US20100310357A1 - Ring wing-type actinic fluid drive - Google Patents

Ring wing-type actinic fluid drive Download PDF

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Publication number
US20100310357A1
US20100310357A1 US12/745,744 US74574408A US2010310357A1 US 20100310357 A1 US20100310357 A1 US 20100310357A1 US 74574408 A US74574408 A US 74574408A US 2010310357 A1 US2010310357 A1 US 2010310357A1
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US
United States
Prior art keywords
actinic
fluid drive
ring wing
angle
main flow
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.)
Abandoned
Application number
US12/745,744
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English (en)
Inventor
Nikolaos Papageorgiou
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Individual
Original Assignee
Individual
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
Priority claimed from GR20070100750A external-priority patent/GR1006157B/el
Priority claimed from GR20080100707A external-priority patent/GR20080100707A/el
Application filed by Individual filed Critical Individual
Publication of US20100310357A1 publication Critical patent/US20100310357A1/en
Abandoned legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • F04D17/08—Centrifugal pumps
    • F04D17/16—Centrifugal pumps for displacing without appreciable compression
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63H—MARINE PROPULSION OR STEERING
    • B63H1/00—Propulsive elements directly acting on water
    • B63H1/02—Propulsive elements directly acting on water of rotary type
    • B63H1/12—Propulsive elements directly acting on water of rotary type with rotation axis substantially in propulsive direction
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/10—Shape of wings
    • B64C3/14—Aerofoil profile
    • B64C3/141—Circulation Control Airfoils
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/001—Flying saucers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/06—Aircraft not otherwise provided for having disc- or ring-shaped wings
    • B64C39/062—Aircraft not otherwise provided for having disc- or ring-shaped wings having annular wings
    • B64C39/064—Aircraft not otherwise provided for having disc- or ring-shaped wings having annular wings with radial airflow
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • F04D17/08—Centrifugal pumps
    • F04D17/16—Centrifugal pumps for displacing without appreciable compression
    • F04D17/161—Shear force pumps
    • 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
    • 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
    • F05B2250/00—Geometry
    • F05B2250/20—Geometry three-dimensional
    • F05B2250/23—Geometry three-dimensional prismatic
    • F05B2250/232—Geometry three-dimensional prismatic conical
    • 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
    • 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
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/10—Drag reduction

Definitions

  • the invention relates to thrust or fluid drive systems, such as those of fans, pumps, wind power plants, water craft and aircraft.
  • the relative systems utilize an existing flow (repeller) or convert a given power (thermal, electrical, mechanical, etc.) to flow that generates force (or power) when it is applied to the surface of a solid body, which we call a wing.
  • Wings (bearing surfaces) have a leading and a trailing edge, which define the wing chord and present an angle of attack in relation to a flow.
  • a wing must be found in a flow.
  • the fluid drives of pumps, repellers (power generators), ships, aircraft, helicopters, etc. primarily use propellers that form an axial flow (if it does not already exist) and the wings thereof are simultaneously the application surfaces of the generated buoyancy or lift.
  • the known relative systems utilize finite wings (but with wing tips) or resistance surfaces (diffusers) which have power losses due to wing tip vortices and friction, are dangerous, and can be improved.
  • the object of the invention is to create relative actinic (radial flow) thrust or fluid drive systems.
  • the invention either exploits an existing flow (e.g., wind, bulbous bow flow), or forms an actinic main flow which flows around at least one ring wing.
  • a ring wing ( 11 ) (an annular wing) is a body such as a truncated cone, the leading and trailing edges thereof (corresponding to top and bottom surfaces, circular periphery of a truncated cone) define the chord of ring wing ( 11 ) (rectilinear side length) and the latter forms the angle of inclination ( ⁇ ) with the plane of the top surface ( FIG. 1 ).
  • the ring wing surface may have different forms, such as, e.g., a longitudinal grooved form (shark skin), straight, elliptical or curved, or also can be provided with a slit peripherally to the leading edge.
  • An actinic fluid drive is the drive system in which at least one ring wing ( 11 ) is found in an actinic main flow ( 15 ), the direction (plane) of which forms the angle of attack ( ⁇ ) along with the chord on the leading edge of ring wing ( 11 ), this angle of attack being greater than 0 and smaller than 90 degrees—particularly greater than 8 degrees, and the actinic main flow ( 15 ) is inclined (generation of thrust) analogous to the angle of attack ( ⁇ ) according to the Coanda effect ( FIG. 3 ).
  • the characteristic values of the AF are dependent on the velocity of the ambient flow (or transport velocity) and may be adjustable (e.g., by adjustable trailing edge diameter or varied ring wing bottom surface periphery).
  • the main flow ( 15 ) reduces the pressure over the upper side of the ring wing (the lower side of the wing is either without flow or is a closed conductor) and is inclined due to the angle of inclination ( ⁇ ) and the elevated ambient pressure (fluid pressure over the level of main flow) analogous to the angle of attack ( ⁇ ) (Coanda effect); thrust is generated, and the flow becomes laminar.
  • Main flow ( 15 ) here is the flow which is responsible for the function of the AF (it can be produced by a secondary flow, or secondary flows). It can arise directly from an axial flow (ring wing top surface form— FIG. 3 ), from a radial impeller ( 12 ), or indirectly from a secondary flow (two phases).
  • a radial impeller (with one or two intake surfaces) converts an axial flow to a radial flow and can form an actinic flow, or can produce mechanical power from a flow.
  • the thrust of an AF increases if the system comprises ring wings ( 11 ) placed one behind the other, where the second ring wing surrounds the first (the third surrounds the second, etc.) and the angle of inclination ( ⁇ ) of each ring wing ( 11 ) is greater than the previous one.
  • the AF can be provided with a ring conductor ( 13 ), which surrounds the trailing edge of the last ring wing ( 11 ) (ring wing top and bottom surface form) and the main flow ( 15 ) after being conducted to the intake surface of a radial impeller ( 12 ), is recycled to the leading edge of the first ring wing ( 11 ).
  • the closed actinic fluid drive (CAF) is one of the least dangerous, both for the conducting system as well as for the working environment ( FIG. 4 ).
  • the advantages of the AF are: the absence of wing tip vortices, the good efficiency, the small surface area required for the production of a specific power, the safe operation and the large field of application.
  • the AF can replace the propeller for any relative applications and can also reduce the form drag (e.g., in rockets, bulbous bows of ships, aircraft tips, hubs, etc.).
  • the AF can operate, e.g., as: fans, ventilators, two-phase pumps, propulsion or lift generators (water-air propellers), repellers (which produce mechanical power from a flow) and as actinic ring wing profile channel measuring systems.
  • FIG. 1 shows the section of a ring wing ( 11 ).
  • FIG. 2 shows the section of an open actinic fluid drive (OAF) (fresh fluid comes into the system).
  • OAF open actinic fluid drive
  • FIG. 3 shows the section of an OAF for reducing the form drag (e.g. bulbous bow as the ring wing).
  • FIG. 4 shows the section of a CAF.
  • FIG. 5 shows the section of a CAF, which is mounted in a rotatable manner and can also function as a steering wheel (rudder) (e.g., pod—Z drive in ships, repeller).
  • rudder e.g., pod—Z drive in ships, repeller.
  • FIG. 6 shows the section of an AF which can operate as a repeller or a propeller.
  • FIG. 7 shows the section of a CAF which can operate both as a two-phase jet pump as well as a repeller.
  • the surfaces of ring wing ( 11 ) and the leading and trailing edges are oriented by diameters D 1 and D 2 (top and bottom surfaces of the truncated cone) and by the angle of inclination ( ⁇ ).
  • the chord of the ring wing is identical to its side length ( 11 ), the bottom and top surfaces are horizontal and close to one another.
  • FIG. 2 explains an open actinic fluid drive system.
  • Impeller ( 12 ) accelerates a fluid ( 18 ) and forms an actinic main flow ( 15 ) over a ring wing ( 11 ), the chord of which forms the angle of attack ( ⁇ ) along with the flow plane on the impeller outlet ( 12 ) (ring wing leading edge) (the chord here being different from the elliptic side length of the ring wing).
  • the angle of inclination ( ⁇ ) of the ring wing is equal to the angle of attack ( ⁇ ).
  • the same construction can operate as a repeller, whereby a flow ( 18 ) sets impeller ( 12 ) in motion and is converted to main flow ( 15 ) of the system (actinic after the impeller outlet) and the impeller produces power, which drives a rotor ( 20 ).
  • the flow which e.g., a ship (rocket) forms on the bulbous bow (tip) during its movement, is utilized by two ring wings ( 11 ), which produce thrust in the direction of motion.
  • the form of the top surface of the ring wing (curved) forms the actinic main flow ( 15 ) and determines the angle of attack ( ⁇ ), which is not equal to the angle of inclination ( ⁇ ).
  • ⁇ the angle of attack
  • the entire resistance force on the front surface, which forms the actinic main flow is greater than the buoyancy or lift, but smaller than in the case without the ring wing.
  • the AF reduces the overall resistance force and saves energy.
  • impeller ( 12 ) accelerates a closed actinic main flow ( 15 ) over two combined ring wings ( 11 ), the chords of which are not identical to their elliptical bearing surfaces, with the angle of inclination ( ⁇ ), which is equal to the angle of attack ( ⁇ ), being greater for the second wing, and the ring conductor ( 13 ), which surrounds the last ring wing (ring wings with ellipsoid bottom and top surface form) guides the flow ( 15 ) to the intake surface of radial impeller ( 12 ).
  • Conductor ( 13 ) is provided with rotatable blades ( 14 ), which equilibrate the torque of impeller ( 12 ) and permit the rotation of the system around the axis of rotation of impeller ( 12 ).
  • Rotatable blades ( 14 ) are not necessary for a fluid drive system with two impellers (and corresponding ring wings), which rotate in opposite directions (left and right), whereas they are necessary, e.g., in a Diskopter system (corresponding to a helicopter and roll of the tail rotor).
  • impeller ( 12 ) accelerates a closed actinic main flow ( 15 ), which flows around two combined ring wings ( 11 ) and thus form a CAF.
  • the CAF has aero-hydrodynamic form, is mounted in a rotatable manner ( 19 ) (e.g., pod or Z-ship drive) and can function as a steering wheel (rudder).
  • an existing fluid flow ( 18 ) (wind, river, etc.) flows around the outer intake surface of an actinic impeller ( 12 ) as well as peripherally distributed blades ( 16 ) and produces the actinic main flow ( 15 ), which flows around two combined ring wings ( 11 ) and also moves impeller ( 12 ) via a ring conductor ( 13 ) (inner intake surface). Impeller ( 12 ) and blades ( 16 ) produce power, which drives a rotor ( 20 ).
  • the CAF is found within a conductor ( 17 ) and has an aero-hydrodynamic form.
  • a jet pump power is offered to the CAF and an impeller ( 12 ) accelerates the closed main flow ( 15 ), which forms a secondary flow ( 18 ), and ambient fluid ( 18 ) is transported from the inlet to the outlet surface of conductor ( 17 ).
  • the secondary flow ( 18 ) of conductor ( 17 ) generates the main flow ( 15 ) of the CAF and impeller ( 12 ) produces power, which drives a rotor ( 20 ).

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Ocean & Marine Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Sustainable Energy (AREA)
  • Wind Motors (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Other Liquid Machine Or Engine Such As Wave Power Use (AREA)
US12/745,744 2007-12-11 2008-12-02 Ring wing-type actinic fluid drive Abandoned US20100310357A1 (en)

Applications Claiming Priority (5)

Application Number Priority Date Filing Date Title
GR20070100750A GR1006157B (el) 2007-12-11 2007-12-11 Ακτινικο συστημα προωσης-κυκλικη πτερυγα
GR20070100750 2007-12-11
GR20080100707A GR20080100707A (el) 2008-11-03 2008-11-03 Ακτινικη προωση ρευστων-κυκλικη πτερυγα
GR2008011707 2008-11-03
PCT/GR2008/000067 WO2009074834A1 (de) 2007-12-11 2008-12-02 Kreisflügel - aktinischer fluidantrieb (af)

Publications (1)

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US20100310357A1 true US20100310357A1 (en) 2010-12-09

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ID=40561761

Family Applications (1)

Application Number Title Priority Date Filing Date
US12/745,744 Abandoned US20100310357A1 (en) 2007-12-11 2008-12-02 Ring wing-type actinic fluid drive

Country Status (3)

Country Link
US (1) US20100310357A1 (de)
EP (1) EP2252796A1 (de)
WO (1) WO2009074834A1 (de)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8356566B1 (en) 2011-03-18 2013-01-22 David Alan Sellins Multi-directional marine propulsor apparatus
US10464668B2 (en) 2015-09-02 2019-11-05 Jetoptera, Inc. Configuration for vertical take-off and landing system for aerial vehicles
US10875658B2 (en) 2015-09-02 2020-12-29 Jetoptera, Inc. Ejector and airfoil configurations
US11001378B2 (en) 2016-08-08 2021-05-11 Jetoptera, Inc. Configuration for vertical take-off and landing system for aerial vehicles
US11148801B2 (en) 2017-06-27 2021-10-19 Jetoptera, Inc. Configuration for vertical take-off and landing system for aerial vehicles
KR102415854B1 (ko) * 2021-02-24 2022-07-05 주식회사 피제이 무소음 송풍 유닛 및 상기 무소음 송풍 유닛을 포함하는 무소음 비행 추진체
WO2023249139A1 (ko) * 2022-06-23 2023-12-28 주식회사 피제이 무소음 송풍 유닛 및 상기 무소음 송풍 유닛을 포함하는 무소음 비행 추진체

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2486892B (en) 2010-12-23 2017-11-15 Dyson Technology Ltd A fan
GB2486889B (en) 2010-12-23 2017-09-06 Dyson Technology Ltd A fan
GB2486890B (en) 2010-12-23 2017-09-06 Dyson Technology Ltd A fan
GB2492962A (en) 2011-07-15 2013-01-23 Dyson Technology Ltd Fan with tangential inlet to casing passage
GB2492961A (en) 2011-07-15 2013-01-23 Dyson Technology Ltd Fan with impeller and motor inside annular casing
GB2492963A (en) * 2011-07-15 2013-01-23 Dyson Technology Ltd Fan with scroll casing decreasing in cross-section
JP1518058S (de) 2014-01-09 2015-02-23
JP1518059S (de) 2014-01-09 2015-02-23

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2583374A (en) * 1950-10-18 1952-01-22 Hydraulic Supply Mfg Company Exhaust fan
US3203498A (en) * 1959-10-16 1965-08-31 Hovercraft Dev Ltd Vehicles supported on a cushion of air with recovery means for escaping curtain fluid
US3489374A (en) * 1968-03-25 1970-01-13 Paul J Morcom Air-ground vehicle
US3543781A (en) * 1968-06-26 1970-12-01 John A C Kentfield Fluid rectifiers
US5503351A (en) * 1994-09-06 1996-04-02 Vass; Gabor I. Circular wing aircraft
US6123618A (en) * 1997-07-31 2000-09-26 Jetfan Australia Pty. Ltd. Air movement apparatus

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB129142A (en) * 1918-07-19 1919-07-10 Austin Cairns Improvements in Means for Propelling Aërial Machines.
FR860896A (fr) * 1938-10-22 1941-01-25 Brev Et Procedes Coanda Sa D E Perfectionnements aux injecteurs et éjecteurs
FR2082745A5 (de) * 1970-05-25 1971-12-10 Comp Generale Electricite

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2583374A (en) * 1950-10-18 1952-01-22 Hydraulic Supply Mfg Company Exhaust fan
US3203498A (en) * 1959-10-16 1965-08-31 Hovercraft Dev Ltd Vehicles supported on a cushion of air with recovery means for escaping curtain fluid
US3489374A (en) * 1968-03-25 1970-01-13 Paul J Morcom Air-ground vehicle
US3543781A (en) * 1968-06-26 1970-12-01 John A C Kentfield Fluid rectifiers
US5503351A (en) * 1994-09-06 1996-04-02 Vass; Gabor I. Circular wing aircraft
US6123618A (en) * 1997-07-31 2000-09-26 Jetfan Australia Pty. Ltd. Air movement apparatus

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8356566B1 (en) 2011-03-18 2013-01-22 David Alan Sellins Multi-directional marine propulsor apparatus
US10464668B2 (en) 2015-09-02 2019-11-05 Jetoptera, Inc. Configuration for vertical take-off and landing system for aerial vehicles
US10875658B2 (en) 2015-09-02 2020-12-29 Jetoptera, Inc. Ejector and airfoil configurations
US11001378B2 (en) 2016-08-08 2021-05-11 Jetoptera, Inc. Configuration for vertical take-off and landing system for aerial vehicles
US11148801B2 (en) 2017-06-27 2021-10-19 Jetoptera, Inc. Configuration for vertical take-off and landing system for aerial vehicles
KR102415854B1 (ko) * 2021-02-24 2022-07-05 주식회사 피제이 무소음 송풍 유닛 및 상기 무소음 송풍 유닛을 포함하는 무소음 비행 추진체
WO2023249139A1 (ko) * 2022-06-23 2023-12-28 주식회사 피제이 무소음 송풍 유닛 및 상기 무소음 송풍 유닛을 포함하는 무소음 비행 추진체

Also Published As

Publication number Publication date
WO2009074834A1 (de) 2009-06-18
WO2009074834A4 (de) 2009-08-20
WO2009074834A8 (de) 2010-11-11
EP2252796A1 (de) 2010-11-24

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