CN105626158A - Variable geometry turbine with vortex elimination hole structures in front of movable blades - Google Patents
Variable geometry turbine with vortex elimination hole structures in front of movable blades Download PDFInfo
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- CN105626158A CN105626158A CN201610118651.XA CN201610118651A CN105626158A CN 105626158 A CN105626158 A CN 105626158A CN 201610118651 A CN201610118651 A CN 201610118651A CN 105626158 A CN105626158 A CN 105626158A
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- Prior art keywords
- whirlpool
- rotor blade
- turning axle
- disappears
- geometry turbine
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
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- 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
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
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- 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
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- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention provides a variable geometry turbine with vortex elimination hole structures in the front of movable blades. The variable geometry turbine comprises a case and hubs, wherein adjustable static blades and the movable blades are uniformly installed between the case and the hubs in the circumferential direction, upper rotating shafts and lower rotating shafts are installed on the upper end faces and the lower end faces of the adjustable static blades respectively, the upper rotating shafts are embedded into the case, the lower rotating shafts are embedded into the correspondinghub, the movable blades are installed on the correspondinghub, the curved vortex elimination hole structures communicating with blade pressure surfaces and suction surfaces are formed in the front of the movable blades in the radial direction, and load distribution of blade profiles of the movable blades is of a rear-loading type. According to the variable geometry turbine, separation vortexes in the front of the blades can be reduced or even eliminated underthe off-design condition so that aerodynamic loss in channels of the movable blades can be obviously reduced, transverse differential pressure in front of the blades can be reduced underthe design condition, formation of secondary flow can be delayed, and then loss of the secondary flow can be reduced. The variable geometry turbine hasgood characteristic underall operating conditions on the whole.
Description
Technical field
The present invention relates to variable geometry turbine, particularly relate to the variable geometry turbine of a kind of whirlpool pore structure that disappears with rotor blade front portion.
Background technology
Internal combustion turbine often can work under off-design behaviour, and now turbine efficiency can significantly reduce. The coupling that variable geometry turbine technology can effectively regulate and optimize between gas turbine components, it is to increase the acceleration and deceleration characteristic of internal combustion turbine and low-load performance. The installation angle regulating the quiet leaf of turbine is then a kind of effective change method of geometry.
The variable geometry turbine of prior art, when low operating mode, closes little variable stator vane angle and reduces working medium flow and output rating, and under variable stator vane angle, travelling leaf tends to run under the relatively big positive angle of attack, and cause separated flow on front side of dynamic leaf surface; In startup and acceleration operating mode, open big variable stator vane angle to increase gas turbine blower surge nargin and gasifier surplus power, and lower travelling leaf tends to run under the more negative angle of attack, causes dynamic leaf pressure face serious separated flow occur. Showing according to the study, variable stator vane angle closes the three-dimensional separated vorticcs flow field of the little dynamic leaf surface caused and the efficiency causing variable geometry turbine is declined more significantly, and the amplitude declined is up to 5%.
In order to reduce the disadvantageous effect that the dynamic leaf leading edge large attack angle of variable geometry turbine flows and brings, domestic and international researchist proposes the pneumatic design principle that the dynamic leaf of variable geometry turbine to be adopted the more negative angle of attack, and then instructs rotor blade blade design; But, so far, yet there are no and can effectively reduce the relevant report that the flowing of variable geometry turbine rotor blade leading edge large attack angle brings disadvantageous effect.
Summary of the invention
It is an object of the invention to provide the separation eddy current that can reduce under off-design behaviour and even eliminate rotor blade front portion, thus obviously reduce aerodynamic loss in rotor blade passage, but also the horizontal pressure reduction of bucket front can be reduced under design conditions, postpone the formation of secondary stream, thus there is the variable geometry turbine of a kind of whirlpool pore structure that disappears with rotor blade front portion of good whole working condition property
The object of the present invention is achieved like this: comprises casing, stationary blade wheel hub and dynamic impeller hub, dynamic impeller hub is arranged on by stationary blade wheel hub, between casing and stationary blade wheel hub and variable stator vane angle sheet is along the circumferential direction evenly installed, between casing and dynamic impeller hub and rotor blade is along the circumferential direction evenly installed, the upper surface of variable stator vane angle sheet and lower surface arrange turning axle and lower turning axle respectively, upper turning axle is embedded in casing, lower turning axle is embedded in stationary blade wheel hub, rotor blade is arranged on dynamic impeller hub, it is equipped with wheel hub turning axle in dynamic impeller hub, the bending shape being radially provided with through rotor blade pressure face and surface in rotor blade front portion disappears whirlpool pore structure.
The present invention also comprises some constitutional featuress like this:
1. between the suction side outlet in the anterior hole, whirlpool that disappears of rotor blade described in and blade profile leading edge point, axial distance is 0.2��0.4 with the ratio of blade chord length, the axial distance that disappears between hole, whirlpool pressure side outlet and blade profile leading edge point is 0.15��0.35 with the ratio of blade chord length, angle between hole, the whirlpool suction side exporter that disappears is tangential to exit is 10 �㡫40 ��, disappear pressure side outlet direction, hole, whirlpool and exit tangential between angle be 15 �㡫45 ��, the ratio of disappear whirlpool bore dia and blade chord length is 0.005��0.05.
2. between the suction side outlet in the anterior hole, whirlpool that disappears of rotor blade described in and blade profile leading edge point, axial distance is 0.2��0.4 with the ratio of blade chord length, the axial distance that disappears between hole, whirlpool pressure side outlet and blade profile leading edge point is 0.15��0.35 with the ratio of blade chord length, angle between hole, the whirlpool suction side exporter that disappears is tangential to exit is 10 �㡫40 ��, disappear pressure side outlet direction, hole, whirlpool and exit tangential between angle be 15 �㡫45 ��, the ratio of disappear whirlpool bore dia and blade chord length is 0.005��0.05.
3. the whirlpool pore structure that disappears of rotor blade front portion described in comprises radially equidistant arrangement or is 3��15 apertures gradually dredging shape arrangement along wheel hub to casing direction.
4. the boundary place on disappear whirlpool pore structure and the rotor blade surface of rotor blade front portion described in adopts round-corner transition.
5. going up turning axle and the axis of lower turning axle and the rotation of variable stator vane angle sheet described in be all located along the same line, the diameter of axle of upper turning axle is greater than the diameter of axle of lower turning axle.
Compared with prior art, the invention has the beneficial effects as follows: the present invention does not need additional energy and device just can automatically improve the flow field structure in the dynamic leaf passage of variable geometry turbine, the separation eddy current even eliminating rotor blade front portion can be reduced under off-design behaviour, thus obviously reduce aerodynamic loss in rotor blade passage, but also the horizontal pressure reduction of bucket front can be reduced under design conditions, postpone the formation of secondary stream, thus there is good full working scope performance characteristics, in addition, present configuration is also fairly simple, is easy to Project Realization.
Accompanying drawing explanation
Fig. 1 is the meridian view of the variable geometry turbine with the anterior whirlpool pore structure that disappears of rotor blade;
Fig. 2 is the variable geometry turbine rotor blade structural representation with the whirlpool pore structure that disappears;
Fig. 3 is the A-A sectional view in Fig. 1;
Fig. 4 is variable geometry turbine rotor blade blade profile power load distributing schematic diagram.
In figure: czsFor the axial distance disappeared between the suction side outlet of hole, whirlpool and blade profile leading edge point L, czpFor the axial distance disappeared between hole, whirlpool pressure side outlet and blade profile leading edge point L, ��sFor hole, the whirlpool suction side exporter that disappears to exit tangential between angle, ��pFor disappear pressure side outlet direction, hole, whirlpool and exit tangential between angle, CpsFor zero dimension static pressure coefficient, blade profile power load distributing is blade profile pressure side 8, suction side 9 zero dimension static pressure coefficient distributes vertically, and Z/C is the axial distance of zero dimension.
Embodiment
Below in conjunction with accompanying drawing and embodiment, the present invention is described in further detail.
Composition graphs 1��2, the present invention is by wheel hub 1 (comprising stationary blade wheel hub and dynamic impeller hub), variable stator vane angle sheet 3, rotor blade 4 and casing 6 form, variable stator vane angle sheet 3 and rotor blade 4 are along the circumferential direction evenly installed between wheel hub 1 and casing 6, variable stator vane angle sheet 3 is front, rotor blade 4 is rear, variable stator vane angle sheet upper, lower surface arranges turning axle 5 respectively, lower turning axle 2, its axle center on same rotation so that variable stator vane angle rotate, and the diameter of axle of upper turning axle is greater than lower turning axle, lower turning axle only plays the role of positioning, upper turning axle is embedded in casing 6, lower turning axle is embedded in wheel hub 1, rotor blade 4 is arranged on wheel hub 1, the bending shape radially having through blade pressure surface and a surface in rotor blade front portion disappears whirlpool pore structure 7.
Composition graphs 3, manufacture the variable geometry turbine of the whirlpool pore structure that disappears with rotor blade front portion of the present invention, first traditional design method is adopted to design variable geometry turbine variable stator vane angle sheet and rotor blade, then for the given concrete structure of variable geometry turbine rotor blade and the situation such as aerodynamic parameter and operation condition scope, the concrete structural parameter of the whirlpool pore structure that disappears comprise the axially distance c disappeared between the suction side outlet of hole, whirlpool and blade profile leading edge pointzs, the axially distance c that disappears between hole, whirlpool pressure side outlet and blade profile leading edge pointzp, hole, the whirlpool suction side exporter that disappears tangential to exit between angle ��s, disappear pressure side outlet direction, hole, whirlpool and exit tangential between angle ��p, disappear whirlpool bore dia and hole, the whirlpool hole count that disappears can carry out by means of existing Fluid Mechanics Computation software simulating or correlation test obtains.
It is noted that be in the hole, whirlpool that disappears at different leaf higher position place, its structural parameter can be different. Generally, the hole, whirlpool that disappears should be within the scope of disengaging zone in the position of blade both sides, therefore between hole, the whirlpool suction side of disappearing outlet and blade profile leading edge point, axial distance is 0.2��0.4 with the ratio of blade chord length, and the ratio of axial distance and blade chord length between hole, whirlpool pressure side outlet and blade profile leading edge point that disappears is 0.15��0.35. In order to more effectively blow down disengaging zone, jet direction should paste the ejection of wall face as far as possible, but consider processing factors and lose in the hole, whirlpool that disappears and should remain on little value as far as possible, therefore the angle between hole, the whirlpool suction side exporter that disappears is tangential to exit is 10 �㡫40 ��, disappear pressure side outlet direction, hole, whirlpool and exit tangential between angle be 15 �㡫45 ��. For the selection of the whirlpool bore dia that disappears, the whirlpool bore dia that disappears is too big, and jet effect is too strong, and main flow interference is too big, and the whirlpool bore dia that disappears is too little can not meet jet intensity requirement, and the ratio of therefore disappear whirlpool bore dia and blade chord length is 0.005��0.05.
In addition, when variable geometry turbine is in varying duty, the disengaging zone of rotor blade pressure side 8 or suction side 9 is mostly produce from wheel hub end wall, and upwards develop, therefore disengaging zone is even eliminated in order to more effectively reduce, the whirlpool pore structure that disappears radially should equidistantly be arranged or be arranged in gradually dredging shape along wheel hub to casing direction, and hole count is 3��15.
In order to guarantee that the anterior flow field of rotor blade can not be had a negative impact by the variable geometry turbine variable stator vane angle hole, whirlpool that disappears when zero corner, the horizontal pressure reduction of the anterior pressure side of rotor blade and suction side is unsuitable excessive, and also namely the power load distributing of rotor blade blade profile should be rear load (namely in the anterior pressure side of blade profile, suction side static pressure difference less than rear portion).
In addition, the damage control in leaf passage is moved under adopting round-corner transition to be also conducive to zero corner by the boundary place of disappear whirlpool pore structure and the blade surface of rotor blade front portion.
The know-why of the present invention is as follows:
Variable stator vane angle rotates and changes quiet leaf throat area, causes under downstream blade row are in off-design behaviour and runs. Under zero corner, dynamic leaf blade profile power load distributing is rear load, namely in the anterior pressure side of blade profile, suction side static pressure difference less than rear portion. When variable stator vane angle pass hour, the dynamic leaf angle of attack tends to the positive angle of attack, and front stationary point is moved to pressure face, and dynamic leaf front cross pressure reduction increases, and dynamic leaf working order is changed into uniform load by rear load or front portion loads. And when variable stator vane angle is opened, the dynamic leaf air inlet angle of attack is changed into the negative angle of attack, front stationary point is moved to surface, and the anterior suction side pressure of dynamic leaf is progressively greater than pressure side, and horizontal pressure reduction direction is sent out and turned, and progressively becomes big. The present invention disappears hole, whirlpool in the bending shape that some through blade pressure surfaces and surface are beaten in variable geometry turbine rotor blade front portion, when variable stator vane angle pass hour, the anterior bigger horizontal pressure reduction of dynamic leaf orders about main flow, and from disappearing, hole, whirlpool pressure side outlet enters the hole, whirlpool that disappears, then flow out from suction side, form " jet " effect, the separation vortex district even blowing down suction side can be reduced, thus reduce loss in dynamic leaf passage. And when variable stator vane angle is opened, dynamic leaf front portion changes nyctitropic horizontal pressure reduction orders about main flow the suction side outlet of hole, whirlpool enters the hole, whirlpool that disappears from disappearing, then flow out from pressure side, the big scale flow separation zone even blowing down pressure side can be reduced, can obviously reduce loss in dynamic leaf passage equally. In addition, when variable stator vane angle is in zero corner, the hole, whirlpool that disappears can reduce the horizontal pressure reduction of rotor blade front portion further, thus effectively reduces secondary flow.
The variable geometry turbine of a kind of whirlpool pore structure that disappears with rotor blade front portion, comprise casing, wheel hub, variable stator vane angle sheet and rotor blade are along the circumferential direction evenly installed between casing and wheel hub, variable stator vane angle sheet is front, rotor blade is rear, variable stator vane angle sheet upper, lower surface is arranged respectively, lower turning axle, its axle center is on same rotation, and the diameter of axle is different, upper turning axle is embedded in casing, lower turning axle is embedded in wheel hub, dynamic impeller hub is arranged on by stationary blade wheel hub, rotor blade is arranged on dynamic impeller hub, it is equipped with wheel hub turning axle in dynamic impeller hub, it is characterized in that: the bending shape radially having through blade pressure surface and a surface in rotor blade front portion disappears whirlpool pore structure, and the power load distributing of rotor blade blade profile is rear load.
The present invention can also comprise:
1, the described rotor blade front portion ratio of axial distance and blade chord length between the suction side outlet in hole, whirlpool and blade profile leading edge point that disappears is 0.2��0.4, the axial distance that disappears between hole, whirlpool pressure side outlet and blade profile leading edge point is 0.15��0.35 with the ratio of blade chord length, angle between hole, the whirlpool suction side exporter that disappears is tangential to exit is 10 �㡫40 ��, disappear pressure side outlet direction, hole, whirlpool and exit tangential between angle be 15 �㡫45 ��, the ratio of disappear whirlpool bore dia and blade chord length is 0.005��0.05.
2, the whirlpool pore structure that disappears of described rotor blade front portion comprises radially equidistant arrangement or is 3��15 apertures gradually dredging shape arrangement along wheel hub to casing direction.
3, the boundary place of disappear whirlpool pore structure and the blade surface of described rotor blade front portion adopts round-corner transition.
It is an object of the invention to provide the variable geometry turbine of a kind of whirlpool pore structure that disappears with rotor blade front portion, comprise casing, wheel hub, variable stator vane angle sheet and rotor blade are along the circumferential direction evenly installed between casing and wheel hub, variable stator vane angle sheet is front, rotor blade is rear, variable stator vane angle sheet upper, lower surface is arranged respectively, lower turning axle, its axle center is on same rotation, and the diameter of axle is different, upper turning axle is embedded in casing, lower turning axle is embedded in wheel hub, rotor blade is arranged on wheel hub, the bending shape radially having through blade pressure surface and a surface in rotor blade front portion disappears whirlpool pore structure, and the power load distributing of rotor blade blade profile is rear load. inventive design not only can reduce, with the disappear variable geometry turbine of whirlpool pore structure of rotor blade front portion, the separation eddy current even eliminating bucket front under off-design behaviour, thus obviously reduce aerodynamic loss in rotor blade passage, but also the horizontal pressure reduction of bucket front can be reduced under design conditions, postpone the formation of secondary stream, and then reducing secondary stream loss, the variable geometry turbine of inventive design has good whole working condition property on the whole.
Claims (9)
1. the variable geometry turbine with the anterior whirlpool pore structure that disappears of rotor blade, comprise casing, stationary blade wheel hub and dynamic impeller hub, dynamic impeller hub is arranged on by stationary blade wheel hub, between casing and stationary blade wheel hub and variable stator vane angle sheet is along the circumferential direction evenly installed, between casing and dynamic impeller hub and rotor blade is along the circumferential direction evenly installed, the upper surface of variable stator vane angle sheet and lower surface arrange turning axle and lower turning axle respectively, upper turning axle is embedded in casing, lower turning axle is embedded in stationary blade wheel hub, rotor blade is arranged on dynamic impeller hub, it is equipped with wheel hub turning axle in dynamic impeller hub, it is characterized in that: the bending shape being radially provided with through rotor blade pressure face and surface in rotor blade front portion disappears whirlpool pore structure.
2. the variable geometry turbine of a kind of whirlpool pore structure that disappears with rotor blade front portion according to claim 1, it is characterized in that: between the suction side outlet in the anterior hole, whirlpool that disappears of described rotor blade and blade profile leading edge point, axial distance is 0.2��0.4 with the ratio of blade chord length, the axial distance that disappears between hole, whirlpool pressure side outlet and blade profile leading edge point is 0.15��0.35 with the ratio of blade chord length, angle between hole, the whirlpool suction side exporter that disappears is tangential to exit is 10 �㡫40 ��, disappear pressure side outlet direction, hole, whirlpool and exit tangential between angle be 15 �㡫45 ��, the ratio of whirlpool bore dia and the blade chord length of disappearing is 0.005��0.05.
3. the variable geometry turbine of a kind of whirlpool pore structure that disappears with rotor blade front portion according to claim 1 and 2, it is characterised in that: the whirlpool pore structure that disappears of described rotor blade front portion comprises radially equidistant arrangement or is 3��15 apertures gradually dredging shape arrangement along wheel hub to casing direction.
4. the variable geometry turbine of a kind of whirlpool pore structure that disappears with rotor blade front portion according to claim 1 and 2, it is characterised in that: the boundary place on disappear whirlpool pore structure and the rotor blade surface of described rotor blade front portion adopts round-corner transition.
5. the variable geometry turbine of a kind of whirlpool pore structure that disappears with rotor blade front portion according to claim 3, it is characterised in that: the boundary place on disappear whirlpool pore structure and the rotor blade surface of described rotor blade front portion adopts round-corner transition.
6. the variable geometry turbine of a kind of whirlpool pore structure that disappears with rotor blade front portion according to claim 1 and 2, it is characterized in that: the axis of described upper turning axle and lower turning axle and the rotation of variable stator vane angle sheet are all located along the same line, and the diameter of axle of upper turning axle is greater than the diameter of axle of lower turning axle.
7. the variable geometry turbine of a kind of whirlpool pore structure that disappears with rotor blade front portion according to claim 3, it is characterized in that: the axis of described upper turning axle and lower turning axle and the rotation of variable stator vane angle sheet are all located along the same line, and the diameter of axle of upper turning axle is greater than the diameter of axle of lower turning axle.
8. the variable geometry turbine of a kind of whirlpool pore structure that disappears with rotor blade front portion according to claim 4, it is characterized in that: the axis of described upper turning axle and lower turning axle and the rotation of variable stator vane angle sheet are all located along the same line, and the diameter of axle of upper turning axle is greater than the diameter of axle of lower turning axle.
9. the variable geometry turbine of a kind of whirlpool pore structure that disappears with rotor blade front portion according to claim 5, it is characterized in that: the axis of described upper turning axle and lower turning axle and the rotation of variable stator vane angle sheet are all located along the same line, and the diameter of axle of upper turning axle is greater than the diameter of axle of lower turning axle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610118651.XA CN105626158A (en) | 2016-03-03 | 2016-03-03 | Variable geometry turbine with vortex elimination hole structures in front of movable blades |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610118651.XA CN105626158A (en) | 2016-03-03 | 2016-03-03 | Variable geometry turbine with vortex elimination hole structures in front of movable blades |
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| CN105626158A true CN105626158A (en) | 2016-06-01 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201610118651.XA Pending CN105626158A (en) | 2016-03-03 | 2016-03-03 | Variable geometry turbine with vortex elimination hole structures in front of movable blades |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110685976A (en) * | 2019-09-12 | 2020-01-14 | 武汉大学 | Suction jet device for blade boundary layer |
| CN111608735A (en) * | 2019-02-26 | 2020-09-01 | 三菱重工业株式会社 | Blade and machine provided with same |
| CN113513368A (en) * | 2021-07-08 | 2021-10-19 | 哈尔滨工程大学 | Turbine capable of directly backing with primary and secondary moving blade structures |
| CN113513373A (en) * | 2021-07-08 | 2021-10-19 | 哈尔滨工程大学 | Variable geometry turbine one-dimensional pneumatic design method |
| CN116752915A (en) * | 2023-08-15 | 2023-09-15 | 东北石油大学三亚海洋油气研究院 | Power rotor device for hydraulic-magnetic transmission borehole cleaning tool |
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| CN104100305B (en) * | 2014-07-22 | 2016-01-27 | 哈尔滨工程大学 | A kind of large meridian expansion variable geometry turbine with orthogonal type adjustable stator blade |
| CN205422837U (en) * | 2016-03-03 | 2016-08-03 | 哈尔滨工程大学 | Become turbine how much with moving vane front portion whirlpool pore structure that disappears |
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| US2166823A (en) * | 1937-10-19 | 1939-07-18 | Gen Electric | Elastic fluid turbine nozzle |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111608735A (en) * | 2019-02-26 | 2020-09-01 | 三菱重工业株式会社 | Blade and machine provided with same |
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| CN113513368A (en) * | 2021-07-08 | 2021-10-19 | 哈尔滨工程大学 | Turbine capable of directly backing with primary and secondary moving blade structures |
| CN113513373A (en) * | 2021-07-08 | 2021-10-19 | 哈尔滨工程大学 | Variable geometry turbine one-dimensional pneumatic design method |
| CN113513373B (en) * | 2021-07-08 | 2023-05-30 | 哈尔滨工程大学 | One-dimensional pneumatic design method for variable geometry turbine |
| CN116752915A (en) * | 2023-08-15 | 2023-09-15 | 东北石油大学三亚海洋油气研究院 | Power rotor device for hydraulic-magnetic transmission borehole cleaning tool |
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