CN105332948B - A kind of implementation method of the bionical movable vane of compressor - Google Patents
A kind of implementation method of the bionical movable vane of compressor Download PDFInfo
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- CN105332948B CN105332948B CN201510697569.2A CN201510697569A CN105332948B CN 105332948 B CN105332948 B CN 105332948B CN 201510697569 A CN201510697569 A CN 201510697569A CN 105332948 B CN105332948 B CN 105332948B
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- leading edge
- camber line
- mean camber
- movable vane
- knot shape
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Abstract
A kind of modified compressor blade and its implementation, the movable vane blade include：Leading edge and trailing edge, the a height of H of leading edge leaf, waveform knot shape raised structures are provided with the top of leading edge, the curve form of waveform knot shape raised structures is cubic spline curve, its each crest is different with the amplitude of trough, and described waveform knot shape raised structures are arranged at the top of leading edge in the range of 0.76H~H, and each wave amplitude put is A on curve, the corresponding a length of L of benchmark mean camber line of each point, wherein 0<A≤0.05L, wavelength is W, wherein 0<W≤0.1H, the present invention sets the waveform knot shape projection of certain wave amplitude and wavelength in movable vane leading edge top area, utilizes its low-resistance characteristic according to the design feature of humpback flipper leading edge knot shape projection, the flow losses of bucket tip region are reduced, Capability of Compressor is improved.
Description
Technical field
It is specifically a kind of to reduce the modified gas compressor blade of loss the present invention relates to a kind of technology in compressor field
Piece and its implementation.
Background technology
Modern aeroengine requires that compressor has higher airload and less series.Designed in compressor
Cheng Zhong, the raising of pneumatic load of blades is usually associated with compressor loss raising, and secondary flow phenomenon (such as leaf of compressor
Top leakage flow) loss of regional area can be caused to increase.Capability of Compressor can be greatly reduced in excessive loss, cause very not
The consequence of profit.Therefore, reduction loss is to develop the vital task during high performance gas-turbine engine.
The method of loss is reduced in compressor design can be divided into two major classes of active control and passive control.Compared to actively
Control, passive control technology design structure is simple, is also easily realized in aero-engine, therefore passive control technology is able to
It is widely used in compressor design.In many passive control technologies, a kind of effective flow control technique when blade is retrofited,
In terms of flexural tensile elastic modulus moulding, local geometric modification, it is easily achieved, and reliability is also higher, has been widely used in pressure
Mechanism of qi is designed.
The passive flow control technique of blade remodeling can combine bionics principle.The flipper of marine organisms humpback has
The mobility of height and good hydrodynamic characterisitic, are mainly due to the gongylodont knot shape projection of leading edge.Knot shape projection can be answered
For gas compressor moving blade leading edge top area, so as to form a kind of new bionical movable vane, there can be leaf to movable vane top area
The larger situation of the flow losses that cause of top leakage flow, plays a role in improving.
By the retrieval discovery to prior art, Chinese patent literature CN104612758A, publication date is May 13 in 2015
Day, a kind of low-pressure turbine blade of low loss is disclosed, it is that along the high direction of leaf original low-pressure turbine blade is divided into blade root
Petiolarea, blade tip petiolarea and two-dimensional flow area, while leading edge portion is formed multiple sawtooth in the enterprising traveling wave shape wave cutting of its leading edge,
And the lengthening of 3% axial chord length is carried out to original low-pressure turbine blade, to make up the decline of leaf acting ability after cutting, this prolongs
Length in blade fairy fox leading edge point along mean camber line direction by carrying out, and its low-pressure turbine blade for providing low loss is to original low
Pressure turbo blade leading edge carries out the improvement that is hungry, it is therefore an objective to reduce high Re state waves while original suppression two-dimensional flow area separation
The extraneoas loss that shape wave leading edge is caused, improves the scope of application of this passive control program, and allows this control program right
Petiolarea three-dimensional separation is effectively controlled.But the device only considers loss problem in low-pressure turbine environment, it is impossible to solve
Situation under gas compressor moving blade environment, and the device only have studied the chord length of circular turbo blade and keeps constant feelings along leaf height
Condition, the blade scene different situation high to different leaves is not illustrated.
Chinese patent literature CN202391808U, publication date is August in 2012 22, discloses a kind of low noise axial stream wind
Wheel, including multiple blades being arranged on wheel hub, multiple blades centered on the center of rotation axis of wind wheel equidistantly or not
It is distributed at equal intervals on wheel hub, it is characterised in that blade inlet edge interlude is shaped as smooth waveform space curve.But
The device only considers noise problem in axial-flow windwheel environment, does not solve the problems, such as the loss under gas compressor moving blade environment.
The content of the invention
The present invention is directed to deficiencies of the prior art, proposes a kind of modified compressor blade and its realization side
Method, bionics principle and the passive flow control technique of blade remodeling is combined, by gas compressor moving blade leading edge top area
Using bionics knot shape raised structures, so as to significantly reduce flow losses, the high performance demand for development of turbomachine is met.
The present invention is achieved by the following technical solutions：
The present invention relates to a kind of modified compressor blade, including：Leading edge and trailing edge, wherein：Wave is provided with the top of leading edge
Shape knot shape raised structures, the curve form of the waveform knot shape raised structures is cubic spline curve, its each crest and ripple
The amplitude of paddy is different.
Described cubic spline curve, is obtained in the following manner：A segmentation, a=x are given on interval [a, b]0<x1
<...<xn-1<xnFunction F (x) on=b, the interval, i.e. cubic spline curve meet following condition：In each minizone
[xi-1,xi] (i=1,2 ..., n) in F (x) be cubic polynomial function respectively；In node xi(i=1,2 ..., n) place, F(k)
(xi- 0)=F(k)(xi+ 0), (k=0,1,2), i.e., the cubic polynomial function on minizone is in node xiLocate Second Order Continuous；Node
(xi,yi) meet condition yi=F (xi) (i=1,2 ..., n).
The a height of H of described leading edge, waveform knot shape raised structures are arranged at the top of leading edge in the range of 0.76H~H.
Wave amplitude on the curve of described waveform knot shape raised structures at crest or trough is A, corresponding to the position
The a length of L of benchmark mean camber line, wherein 0<A≤0.05L.
The a length of W of curve ripple of described waveform knot shape raised structures, wherein 0<W≤0.1H.
The present invention relates to the implementation method of above-mentioned modified compressor blade, comprise the following steps：
1) parametric modeling is carried out to prototype movable vane, determines that the folded mode of blade radial product is folded for trailing edge product, that is, ensure imitative
The curve of the trailing edge of lively leaf keeps constant with prototype movable vane；
2) using the mean camber line of prototype movable vane as benchmark mean camber line, defined according to mean camber line：With the pressure face camber line of blade profile
With the public circle of contact deferent of suction surface tangential, the benchmark mean camber line of the high section blade profile of the different leaves of prototype movable vane, meter are obtained
The size that calculation obtains benchmark mean camber line a length of L, L changes with the high H of leading edge leaf change；
3) waveform knot shape raised structures are introduced in the leading edge locus of movable vane top area, i.e., in specified leaf high scope
It is interior, wave crest point, trough point and the chord length invariant point of all undaform knot shape raised structures in leading edge are chosen as node, using three
These points are connected by secondary SPL, it is ensured that leading edge point line Second Order Continuous of the movable vane in the leaf high scope, i.e. its curvature are
Continuously；
4) curve of the waveform knot shape projection is determined that wave amplitude size is with benchmark mean camber line L's by wave amplitude A and wavelength W
Percentage is weighed, and wavelength size is with prototype movable vane leading edge datum line and the radial distance of two end wall profile intersection points, i.e. leading edge
The high H of leaf percentage is weighed；
5) according to step 4) in wave amplitude, the benchmark mean camber line of nearby rim segment obtains a length of (L+ of mean camber line at extension crest
A nearby the benchmark mean camber line of rim segment obtains mean camber line a length of (L-A) remodeling blade profile at remodeling blade profile), shortening trough；
6) according to step 4) in wavelength, determine benchmark mean camber line of at each crest and trough place in the high position of leaf
It is long, by way of extending the benchmark mean camber line of nearby rim segment at crest and shortening at trough the nearby benchmark mean camber line of rim segment
Blade profile of retrofiting is obtained, by step 1) in the product that determines fold the mode blade profile high to different leaves and carry out footpath vector product and fold, obtain bionical dynamic
Leaf.
Described step 5) in, the long L of the different benchmark mean camber lines of crest and wave trough position is differed.
Technique effect
Compared with prior art, the design feature of the invention according to humpback flipper leading edge knot shape projection, before movable vane
Edge top area sets the waveform knot shape raised structures of certain wave amplitude and wavelength, using its low-resistance characteristic, reduces blade top
The flow losses in portion region.
Brief description of the drawings
Fig. 1 is prototype movable vane schematic diagram；
Fig. 2 is bionical movable vane schematic diagram；
Fig. 3 is bionical movable vane meridian plane schematic diagram；
Fig. 4 is schematic cross-section at bionical movable vane radial direction crest；
In figure：1 leading edge；2 trailing edges；3 leaf tops；4 blade roots；5 waveform knot shape raised structures；6 casings；7 nave bosses；In 8 benchmark
Camber line.
Embodiment
Embodiments of the invention are elaborated below, the present embodiment is carried out lower premised on technical solution of the present invention
Implement, give detailed embodiment and specific operating process, but protection scope of the present invention is not limited to following implementations
Example.
Embodiment 1
Modified compressor blade is accomplished by the following way in the present embodiment：
1) parametric modeling is carried out to prototype movable vane as shown in Figure 1, the prototype movable vane includes：Leading edge 1, trailing edge 2, leaf
Top 3 and blade root 4, determine that the folded mode of blade radial product is folded for trailing edge product, that is, ensure the curve and prototype of the trailing edge 2 of bionical movable vane
Movable vane keeps constant；
2) defined according to mean camber line：With the pressure face camber line and the public circle of contact deferent of suction surface tangential of blade profile,
The benchmark mean camber line of the high section blade profile of the different leaves of prototype movable vane is obtained, calculating obtains a length of L of benchmark mean camber line, and L size is with preceding
The high H of edge leaf change and change；
3) waveform knot shape raised structures are introduced in the leading edge locus of movable vane top area, i.e., in specified leaf high scope
It is interior, wave crest point, trough point and the chord length invariant point of all undaform knot shape raised structures in leading edge 1 are chosen as node, are used
These points are connected by cubic spline curve, it is ensured that leading edge point line Second Order Continuous of the movable vane in the leaf high scope, i.e. its curvature
It is continuous；
4) waveform knot shape raised structures determine that wave amplitude size is with the long L of benchmark mean camber line by the wave amplitude A and wavelength W of curve
Percentage weigh, value is typically in the range of 0~0.05L, and wavelength size is held with prototype movable vane leading edge datum line and two
The radial distance H (leading edge leaf high) of wall-shaped line intersection point percentage is weighed, and value is typically in the range of 0~0.1H；
5) according to step 4) in wave amplitude, the benchmark mean camber line of nearby rim segment obtains a length of (L+ of mean camber line at extension crest
A nearby the benchmark mean camber line of rim segment obtains mean camber line a length of (L-A) remodeling blade profile at remodeling blade profile), shortening trough；
Step 5) it should be noted that because prototype movable vane is different in the high position blade profile of different leaves, so different ripples
The benchmark mean camber line L length of peak and wave trough position is differed；
6) according to the wavelength in step 4, determine that benchmark mean camber line of at each crest and trough place in the high position of leaf is long
L, extending the benchmark mean camber line of nearby rim segment at crest and shortening at trough nearby by way of the benchmark mean camber line of rim segment
Blade profile of retrofiting is obtained, by step 1) in the product that determines fold the mode blade profile high to different leaves and carry out footpath vector product and fold, obtain bionical dynamic
Leaf.
As shown in Fig. 2 being the setting waveform knot shape projection knot realized according to the above method on the basis of prototype movable vane
The modified compressor blade of structure 5, the waveform knot shape raised structures 5 are arranged at the top of leading edge 1 of modified compressor blade.
As shown in figure 3, described bionic blade is located between casing 6 and nave boss 7, a height of H of its leading edge 1, bionical movable vane
Waveform knot shape raised structures 5 are distributed between 0.76H~H, and the waveform knot shape raised structures are in a cyclically-varying
Waveform curve, and for cubic spline curve, curve Second Order Continuous.
As shown in figure 4, the described wavelength of waveform knot shape raised structures 5 is W, wave amplitude is A, and the mean camber line of prototype blade is
The benchmark mean camber line of bionical movable vane, a length of L changes with H change.Wave amplitude A is taken as 0.03L, and wavelength W is taken as 0.08H, described
Waveform knot shape raised structures 5 contain 3 cycles.
A length of 1.03 times of benchmark mean camber lines 8 length of mean camber line at described bionical movable vane crest, i.e. 1.03L, accordingly
Mean camber line length is 0.97L at trough.Three crests are located at leading edge 0.82H, 0.92H and 0.98H, and three troughs are located at
At 0.78H, 0.86H and 0.94H, due to the benchmark mean camber line L of the bionical movable vane, so the wave amplitude at crest and trough
It is each unequal.
Folded mode is accumulated according to trailing edge to fold the high blade profile footpath vector product of each leaf, obtains the bionical movable vane.
The modified compressor blade of the present invention is of the invention according to humpback flipper leading edge knot shape compared with prior art
The design feature of projection, the waveform knot shape raised structures of certain wave amplitude and wavelength are set in movable vane leading edge top area, are utilized
Its low-resistance characteristic, reduces the flow losses of bucket tip region, 5% is reduced with respect to total pressure loss coefficient.
Embodiment 2
The difference of the present embodiment compared with Example 1 is：
Described wave amplitude A takes 0.05L, wavelength W to be taken as 0.1H.
It can be obtained through numerical computations, the modified compressor blade of the value causes relative total pressure loss coefficient to reduce 3%,
The flow losses of bucket tip region are reduced, so as to improve Capability of Compressor.
Claims (5)
1. a kind of implementation method of the bionical movable vane of compressor, it is characterised in that the bionical movable vane of the compressor includes：Leading edge and tail
Edge, wherein：Waveform knot shape raised structures are provided with the top of leading edge, the curve form of the waveform knot shape raised structures is three samples
Bar curve, its each crest is different with the amplitude of trough；
Described cubic spline curve, is obtained in the following manner：A segmentation, a=x are given on interval [a, b]0＜ x1
＜ ... ＜ xn-1＜ xnFunction F (x) on=b, the interval, i.e. cubic spline curve meet following condition：In each minizone
[xi-1,xi] (i=1,2 ... n) interior F (x) is cubic polynomial function respectively；In node xi(i=1,2 ..., n) place, F(k)
(xi- 0)=F(k)(xi+ 0), (k=0,1,2), i.e., the cubic polynomial function on minizone is in node xiLocate Second Order Continuous；Node
(xi,yi) meet condition yi=F (xi) (i=1,2 ..., n)；
Described implementation method, its step includes：
1) parametric modeling is carried out to prototype movable vane, determines that the folded mode of blade radial product is folded for trailing edge product, that is, ensure bionical dynamic
The curve of the trailing edge of leaf keeps constant with prototype movable vane；
2) using the mean camber line of prototype movable vane as benchmark mean camber line, defined according to mean camber line：With the pressure face camber line of blade profile and suction
The public circle of contact deferent of power face tangential, obtains the benchmark mean camber line of the high section blade profile of the different leaves of prototype movable vane, calculates
To a length of L of benchmark mean camber line, L size changes with the high H of leading edge leaf change；
3) waveform knot shape raised structures are introduced in the leading edge locus of movable vane top area, i.e., in specified leaf high scope, choosing
Take in leading edge that the wave crest point of all undaform knot shape raised structures, trough point and chord length invariant point are as node, using three samples
These points are connected by bar curve, it is ensured that leading edge point line Second Order Continuous of the movable vane in the leaf high scope, i.e. its curvature are continuous
's；
4) curve of the waveform knot shape projection determines that wave amplitude size is with benchmark mean camber line L percentage by wave amplitude A and wavelength W
Than weighing, wavelength size is with prototype movable vane leading edge datum line and the radial distance of two end wall profile intersection points, the i.e. high H of leading edge leaf
Percentage weigh；
5) according to step 4) in wave amplitude, the benchmark mean camber line of nearby rim segment obtains mean camber line a length of (L+A) at extension crest
Nearby the benchmark mean camber line of rim segment obtains mean camber line a length of (L-A) remodeling blade profile at remodeling blade profile, shortening trough；
6) according to step 4) in wavelength, determine that benchmark mean camber line of at each crest and trough place in the high position of leaf is long, lead to
Cross at extension crest the nearby benchmark mean camber line of rim segment and shorten the mode of the nearby benchmark mean camber line of rim segment at trough and obtain
Retrofit blade profile, by step 1) in the product that determines fold the mode blade profile high to different leaves and carry out footpath vector product and fold, obtain bionical movable vane.
2. implementation method according to claim 1, it is characterized in that, a height of H of described leading edge, waveform knot shape raised structures
It is arranged at the top of leading edge in the range of 0.76H~H.
3. implementation method according to claim 2, it is characterized in that, the curve upper ripple of described waveform knot shape raised structures
Wave amplitude at peak or trough is A, a length of L of benchmark mean camber line corresponding to the position, wherein 0 ＜ A≤0.05L.
4. implementation method according to claim 3, it is characterized in that, the curve wavelength of described waveform knot shape raised structures
For W, wherein 0 ＜ W≤0.1H.
5. implementation method according to claim 1, it is characterized in that, described step 5) in, different crests and trough position
The long L of benchmark mean camber line put is differed.
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Families Citing this family (9)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106156436B (en) * | 2016-07-12 | 2019-07-19 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of compressor modeling method of blade angle-adjustable classification regulation |
| CN106250644B (en) * | 2016-08-05 | 2019-05-28 | 上海交通大学 | Dual arc blade profile compressor blade implementation method |
| EP3361049A1 (en) * | 2017-02-10 | 2018-08-15 | Siemens Aktiengesellschaft | Method for modifying a turbine |
| FR3087482B1 (en) * | 2018-10-18 | 2021-12-17 | Safran Aircraft Engines | PROFILED STRUCTURE FOR AIRCRAFT OR TURBOMACHINE |
| CN110821851B (en) * | 2019-11-22 | 2021-03-09 | 南京航空航天大学 | Multistage axial compressor expands steady structure based on sawtooth trailing edge blade |
| CN111079239B (en) * | 2019-12-19 | 2023-07-21 | 中国航空发动机研究院 | Bionic compressor blade grid modeling method |
| CN111622808B (en) * | 2020-05-25 | 2021-05-04 | 武汉大学 | Bionic blade based on steam turbine blade profile transformation and design method |
| CN113553671B (en) * | 2021-07-08 | 2022-07-08 | 浙江大学 | Bionic anti-cavitation axial flow impeller design method |
| CN114593088B (en) * | 2022-03-21 | 2024-03-26 | 西安热工研究院有限公司 | improved design method for capacity-expansion transformation of movable blade of adjustable axial flow fan of power station movable blade |
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| CN202391808U (en) * | 2011-12-13 | 2012-08-22 | 广东美的电器股份有限公司 | Low-noise axial flow air wheel |
| CN104302926A (en) * | 2012-03-06 | 2015-01-21 | 施乐百欧洲公司 | Axial fan |
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| DE19812624A1 (en) * | 1998-03-23 | 1999-09-30 | Bmw Rolls Royce Gmbh | Rotor blade of an axial flow machine |
| DE502004009528D1 (en) * | 2004-06-02 | 2009-07-09 | Rolls Royce Deutschland | Compressor blade with reduced aerodynamic blade excitation |
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| CN202391808U (en) * | 2011-12-13 | 2012-08-22 | 广东美的电器股份有限公司 | Low-noise axial flow air wheel |
| CN104302926A (en) * | 2012-03-06 | 2015-01-21 | 施乐百欧洲公司 | Axial fan |
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