sleeve 2-1 by bolts, the number of bolts at the joint is at least 8, and the two semicircular cover plates 3-1 are mutually fixed by at least 4 bolts. The number of all screw connections can be determined on a case-by-case basis.
Further, the outer diameters of the bottom plate 3-2-2 and the semicircular cover plate 3-1 are 0.9-0.95 times of the outer diameter of the outer ring 3-4. The inner diameter of the semicircular cover plate 3-1 is 0.95-0.99 times of the outer diameter of the sleeve. So that it can be clamped and fixed on the vertical pipe 1 to avoid sliding and rotation. The outer surface of the bottom plate 3-2-2 and the semicircular cover plate 3-1 are flush with the upper end surface and the lower end surface of the outer ring 3-4.
Furthermore, the upper and lower planes of the gear teeth 3-4-1 of the outer ring 3-4 are respectively provided with a sealing ring groove 3-4-4, and a sealing groove 3-1-3 is arranged between the two semicircular cover plates 3-1. After the installation is completed, the gears are all in the closed space, so that the problems that foreign matters in the seawater enter to cause the failure of the rotating unit 3, the corrosion and rust of the meshing gears of the rotating unit 3 are reduced, and the like are avoided.
Further, a plurality of hemispherical pits 2-1-2 are arranged on the surface curved surface of the outer surface of the sleeve 2-1, the hemispherical pits 2-1-2 are arranged in a matrix or delta arrangement mode, and the diameter of the hemispherical pits is 1/20-1/10 of the outer diameter of the sleeve 2-1 through CFD calculation. The distance between the two hemispherical pits 2-1-2 is 1 to 2 times of the sphere diameter. The hemispherical pits 2-1-2 occupy 8% to 20% of the surface area of the outer surface of the sleeve 2-1. Screw holes connected with the rotating unit 3 are designed on two end faces of the sleeve 2-1, and the number of screw holes on each end face is at least 8. The wall thickness of the sleeve 2-1 is the same as the hemispherical pit diameter.
Further, the length of the connector 2-2 is 1/3-1/2 of the outer diameter of the sleeve 2-1. The distribution mode is as follows: the connecting bodies 2-2 are distributed at the positions, close to the two ends, of the curved surface of the sleeve, and the connecting bodies 2-2 are distributed at equal intervals. The surface of the connector 2-2 is a smooth surface or is provided with at least 4 forward flow diversion trenches which are distributed at equal intervals. The cross section of the connector 2-2 is any one of the following forms:
a. the broken section is rectangular, the long side is 4-6 times of the diameter of the hemispherical pit 2-1-2, the short side is 2-4 times of the diameter of the hemispherical pit 2-1-2, and the short side is along the horizontal direction;
b. the section is square, and the side length is 2-6 times of the diameter of the hemispherical pit 2-1-2;
c. the cross section is elliptical, the major axis is 4-6 times of the diameter of the hemispherical pit 2-1-2, the minor axis is 2-4 times of the diameter of the hemispherical pit 2-1-2, and the minor axis is along the horizontal direction;
d. the cross section is round, and the diameter of the cross section is 2-6 times of the diameter of the hemispherical pit 2-1-2.
Further, the length of the rear body tail wing 2-3 is the same as that of the sleeve 2-1, the included angle alpha of the V shape is 80-100 degrees, and the length of each side of the V shape is 0.65-0.75 times of the outer diameter of the sleeve 2-1. The wall thickness of the rear body tail wing 2-3 is the same as the wall thickness of the sleeve, the rear body tail wing 2-3 is provided with a plurality of through holes 2-3-1 which are vertical to the wall surface of the rear body tail wing 2-3 and are arranged in a matrix or delta shape, and the section shape of the through holes 2-3-1 is any one of the following forms:
a. the diameter of the through hole 2-3-1 is the same as that of the hemispherical pit 2-1-2 on the surface of the sleeve 2-1 in a round shape;
b. oval, the major axis takes 1-2 times of the diameter of the hemispherical pit 2-1-2, and the minor axis takes 0.5-1 times of the diameter of the hemispherical pit 2-1-2;
c. the length of the rectangle is 1-2 times of the diameter of the hemispherical pit 2-1-2, and the width is 0.5-1 times of the diameter of the hemispherical pit 2-1-2;
d. the diameter of the external circle of the regular polygon is 0.5-1.5 times of the diameter of the hemispherical pit 2-1-2.
The materials of the restraining device 2 and the rotating unit 3 are selected to meet the requirements of light weight, good mechanical strength, corrosion resistance, convenient processing and the like. The following are selected material schemes for making the device of the present invention:
a. and steel is selected, and the surfaces of the inhibition device 2 and the rotary unit 3 can be plated with a layer of metal chromium, so that rust is reduced. Wherein stainless steel material can be selected for the interior of the rotary unit 3;
b. the aluminum alloy material is selected, and has the advantages of light material, high strength, corrosion resistance and easy processing;
c. the polyurethane material is selected, and has the advantages of higher mechanical strength and oxidation stability, long service life, temperature resistance of between 20 ℃ below zero and 120 ℃ at high temperature, no toxicity, no smell, environmental protection, no pollution, light weight and load reduction;
d. the carbon fiber composite material has the advantages of light weight and high strength. Compared with steel, the weight of the steel is only 1/5 of that of the steel under the condition of equal strength.
The invention relates to a working principle and a suppression method of a rear body arrangement tail airfoil type rotary vortex-induced vibration suppression device, which specifically comprises the following steps:
when ocean currents flow through the vertical pipe 1, periodical vortex shedding alternately occurs at the tail part of the ocean vertical pipe, the shedding of the vortex changes the stress distribution on the surface of the vertical pipe 1, periodic vortex-induced vibration is initiated, and great damage is caused to the vertical pipe. When the vortex shedding frequency is close to the natural frequency of the vertical pipe, a locking phenomenon is formed, the vertical pipe can vibrate severely, and serious fatigue damage is caused to the vertical pipe. It is therefore necessary to install vortex-induced vibration suppression devices on risers. According to the CFD calculation result, the hemispherical diameter of the surface of the device is 1/20-1/10 of the outer diameter of the sleeve 2-1, and the design scheme of the tail fin of the body after being additionally arranged greatly reduces the intensity of vorticity and reduces the amplitude of vortex-induced vibration.
The positive direction of the x-axis in the rectangular coordinate system is 0 degree. When the incoming flow direction is 0 deg., the rear body tail 2-3 is turned by the rotating unit 3 to 180 deg. downstream of the incoming flow direction. When the incoming flow direction changes, and the incoming flow direction is 30 degrees or 90 degrees, the pressure of the flow field around the vertical pipe 1 changes, and the rear body tail wing 2-3 is turned to the downstream 210 degrees or 270 degrees of the incoming flow direction through the rotary unit 3. The rotation of the restraining device, like the well known wind vane, varies with the direction of the fluid, and the rear body tail 2-3 is always downstream in the direction of incoming flow.
When the incoming flow passes through the sleeve 2-1, the flow field around the sleeve 2-1 is disturbed due to the hemispherical pits 2-1-2 distributed on the sleeve 2-1, and the energy for forming vortex is weakened. CFD shows that the design of the hemispherical pits 2-1-2 on the surface of the sleeve 2-1 can reduce the transverse vibration of the vertical pipe by more than 20% compared with other published restraining devices in similar forms.
The addition of the rear tail fin 2-3 solves the instability caused by the abrupt change of the wake speed in the existing restraining device. When the incoming shear layer leaves the edge of the sleeve 2-1, it reattaches to the surface of the rear body tail 2-3 along the forward flow guide groove on the surface of the connecting body 2-2, and the energy is weak due to the relatively small fluctuation of the shear layer. Thus, by expanding the shear layer, the formation of vortices is retarded and fluctuations in near wake zone pressure can be reduced.
When the incoming flow shearing layer is attached to the surface of the rear body tail wing 2-3, closed circular flows are formed on two sides, and the symmetrical circular flows prevent alternating karman vortex streets from being formed from one side to the other side in the near-wake flow area; in turn, it stabilizes the near wake region, delaying the formation of karman vortex street; because the pressure gradient of the circulation in the transverse direction is symmetrical, a force elimination effect appears, the fluctuation pressure gradient of the near wake area is reduced, the formation of vortex is delayed, and the nearby wake area is stabilized, so that the amplitude of vibration is reduced; meanwhile, through holes 2-3-1 on the rear body tail wing 2-3 weaken forward flow resistance increase, so that pressure gradient in a near-wake area is reduced, and vortex-induced vibration is restrained.
Compared with the prior art, the invention has the following advantages and beneficial effects:
1. the device is provided with the closed rotating unit, is suitable for different ocean current directions, and can avoid the problems of foreign matter entering, corrosion and rust reduction and the like. The rotary unit is designed into a planetary gear type, and the design of the planetary gear type is characterized by stable rotary motion and strong shock resistance and vibration resistance.
2. The design of the hemispherical pits on the outer surface of the sleeve of the device has better effect than the traditional vortex-induced vibration suppression device through CFD verification.
As shown in fig. 12, the surface of the sleeve is designed with 3 hemispherical pits of different sizes when the rear body tail fin is not additionally arranged. By observing the stress curve, the design scheme with the hemispherical diameter of 1/20 and 1/10 of the sleeve outer diameter is more obvious in optimization of the vortex-induced vibration suppression effect than the scheme with the spherical diameter of 1/5 of the sleeve outer diameter, and the scheme with the hemispherical diameter of 1/20 of the sleeve outer diameter is best in optimization effect. Comparing the optimal scheme with a sleeve with smooth surface and a sleeve with square pits on the surface:
as shown in fig. 13, the sleeve design with smooth surface has an average stress range of-0.01942N to 0.0165N, square pit design with average stress range of-0.015222N to 0.01466N, hemispherical diameter of 1/20 sleeve outer diameter design, and average stress range of-0.01175N to 0.01198N.
Compared with a sleeve with a smooth surface, the design scheme that the hemispherical diameter of the surface is 1/20 of the outer diameter of the sleeve optimizes the vortex-induced vibration inhibition effect by 33.94%. Compared with a pit sleeve with a square surface, the design scheme with the hemispherical surface diameter of 1/20 of the sleeve outer diameter optimizes the vortex-induced vibration inhibition effect by 20.58%. The CFD calculation results show that the design scheme that the hemispherical diameter of the surface is 1/20 of the outer diameter of the sleeve reduces the strength of vorticity.
3. The device is provided with a rear tail wing. With this arrangement, riser lateral amplitude is reduced and vortex induced vibration is suppressed.
As shown in fig. 14, the design of the fairing inhibitor with the splitter plate has an average stress range of-0.003124N to 0.003134N, a hemispherical surface diameter of 1/20 of the outer diameter of the sleeve, and an average stress range of-0.000955N to 0.001069N.
After the rear body fin is additionally arranged, the rear body fin is compared with a fairing restraining device with a splitter plate. The hemispherical diameter of the surface is 1/20 of the outer diameter of the sleeve, and the vortex-induced vibration suppression effect is optimized by 67.66% according to the design scheme of the rear body tail fin additionally arranged. Compared with the design scheme of the sleeve with a smooth surface, the hemispherical diameter of the surface is 1/20 of the outer diameter of the sleeve, and the design scheme of the tail fin of the body after being additionally arranged optimizes 94.37 percent of the vortex-induced vibration inhibition effect.
Drawings
FIG. 1 is a riser, restraint device, swivel unit assembly combination of the present invention;
figure 2 is an isometric view of the suppression device of the present invention;
FIG. 3 is a cross-sectional view of the suppression device of the present invention;
FIG. 4 is a side view of the suppression device of the present invention;
FIG. 5 is a schematic illustration of the fixed connection of the rotary unit to the riser (section), restraint device (section) of the present invention;
FIG. 6 is a schematic illustration of the rotary unit of the present invention with only one cover plate added;
FIG. 7 is a schematic view of the internal structure of the rotary unit of the present invention;
FIG. 8 is a part view of the outer race of the rotary unit of the present invention;
FIG. 9 is a cover part view of the rotary unit of the present invention;
FIG. 10 is a part view of the sun gear of the rotary unit of the present invention;
FIG. 11 is a planetary gear part diagram of the rotary unit of the present invention;
fig. 12 is a CFD verification scheme of the invention: the hemispherical diameter of the surface is 1/20, 1/10 and 1/5 of the outer diameter of the sleeve, and the curve chart is a cylindrical stress time calendar;
fig. 13 is a CFD validation scheme of the invention: a cylindrical stress time calendar curve graph with smooth surface and square pits on the surface and a hemispherical diameter of 1/20 of the outer diameter of the sleeve;
fig. 14 is a CFD validation scheme of the present invention: the hemispherical diameter of the surface of the device with the split-flow plate type fairing is 1/20 of the outer diameter of the sleeve, and the stress time calendar curve chart of the suppressing device with the rear tail fin is additionally arranged;
the reference numerals in the drawings illustrate:
1. a riser;
2. a suppression device; 2-1, a sleeve; 2-1 to 1, screw holes; 2-1-2. Hemispherical pits; 2-2, a connector; 2-3, a rear tail fin; 2-3-1. Through holes;
3. a rotating unit; 3-1, a semicircular cover plate; 3-1 to 1, screw holes; 3-1-2, fixing screw holes; 3-1-3, sealing the groove; 3-2, a center wheel; 3-2-1. Gear teeth; 3-2-2. A bottom plate; 3-2-3. A seal ring groove; 3-2-4, screw holes; 3-3, planet gears; 3-3-1. Gear teeth; 3-4, an outer ring; 3-4-1. Gear teeth; 3-4-2, counter bore; 3-4-3, screw holes; 3-4-4. Seal ring groove.
Detailed Description
The present invention will be described in further detail with reference to the drawings and examples, in order to make the objects, technical solutions and advantages of the present invention more apparent. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the scope of the invention.
According to the rear body arrangement tail wing type rotary vortex-induced vibration suppression device, as shown in fig. 1, 2, 3 and 4, a sleeve 2-1 of the suppression device 2 is sleeved on a vertical pipe 1, two ends of the sleeve 2-1 are respectively provided with a rotary unit 3, and bolts are used for connecting and fixing with outer ring screw holes 3-4-3 of the rotary unit 3 through screw holes 2-1-1. Two ends of the curved surface of the sleeve 2-1 are respectively and rigidly connected with a connector 2-2 in the same direction, and the other ends of the two connectors 2-2 are rigidly connected with the rear body tail wing 2-3.
As shown in fig. 1, 5, 6 and 8, the outer ring 3-4 belongs to an internal gear, at least 8 screw holes 3-4-3 are uniformly distributed on the upper surface of the outer ring, counter bores 3-4-2 are formed in the upper surface and the lower surface of the outer ring, a sealing ring groove 3-4-4 is formed in the upper surface and the lower surface of the outer ring, and a wear-resistant ceramic sealing ring is placed in the sealing ring groove 3-4-4. The outer ring 3-4 is fixedly connected with the sleeve 2-1 through screw holes 3-4-3 by bolts. The outer ring 3-4 is clamped between the cover plate 3-1 and the bottom plate 3-2-2 after being installed.
As shown in fig. 5, 8 and 9, the cover plates 3-1 are clamped on the vertical pipe 1 through the fixing screw holes 3-1-2 by using bolts, at least 10 screw holes 3-1-1 are shared on the two cover plates 3-1, correspond to the screw holes 3-2-4 on the central wheel, and are connected and fixed by using bolts. The contact surface of the two cover plates 3-1 is provided with a sealing groove 3-1-3, and a wear-resistant ceramic sealing ring is arranged in the sealing groove 3-1-3.
As shown in fig. 6, 7, 10 and 11, the center wheel 3-2 is sleeved on the vertical pipe 1 and is connected and fixed with the cover plate 3-1 through at least 10 screw holes 3-2-4 by bolts. At least 4 planetary gears 3-3 are arranged around the central gear 3-2 and uniformly distributed around the central gear 3-2. The gear teeth 3-3-1 of the planet wheel 3-3 are meshed with the gear teeth 3-4-1 of the outer ring 3-4 and the gear teeth 3-2-1 of the central wheel 3-2 to form a planetary gear train, and are important components of the rotating unit 3.
The invention relates to a suppression method of a rear body arrangement tail airfoil type rotary vortex-induced vibration suppression device, which comprises the following steps:
when the direction of the ocean current changes, the pressure of the flow field around the vertical pipe 1 changes, and the rear body tail wing 2-3 turns to the rear part of the vertical pipe 1 through the rotating unit 3. The rear body tail wing 2-3 can always play a role in stabilizing wake flow.
According to the rear body arrangement tail airfoil type rotary vortex-induced vibration suppression device, different pits are verified through CFD simulation, and the suppression effect is as follows:
taking a riser sleeve in the restraining device as a research object, wherein the clearance between the riser and the sleeve is ignored in calculation, and the riser and the sleeve are combined and then simplified into a cylinder in calculation. And comparing the smooth cylinder with cylinders with pits of different sizes and different forms on the surface. The numerical simulation adopts a 2-dimensional calculation model. And carrying out numerical simulation calculation by adopting Solidworks modeling, hexpress drawing grids and Fine/marine. The diameter D of the sleeve cylinder is 10mm, and the height D is 5mm.
The calculation is carried out in a flow field with Re=10000, and the motion viscosity coefficient is 1.18X10 (-6) m 2 And/s (sea water at 15 ℃) is calculated by adopting unsteady state and single-phase flow, the front, back, left and right sides of a calculation domain are set to be far-field EXT, the upper and lower sides are set to be MIR, and the time step is 0.001s.
And the vibration condition of the cylinder is reflected by the transverse stress by the aid of the mechanical/Marine numerical simulation calculation and the transverse stress monitoring of the cylinder. Meanwhile, the formation and development of the vortex are monitored, and the stress condition of the vertical pipe is reflected through the vortex.
The calculation adopts a comparison and improvement mode, and the design is gradually optimized. Hemispherical pits with diameters of 0.5mm (1/20 of the outer diameter of the sleeve), 1mm (1/10 of the outer diameter of the sleeve) and 2mm (1/5 of the outer diameter of the sleeve) are cut out on the curved surface of the cylinder, and the pits are distributed on the surface of the cylinder, and the three conditions are compared to select the optimal hemispherical diameter size. The optimal design scheme is determined by comparing the calculation result of the optimal scheme of the hemispherical concave pits on the surface with the simplified model of the cylindrical column with the smooth surface and the square concave pits on the surface (patent US6685394B 1).
Comparing the cylindrical stress time history curves with different hemispherical diameters on the surface of the sleeve in the figure 12, the design scheme with the hemispherical diameters of 1/20 and 1/10 of the sleeve outer diameter has obvious effect of inhibiting vortex-induced vibration compared with the scheme with the hemispherical diameter of 1/5 of the sleeve outer diameter, and the scheme with the hemispherical diameter of 1/20 of the sleeve outer diameter has the best optimization effect.
As shown in fig. 13, the cylindrical design with smooth surface has an average stress range of-0.01942N to 0.0165N, the square pit design with square surface has an average stress range of-0.015222N to 0.01466N, the hemispherical diameter of the surface has a design of 1/20 of the sleeve outer diameter, and the average stress range is-0.01175N to 0.01198N.
Compared with a cylindrical sleeve with a smooth surface, the design scheme with the hemispherical diameter of the surface being 1/20 of the outer diameter of the sleeve optimizes the vortex-induced vibration inhibition effect by 33.94%. Compared with a pit sleeve with a square surface, the design scheme with the hemispherical surface diameter of 1/20 of the sleeve outer diameter optimizes the vortex-induced vibration inhibition effect by 20.58%. The CFD calculation result shows that the design scheme that the hemispherical diameter of the surface is 1/20 of the outer diameter of the sleeve reduces the strength of vorticity, and a good optimization effect is achieved.
And then optimizing the cylindrical sleeve scheme with hemispherical pits, adding a rear tail fin, and comparing with the fairing suppression device with the splitter plate to determine the final optimization scheme.
The rear body arrangement tail airfoil type rotary vortex-induced vibration suppression device has the following suppression effects by comparing different suppression devices:
and taking the restraining device of the tail fin of the post body as a research object, wherein the model, the grid generation and the calculation parameter setting in the Fine/marine are the same as those in the step two.
As shown in FIG. 14, to further improve the design that the hemispherical diameter of the surface is 1/20 of the outer diameter of the sleeve, a rear tail device is arranged at the position 0.5D (D is the diameter of the cylinder) behind the cylinder and is used for reattaching the shear layer, stabilizing the wake better and reducing the influence of the wake on the riser. The design is compared with the simplified model of the fairing suppression device with the splitter plate (patent US9534618B 1).
As shown in fig. 14, the fairing inhibitor with the splitter plate has an average stress range of-0.003124N to 0.003134N, a hemispherical surface diameter of 1/20 of the outer diameter of the sleeve, and an average stress range of-0.000955N to 0.001069N.
After the rear body fin is additionally arranged, the rear body fin is compared with a fairing restraining device with a splitter plate, the hemispherical diameter of the surface is 1/20 of the outer diameter of the sleeve, and the vortex-induced vibration restraining effect of the design scheme of the rear body fin is optimized by 67.66%. Compared with the design scheme of a cylindrical sleeve with a smooth surface, the hemispherical diameter of the surface is 1/20 of the outer diameter of the sleeve, and the design scheme of the tail fin of the body after being additionally arranged optimizes the vortex-induced vibration inhibition effect by 94.37 percent.
In view of the above, it is shown that the hemispherical diameter of the surface is 1/20 of the outer diameter of the sleeve, and the design of the rear body fin achieves the ideal effect of inhibiting vortex-induced vibration. The reattachment of the shear layer was observed to form a closed loop on both sides when the shear layer was attached to the back body surface. Since the pressure gradient of the circulation in the transverse direction is symmetrical, a force cancellation effect occurs, thereby reducing the amplitude of the vibrations. The effect of well inhibiting vortex-induced vibration and reducing fatigue damage of the vertical pipe is achieved.
The foregoing description is only one embodiment of the present invention. Of course, the invention is capable of other various embodiments and its several details are capable of modification in various, equivalent arrangements and changes, all of which are within the purview of one skilled in the art and capable of modification in accordance with the invention without departing from the spirit and intended scope of the invention as defined in the appended claims.
Claims (7)
1. The rear body arrangement tail wing type rotary vortex-induced vibration suppression device is characterized by comprising a suppression device (2) and two rotary units (3) which are sleeved on a vertical pipe (1), wherein two ends of the suppression device (2) are fixedly connected with one rotary unit (3) respectively, and the rotary units (3) are clamped on the vertical pipe (1);
the restraining device (2) is composed of a sleeve (2-1), at least two connecting bodies (2-2) and a rear tail wing (2-3), wherein the sleeve (2-1) is of a circular tube structure, the connecting bodies (2-2) are columnar bodies, the rear tail wing (2-3) is of a V-shaped cross section, and the V-shaped openings are symmetrically distributed on the downstream side in the incoming flow direction of the vertical tube (1) and face the downstream side; the connecting body (2-2) is positioned between the sleeve (2-1) and the rear body tail wing (2-3), one end of the connecting body is fixedly connected with the sleeve (2-1), and the other end of the connecting body is fixedly connected with the rear body tail wing (2-3);
the rotary unit (3) is of a planetary gear type structure and comprises a central wheel (3-2), at least 4 planetary wheels (3-3), an outer ring (3-4), two semicircular ring cover plates (3-1) and a bottom plate (3-2-2), wherein the central wheel (3-2), the planetary wheels (3-3) and the outer ring (3-4) are distributed from inside to outside in an inner, middle and outer mode and are meshed and connected through gear teeth arranged on the planetary wheels respectively, the bottom plate (3-2-2) is arranged at the bottom of the rotary unit (3) and fixedly connected with the central wheel (3-2), and the two semicircular ring cover plates (3-1) are arranged at the upper part of the rotary unit (3) in a mirror joint mode and fixedly connected with the central wheel (3-2), so that a closed structure is formed;
the outer diameters of the bottom plate (3-2-2) and the semicircular cover plate (3-1) are 0.9-0.95 times of the outer diameter of the outer ring (3-4); the inner diameter of the semicircular cover plate (3-1) is 0.95-0.99 times of the outer diameter of the sleeve (2-1).
2. The rear body arrangement tail airfoil type rotary vortex-induced vibration suppression device according to claim 1, wherein sealing ring grooves (3-4-4) are formed in the upper plane and the lower plane of gear teeth (3-4-1) of the outer ring (3-4), and sealing grooves (3-1-3) are formed in the end face of the semicircular cover plate (3-1).
3. The rear body arrangement tail airfoil type rotary vortex-induced vibration suppression device according to claim 1, wherein a plurality of hemispherical pits (2-1-2) are arranged on the surface curved surface of the sleeve (2-1), the hemispherical pits (2-1-2) are arranged in a matrix or delta-shaped manner, the diameter of each hemispherical pit is 1/20-1/10 of the outer diameter of the sleeve (2-1), the distance between the two hemispherical pits (2-1-2) is 1-2 times of the sphere diameter, screw holes connected with the rotary units (3) are arranged on two end faces of the sleeve (2-1), and the number of screw holes on each end face is at least 8; the wall thickness of the sleeve (2-1) is the same as the diameter of the hemispherical pit.
4. The rear body arrangement tail airfoil type rotary vortex-induced vibration suppression device according to claim 1, wherein the length of the connecting body (2-2) is 1/3-1/2 of the outer diameter of the sleeve (2-1), the section of the connecting body is any one of square, elliptic and circular, and the outer surface of the connecting body is provided with a forward flow guide groove.
5. The rear body arrangement tail wing type rotary vortex-induced vibration suppression device according to claim 1, wherein the length of the rear body tail wing (2-3) is the same as that of the sleeve (2-1), the included angle alpha of the V shape is 80-100 degrees, a plurality of through holes (2-3-1) which are perpendicular to the wall surface of the rear body tail wing (2-3) and are arranged in a matrix or delta shape are arranged on the rear body tail wing (2-3), and the cross section of the through holes (2-3-1) is round, elliptic, square or regular polygon.
6. The rear body arranged tail airfoil type rotating vortex-induced vibration suppression device according to any one of claims 1 to 5, wherein the material of the suppression device (2) and the rotating unit (3) is any one of steel material with surface plated with metal chromium, stainless steel, aluminum alloy, polyurethane and carbon fiber composite material.
7. A method for implementing a rear body arranged tail airfoil type rotary vortex-induced vibration suppression device according to any one of claims 1 to 5, which is characterized by comprising the following specific implementation procedures:
when the incoming flow direction is 0 degree, the rear body tail wing (2-3) turns to the downstream 180 degrees of the incoming flow direction through the rotating unit (3), when the incoming flow direction changes, namely 30 degrees or 90 degrees, the pressure of the surrounding flow field of the vertical pipe (1) changes, the rear body tail wing (2-3) turns to the downstream 210 degrees or 270 degrees of the incoming flow direction through the rotating unit (3), and the rear body tail wing (2-3) is always positioned at the downstream of the incoming flow direction;
when the incoming flow flows through the sleeve (2-1), as hemispherical pits are distributed on the sleeve (2-1), the flow field around the sleeve (2-1) is disturbed, and the energy for forming vortex is weakened;
when the incoming flow shear layer leaves the edge of the sleeve (2-1), the incoming flow shear layer is reattached to the surface of the tail wing (2-3) of the rear body along the forward flow diversion trench on the surface of the connecting body (2-2), and the fluctuation of the shear layer is relatively small and the energy is weaker, so that the formation of vortex is delayed, and the fluctuation of the pressure in a near-wake flow area is reduced;
when the incoming flow shearing layer is attached to the surface of the tail wing (2-3), closed circulation is formed on two sides, and the symmetrical circulation prevents alternating karman vortex streets from being formed from one side to the other side in the near-wake area; in turn, it stabilizes the near wake region, delaying the formation of karman vortex street; because the pressure gradient of the circulation in the transverse direction is symmetrical, a force elimination effect is generated, the fluctuation pressure gradient of the near wake flow area is reduced, the formation of vortex is delayed, and the nearby wake flow area is stabilized, so that the amplitude of vibration is reduced; meanwhile, through holes (2-3-1) on the tail fin (2-3) of the rear body weaken forward flow resistance, so that the pressure gradient of a near-wake flow area is reduced, and vortex-induced vibration is restrained.
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| CN110792398B (en) * | 2019-11-04 | 2021-09-28 | 河海大学 | Device for inhibiting vortex-induced vibration of marine riser |
| CN111306148B (en) * | 2020-03-09 | 2022-02-11 | 中国海洋石油集团有限公司 | Marine riser vortex-induced vibration suppression device |
| CN111613352B (en) * | 2020-06-04 | 2022-05-10 | 中国核动力研究设计院 | Vortex-induced vibration suppression device for cylindrical structure |
| CN111735502B (en) * | 2020-07-16 | 2021-11-19 | 扬州大学 | Vortex vibration variable flow protection device based on wind field monitoring |
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| CN201050579Y (en) * | 2007-04-24 | 2008-04-23 | 丁开仙 | Enclosed type planet gear reducer |
| CN105863526A (en) * | 2016-06-22 | 2016-08-17 | 西南石油大学 | Device and method for suppressing vortex-induced vibration of rotationally-telescopic tail swinging type riser |
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