WO2019226060A4 - A turbine blade and a turbine comprising such a blade - Google Patents

A turbine blade and a turbine comprising such a blade Download PDF

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Publication number
WO2019226060A4
WO2019226060A4 PCT/PL2019/000043 PL2019000043W WO2019226060A4 WO 2019226060 A4 WO2019226060 A4 WO 2019226060A4 PL 2019000043 W PL2019000043 W PL 2019000043W WO 2019226060 A4 WO2019226060 A4 WO 2019226060A4
Authority
WO
WIPO (PCT)
Prior art keywords
length
chord
segment
segn
curvature radius
Prior art date
Application number
PCT/PL2019/000043
Other languages
French (fr)
Other versions
WO2019226060A1 (en
Inventor
Paweł LICZNERSKI
Original Assignee
Abt Accord Spółka Z Ograniczoną Odpowiedzialnością
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Abt Accord Spółka Z Ograniczoną Odpowiedzialnością filed Critical Abt Accord Spółka Z Ograniczoną Odpowiedzialnością
Publication of WO2019226060A1 publication Critical patent/WO2019226060A1/en
Publication of WO2019226060A4 publication Critical patent/WO2019226060A4/en

Links

Classifications

    • 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
    • F03D—WIND MOTORS
    • F03D1/00—Wind motors with rotation axis substantially parallel to the air flow entering the rotor 
    • F03D1/06—Rotors
    • F03D1/0608—Rotors characterised by their aerodynamic shape
    • F03D1/0633—Rotors characterised by their aerodynamic shape of the blades
    • F03D1/0641—Rotors characterised by their aerodynamic shape of the blades of the section profile of the blades, i.e. aerofoil profile
    • 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
    • F03B17/00—Other machines or engines
    • F03B17/06—Other machines or engines using liquid flow with predominantly kinetic energy conversion, e.g. of swinging-flap type, "run-of-river", "ultra-low head"
    • F03B17/061—Other machines or engines using liquid flow with predominantly kinetic energy conversion, e.g. of swinging-flap type, "run-of-river", "ultra-low head" with rotation axis substantially in flow direction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2210/00—Working fluid
    • F05B2210/16—Air or water being indistinctly used as working fluid, i.e. the machine can work equally with air or water without any modification
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2240/00—Components
    • F05B2240/20—Rotors
    • F05B2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05B2240/301—Cross-section characteristics
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2250/00—Geometry
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2250/00—Geometry
    • F05B2250/70—Shape
    • F05B2250/71—Shape curved
    • F05B2250/711—Shape curved convex
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2250/00—Geometry
    • F05B2250/70—Shape
    • F05B2250/71—Shape curved
    • F05B2250/712—Shape curved concave
    • 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
    • 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
    • Y02E10/70—Wind energy
    • Y02E10/72—Wind turbines with rotation axis in wind direction

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Sustainable Energy (AREA)
  • Power Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The invention relates to a turbine blade having a suction surface (6) the profile of which comprises starting from a leading surface (3): - at least one segment (SEG1-SEGn) which has a curve inflection point (C1-Cn) and which is formed by a first convex curve (KA1-KAn) having a first mean curvature radius (RA1-RAn) and a first curvature length (LA1-LAn), a second convex curve (KB1-KBn) having a second mean curvature radius (RB1-RBn) and a second curvature length (LB1-LBn), and by one concave curve (KC1-KCn) having a third mean curvature radius (RC1-RCn) and a third curvature length (LC1-LCn); and - a terminal segment (SEGt) formed by a concave curve (Kt) having a terminal mean curvature radius (Rt) and a terminal curvature length (Lt); characterized in that for each segment (SEG1_SEGn) having a curve inflection point (C1-Cn): the ratio (RC:RA) of the third mean curvature radius (RC) to the first mean curvature radius (RA) ranges from 0.55 to 0.95; the ratio (RB:RC) of the second mean curvature radius (RB) to the third mean curvature radius (RC) ranges from 0.35 to 0.75; the ratio (LC:LA) of the third curvature length (LC) to the first curvature length (LA) ranges from 0.55 to 0.95; the ratio (LB:LA) of the second curvature length (LB) to the first curvature length (LA) ranges from 0.35 to 0.75; and for the terminal segment (SEGt): the terminal mean curvature radius (Rt) is smaller than the first mean curvature radius (RAn) of the preceding adjacent segment (SEGn) having a curve inflection point (Cn); a chord (CHt) of the terminal segment (SEGt) is slanted relative to a chord (CHn) of the preceding adjacent segment (SEGn) having a curve inflection point (Cn) at an obtuse angle (a(n;t)); the ratio (LCHt:LCHn) of the length (LCHt) of the chord (CHt) of the terminal segment (SEGt) to the length (LCHn) of the chord (CHn) of the preceding adjacent segment (SEGn) having a curve inflection point (Cn), ranges from 0.55 to 0.95.

Claims

AMENDED CLAIMS received by the International Bureau on 18 November 2019 (18.1 1 .2019)
1. A turbine blade comprising a bottom surface (2) and a top surface (1) and a leading surface (3) and a trailing surface (4), wherein a pressure surface (5) and a suction surface (6) are connected along the leading surface (3) and the trailing surface (4), wherein the pressure surface (5) and the suction surface (6) are extended over profiles constructed of component curves, wherein a profile forming the suction surface (6) comprises starting from the leading surface (3):
- at least one segment (SEG1-SEGn) which has a curve inflection point (C1-Cn) and which is formed by two convex curves comprising a first convex curve (KA1 -KAn) having a first mean curvature radius (RA1 -RAn) and a first curvature length (LA1-LAn) and a second convex curve (KB1-KBn) having a second mean curvature radius (RB1 -RBn) and a second curvature length (LB1-LBn), and by one concave curve (KC1 -KCn) having a third mean curvature radius (RC1 -RCn) and a third curvature length (LC1 -LCn), successively located one after the other starting from the side of the leading surface (3); and
- a terminal segment (SEGt) which is located behind the endmost segment (SEG1-SEGn) having a curve inflection point (C1 -Cn) and formed by a convex curve (Kt) having a terminal mean curvature radius (Rt) and a terminal curvature length (Lt);
characterized in that
for each segment (SEGTSEGn) having a curve inflection point (C1-Cn):
- the ratio (RC:RA) of the third mean curvature radius (RC) to the first mean curvature radius (RA) ranges from 0.55 to 0.95,
- the ratio (RB:RC) of the second mean curvature radius (RB) to the third mean curvature radius (RC) ranges from 0.35 to 0.75,
- the ratio (LC:LA) of the third curvature length (LC) to the first curvature length (LA) ranges from 0.55 to 0.95,
- the ratio (LB:LA) of the second curvature length (LB) to the first curvature length (LA) ranges from 0.35 to 0.75;
and for the terminal segment (SEGt):
- the terminal mean curvature radius (Rt) is smaller than the first mean 15 curvature radius (RAn) of the preceding adjacent segment (SEGn) having a curve inflection point (Cn),
- a chord (CHt) of the terminal segment (SEGt) is slanted relative to a chord (CHn) of the preceding adjacent segment (SEGn) having a curve inflection point (Cn) at an obtuse angle (a(n;t));
- the ratio (LCHLLCHn) of the length (LCHt) of the chord (CHt) of the terminal segment (SEGt) to the length (LCHn) of the chord (CHn) of the preceding adjacent segment (SEGn) having a curve inflection point (Cn), ranges from 0.55 to 0.95.
2. The turbine blade according to Claim 1 , characterized in that it comprises a number of the segments (SEG1 -SEGn) having curve inflection points (C1-Cn), wherein for each pair of such segments (SEG1_SEGn):
- the ratio (LCHn:LCHn-1) of the length (LCHn) of the chord (CHn) of a given segment (SEGn) to the length (LCHn-1) of the chord (CHn-1 ) of the preceding adjacent segment (SEGn-1 ) located in front of the given segment toward the leading surface (3), ranges from 0.55 to 0.95;
and/or
- the ratio (a(h;h+1):a(h-1 ;h)) of an angle (ct(n;n+1 )) of a slant of the chord (CHn) of a given segment (SEGn) relative to the chord (CHn+1) of the adjacent segment (SEGn) located in front of this given segment toward the trailing surface (4), to the angle (a(n-1 ;n)) of a slant of the chord (CHn) of this given segment (SEGn) relative to the chord (CHn-1 ) of the adjacent segment (SEGn-1 ) located in front of this given segment toward the leading surface (3), ranges from 0.55 to 0.95.
3. The turbine blade according to Claim 1 or 2, characterized in that adjacent chords (CH1-CHt) of adjacent segments (SEG1 -SEGt) on the suction surface (6) are slanted relative to each other at obtuse angles (a(1 ...n;2...t)) that preferably range from 100° to 170°.
4. The turbine blade according to any one of the preceding Claims, characterized in that the top length (CHup) of the chord of the whole blade profile in the position of the top surface (1) is greater than or equal to the bottom 16 length (CHdown) of the chord of the whole blade profile in the position of the bottom surface (2).
5. The turbine blade according to any one of the preceding Claims, characterized in that the chord (CHdown) of the whole blade profile in the position of the bottom surface (2) is slanted relative to the chord (CHup) of the whole blade profile in the position of the top surface (1) at an angle (b) ranging from 0° to 45°, and preferably ranging from 10° to 20°.
6. The turbine blade according to any one of the preceding Claims, characterized in that the position of the external edge (3up) of the leading surface (3) in the top surface (1 ) is linearly dislocated along the blade rotation axis (O) outward in the direction from the external edge (3down) of the leading surface (3) in the bottom surface (2) to a certain distance (M), wherein the ratio (M:CHup) of this given dislocation distance (M) to the whole blade profile top chord length (CHup) ranges from 0.05 to 0.75.
7. A turbine comprising
a hub (7) which is rotatable about a rotation axis (O), and
a number of turbine blades as defined in any one of Claims 1 -6 which are mounted circumferentially on the hub (7),
wherein an acute angle (g) of a slant of the chord (CHdown) of the whole blade profile in the position of the bottom surface (2) relative to the rotation axis (O) of the hub (7) ranges from -25° to +55°.
PCT/PL2019/000043 2018-05-21 2019-05-20 A turbine blade and a turbine comprising such a blade WO2019226060A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
PLP.425656 2018-05-21
PL42565618A PL425656A1 (en) 2018-05-21 2018-05-21 Turbine blade

Publications (2)

Publication Number Publication Date
WO2019226060A1 WO2019226060A1 (en) 2019-11-28
WO2019226060A4 true WO2019226060A4 (en) 2020-01-23

Family

ID=67070893

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/PL2019/000043 WO2019226060A1 (en) 2018-05-21 2019-05-20 A turbine blade and a turbine comprising such a blade

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PL (1) PL425656A1 (en)
WO (1) WO2019226060A1 (en)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112065658B (en) * 2020-08-24 2022-07-08 河南恒聚新能源设备有限公司 Moving blade and vertical axis turbine wind power generation device
CN114183296B (en) * 2021-11-10 2022-06-21 常州市宏发纵横新材料科技股份有限公司 Wind-powered electricity generation blade spanwise piecemeal connection structure

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
PL186359B1 (en) 1997-11-26 2003-12-31 Latyszew Mikolaj Axial-flow water turbine runner vane
ES2294927B1 (en) 2006-05-31 2009-02-16 Gamesa Eolica, S.A. AIRLINER SHOVEL WITH DIVERGING OUTPUT EDGE.
WO2009105835A1 (en) * 2008-02-28 2009-09-03 Windworks Engineering Limited An airfoil for a vertical axis wind turbine
US8393872B2 (en) 2009-10-23 2013-03-12 General Electric Company Turbine airfoil
US9085984B2 (en) * 2012-07-10 2015-07-21 General Electric Company Airfoil
CN104420888B (en) * 2013-08-19 2016-04-20 中国科学院工程热物理研究所 Convergent runner transonic turbine blade and apply its turbine
JP6490421B2 (en) * 2014-12-25 2019-03-27 テラル株式会社 Rotor

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Publication number Publication date
PL425656A1 (en) 2019-12-02
WO2019226060A1 (en) 2019-11-28

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