WO2005040559A1 - High lift rotor or stator blades with multiple adjacent airfoils cross-section - Google Patents

High lift rotor or stator blades with multiple adjacent airfoils cross-section Download PDF

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Publication number
WO2005040559A1
WO2005040559A1 PCT/EP2004/011546 EP2004011546W WO2005040559A1 WO 2005040559 A1 WO2005040559 A1 WO 2005040559A1 EP 2004011546 W EP2004011546 W EP 2004011546W WO 2005040559 A1 WO2005040559 A1 WO 2005040559A1
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WO
WIPO (PCT)
Prior art keywords
high lift
lift rotor
stator blades
fin
fins
Prior art date
Application number
PCT/EP2004/011546
Other languages
French (fr)
Inventor
Paolo Pietricola
Original Assignee
Paolo Pietricola
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 Paolo Pietricola filed Critical Paolo Pietricola
Priority to EP04790405A priority Critical patent/EP1687511A1/en
Publication of WO2005040559A1 publication Critical patent/WO2005040559A1/en

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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
    • F01D5/146—Shape, i.e. outer, aerodynamic form of blades with tandem configuration, split blades or slotted blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • F04D29/544—Blade shapes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F04D29/682—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid extraction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F04D29/684—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid injection
    • 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
    • F05D2240/301—Cross-sectional characteristics

Definitions

  • This invention relates to high performance rotor or stator blades and more particularly for applications in variable pitch fan (adopting- the twisted stator row upstream the rotor as well the rotor blades described in the patent application WO02055845 "A Turbine Engine"), turbo-machinery and wind turbine.
  • variable pitch systems especially applied to fan assemblies, introduce problems in the achievable performance and in the stall flutter because of the reduced number of blades. Indeed, the lower the number of blades and: the lower the efficiency; the lower the performance; and the ligher the pressure losses.
  • Fig. la and lb show the main geometric characteristics of the airfoils (a is the trailing edge, u is the leading edge, d is the upper surface, u is the lower surface, c is the chord and m is the middle line) and the attach angles ⁇ , respectively, in a traditional concave-convex airfoil and in a MAS concave-convex one;
  • Fig. 2a and 2b outline the streamlines path and the average speeds v in the boundary layer on the upper surface, respectively, in a traditional airfoil and in a MAS one (note that the main airfoil P, the attach angle and the external conditions are the same in both the airfoils) ;
  • Fig. 3a, 3b and 3c define, respectively, the speed triangle upstream an axial compressor stage and the speed triangles downstream the same compressor stage realized with traditional airfoils and with MAS ones;
  • Fig. 4a 7 4b and 4c define, respectively, the speed triangle upstream an axial turbine stage and the speed triangles downstream the same turbine stage realized with traditional airfoils and with MAS ones;
  • Fig. 5 show few examples of MAS airfoils: 1 is the main fin; 2 ⁇ 2n' are the fin located upstream the leading edge; 3 ⁇ 3n' is the fin located downstream the trailing edge; S ⁇ Sn' are the slots; and P is the main airfoils which circumscribes all the fin's airfoils; Fig.
  • FIG. 6a, 6b and ⁇ c respectively, show the rotor blade of a variable pitch fan in frontal, lateral and perspective views and the relative cross-sections in which are recognizable the multiple adjacent airfoils fins 1 and 2 as well the main airfoils P;
  • Fig. 7 sketch out few examples of general MAB plane shapes
  • Fig. 8, 9 and 10 show few examples of rotor MAB
  • Fig. 11 shows few different design chose of the same tapered rotor MAB: 1 is the main fin; 2 is the secondary fin; t is the tip fin that reduces the free vortex generation and has a structural function while t' is the 'tip fin further useful to achieves the blades performance; h is the root fin that has only structural function (It's the hub in fix pitch or the base-plate in variable pitch) while h' is the root fin useful also to achieves the blades performance; and a is the projection among the fins needed to strengths the blades, protects the shape of the slots and avoids vortices propagation; it is underlined that it is possible to design any combination among the shape and type of MAB, with several MAS and projections a both for rotor or stator blades;
  • Fig. 12 shows the example of a twisted stator blade
  • Fig. 13 shows the example of the variable pitch rotor 110 with the MAB 30 shown in Fig. 6;
  • Fig. 14 shows the example of the rotor 120 of an axial compressor with the MAB 40
  • Fig. 15 shows the example of the rotor 130 of a centrifugal pump with the MAB 50.
  • the air-flow that encircles the upper surface increases continuously the speed and decreases the pressure from the leading edge towards the airfoil thickest point. Instead, from the thickest point moving towards the trailing edge the air-speed decreases and there is the pressure recovery; but, inside the boundary layer, the particles closer to the airfoil surface endure a greater air-speed deceleration than the expected one because of the energy loses due to the friction. In this latter case, it can be considered that the particles assume an opposite direction to the motion and are generated vortices. Thus, on the upper surface of the airfoil there is the separation of the boundary layer.
  • the stall flutter depends from the number of the blades and more particularly depends from the solidity, the ratio between the chords and the mechanical pitch (distance between the airfoils) : the separation point moves towards the trailing edge increasing the solidity.
  • the traditional technique it is possible to design airfoil with high camber that work with high values of attach angles only when the solidity has very high values.
  • the airfoils camber increase closer to the hub.
  • the first object of this invention to provide rotor blades to increase both the lift and the efficiency of the propellers, especially with low values of the solidity.
  • it has to be increased the rotor blades camber but moving the boundary layer separation points towards the trailing edges. Therefore it's necessary to increase the energy of the boundary layer on the upper surface of the airfoils.
  • a useful solution is the MAB. Indeed introducing the slots S, shaped between the fins, part of the energy of the lower-surface 7 s boundary layer is carried to the upper-surface's one. Referring to the Fig.
  • the particles of the boundary layer in the point D are mixed with the higher energy particles that come from the slot S.
  • the energy of the boundary layer is bigger than in the traditional airfoil and the separation point is moved towards the trailing edge even with high camber.
  • it's possible to increase the lift because of the increased surface. Referring to Fig. 1 and Fig. 2, it's evident that the total surface of a traditional airfoil is lower than the surface of a MAS one which has the same main airfoil P.
  • it's necessary to increases the work L that the rotor blades supply to the flow.
  • the following description it has been referred to axial applications, but the same theory and results can be applied to centrifugal ones. From the energetic equations of the fluid, it's obtained a relation called "equation of the work to the differences of kinetic energies" that it's suitable to estimate the pressure rise by the propeller and the axial compressors.
  • the work is expressed in relation to the absolute kinetic energies C, of the relative energies W and of the driving energies U; and the work L is dues to the change of these speeds amongst the sections upstream and downstream the rotor blades.
  • Fig. 3 show a graphical comparison between two similar stages of an axial compressor. The stagger angles, the mechanical pitch and the operating conditions are the same in both the configurations, but not the airfoils.
  • the speed triangle upstream the rotors rows is the same; instead the speed triangles downstream the rotor row are sketched out considering the maximum deflection allowed by the airfoils without incur in the stall flutter. It's
  • stator blades to increase both the rotor efficiency and the rotor pressure ratio, especially with low values of the solidity.
  • it has to be increased the stator blades camber but moving the boundary layer separation points towards the trailing edges. Indeed, increasing the streamline deflections of the stator row without incur in the stall flutter, the rotor stagger angles can be decreased (increasing the rotor efficiency) and the attach angles increase (increasing the rotor pressure ratio) .
  • the solution is therefore to adopt stator MAB.
  • rotor blades to increase the energy achievable from the turbines, especially with low values of the solidity. In order to achieve this objective it's necessary to increase the work L that the rotor blades capture from the flow. With the same theory illustrated above for the operating machine, it is known that the energy absorbed from the axial turbines is proportional to the following equation:
  • Fig. 4 show a graphical comparison between two similar stages of an axial turbine. The stagger angles, the mechanical pitch and the operating conditions are the same in both the configurations, but not the airfoils.
  • the speed triangle upstream the rotors rows is the same; instead the speed triangles downstream the rotor row are sketched out considering the maximum deflection allowed by the airfoils without incur in the stall flutter. It's

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Geometry (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

High lift rotor or stator blades with multiple adjacent airfoils cross-section, constituted from a main fin 1 and from at least one other secondary fin 2 and/or 3 joined through a root h and a tip t, and in the span between the root and tip is always imaginable a main airfoil P that circumscribes all the fin's airfoils. The peculiarity of this blades consists in the slots between the fins that enables transfering part of the air-flow with high energy, from the lower to the upper surface of the blades, with consequent increases of the boundary layer energy on the upper surface. Adopting the slots is possible to design blades that have both the camber and the surface greater than the actual blades in use, consequently increasing the lift and delaying the onset of the stall flutter.

Description

High lift rotor or stator blades with multiple adjacent airfoils cross-section.
Description
This invention relates to high performance rotor or stator blades and more particularly for applications in variable pitch fan (adopting- the twisted stator row upstream the rotor as well the rotor blades described in the patent application WO02055845 "A Turbine Engine"), turbo-machinery and wind turbine. The variable pitch systems, especially applied to fan assemblies, introduce problems in the achievable performance and in the stall flutter because of the reduced number of blades. Indeed, the lower the number of blades and: the lower the efficiency; the lower the performance; and the ligher the pressure losses. The fact is that reducing the number of blades: both the work and the lift coefficient decrease because of the reduced stream line deflection amongst the airfoils leading and trailing edges; the aerodynamic forces decrrease because of the lower rotor blades surface and the lower lift coefficient; the pressure loses increase and the efficiency decrease because of the boundary layer detachment point, on the airfoils upper surface, moves towards the leading edge. It is therefore the main object of this invention to provide blades which have big surfaces, big camber and boundary layer detachment points closed to the trailing edge; even if applied in stator and rotor rows with both low number of blades and high attach angles .
The blades according to the invention will be referred hereafter with the acronym MAB "Multiple Airfoils Blade"; instead the multiple adjacent airfoils cross-section will be referred hereafter with the acronym MAS "Multiple Airfoils Section". The objects of this invention will become readily apparent from the following description of the drawing in which:
Fig. la and lb show the main geometric characteristics of the airfoils (a is the trailing edge, u is the leading edge, d is the upper surface, u is the lower surface, c is the chord and m is the middle line) and the attach angles α, respectively, in a traditional concave-convex airfoil and in a MAS concave-convex one; Fig. 2a and 2b outline the streamlines path and the average speeds v in the boundary layer on the upper surface, respectively, in a traditional airfoil and in a MAS one (note that the main airfoil P, the attach angle and the external conditions are the same in both the airfoils) ;
Fig. 3a, 3b and 3c define, respectively, the speed triangle upstream an axial compressor stage and the speed triangles downstream the same compressor stage realized with traditional airfoils and with MAS ones; Fig. 4a7 4b and 4c define, respectively, the speed triangle upstream an axial turbine stage and the speed triangles downstream the same turbine stage realized with traditional airfoils and with MAS ones; Fig. 5 show few examples of MAS airfoils: 1 is the main fin; 2÷2n' are the fin located upstream the leading edge; 3÷3n' is the fin located downstream the trailing edge; S÷Sn' are the slots; and P is the main airfoils which circumscribes all the fin's airfoils; Fig. 6a, 6b and βc, respectively, show the rotor blade of a variable pitch fan in frontal, lateral and perspective views and the relative cross-sections in which are recognizable the multiple adjacent airfoils fins 1 and 2 as well the main airfoils P;
Fig. 7 sketch out few examples of general MAB plane shapes;
Fig. 8, 9 and 10 show few examples of rotor MAB;
Fig. 11 shows few different design chose of the same tapered rotor MAB: 1 is the main fin; 2 is the secondary fin; t is the tip fin that reduces the free vortex generation and has a structural function while t' is the 'tip fin further useful to achieves the blades performance; h is the root fin that has only structural function (It's the hub in fix pitch or the base-plate in variable pitch) while h' is the root fin useful also to achieves the blades performance; and a is the projection among the fins needed to strengths the blades, protects the shape of the slots and avoids vortices propagation; it is underlined that it is possible to design any combination among the shape and type of MAB, with several MAS and projections a both for rotor or stator blades;
Fig. 12 shows the example of a twisted stator blade
20, partially constituted from MAS airfoils, lodged inside one Air-Intake 100; Fig. 13 shows the example of the variable pitch rotor 110 with the MAB 30 shown in Fig. 6;
Fig. 14 shows the example of the rotor 120 of an axial compressor with the MAB 40;
Fig. 15 shows the example of the rotor 130 of a centrifugal pump with the MAB 50.
Referring to Fig. 2, with positive attach angles, the air-flow that encircles the upper surface increases continuously the speed and decreases the pressure from the leading edge towards the airfoil thickest point. Instead, from the thickest point moving towards the trailing edge the air-speed decreases and there is the pressure recovery; but, inside the boundary layer, the particles closer to the airfoil surface endure a greater air-speed deceleration than the expected one because of the energy loses due to the friction. In this latter case, it can be considered that the particles assume an opposite direction to the motion and are generated vortices. Thus, on the upper surface of the airfoil there is the separation of the boundary layer. When the separation point moves towards the leading edge the streamlines don't follow anymore the airfoil deflection (see point D in Fig. 2a) and a lot of vortices becomes generated; it does appear the stall flutter. It's clear that the vortices always dissolve energy and the higher the vortices propagation beyond the trailing edge and the lower are both the aerodynamic and acoustic efficiencies. The separation point moves towards, the leading edge increasing the camber and the attach angles. Moreover, both in stator and rotor row applications, the stall flutter depends from the number of the blades and more particularly depends from the solidity, the ratio between the chords and the mechanical pitch (distance between the airfoils) : the separation point moves towards the trailing edge increasing the solidity. Thus, with the traditional technique, it is possible to design airfoil with high camber that work with high values of attach angles only when the solidity has very high values. For example it can be considered the different camber of the propeller airfoils in the actual turbo-fan: the airfoils camber increase closer to the hub. After this consideration it is simpler to understand the reason that didn't allows to the variable pitch rotor to be developed in turbo-fan and turbo- machinery. Indeed, in these latter applications the benefits concerning the variable pitch technique become sensibly reduced with the reduction of the rotor blades (reduced values of the solidity) . It is therefore the first object of this invention to provide rotor blades to increase both the lift and the efficiency of the propellers, especially with low values of the solidity. In order to achieve this objective it has to be increased the rotor blades camber but moving the boundary layer separation points towards the trailing edges. Therefore it's necessary to increase the energy of the boundary layer on the upper surface of the airfoils. A useful solution is the MAB. Indeed introducing the slots S, shaped between the fins, part of the energy of the lower-surface7 s boundary layer is carried to the upper-surface's one. Referring to the Fig. 2b, the particles of the boundary layer in the point D are mixed with the higher energy particles that come from the slot S. Thus, in the point C the energy of the boundary layer is bigger than in the traditional airfoil and the separation point is moved towards the trailing edge even with high camber. Furthermore it's possible to increase the lift because of the increased surface. Referring to Fig. 1 and Fig. 2, it's evident that the total surface of a traditional airfoil is lower than the surface of a MAS one which has the same main airfoil P.
It is a still further object of this invention to provide rotor blades to increase the compressors and fans pressure ratio, especially with low values of the solidity. In order to achieve this objective it's necessary to increases the work L that the rotor blades supply to the flow. The following description it has been referred to axial applications, but the same theory and results can be applied to centrifugal ones. From the energetic equations of the fluid, it's obtained a relation called "equation of the work to the differences of kinetic energies" that it's suitable to estimate the pressure rise by the propeller and the axial compressors. The work is expressed in relation to the absolute kinetic energies C, of the relative energies W and of the driving energies U; and the work L is dues to the change of these speeds amongst the sections upstream and downstream the rotor blades. In the compressors, pumps, fans, propellers, and more generally in the operating machine:
L = (C2 2 - C?) I2 + (W2 - W?)I 2 + (U2 2 - U )l' 2
In axial machines, it's possible to consider the same driving speed U for both the leading and trailing edges (Ui = U2 = U = Cost.) . Defining y the angles between the absolute speeds C and the driving ones U, and referring to the Carnot theorem, is obtained the "Euler" equation of the work: = U2 • C2 • cos.y2 - Ul ■ Cl ■ cosyl = U ■ (C2 ■ cosy2 - Cl ■ cos^)
It's clear that to increase the work it's necessary
to increase C2 - cosy2 and/or decrease , • cosy1. In
practice it's necessary to increase the deflection of the streamlines among the rotor airfoils. That can be done in one hand increasing the camber of the rotor airfoils, in the other hand increasing the attach angles. Thus the proposed solution is again the MAB. Fig. 3, show a graphical comparison between two similar stages of an axial compressor. The stagger angles, the mechanical pitch and the operating conditions are the same in both the configurations, but not the airfoils. Thus the speed triangle upstream the rotors rows is the same; instead the speed triangles downstream the rotor row are sketched out considering the maximum deflection allowed by the airfoils without incur in the stall flutter. It's
evident that C2 ' - cosy2' is bigger than C2-cos'2 and
therefore that increasing the streamline deflection it's increased the work conferred to the gas or fluid.
It is a still further object of this invention to provide stator blades to increase both the rotor efficiency and the rotor pressure ratio, especially with low values of the solidity. In order to achieve this objective it has to be increased the stator blades camber but moving the boundary layer separation points towards the trailing edges. Indeed, increasing the streamline deflections of the stator row without incur in the stall flutter, the rotor stagger angles can be decreased (increasing the rotor efficiency) and the attach angles increase (increasing the rotor pressure ratio) . The solution is therefore to adopt stator MAB. It is a still further object of this invention to provide rotor blades to increase the energy achievable from the turbines, especially with low values of the solidity. In order to achieve this objective it's necessary to increase the work L that the rotor blades capture from the flow. With the same theory illustrated above for the operating machine, it is known that the energy absorbed from the axial turbines is proportional to the following equation:
L = U - (Cl ■ COSJ/J -C2 -cos >2)
As described for the axial compressor stage, to
increase the work it's necessary to increase C2-cos_>2
and/or decreaseC, -cos . In practice it's again
necessary to increase the deflection of the streamlines among the rotor airfoils. That can be done in one hand increasing the camber of the rotor airfoils, in the other hand increasing the attach angles. Thus the proposed solution is again the MAB. Fig. 4, show a graphical comparison between two similar stages of an axial turbine. The stagger angles, the mechanical pitch and the operating conditions are the same in both the configurations, but not the airfoils. Thus the speed triangle upstream the rotors rows is the same; instead the speed triangles downstream the rotor row are sketched out considering the maximum deflection allowed by the airfoils without incur in the stall flutter. It's
evident that C2 ' - cosy2 is bigger than C2-cos'2 and
therefore that increasing both the gas and fluid streamline deflection it's increased the attainable energy.

Claims

Claims 1. High lift rotor or stator blades having multiple adjacent airfoils cross-section, said airfoils being partially or completely placed on themselves; the blades being constituted by a main fin (1) and by at least a second fin (2) placed nearby the leading edge of the main fin (1) , and/or at least a third fin (3) placed nearby the trailing edge of the main fin; the secondary fin being located close to the upper and/or lower surface of the main fin (1); said fins (1,2,3) being joined through a root (h) and a tip (t) forming, in the span between them, a main airfoil (p) that circumscribes all the airfoils of the fins; each of said blades having at least one slot (S) that provide to transfer part of the flow, with high energy, from the lower to the upper surface of the blades, with consequent increases of the boundary layer energy on the upper surface .
2. High lift rotor or stator blades according to claim 1, characterised in that the second fins (2) are two or more .
3. High lift rotor or stator blades according to claim 1, characterised in that the third fins (2) are two or more.
4. High lift rotor or stator blades according to claim 1, characterized in that the blades, as well the fins (1,2,3), are twisted and/or untwisted, tapered and/or with a constant chord, with or without a movable part, completely adjustable or fixed.
5. High lift rotor or stator blades according to claim 1, characterized in that each blade on the whole is single, being the fins joined through a root (h) and a tip (t) that reduce the external free vortices; said blades being realized both from several assembled pieces or from a single one.
6. High lift rotor or stator blades according to the claim 1, characterized in that the dimensions of the slots (S) are similar and/or different to the dimensions of the fin's chords.
7. High lift rotor or stator blades according to the claim 1, characterized in that the dimension of the main fin chord is similar and/or different to the dimensions of the secondary fins chords.
8. High lift rotor or stator blades according to the claim 1, characterized in that the airflow and the boundary layer across the slots (S) are of the laminar and/or turbulent types.
9. High lift rotor or stator blades according to claim 1, characterized in that the airfoils of the fins, as well the main airfoil (p) , are thick or thin are of the symmetrical, conventional cambered, reflexed, aft-loaded, supercritical type or a combination of the former characteristics.
10. High lift rotor or stator blades according to claim 1, characterized in that the slots (S) are of the convergent, divergent and/or with constant area type, in the axial and radial directions.
11. High lift rotor or stator blades according to claim 1, characterized in that among the fins is placed at least one laminar or curved projection (a) that strengths the blades, protects the shape of the slot and avoids vortices propagation.
12. High lift rotor or stator blades according to claim 11, characterized in that the projection (a) has the plane shape coincident with the main airfoil (P) or a different shape; the shape of said projection is thus contained in the main airfoil (P) perimeter or not.
13. High lift rotor or stator blades according to claim 1, characterized in that at least one fin is rotatable in respect of the other ones so that to modify the shape of the slot (S) .
14. High lift rotor or stator blades according to claim 1, characterized in that at least in one section of the blade the flow is transonic or supersonic; and the upstream fin produces shock waves allowing to the following fins to work with subsonic flow.
15. High lift rotor or stator blades according to claim 1, characterized in that the blades are realized in superconductor material ad they are crossed from high density electrical currents so that to generate high magnetic field.
16. High lift rotor or stator blades according to claim 1, characterized in that a plurality of the bladesw are employed in turbine engine, axial & centrifugal compressors, axial & centrifugal ventilator, propeller, fan, axial & centrifugal pumps, axial & centrifugal turbines in aeronautical, maritime and space fields.
PCT/EP2004/011546 2003-10-17 2004-10-14 High lift rotor or stator blades with multiple adjacent airfoils cross-section WO2005040559A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP04790405A EP1687511A1 (en) 2003-10-17 2004-10-14 High lift rotor or stator blades with multiple adjacent airfoils cross-section

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
ITBA2003A000052 2003-10-17
IT000052A ITBA20030052A1 (en) 2003-10-17 2003-10-17 ROTORIC AND STATHIC POLES WITH MULTIPLE PROFILES

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WO2005040559A1 true WO2005040559A1 (en) 2005-05-06

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IT (1) ITBA20030052A1 (en)
WO (1) WO2005040559A1 (en)

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WO2007105174A1 (en) 2006-03-14 2007-09-20 Tecsis Tecnologia E Sistemas Avançados Ltda Multi-element blade with aerodynamic profiles
EP1947293A1 (en) * 2007-01-18 2008-07-23 Siemens Aktiengesellschaft Guide vane for a gas turbine
GB2455095A (en) * 2007-11-28 2009-06-03 Rolls Royce Plc Gas turbine engine blade arrangement
EP2078824A1 (en) * 2008-01-10 2009-07-15 Snecma Double-blade with wings
EP2092163A1 (en) * 2006-11-14 2009-08-26 Volvo Aero Corporation Vane assembly configured for turning a flow ina a gas turbine engine, a stator component comprising the vane assembly, a gas turbine and an aircraft jet engine
EP2107235A1 (en) * 2008-04-02 2009-10-07 Lm Glasfiber A/S A wind turbine blade with an auxiliary airfoil
WO2010125599A3 (en) * 2009-04-27 2011-06-03 Leonardo Valentini Rotor blade with aerodynamic flow static diverter for vertical axis wind turbine
JP2011521169A (en) * 2008-05-27 2011-07-21 ビンドテック トルシャウン アンパーツゼルスカブ Blades for wind turbine or hydro turbine rotor
US20120148396A1 (en) * 2010-12-08 2012-06-14 Rolls-Royce Deutschland Ltd & Co Kg Fluid-flow machine - blade with hybrid profile configuration
US20130170969A1 (en) * 2012-01-04 2013-07-04 General Electric Company Turbine Diffuser
US20130209224A1 (en) * 2012-02-10 2013-08-15 Mtu Aero Engines Gmbh Turbomachine
WO2015044615A1 (en) 2013-09-30 2015-04-02 Electricfil Automotive Rotor for a vertical-axis wind turbine
DE102014203601A1 (en) * 2014-02-27 2015-08-27 Rolls-Royce Deutschland Ltd & Co Kg Blade row group
DE102014203604A1 (en) * 2014-02-27 2015-08-27 Rolls-Royce Deutschland Ltd & Co Kg Blade row group
EP2977548A1 (en) * 2014-07-22 2016-01-27 Techspace Aero S.A. Axial turbomachine compressor blade with branches
US20160024933A1 (en) * 2014-07-22 2016-01-28 Techspace Aero S.A. Blading with branches on the shroud of an axial-flow turbomachine compressor
US20160024932A1 (en) * 2014-07-22 2016-01-28 Techspace Aero S.A. Axial turbomachine compressor blade with branches at the base and at the head of the blade
JPWO2015072256A1 (en) * 2013-11-15 2017-03-16 株式会社Ihi Axial turbomachine blade structure and gas turbine engine
EP3255244A1 (en) * 2016-05-20 2017-12-13 United Technologies Corporation Tandem tip blades and corresponding gas turbine engine
US20180195528A1 (en) * 2017-01-09 2018-07-12 Rolls-Royce Coporation Fluid diodes with ridges to control boundary layer in axial compressor stator vane
EP3388663A4 (en) * 2015-12-10 2018-12-05 Li, Yibo Blade capable of efficiently utilizing low velocity fluid, and application of blade
GB2591298A (en) * 2020-01-27 2021-07-28 Gkn Aerospace Sweden Ab Outlet guide vane cooler
SE2050686A1 (en) * 2020-06-10 2021-12-11 Carlson Bjoern Vertical wind turbine
EP3940199A1 (en) * 2020-07-13 2022-01-19 Honeywell International Inc. System and method for air injection passageway integration and optimization in turbomachinery
FR3118792A1 (en) * 2021-01-14 2022-07-15 Safran Aircraft Engines MODULE FOR AN AIRCRAFT TURBOMACHINE
US11448236B2 (en) * 2018-08-17 2022-09-20 Siemens Energy Global GmbH & Co. KG Outlet guide vane

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US8647063B2 (en) 2006-03-14 2014-02-11 Tecsis Tecnologia Sistemas Avançados S.A. Multi-element blade with aerodynamic profiles
EP2092163A4 (en) * 2006-11-14 2013-04-17 Volvo Aero Corp Vane assembly configured for turning a flow ina a gas turbine engine, a stator component comprising the vane assembly, a gas turbine and an aircraft jet engine
EP2092163A1 (en) * 2006-11-14 2009-08-26 Volvo Aero Corporation Vane assembly configured for turning a flow ina a gas turbine engine, a stator component comprising the vane assembly, a gas turbine and an aircraft jet engine
US8257032B2 (en) 2007-01-18 2012-09-04 Siemens Aktiengesellschaft Gas turbine with a guide vane
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US8282357B2 (en) 2007-11-28 2012-10-09 Rolls-Royce Plc Turbine blade
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US8021113B2 (en) 2008-01-10 2011-09-20 Snecma Twin-airfoil blade with spacer strips
WO2009121927A1 (en) * 2008-04-02 2009-10-08 Lm Glasfiber A/S A wind turbine blade with an auxiliary airfoil
US8834130B2 (en) 2008-04-02 2014-09-16 Peter Fuglsang Wind turbine blade with an auxiliary airfoil
EP2107235A1 (en) * 2008-04-02 2009-10-07 Lm Glasfiber A/S A wind turbine blade with an auxiliary airfoil
JP2011521169A (en) * 2008-05-27 2011-07-21 ビンドテック トルシャウン アンパーツゼルスカブ Blades for wind turbine or hydro turbine rotor
WO2010125599A3 (en) * 2009-04-27 2011-06-03 Leonardo Valentini Rotor blade with aerodynamic flow static diverter for vertical axis wind turbine
US20120148396A1 (en) * 2010-12-08 2012-06-14 Rolls-Royce Deutschland Ltd & Co Kg Fluid-flow machine - blade with hybrid profile configuration
EP2463480A3 (en) * 2010-12-08 2014-07-23 Rolls-Royce Deutschland Ltd & Co KG Blade with hybrid airfoil
US9394794B2 (en) 2010-12-08 2016-07-19 Rolls-Royce Deutschland Ltd & Co Kg Fluid-flow machine—blade with hybrid profile configuration
US20130170969A1 (en) * 2012-01-04 2013-07-04 General Electric Company Turbine Diffuser
CN103195572A (en) * 2012-01-04 2013-07-10 通用电气公司 Turbine diffuser
US20130209224A1 (en) * 2012-02-10 2013-08-15 Mtu Aero Engines Gmbh Turbomachine
US10184339B2 (en) * 2012-02-10 2019-01-22 Mtu Aero Engines Gmbh Turbomachine
WO2015044615A1 (en) 2013-09-30 2015-04-02 Electricfil Automotive Rotor for a vertical-axis wind turbine
FR3011285A1 (en) * 2013-09-30 2015-04-03 Electricfil Automotive ROTOR FOR WIND TURBINE IN PARTICULAR VERTICAL AXIS
EP3070264A4 (en) * 2013-11-15 2017-06-21 IHI Corporation Vane structure for axial flow turbomachine and gas turbine engine
JPWO2015072256A1 (en) * 2013-11-15 2017-03-16 株式会社Ihi Axial turbomachine blade structure and gas turbine engine
DE102014203601A1 (en) * 2014-02-27 2015-08-27 Rolls-Royce Deutschland Ltd & Co Kg Blade row group
DE102014203604A1 (en) * 2014-02-27 2015-08-27 Rolls-Royce Deutschland Ltd & Co Kg Blade row group
US10337524B2 (en) 2014-02-27 2019-07-02 Rolls-Royce Deutschland Ltd & Co Kg Group of blade rows
US10113430B2 (en) 2014-02-27 2018-10-30 Rolls-Royce Deutschland Ltd & Co Kg Group of blade rows
EP2977548A1 (en) * 2014-07-22 2016-01-27 Techspace Aero S.A. Axial turbomachine compressor blade with branches
CN105275872A (en) * 2014-07-22 2016-01-27 航空技术空间股份有限公司 Blade with branches for an axial-flow turbomachine compressor
US9863253B2 (en) * 2014-07-22 2018-01-09 Safran Aero Boosters Sa Axial turbomachine compressor blade with branches at the base and at the head of the blade
US9970301B2 (en) 2014-07-22 2018-05-15 Safran Aero Boosters Sa Blade with branches for an axial-flow turbomachine compressor
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US20160024932A1 (en) * 2014-07-22 2016-01-28 Techspace Aero S.A. Axial turbomachine compressor blade with branches at the base and at the head of the blade
US10125612B2 (en) * 2014-07-22 2018-11-13 Safran Aero Boosters Sa Blading with branches on the shroud of an axial-flow turbomachine compressor
US20160024933A1 (en) * 2014-07-22 2016-01-28 Techspace Aero S.A. Blading with branches on the shroud of an axial-flow turbomachine compressor
CN105275872B (en) * 2014-07-22 2019-01-08 赛峰航空助推器股份有限公司 The blade with branch for axial-flow turbine unit compressor
EP3388663A4 (en) * 2015-12-10 2018-12-05 Li, Yibo Blade capable of efficiently utilizing low velocity fluid, and application of blade
US10808678B2 (en) 2015-12-10 2020-10-20 Yibo Li Blade capable of efficiently utilizing low-velocity fluid and application thereof
EP3255244A1 (en) * 2016-05-20 2017-12-13 United Technologies Corporation Tandem tip blades and corresponding gas turbine engine
US10151322B2 (en) 2016-05-20 2018-12-11 United Technologies Corporation Tandem tip blade
US20180195528A1 (en) * 2017-01-09 2018-07-12 Rolls-Royce Coporation Fluid diodes with ridges to control boundary layer in axial compressor stator vane
US10519976B2 (en) * 2017-01-09 2019-12-31 Rolls-Royce Corporation Fluid diodes with ridges to control boundary layer in axial compressor stator vane
US11448236B2 (en) * 2018-08-17 2022-09-20 Siemens Energy Global GmbH & Co. KG Outlet guide vane
GB2591298A (en) * 2020-01-27 2021-07-28 Gkn Aerospace Sweden Ab Outlet guide vane cooler
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SE544250C2 (en) * 2020-06-10 2022-03-15 Carlson Bjoern Vertical wind turbine
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EP3940199A1 (en) * 2020-07-13 2022-01-19 Honeywell International Inc. System and method for air injection passageway integration and optimization in turbomachinery
US11608744B2 (en) 2020-07-13 2023-03-21 Honeywell International Inc. System and method for air injection passageway integration and optimization in turbomachinery
FR3118792A1 (en) * 2021-01-14 2022-07-15 Safran Aircraft Engines MODULE FOR AN AIRCRAFT TURBOMACHINE

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