CN105332948A - Improved compressor blade and achieving method thereof - Google Patents
Improved compressor blade and achieving method thereof Download PDFInfo
- Publication number
- CN105332948A CN105332948A CN201510697569.2A CN201510697569A CN105332948A CN 105332948 A CN105332948 A CN 105332948A CN 201510697569 A CN201510697569 A CN 201510697569A CN 105332948 A CN105332948 A CN 105332948A
- Authority
- CN
- China
- Prior art keywords
- camber line
- leading edge
- mean camber
- movable vane
- blade
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000000034 method Methods 0.000 title claims abstract description 14
- 238000007634 remodeling Methods 0.000 claims description 7
- 238000004904 shortening Methods 0.000 claims description 6
- 230000011218 segmentation Effects 0.000 claims description 2
- 241001059810 Cantharellula umbonata Species 0.000 abstract 1
- 230000007423 decrease Effects 0.000 description 5
- 238000005516 engineering process Methods 0.000 description 4
- 241001456553 Chanodichthys dabryi Species 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 235000001968 nicotinic acid Nutrition 0.000 description 3
- 238000012938 design process Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 239000011664 nicotinic acid Substances 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 230000001629 suppression 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
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/38—Blades
- F04D29/384—Blades characterised by form
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D2240/303—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the leading edge of a rotor blade
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/10—Two-dimensional
- F05D2250/18—Two-dimensional patterned
- F05D2250/183—Two-dimensional patterned zigzag
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses an improved compressor blade and an achieving method thereof. A movable blade body comprises a front edge and a tail edge. The leaf height of the front edge is H, and a corrugated knotted protrusion structure is arranged on the top of the front edge. The curve form of the corrugated knotted protrusion structure is a cubic spline curve, and amplitudes of crests and troughs of the corrugated knotted protrusion structure are different. The corrugated knotted protrusion structure is arranged on the top of the front edge within the range of 0.76 H-H. The wave amplitude of points on the curve is A, and the length of a benchmark mean camber line corresponding to the points is L, wherein A is larger than 0 and smaller than or equal to 0.05 L, the wavelength is W, and the W is larger than 0 and smaller than or equal to 0.1 H. According to the structural characteristic of front edge knotted protrusions of the flipper of the humpback, corrugated knotted protrusions with a certain wave amplitude and wavelength are arranged on the top area of the front edge of the movable blade body, the low resistance characteristic of the corrugated knotted protrusions is utilized, the flow loss on the top area of the blade is reduced, and the performance of a compressor is improved.
Description
Technical field
What the present invention relates to is a kind of technology of gas compressor field, specifically a kind of modified model compressor blade and its implementation reducing loss.
Background technique
Modern aeroengine requires that gas compressor has higher airload and less progression.In gas compressor design process, the raising of pneumatic load of blades often improves along with gas compressor loss, and the secondary flow phenomenon of gas compressor (as blade-tip leakage flow moves) can cause the loss of regional area to increase.Excessive loss significantly can reduce Capability of Compressor, causes very disadvantageous consequence.Therefore, reducing loss is develop the vital task in high performance gas-turbine engine process.
The method reducing loss in gas compressor design can be divided into ACTIVE CONTROL and the large class of Passive Control two.Compared to ACTIVE CONTROL, Passive Control Technology design structure is simple, also easily realizes in aeroengine, and therefore Passive Control technology is able to be widely used in gas compressor design.In many Passive Control technology, during blade remodeling, a kind of effective flow control technique, comprises the aspect such as flexural tensile elastic modulus moulding, local geometric amendment, and it is easy to realize, and reliability is also higher, has been widely used in gas compressor design.
Blade retrofits passive flow control technique can in conjunction with bionics principle.The flipper of marine organisms humpback has the mobility of height and good hydrodynamic characterisitic, mainly owing to the gongylodont knot shape projection of leading edge.Knot shape projection can be applied to gas compressor moving blade leading edge top area, thus forms a kind of novel bionical movable vane, the situation that the flow losses that blade-tip leakage flow can be had to move cause to movable vane top area are larger, plays a role in improving.
Through finding the retrieval of prior art, Chinese patent literature CN104612758A, publication date is on May 13rd, 2015, disclose a kind of low-pressure turbine blade of low loss, it is that original low-pressure turbine blade is divided into blade root petiolarea along leaf height direction, blade tip petiolarea and two-dimensional flow district, in its leading edge, carry out waveform cutting makes leading edge portion form multiple sawtooth simultaneously, and original low-pressure turbine blade is carried out to the lengthening of 3% axial chord length, to make up the decline of the rear leaf acting ability of cutting, this extends through and carries out along mean camber line direction in blade fairy fox leading edge point, it provides the low-pressure turbine blade of low loss to be to be hungry improvement to original low-pressure turbine blade leading edge, object be original suppression two-dimensional flow distinguish from while reduce the extraneoas loss that high Re state wave-shaped front edge causes, improve the Applicable scope of this Passive Control scheme, and this control program effectively can be controlled the separation of petiolarea three-dimensional.But this device only considers loss problem in low-pressure turbine environment, the situation under gas compressor moving blade environment cannot be solved, and this device only have studied the chord length of circular turbine blade along the high situation about remaining unchanged of leaf, the on-the-spot different situation of the blade that different leaf is high is set forth.
Chinese patent literature CN202391808U, publication date is on August 22nd, 2012, disclose a kind of low noise axial-flow windwheel, comprise the multiple blades be arranged on wheel hub, multiple blade centered by the rotating center axis of wind wheel equidistantly or unequal-interval be distributed on wheel hub, it is characterized in that the shape of blade inlet edge intermediate section is level and smooth waveform space curve.But this device only considers noise problem in axial-flow windwheel environment, do not solve the loss problem under gas compressor moving blade environment.
Summary of the invention
The present invention is directed to prior art above shortcomings, a kind of modified model compressor blade and its implementation are proposed, passive flow control technique of bionics principle and blade being retrofited combines, by tying shape raised structures at gas compressor moving blade leading edge top area application bionics, thus significantly reduce flow losses, meet the high performance demand for development of turbomachine.
The present invention is achieved by the following technical solutions:
The present invention relates to a kind of modified model compressor blade, comprise: leading edge and trailing edge, wherein: leading edge top is provided with waveform knot shape raised structures, the curve form of described waveform knot shape raised structures is cubic spline curve, and its each crest is different with the amplitude of trough.
Described cubic spline curve, obtains in the following manner: in interval [a, a b] upper given segmentation, a=x
0<x
1<...<x
n-1<x
n=b, the function F (x) on this interval, namely cubic spline curve meets following condition: at each minizone [x
i-1, x
i] (i=1,2 ..., n), F (x) is cubic polynomial function respectively; At node x
i(i=1,2 ..., n) place, F
(k)(x
i-0)=F
(k)(x
i+ 0), (k=0,1,2), the cubic polynomial function namely on minizone is at node x
iplace's Second Order Continuous; Node (x
i, y
i) satisfy condition y
i=F (x
i) (i=1,2 ..., n).
Described leading edge height is H, and waveform knot shape raised structures is arranged within the scope of the 0.76H ~ H of leading edge top.
On the curve of described waveform knot shape raised structures, the wave amplitude at crest or trough place is A, and the benchmark mean camber line corresponding to this position is long is L, wherein 0<A≤0.05L.
The curve wavelength of described waveform knot shape raised structures is W, wherein 0<W≤0.1H.
The present invention relates to the implementation method of above-mentioned modified model compressor blade, comprise the following steps:
1) carry out parametric modeling to prototype movable vane, determining that blade radial amasss folded mode is that trailing edge is long-pending folded, namely ensures that the curve of the trailing edge of bionical movable vane and prototype movable vane remain unchanged;
2) using the mean camber line of prototype movable vane as benchmark mean camber line, define according to mean camber line: with the pressure side camber line of blade profile and the public circle of contact deferent of suction surface tangential, obtain the benchmark mean camber line of prototype movable vane different leaf height cross sections blade profile, calculate the long size for L, L of benchmark mean camber line to change with the change of leading edge leaf height H;
3) waveform knot shape raised structures is introduced at the leading edge locus of movable vane top area, namely within the scope of the leaf height of specifying, choose the wave crest point of all wave-like type knot shape raised structures in leading edge, trough point and chord length invariant point as node, cubic spline curve is adopted to be connected by these points, ensure the leading edge point line Second Order Continuous of movable vane within the scope of this leaf height, namely its curvature is continuous print;
4) curve of described waveform knot shape projection is determined by wave amplitude A and wavelength W, wave amplitude size is weighed with the percentage of benchmark mean camber line L, wavelength size is with the radial distance of prototype movable vane leading edge reference line and two end wall profile intersection points, and namely the percentage of leading edge leaf height H is weighed;
5) according to step 4) in wave amplitude, the benchmark mean camber line extending the nearly leading edge segments in crest place obtains the long remodeling blade profile for (L+A) of mean camber line, and the benchmark mean camber line shortening the nearly leading edge segments in trough place obtains the long remodeling blade profile for (L ?A) of mean camber line;
6) according to step 4) in wavelength, determine that each crest place and trough place are long at the benchmark mean camber line of leaf high position, blade profile of retrofiting is obtained by the mode of the benchmark mean camber line extending the nearly leading edge segments of benchmark mean camber line and shortening trough place of the nearly leading edge segments in crest place, by step 1) in the long-pending folded mode the determined blade profile high to different leaf carry out footpath vector product and fold, obtain bionical movable vane.
Described step 5) in, different crests is not identical with the long L of benchmark mean camber line of wave trough position.
Technique effect
Compared with prior art, the present invention is according to the structural feature of humpback flipper leading edge knot shape projection, the waveform knot shape raised structures of certain wave amplitude and wavelength is set in movable vane leading edge top area, utilizes its low-resistance characteristic, decrease the flow losses in vane tip region.
Accompanying drawing explanation
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 bionical movable vane radial crest place schematic cross-section;
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; 8 benchmark mean camber lines.
Embodiment
Elaborate to embodiments of the invention below, the present embodiment is implemented under premised on technical solution of the present invention, give detailed mode of execution and concrete operating process, but protection scope of the present invention is not limited to following embodiment.
Embodiment 1
The present embodiment realizes modified model compressor blade in the following manner:
1) parametric modeling is carried out to prototype movable vane as shown in Figure 1, described prototype movable vane comprises: leading edge 1, trailing edge 2, leaf top 3 and blade root 4, determining that blade radial amasss folded mode is that trailing edge is long-pending folded, namely ensures that the curve of the trailing edge 2 of bionical movable vane and prototype movable vane remain unchanged;
2) define according to mean camber line: with the pressure side camber line of blade profile and the public circle of contact deferent of suction surface tangential, obtain the benchmark mean camber line of prototype movable vane different leaf height cross sections blade profile, calculate the long size for L, L of benchmark mean camber line to change with the change of leading edge leaf height H;
3) waveform knot shape raised structures is introduced at the leading edge locus of movable vane top area, namely within the scope of the leaf height of specifying, choose the wave crest point of all wave-like type knot shape raised structures in leading edge 1, trough point and chord length invariant point as node, cubic spline curve is adopted to be connected by these points, ensure the leading edge point line Second Order Continuous of movable vane within the scope of this leaf height, namely its curvature is continuous print;
4) waveform knot shape raised structures is determined by the wave amplitude A of curve and wavelength W, wave amplitude size is weighed with the percentage of the long L of benchmark mean camber line, value is generally within the scope of 0 ~ 0.05L, wavelength size is weighed with the percentage of the radial distance H (leading edge leaf is high) of prototype movable vane leading edge reference line and two end wall profile intersection points, and value is generally in the scope of 0 ~ 0.1H;
5) according to step 4) in wave amplitude, the benchmark mean camber line extending the nearly leading edge segments in crest place obtains the long remodeling blade profile for (L+A) of mean camber line, and the benchmark mean camber line shortening the nearly leading edge segments in trough place obtains the long remodeling blade profile for (L ?A) of mean camber line;
Step 5) it should be noted that because prototype movable vane is different in different leaf high positions blade profile, so different crest is not identical with the benchmark mean camber line L length of wave trough position;
6) according to the wavelength in step 4, determine each crest place and the benchmark mean camber line long L of trough place in leaf high position, blade profile of retrofiting is obtained by the mode of the benchmark mean camber line extending the nearly leading edge segments of benchmark mean camber line and shortening trough place of the nearly leading edge segments in crest place, by step 1) in the long-pending folded mode the determined blade profile high to different leaf carry out footpath vector product and fold, obtain bionical movable vane.
As shown in Figure 2, on the basis of prototype movable vane, according to the modified model compressor blade arranging waveform knot shape raised structures 5 that said method realizes, this waveform knot shape raised structures 5 is arranged at leading edge 1 top of modified model compressor blade.
As shown in Figure 3, described bionic blade is between casing 6 and nave boss 7, its leading edge 1 height is H, the waveform knot shape raised structures 5 of bionical movable vane is distributed between 0.76H ~ H, described waveform knot shape raised structures is a periodically variable waveform curve, and be cubic spline curve, curve Second Order Continuous.
As shown in Figure 4, described waveform knot shape raised structures 5 wavelength is W, and wave amplitude is A, and the mean camber line of prototype blade is the benchmark mean camber line of bionical movable vane, and long is L, changes with the change of H.Wave amplitude A is taken as 0.03L, and wavelength W is taken as 0.08H, and described waveform knot shape raised structures 5 contains 3 cycles.
The mean camber line length at described bionical movable vane crest place is 1.03 times of benchmark mean camber line 8 length, i.e. 1.03L, corresponding trough place mean camber line length is 0.97L.Three crests are positioned at leading edge 0.82H, 0.92H and 0.98H place, and three troughs are positioned at 0.78H, 0.86H and 0.94H place, due to described bionical movable vane benchmark mean camber line L not etc., so the wave amplitude at crest and trough place is each unequal.
Amass folded mode according to trailing edge to fold each leaf high blade profile footpath vector product, obtain described bionical movable vane.
Modified model compressor blade of the present invention compared with prior art the present invention ties the structural feature of shape projection according to humpback flipper leading edge, the waveform knot shape raised structures of certain wave amplitude and wavelength is set in movable vane leading edge top area, utilize its low-resistance characteristic, decrease the flow losses in vane tip region, relative total pressure loss coefficient decreases 5%.
Embodiment 2
The difference of the present embodiment compared with embodiment 1 is:
Described wave amplitude A gets 0.05L, and wavelength W is taken as 0.1H.
Can obtain through numerical calculation, the modified model compressor blade of this value makes relative total pressure loss coefficient decrease 3%, reduces the flow losses in vane tip region, thus improves Capability of Compressor.
Claims (6)
1. a modified model compressor blade, it is characterized in that, comprising: leading edge and trailing edge, wherein: leading edge top is provided with waveform knot shape raised structures, the curve form of this waveform knot shape raised structures is cubic spline curve, and its each crest is different with the amplitude of trough;
Described cubic spline curve, obtains in the following manner: in interval [a, a b] upper given segmentation, a=x
0<x
1<...<x
n-1<x
n=b, the function F (x) on this interval, namely cubic spline curve meets following condition: at each minizone [x
i-1, x
i] (i=1,2 ..., n), F (x) is cubic polynomial function respectively; At node x
i(i=1,2 ..., n) place, F
(k)(x
i-0)=F
(k)(x
i+ 0), (k=0,1,2), the cubic polynomial function namely on minizone is at node x
iplace's Second Order Continuous; Node (x
i, y
i) satisfy condition y
i=F (x
i) (i=1,2 ..., n).
2. modified model compressor blade according to claim 1, is characterized in that, described leading edge height is H, and waveform knot shape raised structures is arranged within the scope of the 0.76H ~ H of leading edge top.
3. modified model compressor blade according to claim 2, it is characterized in that, on the curve of described waveform knot shape raised structures, the wave amplitude at crest or trough place is A, and the benchmark mean camber line corresponding to this position is long is L, wherein 0<A≤0.05L.
4. modified model compressor blade according to claim 3, is characterized in that, the curve wavelength of described waveform knot shape raised structures is W, wherein 0<W≤0.1H.
5. the implementation method of modified model compressor blade according to above-mentioned arbitrary claim, is characterized in that, comprise the following steps:
1) carry out parametric modeling to prototype movable vane, determining that blade radial amasss folded mode is that trailing edge is long-pending folded, namely ensures that the curve of the trailing edge of bionical movable vane and prototype movable vane remain unchanged;
2) using the mean camber line of prototype movable vane as benchmark mean camber line, define according to mean camber line: with the pressure side camber line of blade profile and the public circle of contact deferent of suction surface tangential, obtain the benchmark mean camber line of prototype movable vane different leaf height cross sections blade profile, calculate the long size for L, L of benchmark mean camber line to change with the change of leading edge leaf height H;
3) waveform knot shape raised structures is introduced at the leading edge locus of movable vane top area, namely within the scope of the leaf height of specifying, choose the wave crest point of all wave-like type knot shape raised structures in leading edge, trough point and chord length invariant point as node, cubic spline curve is adopted to be connected by these points, ensure the leading edge point line Second Order Continuous of movable vane within the scope of this leaf height, namely its curvature is continuous print;
4) curve of described waveform knot shape projection is determined by wave amplitude A and wavelength W, wave amplitude size is weighed with the percentage of benchmark mean camber line L, wavelength size is with the radial distance of prototype movable vane leading edge reference line and two end wall profile intersection points, and namely the percentage of leading edge leaf height H is weighed;
5) according to step 4) in wave amplitude, the benchmark mean camber line extending the nearly leading edge segments in crest place obtains the long remodeling blade profile for (L+A) of mean camber line, and the benchmark mean camber line shortening the nearly leading edge segments in trough place obtains the long remodeling blade profile for (L ?A) of mean camber line;
6) according to step 4) in wavelength, determine that each crest place and trough place are long at the benchmark mean camber line of leaf high position, blade profile of retrofiting is obtained by the mode of the benchmark mean camber line extending the nearly leading edge segments of benchmark mean camber line and shortening trough place of the nearly leading edge segments in crest place, by step 1) in the long-pending folded mode the determined blade profile high to different leaf carry out footpath vector product and fold, obtain bionical movable vane.
6. implementation method according to claim 5, is characterized in that, described step 5) in, different crests is not identical with the long L of benchmark mean camber line of wave trough position.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510697569.2A CN105332948B (en) | 2015-10-23 | 2015-10-23 | A kind of implementation method of the bionical movable vane of compressor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510697569.2A CN105332948B (en) | 2015-10-23 | 2015-10-23 | A kind of implementation method of the bionical movable vane of compressor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105332948A true CN105332948A (en) | 2016-02-17 |
| CN105332948B CN105332948B (en) | 2017-08-15 |
Family
ID=55283667
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510697569.2A Active CN105332948B (en) | 2015-10-23 | 2015-10-23 | A kind of implementation method of the bionical movable vane of compressor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105332948B (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106156436A (en) * | 2016-07-12 | 2016-11-23 | 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 and control |
| CN106250644A (en) * | 2016-08-05 | 2016-12-21 | 上海交通大学 | Dual arc blade profile compressor blade implementation method |
| CN110268135A (en) * | 2017-02-10 | 2019-09-20 | 西门子股份公司 | Method for reequiping turbine |
| CN110821851A (en) * | 2019-11-22 | 2020-02-21 | 南京航空航天大学 | Multistage axial compressor expands steady structure based on sawtooth trailing edge blade |
| WO2020079335A1 (en) * | 2018-10-18 | 2020-04-23 | Safran Aircraft Engines | Profiled structure for an aircraft or turbomachine |
| CN111079239A (en) * | 2019-12-19 | 2020-04-28 | 中国航空发动机研究院 | Bionic compressor cascade modeling method |
| CN111622808A (en) * | 2020-05-25 | 2020-09-04 | 武汉大学 | Bionic blade based on existing steam turbine blade profile transformation and design method |
| CN112231828A (en) * | 2020-11-10 | 2021-01-15 | 哈尔滨工业大学 | Leading edge combined convex structure for controlling adhesion flow of airfoil surface and flow control method thereof |
| CN113553671A (en) * | 2021-07-08 | 2021-10-26 | 浙江大学 | Bionic anti-cavitation axial flow impeller design method |
| CN114593088A (en) * | 2022-03-21 | 2022-06-07 | 西安热工研究院有限公司 | Power station movable blade adjustable axial flow fan capacity expansion transformation movable blade modification design method |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20010014285A1 (en) * | 1998-03-23 | 2001-08-16 | Stefan Schlechtriem | Rotor blade an axial-flow engine |
| US20050271513A1 (en) * | 2004-06-02 | 2005-12-08 | Erik Johann | Compressor blade with reduced aerodynamic blade excitation |
| 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 |
-
2015
- 2015-10-23 CN CN201510697569.2A patent/CN105332948B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20010014285A1 (en) * | 1998-03-23 | 2001-08-16 | Stefan Schlechtriem | Rotor blade an axial-flow engine |
| US20050271513A1 (en) * | 2004-06-02 | 2005-12-08 | Erik Johann | Compressor blade with reduced aerodynamic blade excitation |
| 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 |
Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN106156436A (en) * | 2016-07-12 | 2016-11-23 | 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 and control |
| CN106250644A (en) * | 2016-08-05 | 2016-12-21 | 上海交通大学 | Dual arc blade profile compressor blade implementation method |
| CN106250644B (en) * | 2016-08-05 | 2019-05-28 | 上海交通大学 | Dual arc blade profile compressor blade implementation method |
| CN110268135A (en) * | 2017-02-10 | 2019-09-20 | 西门子股份公司 | Method for reequiping turbine |
| US11668196B2 (en) | 2018-10-18 | 2023-06-06 | Safran Aircraft Engines | Profiled structure for an aircraft or turbomachine |
| WO2020079335A1 (en) * | 2018-10-18 | 2020-04-23 | Safran Aircraft Engines | Profiled structure for an aircraft or turbomachine |
| FR3087482A1 (en) * | 2018-10-18 | 2020-04-24 | Safran Aircraft Engines | PROFILED STRUCTURE FOR AIRCRAFT OR TURBOMACHINE |
| JP7463360B2 (en) | 2018-10-18 | 2024-04-08 | サフラン・エアクラフト・エンジンズ | Profile structure for an aircraft or turbomachine - Patent application |
| CN110821851A (en) * | 2019-11-22 | 2020-02-21 | 南京航空航天大学 | Multistage axial compressor expands steady structure based on sawtooth trailing edge blade |
| CN111079239A (en) * | 2019-12-19 | 2020-04-28 | 中国航空发动机研究院 | Bionic compressor cascade modeling method |
| CN111079239B (en) * | 2019-12-19 | 2023-07-21 | 中国航空发动机研究院 | Bionic compressor blade grid modeling method |
| CN111622808A (en) * | 2020-05-25 | 2020-09-04 | 武汉大学 | Bionic blade based on existing steam turbine blade profile transformation and design method |
| CN112231828A (en) * | 2020-11-10 | 2021-01-15 | 哈尔滨工业大学 | Leading edge combined convex structure for controlling adhesion flow of airfoil surface and flow control method thereof |
| CN113553671A (en) * | 2021-07-08 | 2021-10-26 | 浙江大学 | Bionic anti-cavitation axial flow impeller design method |
| CN114593088A (en) * | 2022-03-21 | 2022-06-07 | 西安热工研究院有限公司 | Power station movable blade adjustable axial flow fan capacity expansion transformation movable blade modification 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105332948B (en) | 2017-08-15 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105332948A (en) | Improved compressor blade and achieving method thereof | |
| CN105298924B (en) | Compressor bionics stator blade and its implementation based on humpback flipper | |
| JP6047141B2 (en) | High camber stator vane | |
| US7597544B2 (en) | Blade of axial flow-type rotary fluid machine | |
| US10301941B2 (en) | Turbine engine rotor blade | |
| US7547186B2 (en) | Nonlinearly stacked low noise turbofan stator | |
| JP6001999B2 (en) | Airfoil, compressor, vane, gas turbine engine, and stator row | |
| US9441502B2 (en) | Gas turbine annular diffusor | |
| JP2014109273A5 (en) | ||
| EP2476862A1 (en) | Vane for an axial flow turbomachine and corresponding turbomachine | |
| JP2001355405A (en) | Blade for turbo machine | |
| CN102454633B (en) | Axial compressor | |
| CN111435399B (en) | Modeling method of fan assembly | |
| JP7104379B2 (en) | Axial flow type fan, compressor and turbine blade design method, and blades obtained by the design | |
| CN104632701A (en) | High-bypass-ratio turbo-fan engine fan long-short blade structure | |
| US8777564B2 (en) | Hybrid flow blade design | |
| US9896940B2 (en) | Blade for a gas turbomachine | |
| CN101158991A (en) | Pneumatic power design method for big and small blade compressor | |
| CN104763477A (en) | Partial shroud structure of tip of moving blade of turbo machine | |
| CN105298912A (en) | Bump front edge inlet guider blade | |
| CN115596707B (en) | Axial-flow impeller with vortex generator | |
| CN201547018U (en) | Rotating blade row layout of axial compressor | |
| CN111005770B (en) | Centripetal turbine with splitter blades | |
| JP6741206B2 (en) | Axial flow type fan, compressor and turbine blade modification method, and blade obtained by the modification | |
| CN111305909B (en) | Supercharged stator blade construction method, supercharged stator blade and aircraft engine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |