CN109667790A - A kind of bionical leading edge blade of INVESTIGATION ON A HIGH SPEED CENTRIFUGAL COMPRESSOR - Google Patents
A kind of bionical leading edge blade of INVESTIGATION ON A HIGH SPEED CENTRIFUGAL COMPRESSOR Download PDFInfo
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- CN109667790A CN109667790A CN201910068078.XA CN201910068078A CN109667790A CN 109667790 A CN109667790 A CN 109667790A CN 201910068078 A CN201910068078 A CN 201910068078A CN 109667790 A CN109667790 A CN 109667790A
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- Prior art keywords
- blade
- leading edge
- ripple
- edge
- suction surface
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Links
- 238000011835 investigation Methods 0.000 title claims abstract description 14
- 241000157234 Asio otus Species 0.000 description 7
- 241000566145 Otus Species 0.000 description 5
- 238000005516 engineering process Methods 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 235000001968 nicotinic acid Nutrition 0.000 description 2
- TVEXGJYMHHTVKP-UHFFFAOYSA-N 6-oxabicyclo[3.2.1]oct-3-en-7-one Chemical compound C1C2C(=O)OC1C=CC2 TVEXGJYMHHTVKP-UHFFFAOYSA-N 0.000 description 1
- 241001456553 Chanodichthys dabryi Species 0.000 description 1
- 208000003618 Intervertebral Disc Displacement Diseases 0.000 description 1
- 230000003321 amplification Effects 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 238000005119 centrifugation Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 238000004134 energy conservation Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 239000011229 interlayer Substances 0.000 description 1
- 230000001788 irregular Effects 0.000 description 1
- 239000010410 layer Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 238000003199 nucleic acid amplification method Methods 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 210000000006 pectoral fin Anatomy 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
- F04D29/30—Vanes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
- F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a kind of bionical leading edge blades of INVESTIGATION ON A HIGH SPEED CENTRIFUGAL COMPRESSOR, it include: suction surface, pressure face, leading edge and trailing edge, the leading edge and the trailing edge are the intersecting lens of the suction surface and the pressure face, the width in the leading edge of the blade to the trailing edge direction is gradually reduced, the blade reverses in three-dimensional space in the leading edge to the trailing edge direction, and the leading edge to the trailing edge windup-degree is gradually increased；The leading edge of the blade is corrugated, and the suction surface of the blade and pressure face leading edge section are corrugated, and undulatory several raised spacing are equal and several heights of projection are equal；The spacing of the undulatory several ripples recess is equal and several ripple cup depths are equal；The present invention solves the problems, such as that aerodynamic quality can not be greatly optimized under the high revolving speed of impeller, by the way that blade is improved to up-front bionical characteristic, enables impeller under high speed rotation, realize greatly improving for working performance.
Description
Technical field
The present invention relates to centrifugal compressor field more particularly to a kind of bionical leading edge blades of INVESTIGATION ON A HIGH SPEED CENTRIFUGAL COMPRESSOR.
Background technique
Usual technology is the oval molded line (long axis and short axle ratio) being arranged at centrifugal compressor blade inlet edge,
Blade inlet edge is integrally of a straight line type, and is not had bionical wing structure, can not further be promoted pressure ratio and big flow efficiency.Other
There is bionics blade configuration in axis stream, low speed blower, but its revolving speed and blade tip flow velocity are below the 1/ of INVESTIGATION ON A HIGH SPEED CENTRIFUGAL COMPRESSOR
10, aerodynamic conditions significant difference, design parameter cannot be borrowed directly, be unable to reach the effect of high revolving speed high efficiency high pressure ratio.
Summary of the invention
The present invention provides a kind of bionical leading edge blade of INVESTIGATION ON A HIGH SPEED CENTRIFUGAL COMPRESSOR, with overcome can not at high speed further
The problem of air dynamic behaviour is greatly optimized.
The present invention includes: suction surface, pressure face, leading edge and trailing edge, the leading edge and the trailing edge be the suction surface and
The width of the intersecting lens of the pressure face, leading edge to the trailing edge direction of the blade is gradually reduced, and the blade is described
It is reversed in three-dimensional space in leading edge to the trailing edge direction, the leading edge to the trailing edge windup-degree is gradually increased；The leaf
It adjacent to the edge section is corrugated, the corrugated that the leading edge of piece, which is corrugated, the suction surface and the pressure face,
If several ripple protrusion spacing are equal and ripple to do height of projection equal；The spacing of undulatory several ripple recess
Equal and several ripple cup depths are equal.
Further, the ripple protrusion of the pressure face of the blade is that the ripple of the suction surface is recessed, the blade
The ripple recess of pressure face is the ripple protrusion of the suction surface.
Further, the pressure face of the blade and the ripple height of projection on suction surface are in the blade inlet edge to leaf
Piece trailing edge direction is gradually reduced.
Further, the ratio between the ripple height of projection d and ripple protrusion distance s are between 0.015~0.030.
The present invention also provides a kind of INVESTIGATION ON A HIGH SPEED CENTRIFUGAL COMPRESSOR impellers, comprising: above-mentioned blade, wheel disc and wheel shaft；The wheel
Axis is megaphone-shaped and inner hollow, and the wheel disc central point is provided with through-hole, and the larger diameter end of the cone of the wheel shaft is hung down
Directly in the wheel disc central point, the wheel shaft is connected to the through-hole, and the wheel disc and the wheel shaft are integrally formed；Multiple institutes
Blade trailing edge is stated towards the wheel disc, more and spaced set is in the wheel shaft side, multiple blades and the wheel shaft one
It is body formed.
The present invention solves the problems, such as that aerodynamic quality can not be greatly optimized under the high revolving speed of impeller, by improving blade
For up-front bionical characteristic, enable impeller under high speed rotation, realizes greatly improving for working performance.
Detailed description of the invention
In order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, below will to embodiment or
Attached drawing needed to be used in the description of the prior art does one and simply introduces, it should be apparent that, the accompanying drawings in the following description is this
Some embodiments of invention, for those of ordinary skill in the art, without any creative labor, also
Other drawings may be obtained according to these drawings without any creative labor.
Fig. 1 is blade construction schematic diagram of the invention；
Fig. 2 is ripple bulge-structure design diagram of the invention；
Fig. 3 is impeller front view of the invention；
Fig. 4 is impeller top view of the invention；
Fig. 5 a is the static pressure ratio curve graph of impeller of the invention；
Fig. 5 b is the overall pressure tatio curve graph of impeller of the invention；
Fig. 5 c is impeller of the invention always to quiet efficiency curve diagram；
Fig. 5 d is impeller of the invention always to total efficiency curve figure.
Specific embodiment
In order to make the object, technical scheme and advantages of the embodiment of the invention clearer, below in conjunction with the embodiment of the present invention
In attached drawing, technical scheme in the embodiment of the invention is clearly and completely described, it is clear that described embodiment is
A part of the embodiment of the present invention, instead of all the embodiments.Based on the embodiments of the present invention, ordinary skill people
Member's every other embodiment obtained without making creative work, shall fall within the protection scope of the present invention.
The present invention be a kind of bionical leading edge blade of INVESTIGATION ON A HIGH SPEED CENTRIFUGAL COMPRESSOR, comprising: suction surface 2, pressure face 1, leading edge 3 and
Trailing edge 4, the leading edge 3 and the trailing edge 4 are the intersecting lens of the suction surface 2 and the pressure face 1, the leading edge 3 of the blade
Width on to 4 direction of trailing edge is gradually reduced, blade three-dimensional space in the leading edge 3 to 4 direction of trailing edge
Interior torsion, the leading edge 3 to 4 windup-degree of trailing edge are gradually increased；The leading edge 3 of the blade is corrugated, the suction
Face 2 and the pressure face 1 section at the leading edge 3 are corrugated, the undulatory raised 5 spacing phases of several ripples
If Deng and dry 5 height of protrusion of ripple it is equal；The spacing of the undulatory several ripples recess 6 is equal and several ripple recess 6
Deep equality.
Further, the ripple protrusion 5 of the pressure face 1 of the blade is recessed for the ripple of the suction surface 2, the leaf
The ripple recess 6 of the pressure face 1 of piece is raised for the ripple of the suction surface 2.
Specifically, the two sides of the blade is respectively suction surface 2 as shown in Figure 1, the blade is generally sickle-shaped
With pressure face 1, the opposite both sides that the pressure face 1 and the suction surface 2 intersect are respectively leading edge 3 and trailing edge 4, the leading edge 3
Wider than the trailing edge 4, distortion rotation, institute is presented in the blade in the leading edge 3 to 4 direction of trailing edge in three-dimensional space
It states blade inlet edge 3 and designs corrugated, the pressure face 1 of the blade and 2 leading edge of suction surface, 3 adjacent place setting corrugated, it is described
The ripple protrusion 5 of pressure face 1 is recessed for the ripple of the suction surface 2, and the ripple recess 6 of the pressure face 1 is the suction
The ripple protrusion in face 2, several ripple protrusions 5 are equidistant and height is identical；Ripple and the pressure in the leading edge 3
Face 1 and be that ripple on suction surface 2 is respectively perpendicular.The undulatory design obtains: compressor impeller is as centrifugal compressor
Core component, gas compressor blade impeller blade be molded in design software (such as BladeGen) directly optimization generate.Research hair
Existing humpback pectoral fin and Asio otus assistant have irregular leading edge structure, i.e. Wing aerofoil leading edge protrusion, directly adjust in BladeGen
Completeblade molded line control point, the direct configuration of blade generates high pressure ratio and efficient impeller blade, as shown in Fig. 2, d is ripple
5 height of protrusion, s are the raised 5 center line distances of two ripples, and the bionical wing leading edge structure of this kind of design considerations is conducive to blade
Pressure on pressure face 1 and suction surface 2 is distributed, and the pressure generated when can rotate blade is dispersed, and is reduced blade and is being revolved
Resistance when turning.
Further, the pressure face 1 of the blade and raised 5 height of ripple on suction surface 2 are in the blade inlet edge 3
It is gradually reduced to 4 direction of blade trailing edge.
Specifically, the pressure face 1 of the blade and raised 5 height of the ripple of suction surface 2 the blade inlet edge 3 to
Trailing edge is gradually reduced on 4 direction, the effect which can be oriented to maelstrom caused by compressed air inlet, into
And the resistance of blade when rotated is effectively reduced, and increase and the pressure on the neighbouring pressure face 1 of blade trailing edge 4, blade pressure
Pressure is bigger higher to air compressed action efficiency on face 1.
Using refinement and topological net technology, guarantee the mesh quality and runner integral grid quality of blade surface, grid
Distribution meets the nearly wall of blade and exit velocity highest point first layer net from gradually being encrypted among blade to wheel hub and casing direction
Lattice Yplus < 1 guarantees under the big Mach number of high speed to be vortex at consideration wall surface to the requirement of Grid Edge interlayer.
Further, the ratio between the ripple 5 height d of protrusion and raised 5 distance s of ripple are between 0.015~0.030.
Specifically, as shown in Fig. 2, meeting based on the requirement of similarity under the conditions of high-speed aerodynamics, i.e. centrifugation is calmed the anger
The ratio between flow velocity and Asio otus flying speed in machine.
For wheel speed n rpm clock, impeller diameter Dmm, then its blade tip linear velocity vImpellerFor
vImpeller=π n*D/60,000 (m/s) (1)
For diameter 50mm impeller, when 150000 revs/min of turn up or more, linear velocity up to 390m/s with
On, for Asio otus highest flying speed 50m/s, speed ratio λvFor,
λv=vImpeller/vAsio otus=7.8 (2)
According to hydromechanics it is similar in newton number definition,
Ne=F/ (ρ L2v2) (3)
In formula, NeFor dimensionless newton number, the field of force F load, ρ fluid density, L geometrical characteristic length, v characteristic velocity.
Impeller is rotated with Asio otus flight condition of similarity
NE impeller=NE Asio otus (4)
Consider that the field of force and atmospheric density permanence condition, geometrical length characteristic parameter ratio are λL=LImpeller/LAsio otus=1/ λv (5)
Therefore, the ratio between the 5 height d of protrusion of impeller and raised 5 distance s LImpeller d/s, with d in Asio otus assistant leading edge structure with
The ratio between s LAsio otus d/sMeet,
LImpeller d/s/LAsio otus d/s=1/ λv (6)
According to the ratio between Asio otus assistant leading edge 5 height d of protrusion in bionics and raised 5 distance s LAsio otus d/sFor 0.12~
0.19, the ripple 5 height d of protrusion and 5 distance s ratio L of ripple protrusion of blade in this exampleImpeller d/sScope of design can be set to 0.015
~0.030.Using assistant leading edge bulge-structure, under conditions of 2 surface pressure distribution of suction surface is constant, increase on pressure face 1
High pressure distributed areas, increase blade to air compressed action ability.
By taking eight blade baby compressor impellers as an example, ripple 5 height d=0.05mm of protrusion, 5 distance s of ripple protrusion=
For 1.8285mm, by above-mentioned calculation method obtain the ratio between raised 5 distance s of ripple 5 height d of protrusion and ripple at this time this
Characteristic parameter is 0.0273.As shown in Fig. 5 a-5d, the compressor pressure ratio of bionical leading edge blade impeller is general for compressor pressure ratio, efficiency
All over being improved, highest increases by 9.89%, and efficiency is also obviously improved when big flow, maximum amplification 8.88%.
The present invention also provides a kind of INVESTIGATION ON A HIGH SPEED CENTRIFUGAL COMPRESSOR impellers, comprising: above-mentioned blade, wheel disc 8 and wheel shaft 7；It is described
Wheel shaft 7 is megaphone-shaped and inner hollow, and 8 central point of wheel disc is provided with through-hole, the cone of the wheel shaft 7 it is big straight
Diameter end is connected to perpendicular to 8 central point of wheel disc, the wheel shaft 7 with the through-hole, the wheel disc 8 and 7 one of wheel shaft at
Type；For multiple blade trailing edges 4 towards the wheel disc 8, the lateral margin face of multiple blades and the side of the wheel shaft 7 are radial
Arc matching, and spaced set is integrally formed in 7 side of wheel shaft, multiple blades and the wheel shaft 7.
Specifically, as shown in Figure 3 and Figure 4, the impeller is by the wheel disc 8, the wheel shaft 7 and multiple above-mentioned has
Undulatory blade is constituted, and the wheel shaft 7 is megaphone-shaped, and the wheel disc 8 is to be provided with through-hole at disk protrusion 5 and center,
The wheel shaft 7 is integrally formed with the wheel disc 8, and the wheel shaft 7 is connected to perpendicular to the wheel disc 8 and with the through-hole；This implementation
Eight equidistant moulding of blade of setting are on the wheel disc 8 and 7 side of the wheel shaft, the tail of multiple blades in example
Edge 4 is towards the wheel disc 8, and the lateral margin spaced set of multiple blades is in table on 7 side of wheel shaft and the wheel disc 8
Face, the multiple blade and the wheel shaft 7 are integrally formed at 27 ° of angles, the multiple blade and the wheel shaft 7；In power
The efficient aspect of device energy conservation, further increases the pressure ratio of small-sized high speed centrifugal compressor, and compressor effect is improved in big flow
Rate.
Finally, it should be noted that the above embodiments are only used to illustrate the technical solution of the present invention., rather than its limitations；
Although present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that: its
It is still possible to modify the technical solutions described in the foregoing embodiments, or special to some or all of technologies
Sign is equivalently replaced；And these are modified or replaceed, various embodiments of the present invention that it does not separate the essence of the corresponding technical solution
The range of technical solution.
Claims (5)
1. a kind of bionical leading edge blade of INVESTIGATION ON A HIGH SPEED CENTRIFUGAL COMPRESSOR characterized by comprising suction surface, pressure face, leading edge and tail
Edge, the leading edge and the trailing edge are the intersecting lens of the suction surface and the pressure face, the leading edge of the blade to the tail
The width in edge direction is gradually reduced, and the blade reverses in three-dimensional space in the leading edge to the trailing edge direction, before described
Edge to the trailing edge windup-degree is gradually increased；The leading edge of the blade is corrugated, and the suction surface and the pressure face are adjacent
The nearly edge section is corrugated, if undulatory several ripple protrusion spacing are equal and ripple does height of projection phase
Deng；The spacing of the undulatory several ripples recess is equal and several ripple cup depths are equal.
2. the bionical leading edge blade of INVESTIGATION ON A HIGH SPEED CENTRIFUGAL COMPRESSOR according to claim 1, which is characterized in that the pressure of the blade
The ripple protrusion in face is that the ripple of the suction surface is recessed, and the ripple recess of the pressure face of the blade is the wave of the suction surface
Line protrusion.
3. the bionical leading edge blade of INVESTIGATION ON A HIGH SPEED CENTRIFUGAL COMPRESSOR according to claim 2, which is characterized in that the pressure of the blade
Ripple height of projection on face and suction surface is gradually reduced in the blade inlet edge to blade trailing edge direction.
4. the bionical leading edge blade of INVESTIGATION ON A HIGH SPEED CENTRIFUGAL COMPRESSOR according to claim 3, which is characterized in that the ripple protrusion is high
The ratio between d and ripple protrusion distance s are spent between 0.015~0.030.
5. a kind of INVESTIGATION ON A HIGH SPEED CENTRIFUGAL COMPRESSOR impeller characterized by comprising blade, wheel disc and wheel shaft as claimed in claim 4；
The wheel shaft is megaphone-shaped and inner hollow, and the wheel disc central point is provided with through-hole, the cone of the wheel shaft it is big straight
Diameter end is connected to perpendicular to the wheel disc central point, the wheel shaft with the through-hole, and the wheel disc and the wheel shaft are integrally formed；It is more
A blade trailing edge is matched towards the wheel disc, the lateral margin face of multiple blades with the side radial strut of the wheel shaft,
And spaced set is integrally formed in the wheel shaft side, multiple blades and the wheel shaft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910068078.XA CN109667790A (en) | 2019-01-24 | 2019-01-24 | A kind of bionical leading edge blade of INVESTIGATION ON A HIGH SPEED CENTRIFUGAL COMPRESSOR |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910068078.XA CN109667790A (en) | 2019-01-24 | 2019-01-24 | A kind of bionical leading edge blade of INVESTIGATION ON A HIGH SPEED CENTRIFUGAL COMPRESSOR |
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| CN201910068078.XA Pending CN109667790A (en) | 2019-01-24 | 2019-01-24 | A kind of bionical leading edge blade of INVESTIGATION ON A HIGH SPEED CENTRIFUGAL COMPRESSOR |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110657127A (en) * | 2019-09-16 | 2020-01-07 | 宁波方太厨具有限公司 | Blade for centrifugal fan impeller, centrifugal fan impeller and range hood |
| CN111079239A (en) * | 2019-12-19 | 2020-04-28 | 中国航空发动机研究院 | Bionic compressor cascade modeling method |
| CN111120400A (en) * | 2019-12-24 | 2020-05-08 | 哈尔滨工程大学 | Centrifugal compressor for micro gas turbine |
| CN113090580A (en) * | 2021-04-16 | 2021-07-09 | 中国科学院工程热物理研究所 | Centrifugal impeller blade with S-shaped front edge and modeling method thereof |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110657127A (en) * | 2019-09-16 | 2020-01-07 | 宁波方太厨具有限公司 | Blade for centrifugal fan impeller, centrifugal fan impeller and range hood |
| CN110657127B (en) * | 2019-09-16 | 2021-11-19 | 宁波方太厨具有限公司 | Blade for centrifugal fan impeller, centrifugal fan impeller and range hood |
| CN111079239A (en) * | 2019-12-19 | 2020-04-28 | 中国航空发动机研究院 | Bionic compressor cascade modeling method |
| CN111120400A (en) * | 2019-12-24 | 2020-05-08 | 哈尔滨工程大学 | Centrifugal compressor for micro gas turbine |
| CN113090580A (en) * | 2021-04-16 | 2021-07-09 | 中国科学院工程热物理研究所 | Centrifugal impeller blade with S-shaped front edge and modeling method thereof |
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