CN106996312A - A kind of power blade - Google Patents
A kind of power blade Download PDFInfo
- Publication number
- CN106996312A CN106996312A CN201610071044.2A CN201610071044A CN106996312A CN 106996312 A CN106996312 A CN 106996312A CN 201610071044 A CN201610071044 A CN 201610071044A CN 106996312 A CN106996312 A CN 106996312A
- Authority
- CN
- China
- Prior art keywords
- blade
- turbine
- face
- engine
- pressure
- 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.)
- Pending
Links
Classifications
-
- 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
- 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
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03B—MACHINES OR ENGINES FOR LIQUIDS
- F03B3/00—Machines or engines of reaction type; Parts or details peculiar thereto
- F03B3/12—Blades; Blade-carrying rotors
- F03B3/121—Blades, their form or construction
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/20—Hydro energy
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Architecture (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Wind Motors (AREA)
Abstract
The present invention provides a kind of power blade, the characteristics of with kinetic energy high conversion rate, it is characterised in that be configured with least one groove on the preceding side pressure wind face of the blade direction of rotation of the turbine or the impeller disk of various engines and generator.
Description
Technical field：
The present invention relates to a kind of power blade, the technology is used for Aero-Space, or various hydroelectric turbines, or various
Thermoelectric generator turbine, or various steam-driven generator turbines, or various fluids pour blade and are allowed to move, and by dynamic action in
On the turbine or the impeller disk that blade is constituted, various rocket engines or body, or various aircraft wings or body, or various whirlpools
Turbine, or jet engine, or turbojet, or various fans, or various propellers, or various active rotations
On the turbine or the impeller disk that the blade of suction or discharge fluid is constituted.
Background technology：
At present, Aero-Space or various turbogenerators, or jet engine, or turbojet turbine, or
The pressure wind face of the blade of the impeller disk uses single plane or curved surface, and this kind of structural drag is big, and resistance of failure is poor, fluid resistance
Can be smoothly along blade be to end of blade conduction resistance and forms amplification, the power for especially consuming or wasting in high-speed motion
It is very big, according to current principle of dynamics, the need for can not having adapted to ultrahigh speed motion, when swiftly passing object is single
During one structure, the resistance wave suffered by it is formed as that a structure is most perfect, the resistance body of maximum intensity, therefore suffered resistance
Power is also maximum, and turbogenerator could effectively be improved by only breaking the conducting structure of resistance, or jet engine, or turbine
The fuel availability of jet engine improves thrust-weight ratio.
The content of the invention：
The present invention is exactly to propose in view of the above-mentioned problems, to provide a kind of a kind of new engine blade as mesh
, a kind of this kind of engine blade efficiency high, resistance is small, and fuel availability is high, and thrust-weight ratio is big, and energy-saving effect is notable, to machinery
The destructive power of equipment declines to a great extent.
In order to achieve the above object, the present invention uses following technical proposals：
A kind of power blade, if the turbine of aero-engine or gas turbine or steam turbine or hydroelectric generation turbine be by
Cured leaf piece composition, fluid impact blade, blade drives engine or gas turbine or steam turbine or hydroelectric generation turbine
Turbine rotation acting, there is incision side on each blade, extends along incision side and is formed as pressure face towards the face of fluid impact,
It is characterized in that：At least one groove is provided with the blade pressure surface of engine turbine or fan.
A kind of power blade, if the turbine of aero-engine or gas turbine or steam turbine or hydroelectric generation turbine be by
Cured leaf piece composition, fluid impact blade, blade drives engine or gas turbine or steam turbine or hydroelectric generation turbine
Turbine rotation acting, there is incision side on each blade, extends along incision side and is formed as pressure face towards the face of fluid impact,
It is characterized in that：The groove set on the blade pressure surface of engine turbine or fan extends back or the extension distribution of closing in shape
On the pressure face of blade.
A kind of power blade, if the turbine of aero-engine or gas turbine or steam turbine or hydroelectric generation turbine be by
Cured leaf piece composition, high energy fluid impact blade, blade drives engine or gas turbine or steam turbine or hydroelectric generation
The turbine rotation acting of turbine, there is incision side on each blade, and pressure is formed along the extension of incision side and towards the face of direction of rotation
Power face, incision side at the top of towards behind direction of rotation side extend face be rear power face, the back of pressure face, the bottom in rear power face
Face is back strength face, it is characterised in that：The groove set on the blade pressure surface of engine turbine or fan extends back or spiral shell
Rotation closing in shape extension is distributed on the pressure face of blade.
Preferably, the outer end of the blade is provided with the carinate wing of end of blade to front projection.
Preferably, set fluted on turbine or the impeller disk blade pressure surface, rear direction from groove to pressure face
Upper extension or closing in shape extend to form groove and be distributed on pressure face, to strengthen effect of the fluid to blade.
Preferably, set fluted on turbine or the impeller disk blade pressure surface, rear direction from groove to pressure face
Upper stepped extension or ladder closing in shape, which extend, to be formed groove and is distributed on pressure face, to strengthen effect of the fluid to blade.
Beneficial effect：
By setting recess or stair-stepping construction on the blade of power blade or turbine or the impeller disk, groove prolongs backward
Stretch or the extension of closing in shape is distributed in the pressure face or stepped extension or ladder closing in shape of blade and extends to form groove and be distributed in pressure
On power face, the lifting surface area of blade is added, has been detained the kinetic energy for the fluid for flowing through blade, makes the kinetic energy entrained by fluid maximum
Limit acts on blade, and aero-engine or gas turbine or steam turbine or hydroelectric generation turbine are acted on by blade
Turbine simultaneously does work.
Brief description of the drawings：
Technical scheme and advantage will be illustrated with reference to width figure, in the figure：
Fig. 1 is a kind of schematic diagram of engine blade of the first embodiment of the present invention.
Fig. 2 is a kind of schematic diagram of engine blade piece of second embodiment of the present invention.
Fig. 3 is a kind of schematic diagram of engine blade of third embodiment of the present invention.
Embodiment：
The preferred embodiment of the supermaneuver flight device of the present invention is explained below in conjunction with accompanying drawing, in embodiment
It is main with stair-stepping wind cutting side 3 in 1-3, the internal diameter pressure wind face 8 on the inside of stepped raised setting, outside forms depression extremely
Wind face 5 or the extension of pressure wind face 4 are formed as groove 9 after few one-level external diameter pressure wind face 9, the recess 8 of wind cutting side 3, in fan or turbine or
Set and illustrated exemplified by the mode such as fluted on the precentrum of the impeller disk 1.
Embodiment 1：
As shown in figure 1, a kind of power blade of the first embodiment of the present invention, aero-engine or gas turbine or steaming
The turbine of steam turbine or hydroelectric generation turbine sets some blades 2 to constitute on axle or internal tooth turbine wheel shaft or collar 1, blade
2 be pressure face 3 by the blade face of fluid impact (arrow signified direction), is extended back on pressure face or closing in shape extends to be formed
There is at least one groove 5.
By so constituting, in aeroengine combustor buring room, the air-flow in higher-pressure region is impacted backward with hypervelocity backward
The blade 2 of turbine makes blade 2 be driven the axle or internal tooth turbine wheel shaft or collar 1 of turbine to rotate by ballistic motion, due to
Groove 5 is provided with blade 2 makes the kinetic energy of fluid more be absorbed and be done work by blade 2, really by increasing blade
Resistance obtains more kinetic energy.
Embodiment 2：
As shown in Fig. 2 a kind of power blade of second embodiment of the present invention, aero-engine or gas turbine or steaming
The turbine of steam turbine or hydroelectric generation turbine sets some blades 2 to constitute on axle or internal tooth turbine wheel shaft or collar 1, blade
2 be pressure face 3 by the blade face of fluid impact (arrow signified direction), stepped extension or closing in shape rank backward on pressure face
Trapezoidal extension is formed with least one step groove 7, and the carinate wing 8 of end of blade to front projection is provided with the outer end of blade 2.
By so constituting, in aeroengine combustor buring room, the air-flow in higher-pressure region is impacted backward with hypervelocity backward
The blade 2 of turbine makes blade 2 be driven the axle or internal tooth turbine wheel shaft or collar 1 of turbine to rotate by ballistic motion, due to
Groove 5 is provided with blade 2 makes the kinetic energy of fluid more be absorbed and be done work by blade 2, really by increasing blade
Resistance obtains more kinetic energy.
Although above with setting groove 5 on the pressure face 3 by fluid impact, the mode of groove 6 and stair-stepping groove 7 is entered
Gone explanation, in such a configuration can using the structure of embodiment and other diversified forms as described combination.
Above-described preferred embodiment is illustrative and not restrictive, is not departing from the purport of the present invention
In the case of essential characteristic, the present invention otherwise can also be implemented and be embodied, and the scope of the present invention will by right
Ask and be defined, all deformations in the range of claim restriction are within the scope of the present invention.
Claims (4)
1. the turbine of a kind of power blade, aero-engine or gas turbine or steam turbine or hydroelectric generation turbine is by some
Blade composition, fluid impact blade, blade drives the whirlpool of engine or gas turbine or steam turbine or hydroelectric generation turbine
Wheel rotation acting, there is incision side on each blade, extends along incision side and is formed as pressure face towards the face of fluid impact, its
It is characterised by：At least one groove is provided with the blade pressure surface of engine turbine or fan.
2. the turbine of a kind of power blade, aero-engine or gas turbine or steam turbine or hydroelectric generation turbine is by some
Blade composition, fluid impact blade, blade drives the whirlpool of engine or gas turbine or steam turbine or hydroelectric generation turbine
Wheel rotation acting, there is incision side on each blade, extends along incision side and is formed as pressure face towards the face of fluid impact, its
It is characterised by：The groove set on the blade pressure surface of engine turbine or fan is extended back or the extension of closing in shape is distributed in
On the pressure face of blade.
3. the turbine of a kind of power blade, aero-engine or gas turbine or steam turbine or hydroelectric generation turbine is by some
Blade composition, high energy fluid impact blade, blade drives engine or gas turbine or steam turbine or hydroelectric generation wheel
The turbine rotation acting of machine, there is incision side on each blade, and pressure is formed along the extension of incision side and towards the face of direction of rotation
Face, incision side at the top of towards behind direction of rotation side extend face be rear power face, the back of pressure face, the face of the bottom in rear power face
For back strength face, it is characterised in that：The groove set on the blade pressure surface of engine turbine or fan extends back or spiral
The extension of closing in shape is distributed on the pressure face of blade.
4. the engine as described in claim 1-3 is any, it is characterised in that：The outer end of the blade is provided with to front projection
The carinate wing of end of blade.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610071044.2A CN106996312A (en) | 2016-01-26 | 2016-01-26 | A kind of power blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610071044.2A CN106996312A (en) | 2016-01-26 | 2016-01-26 | A kind of power blade |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106996312A true CN106996312A (en) | 2017-08-01 |
Family
ID=59430885
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610071044.2A Pending CN106996312A (en) | 2016-01-26 | 2016-01-26 | A kind of power blade |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106996312A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5609470A (en) * | 1994-09-30 | 1997-03-11 | Rolls-Ryce Plc | Turbomachine aerofoil with concave surface irregularities |
| CN102278206A (en) * | 2011-05-02 | 2011-12-14 | 李仕清 | Engine with large thrust-weight ratio |
| CN105065122A (en) * | 2015-07-17 | 2015-11-18 | 沈阳航空航天大学 | Hole-sawtooth groove structure for turbine blade air film cooling |
| CN105156356A (en) * | 2015-09-14 | 2015-12-16 | 北京航空航天大学 | Compressor stator cascade with blade root provided with equal-width broken line shaped channels |
-
2016
- 2016-01-26 CN CN201610071044.2A patent/CN106996312A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5609470A (en) * | 1994-09-30 | 1997-03-11 | Rolls-Ryce Plc | Turbomachine aerofoil with concave surface irregularities |
| CN102278206A (en) * | 2011-05-02 | 2011-12-14 | 李仕清 | Engine with large thrust-weight ratio |
| CN105065122A (en) * | 2015-07-17 | 2015-11-18 | 沈阳航空航天大学 | Hole-sawtooth groove structure for turbine blade air film cooling |
| CN105156356A (en) * | 2015-09-14 | 2015-12-16 | 北京航空航天大学 | Compressor stator cascade with blade root provided with equal-width broken line shaped channels |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20170801 |