CN2293387Y - Three-vortex cyclone - Google Patents

Abstract

The utility model relates to a three-vortex cyclone. A blade which is arranged on the periphery of the internal tube of the blade wheel adopts a thickening design scheme, and the section shape of the blade is the sectional shape of the cascade of the aircraft engine. The rear edge portion of the blade is a smooth transition, and the three-vortex cyclone avoids flow distortion caused by the unsmooth surface of the blade. The utility model has the advantages of small viscous friction and high separating effects of the dust.

Description

Three whirlwind

The utility model relates to three whirlwind in a kind of high-temperature flue gas energy-recuperation system.

The blade of whirlwind is the core component of third level cyclone separator in the oil plant catalytic cracking high-temperature flue gas energy-recuperation system, and the flow through flow field quality of whirlwind blades of high-temperature flue gas directly influences the separative efficiency and the energy recovery rate of dust in the flue gas.The domestic and international whirlwind blades that adopts all is the bent plate type at present, the radius of curvature of blade inlet edge is bigger, the disturbance of stream field is big, trailing edge is not a smooth transition, makes blade lifting resistance ratio little, and blade surface is rough, the pressure change of blade air-flow of flowing through is inhomogeneous, easily cause flow distortion, difficult maintenance laminar flow section in a big way, its dust separation efficient is subjected to influence to a certain degree.

The purpose of this utility model is to avoid above-mentioned weak point of the prior art, and provides the disturbance of a kind of leading edge stream field little, and viscous friction is little, and dust separation efficient height can avoid three of flow distortion to revolve whirlwind.

The purpose of this utility model can reach by following measure:

A kind of three whirlwind, comprise pipe 1 and the blade 5 of being located at its outside in the impeller, its special character is, described blade 5 section shapes are aero-engine leaf grating section shape, the maximum ga(u)ge H of described blade 5 is 8～12% of mean camber line 8 arc length, it is located in the maximum ga(u)ge position 10 of described blade 5 is the length place of 15～25% strings of a musical instrument 9 apart from costa 2, and the radius of curvature of the leading edge point 6 of described blade 5 is 1～3% of mean camber line 8 arc length.

The mean camber line 8 of the utility model blade 5 can be the cube curve of tubular axis in the impeller to coordinate with the angle theta of the interior pipe of impeller 1 axis.

θ＝ax ³+bx ²+cx+d＝f(x)

The declination angle of the ray 00 of the intersection point A of pipe 1 in the costa 2 of the utility model blade 5 and the costa 2 of being crossed blade 5 by the axle center of pipe 1 in the impeller and the impeller ' form can be $\mathrm{\φ}=0.5(1/r_1-1/r_2){{\∫}_0}^L\tan \left[f\left(x\right)\right]\mathrm{dx}$

The maximum ga(u)ge H of the utility model blade 5 is that 9% of mean camber line 8 arc length are the best with it, the maximum ga(u)ge position 10 of described blade 5 is that the length place of 23% the string of a musical instrument 9 is the best apart from costa 2 to be located at it, and the radius of curvature of the leading edge point 6 of described blade 5 is that 1% of mean camber line 8 arc length are the best with it.

The accompanying drawing drawing is described as follows:

Fig. 1 is a structural representation of the present utility model.

Fig. 2 is the profile of the utility model blade.

Fig. 3 is the schematic diagram of the utility model leading edge and interior pipe declination angle.

The utility model is described in further detail below in conjunction with accompanying drawing:

Referring to Fig. 1, the utility model mainly is made of pipe 1 in the impeller and the blade 5 that is distributed in its periphery.The shape of blade 5 has adopted thickening degree design, and trailing edge part 3 is a smooth transition, and promptly the section of blade 5 is an aero-engine leaf grating section shape, and it comprises wing profile shape or large-scale fan section shape.Referring to Fig. 2, the x axle is a tubular axis line in the impeller, and the y axle is that all line coordinates are launched on the face of cylinder, and the maximum ga(u)ge H of blade 5 is 8～12% of mean camber line 8 arc length, is the best with 9%; Maximum blade thickness position 10 is 15～25% of the string of a musical instrument 9 length apart from the distance of costa 2, is the best with 23%.The string of a musical instrument 9 is the straight line of 6 of trailing edge point 7 and leading edge point among Fig. 2, and leading edge point 6 and trailing edge point 7 are respectively dissecing a little on costa 2 and the trailing edge line 4.The radius of curvature of blade inlet edge point 6 is 1～3% of mean camber line 8 arc length, is the best with 1%.For the pressure change that makes blade 5 air-flows of flowing through is more even, the angle theta of the axis of pipe 1 in blade mean camber line 8 and the impeller is to be good to tubular axis in the impeller to the cubic equation of coordinate with it, promptly

θ=ax ³+ bx ²In+cx+d=f (x) formula, constant a, b, c, d can require according to the difference of design to select, and mainly determine according to following condition:

1) the θ value of the inlet of pipe 1 in the impeller;

2) the θ value of the outlet of pipe 1 in the impeller;

3) rate of change of pipe 1 outlet in the impeller, inlet θ value.The costa 2 of pipe 1 porch blade 5 and the ray 00 of crossing the intersection point A of pipe 1 in blade inlet edge line 2 and the impeller by pipe 1 axle center in the impeller in the utility model impeller ', form an included angle, be leading edge drift angle φ, referring to Fig. 3, AB is costa 2, this leading edge drift angle φ so that front and rear edges line 2,4 and corresponding cross in the impeller the interradial angle of the tubular axis heart unlikely have big difference be advisable, can guarantee like this under certain cross-sectional area, the section girth minimum of circulating face, thus viscous friction can be reduced.The computing formula of blade inlet edge drift angle φ is: $\mathrm{\φ}=0.5(1/r_1-1/r_2){\∫}_0^L\tan \left[f\left(x\right)\right]\mathrm{dx}$ R in the formula ₁, r ₁Be respectively the radius of interior pipe 1 of impeller and the sub-outer tube 11 of whirlwind; L is the length of blade in the x direction.

The utility model compared with prior art has following advantage:

The blade inlet edge radius of curvature is littler, the trailing edge smooth transition, and the lift-drag ratio of this blade profile is big, and stream field is disturbed Moving little, be easy to the laminar flow section that keeps bigger, viscous friction is little, can effectively avoid flow distortion, greatly improves Dust separation efficient.

Claims (4)

1, a kind of three whirlwind, comprise the blade (5) of managing (1) in the impeller and being located at its outside, it is characterized in that: described blade (5) section shape is an aero-engine leaf grating section shape, the maximum ga(u)ge H of described blade (5) is 8～12% of mean camber line (a 8) arc length, the length place that it is 15～25% the string of a musical instrument (9) apart from costa (2) is located in the maximum ga(u)ge position (10) of described blade (5), and the radius of curvature of the leading edge point (6) of described blade (5) is 1～3% of mean camber line (a 8) arc length.

2, three whirlwind as claimed in claim 1 is characterized in that: the mean camber line (8) of described blade (5) is to the cube curve of tubular axis in the impeller to coordinate with the angle theta of the interior pipe of impeller (1) axis.

θ＝ax ³+bx ²+cx+d＝f(x)

3, three whirlwind as claimed in claim 1 or 2 is characterized in that: the declination angle of the ray 00 of the intersection point A of pipe (1) in the costa (2) of described blade (5) and the costa (2) of crossing blade (5) by the axle center of pipe (1) in the impeller and the impeller ' form is $\mathrm{\φ}=0.5(1/r_1-1/r_2){{\∫}_0}^L\tan \[f\left(x\right)\]\mathrm{dx}$

4, three whirlwind as claimed in claim 1, it is characterized in that: described blade (5) section shape is an aero-engine leaf grating section shape, the maximum ga(u)ge H of described blade (5) is 9% of mean camber line (a 8) arc length, the length place that it is 23% the string of a musical instrument (9) apart from costa (2) is located in the maximum ga(u)ge position (10) of described blade (5), and the radius of curvature of the leading edge point (6) of described blade (5) is 1% of mean camber line (a 8) arc length.

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