WO2020053672A1 - New propeller or rotor blade design to improve engine efficiency and propulsive efficiency - Google Patents

New propeller or rotor blade design to improve engine efficiency and propulsive efficiency Download PDF

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Publication number
WO2020053672A1
WO2020053672A1 PCT/IB2019/055190 IB2019055190W WO2020053672A1 WO 2020053672 A1 WO2020053672 A1 WO 2020053672A1 IB 2019055190 W IB2019055190 W IB 2019055190W WO 2020053672 A1 WO2020053672 A1 WO 2020053672A1
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WO
WIPO (PCT)
Prior art keywords
rotor
blade
propeller
efficiency
improve engine
Prior art date
Application number
PCT/IB2019/055190
Other languages
French (fr)
Inventor
Papa Abdoulaye MBODJ
Original Assignee
Mbodj Papa Abdoulaye
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 Mbodj Papa Abdoulaye filed Critical Mbodj Papa Abdoulaye
Publication of WO2020053672A1 publication Critical patent/WO2020053672A1/en

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/006—Open cycle gas-turbine in which the working fluid is expanded to a pressure below the atmospheric pressure and then compressed to atmospheric pressure
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/16—Blades
    • B64C11/20—Constructional features
    • B64C11/24—Hollow blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
    • B64C21/02—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like
    • B64C21/04—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like for blowing
    • 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
    • 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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • 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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/324—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
    • F04D29/66—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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C2230/00—Boundary layer controls
    • B64C2230/16—Boundary layer controls by blowing other fluids over the surface than air, e.g. He, H, O2 or exhaust gases
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C2230/00—Boundary layer controls
    • B64C2230/28—Boundary layer controls at propeller or rotor blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/40—Application in turbochargers
    • 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
    • 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
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the different thermal engines used to drive a propeller or rotor to produce lift or thrust require a pressure gradient to extract the chemical energy stored in a fuel.
  • a compressor or compression phase is used to increase the pressure in the engine, and the exhaust gases exit the engine and expand at atmospheric pressure. To run the compressor, energy is extracted by a turbine or set of turbines.
  • This invention called new propeller or rotor design to improve engine efficiency, and propulsive efficiency allows the exhaust gases from the engine to expand at a pressure lower than the atmospheric pressure.
  • the airfoil used for the blade has a suction side, which is a low-pressure area at the top of the airfoil (extrados). On that low-pressure side, small holes allow the exhaust gases to escape from the blade.
  • the blade is connected to the exhaust system via a system of pipes, valves, and rotary unions.
  • the engine can be downsized by reducing the number of compressor stages and turbine stages or increase the power generated by the engine. Also, the exhaust gases reenergize the flow on the blade. This action will delay flow separation and improve the lift-to-drag ratio of the blade. State of prior art
  • US6796533B2 shows the method and apparatus for boundary layer reattachment using piezoelectric synthetic jet actuators.
  • the fluid used for this device is not from the exhaust system of a thermal machine, and its function is not to lower the back pressure behind a turbine.
  • US7946801B2 shows the multi-source gas turbine. The function is to cool a turbine blade. Air is taken from the compressor and send inside a hollow turbine blade which has cavities through which air is ejected to create a protective layer for the turbine blade. However, its function is not to lower the back pressure behind a turbine.
  • US20120027568A1 shows the low-pressure steam turbine and method for operating thereof. Its function is to increase the efficiency of the last turbine stage. The pressure is lowered by condensing the steam. This method requires the condensation of the working fluid from the turbine. On the contrary, the new propeller or rotor blade design to improve engine efficiency and propulsive efficiency does not require a phase change to lower the pressure. Furthermore, there is no condenser needed, and the working fluid can be either a gas or a liquid. Besides, a propulsive force or thrust can be produced by the new propeller or rotor blade design to improve engine efficiency and propulsive efficiency.
  • the present invention concerns the new propeller or rotor design to improve engine efficiency and propulsive efficiency technically characterized by a blade with exhaust holes or slots placed on the suction side.
  • the suction side has a lower pressure due to the curvature of the airfoil or airfoils used for the conception of the blade.
  • This system can be used as a propeller or rotor blade for a helicopter or airplane.
  • Fig. 1 is a perspective view of the structure supporting the rotor and guiding the exhaust fluid.
  • Fig. 2 is a profile view of the structure supporting the rotor and guiding the exhaust fluid.
  • Fig. 3 is a perspective view of the structure supporting the rotor and guiding the exhaust fluid with the bearings mounted on the structure.
  • Fig. 4 is a perspective view of the rotor or propeller with blades having the exhaust holes or slots placed on the suction side of the blade.
  • Fig. 5 is a profile view of the rotor or propeller with blades having the exhaust holes or slots placed on the suction side of the blade.
  • Fig. 6 is a perspective view of the rotor or propeller with blades having the exhaust holes or slots placed on the suction side of the blade and connected to a shaft.
  • Fig. 7 is a perspective view of the rotor or propeller with blades having the exhaust holes or slots placed on the suction side of the blade and connected to a shaft driven by an electric motor.
  • Fig. 8 is a perspective view of the rotor or propeller with blades having the exhaust holes or slots placed on the suction side of the blade and connected to a shaft driven by an electric motor and an axial turbine placed in front.
  • Fig. 9 is a perspective view of the rotor or propeller with blades having the exhaust holes or slots placed on the suction side of the blade and connected to a shaft driven by an electric motor and a centrifugal turbine placed in front.
  • Fig. 10 is a perspective view of the rotor or propeller with blades having the exhaust holes or slots placed on the suction side of the blade and connected to an exhaust pipe from a turbine stage.
  • Fig. 11 is a perspective view of the rotors or propellers with blades having the exhaust holes or slots placed on the suction side of the blade.
  • the 1 corresponds to the inlet that allows the exhaust gases from the engine or turbine stage to enter the rotor or propeller.
  • the 2 corresponds to the outlet that allows the exhaust gases from the engine or turbine stage to enter the rotor or propeller.
  • the 3 corresponds to the bearings or rotary unions onto which the rotor or propeller is mounted.
  • a compartment that enclosed the valves that regulate the exhaust gases, the actuator that changes the pitch of the blade, and the electronic control unit that controls the actuator and the valves are enclosed in the rotor or propeller.
  • the 4 corresponds to the rotor or propeller.
  • the 5 corresponds to the holes or slots placed on the suction side of the blades. Also, the tip of the blades (5) allows if necessary the venting of the exhaust fluid to handle higher volume flow rate.
  • the new propeller or rotor design to improve engine efficiency and propulsive efficiency is made of a blade or series of blades that have holes or slots on their suction side (5).
  • the blade is connected to a thermal engine exhaust system via pipes and rotary unions.
  • the valves direct the exhaust gases toward the blades of the rotor or propeller and regulate the flow.
  • the pitch angle of the blade can be varied, and in that case, another rotary union is placed at the hinge point (8).
  • the piping system inside the blade can have thermal insulation, thus avoiding the high temperature to affect the materials and structural integrity of the blade adversely if needed.
  • valves are linked to an electronic control system that closes the valve, thus cutting the flow of hot gases into a blade.
  • Another valve connected to ambient air via an air intake, allows cold air to flow cyclically inside the blade. This will allow the excessive heat to be removed, keeping the blade within an acceptable temperature range.
  • a wastegate is installed within the exhaust system and will allow the venting of the exhaust gases, thus bypassing the blades.
  • the new propeller or rotor design to improve engine efficiency and propulsive efficiency can be placed behind an axial (10) or centrifugal turbine (11) or turbine stages. It can also be placed behind the turbine compartment of a turbocharger (13).
  • the turbocharger compressor (14) can be connected to an electrical generator (15) that transforms the extra shaft power from the turbine into electricity.
  • the rotor is connected to the turbocharger via a rotary union (3).
  • the rotor can be connected to the turbine via a shaft and a gearbox that turns the rotor at a prescribed rotational speed.
  • Another way to spin the rotor is to use an engine crankshaft (7) directly with a gearbox system (6) or an electrical motor (9).
  • the new propeller or rotor design to improve engine efficiency and propulsive efficiency can be used with any thermal engine (piston engine, gas turbine, turboshaft, turboprop) or boosting system (turbocharger).

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Architecture (AREA)
  • Supercharger (AREA)

Abstract

A propeller's or rotor's blade has as main functions the reduction of the pressure behind a turbine and the production of lift. There is a suction side and a higher-pressure side on the blade. This pressure gradient is used to produce lift or thrust. Thermal engines use the chemical energy and extract work from the energy conversion process. A pressure difference is required in those engines to produce work. The new propeller or rotor design to improve thermal engine efficiency is a new blade design that uses the exhaust gases from a thermal engine to reenergize the flow on the blade and improve the production of lift or thrust by delaying flow separation. Also, since the exhaust gases are exiting the blade on the suction side, the backpressure for the thermal engine is lower than the ambient pressure, thus, increasing the amount of work extracted by the engine.

Description

New propeller or rotor blade design to improve engine efficiency and propulsive efficiency.
Background of the invention
The different thermal engines used to drive a propeller or rotor to produce lift or thrust require a pressure gradient to extract the chemical energy stored in a fuel. A compressor or compression phase is used to increase the pressure in the engine, and the exhaust gases exit the engine and expand at atmospheric pressure. To run the compressor, energy is extracted by a turbine or set of turbines.
This invention called new propeller or rotor design to improve engine efficiency, and propulsive efficiency allows the exhaust gases from the engine to expand at a pressure lower than the atmospheric pressure.
The airfoil used for the blade has a suction side, which is a low-pressure area at the top of the airfoil (extrados). On that low-pressure side, small holes allow the exhaust gases to escape from the blade.
The blade is connected to the exhaust system via a system of pipes, valves, and rotary unions.
Thus, the engine can be downsized by reducing the number of compressor stages and turbine stages or increase the power generated by the engine. Also, the exhaust gases reenergize the flow on the blade. This action will delay flow separation and improve the lift-to-drag ratio of the blade. State of prior art
US6796533B2 shows the method and apparatus for boundary layer reattachment using piezoelectric synthetic jet actuators. However, the fluid used for this device is not from the exhaust system of a thermal machine, and its function is not to lower the back pressure behind a turbine.
US7946801B2 shows the multi-source gas turbine. The function is to cool a turbine blade. Air is taken from the compressor and send inside a hollow turbine blade which has cavities through which air is ejected to create a protective layer for the turbine blade. However, its function is not to lower the back pressure behind a turbine.
US20120027568A1 shows the low-pressure steam turbine and method for operating thereof. Its function is to increase the efficiency of the last turbine stage. The pressure is lowered by condensing the steam. This method requires the condensation of the working fluid from the turbine. On the contrary, the new propeller or rotor blade design to improve engine efficiency and propulsive efficiency does not require a phase change to lower the pressure. Furthermore, there is no condenser needed, and the working fluid can be either a gas or a liquid. Besides, a propulsive force or thrust can be produced by the new propeller or rotor blade design to improve engine efficiency and propulsive efficiency.
Brief Summary of the Invention
The present invention concerns the new propeller or rotor design to improve engine efficiency and propulsive efficiency technically characterized by a blade with exhaust holes or slots placed on the suction side. The suction side has a lower pressure due to the curvature of the airfoil or airfoils used for the conception of the blade. This system can be used as a propeller or rotor blade for a helicopter or airplane.
Brief description of the several views of the drawing
Fig. 1 is a perspective view of the structure supporting the rotor and guiding the exhaust fluid.
Fig. 2 is a profile view of the structure supporting the rotor and guiding the exhaust fluid.
Fig. 3 is a perspective view of the structure supporting the rotor and guiding the exhaust fluid with the bearings mounted on the structure.
Fig. 4 is a perspective view of the rotor or propeller with blades having the exhaust holes or slots placed on the suction side of the blade.
Fig. 5 is a profile view of the rotor or propeller with blades having the exhaust holes or slots placed on the suction side of the blade.
Fig. 6 is a perspective view of the rotor or propeller with blades having the exhaust holes or slots placed on the suction side of the blade and connected to a shaft.
Fig. 7 is a perspective view of the rotor or propeller with blades having the exhaust holes or slots placed on the suction side of the blade and connected to a shaft driven by an electric motor.
Fig. 8 is a perspective view of the rotor or propeller with blades having the exhaust holes or slots placed on the suction side of the blade and connected to a shaft driven by an electric motor and an axial turbine placed in front.
Fig. 9 is a perspective view of the rotor or propeller with blades having the exhaust holes or slots placed on the suction side of the blade and connected to a shaft driven by an electric motor and a centrifugal turbine placed in front. Fig. 10 is a perspective view of the rotor or propeller with blades having the exhaust holes or slots placed on the suction side of the blade and connected to an exhaust pipe from a turbine stage.
Fig. 11 is a perspective view of the rotors or propellers with blades having the exhaust holes or slots placed on the suction side of the blade.
Detailed Description of the Invention
As shown in the drawings: The 1 corresponds to the inlet that allows the exhaust gases from the engine or turbine stage to enter the rotor or propeller. The 2 corresponds to the outlet that allows the exhaust gases from the engine or turbine stage to enter the rotor or propeller. The 3 corresponds to the bearings or rotary unions onto which the rotor or propeller is mounted. A compartment that enclosed the valves that regulate the exhaust gases, the actuator that changes the pitch of the blade, and the electronic control unit that controls the actuator and the valves are enclosed in the rotor or propeller. The 4 corresponds to the rotor or propeller. The 5 corresponds to the holes or slots placed on the suction side of the blades. Also, the tip of the blades (5) allows if necessary the venting of the exhaust fluid to handle higher volume flow rate.
The new propeller or rotor design to improve engine efficiency and propulsive efficiency is made of a blade or series of blades that have holes or slots on their suction side (5). The blade is connected to a thermal engine exhaust system via pipes and rotary unions. There is a pipe inside the blade that allows the exhaust gases to flow toward the slots or holes (5). The valves direct the exhaust gases toward the blades of the rotor or propeller and regulate the flow. The pitch angle of the blade can be varied, and in that case, another rotary union is placed at the hinge point (8). The piping system inside the blade can have thermal insulation, thus avoiding the high temperature to affect the materials and structural integrity of the blade adversely if needed. Furthermore, the valves are linked to an electronic control system that closes the valve, thus cutting the flow of hot gases into a blade. Another valve, connected to ambient air via an air intake, allows cold air to flow cyclically inside the blade. This will allow the excessive heat to be removed, keeping the blade within an acceptable temperature range.
In case of a valve malfunction, a wastegate is installed within the exhaust system and will allow the venting of the exhaust gases, thus bypassing the blades.
Also, the new propeller or rotor design to improve engine efficiency and propulsive efficiency can be placed behind an axial (10) or centrifugal turbine (11) or turbine stages. It can also be placed behind the turbine compartment of a turbocharger (13). The turbocharger compressor (14) can be connected to an electrical generator (15) that transforms the extra shaft power from the turbine into electricity. The rotor is connected to the turbocharger via a rotary union (3). Also, the rotor can be connected to the turbine via a shaft and a gearbox that turns the rotor at a prescribed rotational speed. Another way to spin the rotor is to use an engine crankshaft (7) directly with a gearbox system (6) or an electrical motor (9).
Many rotors or propellers can be mounted in parallel to handle a higher volume flow rate (fig.
11).
The new propeller or rotor design to improve engine efficiency and propulsive efficiency can be used with any thermal engine (piston engine, gas turbine, turboshaft, turboprop) or boosting system (turbocharger).

Claims

Claims
1. A New propeller or rotor design to improve engine efficiency and propulsive efficiency characterized by a propeller or rotor blade with holes or slots placed on the low-pressure side of the blade called the suction side and those holes or slots are connected to an exhaust system of a thermal engine and allow the venting of the exhaust fluid through the holes or slots, thus, lowering the backpressure for a thermal engine and improving the propulsive efficiency by delaying flow separation on a propeller or rotor.
2. A new propeller or rotor design to improve engine efficiency and propulsive efficiency according to claim 1, characterized by the holes or slots are connected to the exhaust system of a thermal engine via pipes, valves, and rotary unions.
3. A new propeller or rotor design to improve engine efficiency and propulsive efficiency according to claim 1 and claim 2, characterized by the valves are connected to an electronic control system that regulates the flow of exhaust fluid inside a blade.
4. A New propeller or rotor design to improve engine efficiency and propulsive efficiency according to claim 1 and claim 2, characterized by many blades are placed in parallel, one after the other and rotors or propellers mounted in parallel one after the other.
5. A New propeller or rotor design to improve engine efficiency and propulsive efficiency according to claim land claim 2, characterized by guiding vanes are placed in the pipes connected to the exhaust system of the thermal engine and in holes or slots located on the suction side of a blade.
6. A New propeller or rotor design to improve engine efficiency and propulsive efficiency according to claim 1, characterized by the cross-sectional area of the slots or holes located on the suction side of a blade is varying along the length of the hole or slot.
7. A new propeller or rotor design to improve engine efficiency and propulsive efficiency according to claim 1 and claim 2, characterized by ambient air, taken from air intake and an air pump, is pump inside the blade for cooling.
8. A New propeller or rotor design to improve engine efficiency and propulsive efficiency according to claim 1, characterized by a wastegate is connected to the exhaust system and will open and allow the exhaust gases to bypass a blade in case of a valve malfunction.
9. A new propeller or rotor design to improve engine efficiency and propulsive efficiency according to claim 1, characterized by a rotor is placed inside a nozzle to produce jet thrust.
10. A new propeller or rotor design to improve engine efficiency and propulsive efficiency according to claim 1, characterized by a rotor is placed inside a nozzle to reduce the noise generated by the rotation of the rotor.
11. A new propeller or rotor design to improve engine efficiency and propulsive efficiency according to claim 1, characterized by a rotor or propeller is connected to a shaft and a gearbox system.
12. A new propeller or rotor design to improve engine efficiency and propulsive efficiency according to claim 1, characterized by a rotor is connected to a turbocharger via a rotary union and is placed behind the turbine of a turbocharger.
PCT/IB2019/055190 2018-09-16 2019-06-20 New propeller or rotor blade design to improve engine efficiency and propulsive efficiency WO2020053672A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US201862731956P 2018-09-16 2018-09-16
US62/731,956 2018-09-16

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WO2020053672A1 true WO2020053672A1 (en) 2020-03-19

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Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE304297C (en) *
US1857909A (en) * 1929-11-25 1932-05-10 American Propeller Company Propeller
GB392895A (en) * 1930-08-27 1933-05-25 Francis Edward Colbert Improvements in screw propellers
US2681191A (en) * 1947-08-18 1954-06-15 Rotol Ltd Airscrew-driving gas turbine engine power plant with anti-icing means for the airscrews
US6796533B2 (en) 2001-03-26 2004-09-28 Auburn University Method and apparatus for boundary layer reattachment using piezoelectric synthetic jet actuators
WO2008113088A1 (en) * 2007-03-16 2008-09-25 Arni's Hotprop Turbine Ges.M.B.H. Turboprop engine
DE102009036011A1 (en) * 2009-08-04 2011-02-10 Rolls-Royce Deutschland Ltd & Co Kg Aircraft engine, has flow channel provided with inflow opening and extending within tip area of propeller blade in outflow opening, and gas turbine introducing gas flow e.g. exhaust gas flow, into outflow opening
US7946801B2 (en) 2007-12-27 2011-05-24 General Electric Company Multi-source gas turbine cooling
US20120027568A1 (en) 2010-07-30 2012-02-02 Alstom Technology Ltd Low-pressure steam turbine and method for operating thereof
EP3064431A1 (en) * 2015-03-04 2016-09-07 Centre Internacional de Métodes Numérics en Enginyeria Stall reduction propeller

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE304297C (en) *
US1857909A (en) * 1929-11-25 1932-05-10 American Propeller Company Propeller
GB392895A (en) * 1930-08-27 1933-05-25 Francis Edward Colbert Improvements in screw propellers
US2681191A (en) * 1947-08-18 1954-06-15 Rotol Ltd Airscrew-driving gas turbine engine power plant with anti-icing means for the airscrews
US6796533B2 (en) 2001-03-26 2004-09-28 Auburn University Method and apparatus for boundary layer reattachment using piezoelectric synthetic jet actuators
WO2008113088A1 (en) * 2007-03-16 2008-09-25 Arni's Hotprop Turbine Ges.M.B.H. Turboprop engine
US7946801B2 (en) 2007-12-27 2011-05-24 General Electric Company Multi-source gas turbine cooling
DE102009036011A1 (en) * 2009-08-04 2011-02-10 Rolls-Royce Deutschland Ltd & Co Kg Aircraft engine, has flow channel provided with inflow opening and extending within tip area of propeller blade in outflow opening, and gas turbine introducing gas flow e.g. exhaust gas flow, into outflow opening
US20120027568A1 (en) 2010-07-30 2012-02-02 Alstom Technology Ltd Low-pressure steam turbine and method for operating thereof
EP3064431A1 (en) * 2015-03-04 2016-09-07 Centre Internacional de Métodes Numérics en Enginyeria Stall reduction propeller

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