CN205135721U - Adopt leaf top rib wing structure's turbine blade - Google Patents
Adopt leaf top rib wing structure's turbine blade Download PDFInfo
- Publication number
- CN205135721U CN205135721U CN201520770832.1U CN201520770832U CN205135721U CN 205135721 U CN205135721 U CN 205135721U CN 201520770832 U CN201520770832 U CN 201520770832U CN 205135721 U CN205135721 U CN 205135721U
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- blade
- winglet
- suction surface
- leaf top
- turbine
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Abstract
The utility model belongs to an adopt leaf top rib wing structure's turbine blade, concretely relates to novel turbine movable vane blade leaf top structure. It includes blade pressure face side winglet, blade suction surface side winglet, forms the cavity at leaf top middle part between blade pressure face side winglet and the blade suction surface side winglet. The blade leading edge department of blade pressure face side winglet form leading edge point and be close, the blade leading edge department formation trailing edge point of blade pressure face side winglet. Suction surface side winglet forms the leading edge points of proximity in the suction surface leading edge, and the blade leading edge department of pressure face side winglet forms trailing edge point. Suction surface winglet maximum breadth is between CD. The utility model has the advantages that can pass through this kind of special geometry, near the flow in control leaf top to reducing the leaf top and leaking stream, improve the turbine efficiency, increase turbine output is and improve the heat transfer performance on turbine leaf top, the extension turbine life -span.
Description
Technical field
The invention belongs to a kind of turbine rotor blade blade of gas turbine engine, be specifically related to a kind of design method, construction and device of turbine rotor blade leaf top.
Background technique
Modern gas turbine engines core engine mainly comprises three parts: gas compressor, firing chamber and turbine.Be compacted into pressurized gas during airflow passes gas compressor, then in firing chamber, carry out mixed combustion with fuel oil and become high-temperature high-pressure fuel gas, this gas flow does work to turbine when turbine, promote turbine rotor and rotate, and turbine drives gas compressor.
Turbine rotor blade generally includes leading edge, pressure side, suction surface, trailing edge and Ye Ding.In turbine rotor, in order to prevent rubbing between turbine rotor blade Ye Ding and outer casing wall, certain interval can be left between which.Fluid in mainstream channel under the driving of pressure side and suction surface pressure gradient power by pressure side effluent to suction surface side, form blade-tip leakage flow and corresponding blade tip leakage vortex.Blade-tip leakage flow can form flow losses, and this part fluid does work to turbine rotor, hardly because this reducing the power stage of turbine simultaneously.In order to improve the performance of gas turbine engine, the detrimental effect of blade-tip leakage flow be reduced.
If adopt traditional plane, the method reducing leaf top leakage loss is designed to be as small as possible by blade tip clearance, but the minimum value of blade tip clearance is subject to processing the restriction of the factors such as precision, always has a minimum value.On the other hand, in the turbine rotor of some known gas turbine engines, at motor run duration, the size in this gap can increase along with the increase of service time, and blade tip flowing can cause larger adverse effect to the performance of motor.
By adopt the leaf roof construction of particular design be another for controlling the method for turbine leaf top flowing adverse effect, certain methods known at present comprises and adopts the geometrical construction such as groove and winglet, and these methods are mainly by reducing the method for tip leakage stream.
In fact, the flowing near blade tip, except tip leakage whirlpool, also has scraping whirlpool and Passage Vortex, and wherein these vortex structures are all form flow losses, reduce the reason of turbine efficiency.
Fluid in high-pressure turbine is the combustion gas of high temperature, causes heat erosion and the oxidation on leaf top, reduces the life-span of motor, and outside tip leakage whirlpool, scraping whirlpool and Passage Vortex all can cause leaf top regional area temperature conductivity to reduce.
Summary of the invention
The object of this invention is to provide a kind of turbine blade adopting leaf top rib wing structure, it, by suppressing the development of vortex structures to reduce to flow near leaf top the loss of blending, reaches raising turbine efficiency, increases turbine output, and improve the heat transfer property of turbine, extend the object of engine life.Suppress the development of vortex structures also can reduce the heat transfer of blade surface, thus reach the object improving temperature conductivity.
The present invention is achieved in that a kind of turbine blade adopting leaf top rib wing structure, and it comprises blade pressure surface side winglet, blade suction surface side winglet, forms the cavity in the middle part of leaf top between blade pressure surface side winglet and blade suction surface side winglet.
The starting point A of described pressure side winglet is close to blade inlet edge, and terminating point B is close to blade trailing edge; Pressure side starting point A is positioned on suction surface, and the distance apart from blade inlet edge is the pressure side length of 0%-50%, and the terminating point B of pressure side is positioned on pressure side, and the distance apart from blade trailing edge is the pressure side length of 40%-90%.
The width W of pressure side winglet is the perpendicular distance between pressure side winglet edge to blade pressure surface, and its span is the maximum blade thickness of 0 to 0.5 times.
Suction surface winglet starting point C is positioned on blade suction surface, and the distance apart from blade inlet edge is the suction surface length of 0%-15%, and suction surface winglet terminating point D is being positioned at blade suction surface, and the distance apart from blade trailing edge is the suction surface length of 10%-55%.
Suction surface winglet thickness K is the perpendicular distance between suction surface winglet edge to blade suction surface, from suction surface winglet starting point C, to suction surface winglet terminating point D, vane thickness K is the distribution of first increases and then decreases, suction surface winglet thickness K has a maximum ga(u)ge, span is the maximum blade thickness of 0.1 to 1 times, and the distance of the position distance blade inlet edge of suction surface winglet maximum ga(u)ge is the suction surface length of 20%-60%.
Vane tip has a groove structure, and inner ring molded line is the molded line of leaf top further groove, and the width between groove molded line and Ye Ding outer ring molded line is M, and concrete width gets different value in different positions, the maximum blade thickness that Extreme breadth is less than 2 times.
Blade pressure surface 9 starts at F point, starts transition to leaf pressure on top surface face winglet.Near F point, adopt the mode transition of the line segment of curve or straight line or curve Straight Combination, there is an angle between line segment and pressure side winglet leaf end face, angle can be sharp-pointed angle or adopt chamfered.
Leaf top plane to F point along exhibition to distance P be not more than 10% of blade chord length; The span of the distance T bottom blade and blade end face and groove structure is within the scope of 1%-7% blade chord length.
Blade suction surface from G point to the transition of suction surface winglet.Near G point, adopt the line segment transition of curve or straight line or curve Straight Combination, there is an angle between this line segment and suction surface winglet end face, the scope of this angle H is 35 degree of-120 degree; Angle is sharp-pointed angle or adopts chamfered.
Width between inner ring groove molded line and outer ring winglet profile line gets different value in different positions, in the cross-section on blade and leaf top, inside pressure side winglet and the angle of bottom portion of groove be that W, W are greater than 90 degree; The angle of pressure side winglet inner side surface and bottom portion of groove is that W, W are greater than 70 degree, and in the cross-section on blade and leaf top, the angle of suction surface winglet inner side surface and bottom portion of groove is X, and angle X is greater than 70 degree.
Advantage of the present invention: the leaf roof construction that make use of the cavity combination in the middle part of pressure side winglet, suction surface winglet and leaf top, controls the flowing of blade-tip leakage flow.Wherein pressure side winglet can be used for reducing the pressure driving blade tip clearance import, and increase the separation zone of blade tip clearance pressure side inlet, these effects can make the pressure difference driving blade-tip leakage flow reduce, and reduce effective circulation passage area of blade-tip leakage flow, thus reduce blade-tip leakage flow; Under normal circumstances, the pressure near blade tip clearance suction side is lower, and for blade-tip leakage flow, lower pressure can increase the flow of blade-tip leakage flow.In addition, such pressure distribution can form one is pointed to suction surface pressure gradient by pressure side near casing, thus drives the boundary layer flow on casing to be separated, and forms the vortex structures such as scraping whirlpool.Suction surface winglet in the present invention utilizes leakage flow in the interaction of blade tip clearance outlet port and casing scraping to suppress leakage flow.Now on the pressure side can go out the zone of high pressure of an interruption-forming local in outlet port at blade tip clearance, thus reduce the pressure difference driving blade-tip leakage flow, decrease blade-tip leakage flow flow.On the other hand, this partial high pressure district can form the pressure gradient pointing to blade center passage from suction surface near casing, which suppress the separation of end wall bounda layer, and reduces the scraping vortex structure even eliminated near casing.Between two winglets, adopt the structure of groove, the flowing blending that the eddy's structure in groove is strengthened in blade tip clearance further can be utilized, thus reduce blade-tip leakage flow flow.Except in the gas turbine, this turbine leaf top designing technique can increase turbine output, improves turbine efficiency, therefore also can be widely used in other all kinds of turbine for power stage, such as power turbine etc.
Accompanying drawing explanation
Fig. 1 is a kind of blade and leaf roof construction figure adopting the turbine blade of leaf top rib wing structure provided by the present invention;
Fig. 2 is the schematic top plan view of Fig. 1;
Fig. 3 provided by the present inventionly a kind ofly adopts the blade of the turbine blade of leaf top rib wing structure and the typical section figure on leaf top;
Fig. 4 is little interplane groove;
Fig. 5 is that a kind of leaf roof construction of the turbine blade of leaf top rib wing structure that adopts provided by the present invention is in the mobilization design sketch of leaf top;
The flow field velocity vector distribution of Fig. 6 blade tip clearance middle section (F-F), blade profile and aerofoil profile figure;
Fig. 7 adopts the close blade pressure surface of circle and suction surface;
Fig. 8 is in the chord length moral distribution vertically of suction surface outlet port, leaf top leakage flow;
Fig. 9 be blade downstream along exhibition to flow losses.
In figure, 1 pressure side winglet, 2 suction surface winglets, groove between 3 pressure sides and suction surface, the suction surface of 14 blades, 31 blade inlet edges, 41 blade trailing edges, W pressure side winglet width, A pressure side winglet starting point, B pressure side winglet terminating point, C suction surface winglet starting point, D suction surface winglet terminating point, 9 blade pressure surfaces, K suction surface winglet thickness, the molded line of 22 grooves, 23 Ye Ding outer ring molded line, F point blade pressure surface is to the transition point of pressure side winglet, 7 blade pressure surfaces are to the transition line of pressure side winglet, angle between 35 blade pressure surfaces to the transition line and pressure side winglet leaf end face of pressure side winglet, 8 leaf top planes, P leaf top plane to F point along exhibition to distance, T leaf end face is to the distance of bottom portion of groove, G blade suction surface is to the transition point of suction surface winglet, 11 blade suction surfaces are to the transition line of suction surface winglet, 10 suction surface winglet end faces, angle between H blade pressure surface to the transition line and the little winged petiole end face of suction surface of pressure side winglet, inside 12 pressure side winglet, 13 bottom portion of groove faces, with the angle of bottom portion of groove inside W pressure side rib, 36 suction surface winglet inner side surfaces, with the angle of bottom portion of groove inside X suction surface rib, 39 suction surface winglet thickness, casing faces 37, the interface of 38 Ye Ding middle section leakage flow and passage stream, the thickness of d blade.
Embodiment
Below in conjunction with drawings and Examples, the present invention is described in detail:
As shown in Figure 1, a kind of leaf roof construction of Novel turbine movable vane blade, comprises blade pressure surface side winglet 1, blade suction surface side winglet 2, forms the cavity in the middle part of leaf top between blade pressure surface side winglet 1 and blade suction surface side winglet 2.
As shown in Figure 2, the starting point A of pressure side winglet 1 is close to blade inlet edge 31, and terminating point B is close to blade trailing edge 41; Pressure side starting point A is positioned on suction surface, and the distance apart from blade inlet edge 31 is the pressure side length of 0%-50%, and the terminating point B of pressure side is positioned on pressure side, and the distance apart from blade trailing edge 41 is the pressure side length of 40%-90%.
The width W of pressure side winglet is the perpendicular distance between pressure side winglet edge to blade pressure surface 9, and its span is the maximum blade thickness of 0 to 0.5 times.
Suction surface winglet starting point C is positioned on blade suction surface, and the distance apart from blade inlet edge 31 is the suction surface length of 0%-15%, and suction surface winglet terminating point D is being positioned at blade suction surface, and the distance apart from blade trailing edge 41 is the suction surface length of 10%-55%.
Suction surface winglet thickness K is the perpendicular distance between suction surface winglet edge to blade suction surface 14, from suction surface winglet starting point C, to suction surface winglet terminating point D, vane thickness K is the distribution of first increases and then decreases, suction surface winglet thickness K has a maximum ga(u)ge, span is the maximum blade thickness of 0.1 to 1 times, and the distance of the position distance blade inlet edge 31 of suction surface winglet maximum ga(u)ge is the suction surface length of 20%-60%.
Vane tip has a groove structure 3, and inner ring molded line is the molded line 22 of leaf top further groove, and the width between groove molded line 22 and Ye Ding outer ring molded line 23 is M, and concrete width gets different value in different positions, the maximum blade thickness that Extreme breadth is less than 2 times.
Blade pressure surface 9 starts at F point, starts transition to leaf pressure on top surface face winglet.Near F point, adopt the mode transition of the line segment 7 of curve or straight line or curve Straight Combination, there is an angle 35 between line segment 7 and pressure side winglet leaf end face, angle 35 can be sharp-pointed angle, also can adopt chamfered.
Leaf top plane 8 to F point along exhibition to distance P be not more than 10% of blade chord length; The span of the distance T bottom blade and blade end face 8 and groove structure is within the scope of 1%-7% blade chord length.
Blade suction surface 14 from G point to the transition of suction surface winglet.Near G point, adopt the line segment transition 11 of curve or straight line or curve Straight Combination, the scope that there is an angle H, this angle H between this line segment 11 and suction surface winglet end face 10 is 35 degree of-120 degree; Angle H can be sharp-pointed angle, also can adopt chamfered.
Width between inner ring groove molded line 22 and outer ring winglet profile line gets different value in different positions, in the cross-section on blade and leaf top, inside pressure side winglet 12 and the angle of bottom portion of groove 13 be that W, W are greater than 90 degree; The angle of pressure side winglet inner side surface 12 and bottom portion of groove 13 is that W, W are greater than 70 degree, and in the cross-section on blade and leaf top, the angle of suction surface winglet inner side surface 36 and bottom portion of groove 13 is X, and angle X is greater than 70 degree.
Fig. 6 is the speed in the F-F cross section in the blade and blade top middle section Fig. 5 adopting emulation mode to obtain, the two-dimension speed vector distribution on this cross section.The interface 38 of leakage flow and main flow can be found out from speed vector figure, the design of leaf top suction surface winglet is determined at the concrete property of this flowing interface of design consideration of blade path, the part of 20-60% from blade inlet edge point, suction surface winglet no longer follows interface 38, draws close to blade suction surface.The distance of the position distance blade inlet edge 31 of suction surface winglet maximum ga(u)ge is the suction surface length of 20%-60%, specifically depends on the situations such as blade load.
Fig. 7 is the leaf top not adopting winglet designs, and the diameter adopting the close blade pressure surface of circle and suction surface is d, is defined as the local thickness of blade.
Fig. 8 is that can find out the leaf top adopting the leakage flow 46 on the little winged petiole top of the present invention to be less than the leakage flow 45 on the leaf top not adopting winglet designs, this effect is especially obvious in blade path front portion in the chord length moral distribution vertically of suction surface outlet port, leaf top leakage flow.
Fig. 9 be blade downstream along exhibition to flow losses, the leakage vortex loss 55 during the winglet of leaf top is not adopted to be greater than the leakage vortex loss 56 of middle period of the present invention top design, secondary vortices when not adopting leaf top winglet and scraping eddyloss 53 are greater than secondary vortices and the scraping eddyloss 54 of the top design of this patent middle period, and visible the design reduces flow losses and improves efficiency.
Utilize method for numerical simulation, flow field analysis has been done to the turbine blade on this kind of band pressure side and the little winged petiole top of suction surface, find that the lifting on blade aerodynamic and temperature conductivity can both be brought in the leaf top of this employing cavity and winglet combination.First be that the mass flow rate of blade-tip leakage flow decreases, this makes the flow field in flow channel more even, thus reduces aerodynamic loss, improves turbine efficiency, and improves turbine output, thus improves the power of motor.After have employed this Novel leaf top, leaf top, the coefficient of heat transfer in Ye Ding region also reduces, and which improves the temperature conductivity of turbine, can reach the object in the life-span extending turbine.
Claims (9)
1. one kind adopts the turbine blade of leaf top rib wing structure, it is characterized in that: it comprises blade pressure surface side winglet (1), blade suction surface side winglet (2), forms the cavity in the middle part of leaf top between blade pressure surface side winglet (1) and blade suction surface side winglet (2).
2. a kind of turbine blade adopting leaf top rib wing structure as claimed in claim 1, is characterized in that: the starting point A of described pressure side winglet (1) is close to blade inlet edge (31), and terminating point B is close to blade trailing edge (41); Pressure side starting point A is positioned on suction surface, distance apart from blade inlet edge (31) is the pressure side length of 0%-50%, the terminating point B of pressure side is positioned on pressure side, and the distance apart from blade trailing edge (41) is the pressure side length of 40%-90%.
3. a kind of turbine blade adopting leaf top rib wing structure as claimed in claim 2, it is characterized in that: the width W of pressure side winglet is the perpendicular distance between pressure side winglet edge to blade pressure surface (9), and its span is the maximum blade thickness of 0 to 0.5 times.
4. a kind of turbine blade adopting leaf top rib wing structure as claimed in claim 2, it is characterized in that: suction surface winglet starting point C is positioned on blade suction surface, distance apart from blade inlet edge (31) is the suction surface length of 0%-15%, suction surface winglet terminating point D is being positioned at blade suction surface, and the distance apart from blade trailing edge (41) is the suction surface length of 10%-55%.
5. a kind of turbine blade adopting leaf top rib wing structure as claimed in claim 4, it is characterized in that: suction surface winglet thickness K is the perpendicular distance between suction surface winglet edge to blade suction surface (14), from suction surface winglet starting point C, to suction surface winglet terminating point D, vane thickness K is the distribution of first increases and then decreases, suction surface winglet thickness K has a maximum ga(u)ge, span is the maximum blade thickness of 0.1 to 1 times, the distance of position distance blade inlet edge (31) of suction surface winglet maximum ga(u)ge is the suction surface length of 20%-60%.
6. a kind of turbine blade adopting leaf top rib wing structure as claimed in claim 1, it is characterized in that: vane tip has a groove structure (3), inner ring molded line is the molded line (22) of leaf top further groove, width between groove molded line (22) and Ye Ding outer ring molded line (23) is M, concrete width gets different value in different positions, the maximum blade thickness that Extreme breadth is less than 2 times, width between inner ring groove molded line (22) and outer ring winglet profile line gets different value in different positions, in the cross-section on blade and leaf top, inside pressure side winglet, the angle of (12) and bottom portion of groove (13) is W, W is greater than 90 degree, the angle of pressure side winglet inner side surface (12) and bottom portion of groove (13) is W, W is greater than 70 degree, in the cross-section on blade and leaf top, the angle of suction surface winglet inner side surface (36) and bottom portion of groove (13) is X, and angle X is greater than 70 degree.
7. a kind of turbine blade adopting leaf top rib wing structure as claimed in claim 1, it is characterized in that: blade pressure surface 9 starts at F point, transition is started to leaf pressure on top surface face winglet, the mode transition of the line segment (7) of curve or straight line or curve Straight Combination is adopted near F point, there is an angle (35) between line segment (7) and pressure side winglet leaf end face, angle (35) can be sharp-pointed angle or adopt chamfered.
8. a kind of turbine blade adopting leaf top rib wing structure as claimed in claim 2, is characterized in that: leaf top plane (8) to F point along exhibition to distance P be not more than 10% of blade chord length; The span of the distance T bottom blade and blade top plane (8) and groove structure is within the scope of 1%-7% blade chord length.
9. a kind of turbine blade adopting leaf top rib wing structure as claimed in claim 4, it is characterized in that: blade suction surface (14) from G point to the transition of suction surface winglet, line segment (11) transition of curve or straight line or curve Straight Combination is adopted near G point, the scope that there is an angle H, this angle H between this line segment (11) and suction surface winglet end face (10) is 35 degree of-120 degree; Angle (H) is for sharp-pointed angle or adopt chamfered.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520770832.1U CN205135721U (en) | 2015-09-30 | 2015-09-30 | Adopt leaf top rib wing structure's turbine blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520770832.1U CN205135721U (en) | 2015-09-30 | 2015-09-30 | Adopt leaf top rib wing structure's turbine blade |
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| Publication Number | Publication Date |
|---|---|
| CN205135721U true CN205135721U (en) | 2016-04-06 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201520770832.1U Withdrawn - After Issue CN205135721U (en) | 2015-09-30 | 2015-09-30 | Adopt leaf top rib wing structure's turbine blade |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105179022A (en) * | 2015-09-30 | 2015-12-23 | 北京大学 | Turbine blade of blade top rib wing structure |
| CN106837867A (en) * | 2016-12-07 | 2017-06-13 | 浙江理工大学 | Axial flow blower 3 d impeller with leaf vein texture and splitterr vanes |
| EP3255249A1 (en) * | 2016-06-07 | 2017-12-13 | United Technologies Corporation | Gas turbine engine blade including squealer tip pocket |
| CN108868898A (en) * | 2017-05-05 | 2018-11-23 | 通用电气公司 | The device and method of airfoil for cooling turbine engines |
| CN113653672A (en) * | 2021-08-31 | 2021-11-16 | 佛山市南海九洲普惠风机有限公司 | Axial flow impeller with splitter blades |
| CN113883092A (en) * | 2021-09-10 | 2022-01-04 | 苏州浪潮智能科技有限公司 | Design method of winglet |
| CN115977999A (en) * | 2023-01-12 | 2023-04-18 | 山东科技大学 | Subsonic compressor, rotor blade and flow stability expansion control method |
-
2015
- 2015-09-30 CN CN201520770832.1U patent/CN205135721U/en not_active Withdrawn - After Issue
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105179022A (en) * | 2015-09-30 | 2015-12-23 | 北京大学 | Turbine blade of blade top rib wing structure |
| CN105179022B (en) * | 2015-09-30 | 2017-06-27 | 北京大学 | A kind of turbo blade of use leaf top rib wing structure |
| EP3255249A1 (en) * | 2016-06-07 | 2017-12-13 | United Technologies Corporation | Gas turbine engine blade including squealer tip pocket |
| US10801331B2 (en) | 2016-06-07 | 2020-10-13 | Raytheon Technologies Corporation | Gas turbine engine rotor including squealer tip pocket |
| CN106837867A (en) * | 2016-12-07 | 2017-06-13 | 浙江理工大学 | Axial flow blower 3 d impeller with leaf vein texture and splitterr vanes |
| CN106837867B (en) * | 2016-12-07 | 2023-05-30 | 浙江理工大学 | Axial flow fan ternary impeller with vein structure and splitter blades |
| CN108868898B (en) * | 2017-05-05 | 2021-03-12 | 通用电气公司 | Apparatus and method for cooling an airfoil tip of a turbine engine |
| CN108868898A (en) * | 2017-05-05 | 2018-11-23 | 通用电气公司 | The device and method of airfoil for cooling turbine engines |
| CN113653672A (en) * | 2021-08-31 | 2021-11-16 | 佛山市南海九洲普惠风机有限公司 | Axial flow impeller with splitter blades |
| CN113653672B (en) * | 2021-08-31 | 2023-11-10 | 佛山市南海九洲普惠风机有限公司 | Axial flow impeller with splitter blades |
| CN113883092A (en) * | 2021-09-10 | 2022-01-04 | 苏州浪潮智能科技有限公司 | Design method of winglet |
| CN113883092B (en) * | 2021-09-10 | 2024-01-26 | 苏州浪潮智能科技有限公司 | Design method of winglet |
| CN115977999A (en) * | 2023-01-12 | 2023-04-18 | 山东科技大学 | Subsonic compressor, rotor blade and flow stability expansion control method |
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Granted publication date: 20160406 Effective date of abandoning: 20170627 |
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| AV01 | Patent right actively abandoned |