US20160319668A1 - Textured leading edge for aerospace and nautical structures - Google Patents
Textured leading edge for aerospace and nautical structures Download PDFInfo
- Publication number
- US20160319668A1 US20160319668A1 US14/698,334 US201514698334A US2016319668A1 US 20160319668 A1 US20160319668 A1 US 20160319668A1 US 201514698334 A US201514698334 A US 201514698334A US 2016319668 A1 US2016319668 A1 US 2016319668A1
- Authority
- US
- United States
- Prior art keywords
- grooves
- surface area
- groove
- fluid
- opposite
- 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.)
- Granted
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
- B63B—SHIPS OR OTHER WATERBORNE VESSELS; EQUIPMENT FOR SHIPPING
- B63B1/00—Hydrodynamic or hydrostatic features of hulls or of hydrofoils
- B63B1/32—Other means for varying the inherent hydrodynamic characteristics of hulls
- B63B1/34—Other means for varying the inherent hydrodynamic characteristics of hulls by reducing surface friction
- B63B1/36—Other means for varying the inherent hydrodynamic characteristics of hulls by reducing surface friction using mechanical means
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
- B63B—SHIPS OR OTHER WATERBORNE VESSELS; EQUIPMENT FOR SHIPPING
- B63B1/00—Hydrodynamic or hydrostatic features of hulls or of hydrofoils
- B63B1/02—Hydrodynamic or hydrostatic features of hulls or of hydrofoils deriving lift mainly from water displacement
- B63B1/04—Hydrodynamic or hydrostatic features of hulls or of hydrofoils deriving lift mainly from water displacement with single hull
- B63B1/06—Shape of fore part
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
- B63H—MARINE PROPULSION OR STEERING
- B63H25/00—Steering; Slowing-down otherwise than by use of propulsive elements; Dynamic anchoring, i.e. positioning vessels by means of main or auxiliary propulsive elements
- B63H25/06—Steering by rudders
- B63H25/38—Rudders
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/26—Construction, shape, or attachment of separate skins, e.g. panels
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
- F15D—FLUID DYNAMICS, i.e. METHODS OR MEANS FOR INFLUENCING THE FLOW OF GASES OR LIQUIDS
- F15D1/00—Influencing flow of fluids
- F15D1/002—Influencing flow of fluids by influencing the boundary layer
- F15D1/0025—Influencing flow of fluids by influencing the boundary layer using passive means, i.e. without external energy supply
- F15D1/003—Influencing flow of fluids by influencing the boundary layer using passive means, i.e. without external energy supply comprising surface features, e.g. indentations or protrusions
- F15D1/005—Influencing flow of fluids by influencing the boundary layer using passive means, i.e. without external energy supply comprising surface features, e.g. indentations or protrusions in the form of dimples
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C2230/00—Boundary layer controls
- B64C2230/22—Boundary layer controls by using a surface having multiple apertures of relatively small openings other than slots
-
- 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
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
- F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
-
- 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
- F05D2220/30—Application in turbines
- F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
-
- 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
-
- 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
- F05D2250/00—Geometry
- F05D2250/60—Structure; Surface texture
- F05D2250/63—Structure; Surface texture coarse
-
- 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
- Y02T70/00—Maritime or waterways transport
- Y02T70/10—Measures concerning design or construction of watercraft hulls
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Ocean & Marine Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
- This disclosure pertains to a surface area of a structure that has been fabricated with a textured surface that reduces the surface wear rate or erosion caused by a high speed flow of fluid containing abrasive particles over the surface area. By “fluid”, what is meant is a liquid, a gas or a combination thereof. More particularly, this disclosure pertains to a leading edge surface such as a rotor leading edge surface, an aircraft airfoil leading edge surface, a propeller leading edge surface, etc. that is fabricated with a textured surface comprised of a plurality of grooves that alter or break up a high speed flow of fluid containing abrasive particles over the textured surface. The grooves are contacted by the high speed flow of fluid containing the abrasive particles and alter or break up the flow of fluid and abrasive particles and thereby reduce surface wear rate or erosion of the structure leading edge.
- On structures such as aircraft rotor blades, aircraft airfoil surfaces on wings, wind turbine blades, marine propellers and rudders, and other such similar structures, the leading edges of these structures experience a surface wear rate or erosion as the leading edges are moved at a high speed through fluid such as air or water during operation of the structures. This is particularly true where the leading edges of the structures are moved at high speed through a fluid containing airborne or waterborne abrasive particles, such as sand in the air or water.
- In the past, attempts to address the surface wear rate or erosion of the leading edge surfaces of structures involved the use of sacrificial coatings on the leading edge surfaces, replaceable metallic and non-metallic shields secured to the leading edge surfaces, or replacement of the entire structure when the leading edge surface of the structure was eroded beyond usable limits. However, each of these solutions is expensive, and some undesirably add weight to the structure.
- The textured surface of this disclosure is designed to minimize the erosion that sand or other airborne or waterborne abrasive particles moving at high speed, or gases moving at high speed cause on the leading edge surfaces of structures such as aircraft rotor blades, aircraft airfoil surfaces on wings, wind turbine blades, marine propellers and rudders, and other such similar structures. The textured surface can be formed into a surface area of a leading edge of a structure, or applied to the surface area of the leading edge of the structure.
- Basically, the textured surface is characterized by a plurality of grooves that are recessed into the surface area or formed on the surface area of the leading edge surface of the structure. The plurality of grooves can have a variety of shapes and combinations of shapes. The shapes may have a range of different orientations with respect to the leading edge area of the structure and the direction of fluid flow over the leading edge surface. Spacings between the plurality of grooves may also be varied to suit the modified leading edge surface to conditions it will encounter.
- The plurality of grooves are positioned on or near the leading edge surface area of the structure that moves at a high speed through a fluid flow containing abrasive particles in operation of the structure. The grooves on the leading edge surface area alter or break up the flow direction of the fluid contacting the grooves and alter or break up the flow direction of the abrasive particles contacting the grooves. The altered fluid flow direction and altered particle flow direction reduces surface wear rate or erosion of the structure leading edge region.
- Further features of the textured surface are set forth in the following detailed description and drawing figures.
-
FIG. 1 is a representation of a perspective view of a textured surface on a leading edge surface of a structure. -
FIG. 2 is a representation of a side cross-section view of the textured surface on a leading edge surface of a structure. -
FIG. 3 is a representation of a plan view of a textured surface on a surface area of a structure. -
FIG. 4 is a representation of a cross-section view of a textured surface on a surface area of a structure. -
FIG. 5 is a representation of a cross-section view of a textured surface on a surface area of a structure. -
FIG. 6 is a representation of a cross-section view of a textured surface on a surface area of a structure. -
FIG. 1 is a perspective view of a cross-section of a portion of a structure fabricated with a textured surface of this disclosure. In the representation ofFIG. 1 , thestructure 10 is a portion of a propeller rotor blade. However, the textured surface is not limited to use on only rotor blade surfaces. As stated earlier, a textured surface can be fabricated on structures such as aircraft rotor blades, aircraft airfoil surfaces on wings, wind turbine blades, marine propellers and rudders, and other such similar structures having a leading edge surface area that experiences a surface wear rate or erosion as the leading edge surface area is moved at high speed through a fluid such as air or water during operation of the structure. As a few examples of structures that move at high speed through a fluid, a helicopter rotor blade or an airplane propeller could be moving through air at least 713 km/h, a jet engine turbine blade could be moving through air at least 2655 km/h, and a ship bow could be moving through water at least 26 knots (48 km/h). -
FIG. 2 is a representation of a cross-section view of thestructure 10 ofFIG. 1 . A textured surface is applied to afirst surface area 14 on the leading edge of the structure. InFIG. 2 the leading edge has a u-shaped cross-section. However, it should be understood that the textured surface could be used on a surface area of a leading edge surface having other cross-section configurations such as triangular, semicircular, etc. - Because the
first surface area 14 of the structure is the surface area that passes at high speed through a fluid where the fluid could contain abrasive particles such as sand, it is only necessary that thefirst surface area 14 be fabricated with the textured surface of this disclosure. Asecond surface area 16 and athird surface area 18 of thestructure 10 that are adjacent thefirst surface area 14 are not directly contacted by the high speed fluid or the particles in the high speed fluid during operation of the structure. Although it may not be necessary that thesecond surface area 16 and thethird surface area 18 be fabricated with the textured surface, its use in these areas will be dictated by operating conditions encountered in the specific application. - Referring back to
FIG. 1 , the textured surface of thefirst surface area 14 is characterized by a plurality ofgrooves 22. Thegrooves 22 can be recessed into the material of thefirst surface area 14. - The plurality of
grooves 22 can have a variety of different configurations. As represented inFIG. 3 , thegrooves 22 have oblong configurations with straight, parallel side edges and rounded end edges. Thegrooves 22 are formed in thefirst surface area 14 of thestructure 10 with each groove having a length dimension between afirst end edge 24 and asecond end edge 26 of the groove, a width dimension between afirst side edge 28 and an oppositesecond side edge 30 of the groove, and a depth dimension between atop opening 32 of thegroove 22 and abottom surface 34 of the groove. Thegrooves 22 represented inFIG. 3 are arranged end to end and side by side with respect to the direction of fluid flow over the leading edgefirst surface area 14 represented by thearrow 36. However, thegrooves 22 could have a range of different orientations with respect to the direction of fluid flow. The configurations of the grooves, the orientations of the grooves, the spacings betweenadjacent grooves 22, etc. may be varied to suit the modified leading edgefirst surface area 14 to conditions it will encounter in use of thestructure 10. - As represented in
FIGS. 4, 5, and 6 , thegrooves 22 can have a variety of different cross-section configurations across their length dimensions. The cross-section configurations could be rectangular or square 40 as represented inFIG. 4 , circular as semicircular 42 as represented inFIG. 5 , elliptical or parabolic 44 as represented inFIG. 6 , etc. The particular cross-section configuration of thegrooves 22 will depend on the specific structure having the textured surface on its leading edge surface, and the service conditions in which the structure will be used. In addition, the plurality ofgrooves 22 could have variations in width to depth aspect ratio in order to minimize the abrasive wear on the leadingedge surface 14. The cross-section configurations of the grooves should not be limited to only the configurations shown in the drawing figures. - An example of the dimensions of a
groove 22 such as thesquare cross-section groove 40 represented inFIG. 4 include a depth between thetop opening 32 and thebottom surface 34 of one millimeter, a width between thefirst side edge 28 and thesecond side edge 30 of one millimeter, and a length dimension between thefirst end edge 24 as shown inFIG. 3 and thesecond end edge 26 as shown inFIG. 3 of two millimeters. - As stated earlier, the plurality of
grooves 22 are positioned on the leading edgefirst surface area 14 of thestructure 10 that moves at a high speed through a fluid flow containing abrasive particles in operation of thestructure 10. Thegrooves 22 on thefirst surface area 14 alter or break up the flow direction of the fluid contacting thegrooves 22 and alter or break up the flow direction of the abrasive particles contacting thegrooves 22 without adding weight to the structure. The altered fluid flow direction and altered particle flow direction reduces the surface wear rate or erosion of thefirst surface area 14 of thestructure 10. The erosion rate can be reduced by up to 50%. Thus, thegrooves 22 increase the service life of thestructure 10 with no performance penalty, potentially doubling the service life. - The
grooves 22 of the texturedfirst surface area 14 could be constructed or recessed into the material of the leading edge surface of thestructure 10 by traditional manufacturing methods, such as laser etching, machining, chemical milling, etc. This would particularly be the case where the plurality ofgrooves 22 are being formed into the leading edgefirst surface area 14 of a structure that would be discarded when the texturedfirst surface area 14 has worn out and the structure has lost its service performance. - Alternatively, the
grooves 22 of thetextured surface 14 could be formed in a temporary layer that is applied to the leadingfirst surface area 14 of thestructure 10. The temporary layer is not a permanent part of thestructure 10, but is removed from thestructure 10 when worn out and replaced with a new temporary layer having thegrooves 22 of the texturedfirst surface area 14. This would particularly be the case where the temporary layer could be manufactured less expensively than discarding and replacing thestructure 10 when the texturedfirst surface area 14 has worn out. The temporary layer having thegrooves 22 of thetextured surface 14 could be secured to the leading edgefirst surface area 14 of thestructure 10 by fasteners, screws, adhesives, snap fit connections, welding or other equivalent methods. - Furthermore, the
grooves 22 of the texturedfirst surface area 14 could be formed into metallic material, plastics, rubbers, ceramics, composites, and a combination of these. - Still further, when the
grooves 22 of the texturedfirst surface area 14 have worn out, thegrooves 22 could be renewed in place on the texturedfirst surface area 14 by the traditional manufacturing methods mentioned earlier. - Additional manufacturing methods such as 3D printing and other fabrication methods classified as “additive manufacturing” could be used to construct the
grooves 22 on the texturedfirst surface area 14. Such additive manufacturing methods are characterized by thegrooves 22 of the texturedfirst surface area 14 of thestructure 10 being made starting with a 3D drawing electronic file, which is converted into a set of very thin layers, which are then deposited one by one and bonded all together in one cohesive object in constructing the texturedfirst surface area 14 of thestructure 10. - Furthermore, 3D printing and any other of the above listed methods may be used to rebuild the textured
first surface area 14 of thestructure 10 when thefirst surface area 14 is worn out, without remaking theentire structure 10. This would achieve further cost savings. - As various modifications could be made in the construction of the apparatus and its method of operation herein described and illustrated without departing from the scope of the invention, it is intended that all matter contained in the foregoing description or shown in the accompanying drawings shall be interpreted as illustrative rather than limiting. Thus, the breadth and scope of the present disclosure should not be limited by any of the above described exemplary embodiments, but should be defined only in accordance with the following claims appended hereto and their equivalents. CLAIMS
Claims (27)
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US14/698,334 US9482096B1 (en) | 2015-04-28 | 2015-04-28 | Textured leading edge for aerospace and nautical structures |
EP16153900.2A EP3088290B1 (en) | 2015-04-28 | 2016-02-02 | A textured leading edge for aerospace and nautical structures |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US14/698,334 US9482096B1 (en) | 2015-04-28 | 2015-04-28 | Textured leading edge for aerospace and nautical structures |
Publications (2)
Publication Number | Publication Date |
---|---|
US9482096B1 US9482096B1 (en) | 2016-11-01 |
US20160319668A1 true US20160319668A1 (en) | 2016-11-03 |
Family
ID=55315321
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US14/698,334 Active 2035-06-05 US9482096B1 (en) | 2015-04-28 | 2015-04-28 | Textured leading edge for aerospace and nautical structures |
Country Status (2)
Country | Link |
---|---|
US (1) | US9482096B1 (en) |
EP (1) | EP3088290B1 (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2019099143A (en) * | 2017-11-28 | 2019-06-24 | ベッカー マリン システムズ ゲーエムベーハーbecker marine systems GmbH | Rudder plate with module structure, segment for rudder plate or for improving propulsion thereof and method for manufacturing rudder plate |
KR20200076578A (en) * | 2018-12-19 | 2020-06-29 | 두산중공업 주식회사 | Pree-swirler having dimples |
WO2023175263A1 (en) * | 2022-03-18 | 2023-09-21 | Safran Aircraft Engines | Method for manufacturing a turbomachine blade |
Families Citing this family (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
ES2740623T3 (en) * | 2016-03-14 | 2020-02-06 | Airbus Operations Sl | Injection molding procedure and tool for manufacturing a leading edge section with hybrid laminar flow control for an aircraft |
US10808540B2 (en) * | 2018-03-22 | 2020-10-20 | Raytheon Technologies Corporation | Case for gas turbine engine |
US11614106B2 (en) | 2019-08-21 | 2023-03-28 | Lockheed Martin Corporation | Partially submerged periodic riblets |
JP7202342B2 (en) * | 2020-11-17 | 2023-01-11 | 株式会社Subaru | Vehicles and front bumper components that improve aerodynamic characteristics by embossed surfaces |
GB2602354A (en) * | 2020-12-24 | 2022-06-29 | Thales Holdings Uk Plc | A barrier component and a method of manufacturing a barrier component |
IT202100000296A1 (en) | 2021-01-08 | 2022-07-08 | Gen Electric | TURBINE ENGINE WITH VANE HAVING A SET OF DIMPLES |
Citations (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4907765A (en) * | 1985-09-26 | 1990-03-13 | Messerschmitt-Boelkow-Blohm Gmbh | Wall with a drag reducing surface and method for making such a wall |
US5114099A (en) * | 1990-06-04 | 1992-05-19 | W. L. Chow | Surface for low drag in turbulent flow |
US5133516A (en) * | 1985-05-31 | 1992-07-28 | Minnesota Mining And Manufacturing Co. | Drag reduction article |
US6805325B1 (en) * | 2003-04-03 | 2004-10-19 | Rockwell Scientific Licensing, Llc. | Surface plasma discharge for controlling leading edge contamination and crossflow instabilities for laminar flow |
US20080159870A1 (en) * | 2006-12-14 | 2008-07-03 | Hontek Corporation | Method and coating for protecting and repairing an airfoil surface using molded boots, sheet or tape |
US20090126838A1 (en) * | 2007-11-16 | 2009-05-21 | General Electric Company | Uniform heat treatment process for hardening steel |
US20100127125A1 (en) * | 2008-08-05 | 2010-05-27 | Ming Li | Metal sheets and plates having friction-reducing textured surfaces and methods of manufacturing same |
US20110186685A1 (en) * | 2010-02-02 | 2011-08-04 | The Boeing Company | Thin-Film Composite Having Drag-Reducing Riblets and Method of Making the Same |
US20120049008A1 (en) * | 2010-08-24 | 2012-03-01 | Lockheed Martin Corporation | Passive Robust Flow Control Micro Device |
US20130071252A1 (en) * | 2011-09-21 | 2013-03-21 | Bell Helicopter Textron Inc. | Rotor Blade Erosion Protection System |
US8678316B2 (en) * | 2009-01-29 | 2014-03-25 | The Boeing Company | Amorphous metal riblets |
US20140093378A1 (en) * | 2012-02-22 | 2014-04-03 | Patrick Louis Clavette | Erosion and fatigue resistant blade and blade coating |
Family Cites Families (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3578264A (en) * | 1968-07-09 | 1971-05-11 | Battelle Development Corp | Boundary layer control of flow separation and heat exchange |
JP2551048B2 (en) * | 1986-11-19 | 1996-11-06 | ブリヂストンスポーツ株式会社 | Golf ball |
DE19821449A1 (en) * | 1998-05-13 | 1999-11-18 | Loegel Charles | High pressure jet nozzle to generate high pressure fluid jet |
EP1578663B1 (en) * | 2002-04-18 | 2013-06-05 | Airbus Operations GmbH | Perforated skin structure for laminar-flow systems |
DE102008059536A1 (en) * | 2008-11-29 | 2010-06-02 | Eugen Radtke | Surface structure i.e. flat golf ball structure, has shallow recesses distributed on upper boundary surface, where edge sections of recesses pass over spherical convex transition area in upper boundary surface |
GB0905396D0 (en) | 2009-03-30 | 2009-05-13 | Airbus Uk Ltd | Aircraft component with aerodynamic surface coating |
-
2015
- 2015-04-28 US US14/698,334 patent/US9482096B1/en active Active
-
2016
- 2016-02-02 EP EP16153900.2A patent/EP3088290B1/en active Active
Patent Citations (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5133516A (en) * | 1985-05-31 | 1992-07-28 | Minnesota Mining And Manufacturing Co. | Drag reduction article |
US4907765A (en) * | 1985-09-26 | 1990-03-13 | Messerschmitt-Boelkow-Blohm Gmbh | Wall with a drag reducing surface and method for making such a wall |
US5114099A (en) * | 1990-06-04 | 1992-05-19 | W. L. Chow | Surface for low drag in turbulent flow |
US6805325B1 (en) * | 2003-04-03 | 2004-10-19 | Rockwell Scientific Licensing, Llc. | Surface plasma discharge for controlling leading edge contamination and crossflow instabilities for laminar flow |
US20080159870A1 (en) * | 2006-12-14 | 2008-07-03 | Hontek Corporation | Method and coating for protecting and repairing an airfoil surface using molded boots, sheet or tape |
US20090126838A1 (en) * | 2007-11-16 | 2009-05-21 | General Electric Company | Uniform heat treatment process for hardening steel |
US20100127125A1 (en) * | 2008-08-05 | 2010-05-27 | Ming Li | Metal sheets and plates having friction-reducing textured surfaces and methods of manufacturing same |
US8678316B2 (en) * | 2009-01-29 | 2014-03-25 | The Boeing Company | Amorphous metal riblets |
US20110186685A1 (en) * | 2010-02-02 | 2011-08-04 | The Boeing Company | Thin-Film Composite Having Drag-Reducing Riblets and Method of Making the Same |
US20120049008A1 (en) * | 2010-08-24 | 2012-03-01 | Lockheed Martin Corporation | Passive Robust Flow Control Micro Device |
US20130071252A1 (en) * | 2011-09-21 | 2013-03-21 | Bell Helicopter Textron Inc. | Rotor Blade Erosion Protection System |
US20140093378A1 (en) * | 2012-02-22 | 2014-04-03 | Patrick Louis Clavette | Erosion and fatigue resistant blade and blade coating |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2019099143A (en) * | 2017-11-28 | 2019-06-24 | ベッカー マリン システムズ ゲーエムベーハーbecker marine systems GmbH | Rudder plate with module structure, segment for rudder plate or for improving propulsion thereof and method for manufacturing rudder plate |
JP7272782B2 (en) | 2017-11-28 | 2023-05-12 | ベッカー マリン システムズ ゲーエムベーハー | Rudder blade with modular construction, segment for a rudder blade or for a device to improve propulsion, and method for manufacturing a rudder blade |
KR20200076578A (en) * | 2018-12-19 | 2020-06-29 | 두산중공업 주식회사 | Pree-swirler having dimples |
KR102226998B1 (en) * | 2018-12-19 | 2021-03-12 | 두산중공업 주식회사 | Pree-swirler having dimples |
US11719440B2 (en) | 2018-12-19 | 2023-08-08 | Doosan Enerbility Co., Ltd. | Pre-swirler having dimples |
WO2023175263A1 (en) * | 2022-03-18 | 2023-09-21 | Safran Aircraft Engines | Method for manufacturing a turbomachine blade |
FR3133551A1 (en) * | 2022-03-18 | 2023-09-22 | Safran Aircraft Engines | Process for manufacturing a turbomachine blade |
Also Published As
Publication number | Publication date |
---|---|
US9482096B1 (en) | 2016-11-01 |
EP3088290A1 (en) | 2016-11-02 |
EP3088290B1 (en) | 2021-10-13 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US9482096B1 (en) | Textured leading edge for aerospace and nautical structures | |
CN107757879B (en) | Wingtip device for a wing of an aircraft, aircraft and use | |
US7832689B2 (en) | Element for generating a fluid dynamic force | |
US3625459A (en) | Airfoil design | |
CA2974992C (en) | Airframe-integrated propeller-driven propulsion systems | |
RU2611857C2 (en) | Aircraft tail unit surface with front edge section of wavy shape | |
US10315754B2 (en) | Fluid systems that include a co-flow jet | |
US10252789B2 (en) | Fluid systems that include a co-flow jet | |
US8763959B2 (en) | Two-element airfoil configured for minimizing accretion of contaminant | |
US20190389588A1 (en) | Fluid Systems That Prevent the Formation of Ice | |
US10384766B2 (en) | Aircraft wing roughness strip and method | |
EP2863194B1 (en) | Total air temperature sensors | |
US20160009364A1 (en) | Fluid Boundary Layer Control | |
US20200339255A1 (en) | Method of drag reduction on vehicle with internal rotors | |
Graff et al. | Sweeping jet actuators-a new design tool for high lift generation | |
US20160152324A1 (en) | Fluidic fence for performance enhancement | |
US11148787B2 (en) | Aircraft propulsion system comprising a member covered with a grooved structure | |
WO2012112408A1 (en) | Laminar flow wing optimized for transonic cruise aircraft | |
WO2014178205A1 (en) | Surface flow control system and surface flow control method | |
WO2005081701A2 (en) | Blade and wing configuration | |
KR20140015954A (en) | Marine propeller apparatus | |
US10538313B2 (en) | Active flow control system | |
KR20150132922A (en) | Preswirl Stator of Ship Stem | |
KR20140015912A (en) | Marine propeller apparatus | |
KR20150145982A (en) | Pre-swirl Stator of Ship Stem |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
AS | Assignment |
Owner name: THE BOEING COMPANY, ILLINOIS Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:PAESANO, ANTONIO;THOMPSON, ROBERT B.;REEL/FRAME:035517/0829 Effective date: 20150428 |
|
STCF | Information on status: patent grant |
Free format text: PATENTED CASE |
|
FEPP | Fee payment procedure |
Free format text: PAYOR NUMBER ASSIGNED (ORIGINAL EVENT CODE: ASPN); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY |
|
MAFP | Maintenance fee payment |
Free format text: PAYMENT OF MAINTENANCE FEE, 4TH YEAR, LARGE ENTITY (ORIGINAL EVENT CODE: M1551); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY Year of fee payment: 4 |