US20050281676A1 - Multi-hedral rotary wing - Google Patents
Multi-hedral rotary wing Download PDFInfo
- Publication number
- US20050281676A1 US20050281676A1 US10/869,799 US86979904A US2005281676A1 US 20050281676 A1 US20050281676 A1 US 20050281676A1 US 86979904 A US86979904 A US 86979904A US 2005281676 A1 US2005281676 A1 US 2005281676A1
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- United States
- Prior art keywords
- segment
- axis
- rotor blade
- recited
- rotary
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- 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/46—Blades
- B64C27/463—Blade tips
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
A rotary-wing includes a multi-hedral tip section which utilizes a distribution of anhedral and/or dihedral angles that cause a tip vortex to be axially displaced relative to a region on a following blade such that the tip vortex generally avoids influence upon the following blade.
Description
- The present invention relates to aerodynamic structures, and more particularly to multi-hedral rotor blade, which reduces tip vortex influence on a following blade.
- Aerodynamic surfaces produce tip vortices as an artifact of flow. During typical rotorcraft flight operations, rotor blades of a main rotor assembly, due to the airfoil profile and angle of attack of the rotor blades, create a high velocity low pressure field over the upper aerodynamic surface of each rotor blade and a low velocity high pressure field over the lower aerodynamic surface of each rotor blade. At the tip of each rotor blade, this pressure differential effectively engenders airflow circulation from the high pressure field to the low pressure field to create a tip vortex.
- During rotorcraft flight operations, the tip vortex is shed from a preceding rotor blade and at least partially interferes with a following rotor blade. Hover performance of helicopter rotors are especially affected by the strength and location of the tip vortex trailed from the rotor blades. The magnitude of the local induced velocity variation is a strong function of the axial distance of the passing tip vortex beneath the rotor blade. Various rotor blade geometric arrangements, along with blade tip displacement such as anhedral, are utilized to increase hover performance. Although anhedral relatively improves hover performance, anhedral may have negative performance tradeoffs in forward flight performance. Moreover, the degree of anhedral is generally limited by structural considerations associated with the increased out-of-plane mass distribution of the anhedral rotor blade tip. Such increased out-of-plane mass distribution increases the stress in the blade structure and may negatively affect overall rotor system longevity.
- Accordingly, it is desirable to provide a rotor blade tip configuration that reduces the tip vortex influence on a following rotor blade.
- The rotary-wing according to the present invention provides a multi-hedral tip section which utilizes a distribution of anhedral and/or dihedral angles that cause a tip vortex to be axially displaced relative to the region on the following blade strongly impacted by the tip vortex such that the tip vortex passes the following blade to improve hover performance while maintaining acceptable forward flight performance.
- The present invention therefore provides a rotor blade tip configuration that reduces the tip vortex influence on a following rotor blade.
- The various features and advantages of this invention will become apparent to those skilled in the art from the following detailed description of the currently preferred embodiment. The drawings that accompany the detailed description can be briefly described as follows:
-
FIG. 1 is a general perspective view an exemplary rotary wing aircraft embodiment for use with the present invention; -
FIG. 2 is a plan view of a rotor blade for use with the present invention; -
FIG. 3 is an expanded view of a multiple of rotor blades illustrating a tip vortex; -
FIG. 4A is an expanded plan view of a rotor blade with a multi-hedral tip section; -
FIG. 4B is an expanded rear view of the rotor blade multi-hedral tip section ofFIG. 4A ; -
FIG. 5 is an expanded view of a propeller with a multi-hedral tip section of the present invention; -
FIG. 6 is an expanded rear view of another multi-hedral tip section; -
FIG. 7 is an expanded rear view of another multi-hedral tip section; -
FIG. 8 is an expanded rear view of another multi-hedral tip section; -
FIG. 9 is an expanded rear view of another multi-hedral tip section; -
FIG. 10 is an expanded rear view of another multi-hedral tip section; and -
FIG. 11 is an expanded rear view of another multi-hedral tip section. -
FIG. 1 schematically illustrates a rotary-wing aircraft 10 having amain rotor assembly 12. Theaircraft 10 includes anairframe 14 having an extendingtail 16 which mounts an anti-torque rotor 18. Although a particular helicopter configuration is illustrated in the disclosed embodiment, other machines such as turbo-props, tilt-rotor and tilt-wing aircraft will also benefit from the present invention. - Referring to
FIG. 2 , a rotor blade 20 (only one illustrated) of therotor assembly 12 includes aninboard section 22, anintermediate section 24, and anoutboard section 26. The inboard, intermediate, andoutboard sections main rotor blade 20. Therotor blade sections distal end 30 of ablade tip section 28. - The
blade root portion 22 is attached to therotor assembly 12 for rotating therotor blade 20 about the axis of rotation A and for pitching about a longitudinal feathering axis P. Therotor blade 20 defines a leadingedge 22 a and atrailing edge 22 b, which are generally parallel to each other. The distance between the leadingedge 22 a and thetrailing edge 22 b defines a main element chord length Cm. - The
outboard section 26 includes theblade tip section 28 which defines thedistal end 30 of therotor blade 20. Theblade tip section 28 may include variations in chord, pitch, taper, sweep, and airfoil distributions. Although a rotor blade is disclosed in the illustrated embodiment, other aerodynamic members such as aircraft and marine propellers, fans, tilt-rotors, wind turbines, and other rotary-wing devices will benefit from the present invention. - Referring to
FIG. 3 , a precedingrotor blade 20 p, operating in hover, generates a tip vortex V which passes near a section of a followingrotor blade 20 f. The tip vortex V spirals inward of an outer diameter of the followingrotor blade 20 f. That is, the tip vortex V has a helical quality such that thefollowing blade 20 f receives passage of the tip vortex V along the tip section longitudinally inboard of the rotor bladedistal end 30 f. The passage of the tip vortex V from the precedingblade 20 p induces a local velocity variation along the span of the followingrotor blade 20 f to generate a general downwash Vd inboard and upwash Vu outboard of theradial passage location 32, superimposed with global wake induced velocity. This induced velocity field and rotational speed, combined with the blade geometric pitch distribution determines the angle-of-attack distribution that the blade experiences in hover. - Referring to
FIGS. 4A and 4B , the multi-hedralblade tip section 28 includes afirst segment 34 which defines a first axis T1, asecond segment 36 which defines a second axis T2 and athird segment 38 which defines a third axis T3. The first axis T1 is preferably defined parallel to the blade feathering axis P. It should be understood that the Figures are illustrated without a twist within therotor blade 20 for sake of clarity and that the first axis T1 is generally parallel to the longitudinal direction of therotor blade 20, the leadingedge 22 a and/or thetrailing edge 22 b. The second axis T2 is transverse the first axis T1 to define a dihedral between thefirst segment 34 and thesecond segment 36 at, preferably a 90 percent of radius blade station. The third axis T3 is transverse the second axis T2 to define an anhedral between thesecond segment 36 and thethird segment 38 at, preferably a 94 percent of radius blade station. Although a dihedral of 10 degrees and an anhedral of 20 degrees are disclosed in the illustrated embodiment, other angles will likewise benefit herefrom. - The intersection of the third axis T3 and the second axis T2 is most preferably the
radial passage location 32 for the tip vortex V (FIG. 3 ). That is, theradial passage location 32 is axial displaced raised relative the tip vortex V such that tip vortex V is passes below the intersection of the third axis T3 and the second axis T2 and has minimal effect upon the rotorblade tip section 28. - Generally, the
multi-hedral tip section 28 utilizes a distribution of anhedral and/or dihedral angles that cause the tip vortex to be at a lower axial position, relative to the region on the following blade strongly impacted by the tip vortex V such that the tip vortex V passes beneath the following blade to improve hover performance while maintaining an acceptable forward flight performance. - It should be understood that relative positional terms such as “forward,” “aft,” “upper,” “lower,” “above,” “below,” and the like are with reference to the normal operational attitude of the vehicle and should not be considered otherwise limiting. In particular, the usage of the term “below” as in the tip vortex V passes “below” the intersection of the third axis T3 and the second axis T2 is to be broadly construed as below relative the lift and/or thrust generated by the blade, e.g., for a propeller below would indicate that the tip vortex V passes behind the
propeller blade 35 behind theradial passage location 32 p, such that the tip vortex V is axially displaced opposite the thrust direction which is generated by the rotary member (FIG. 5 ), in in the direction of the induced flow. - Referring to
FIGS. 6-11 , several schematics of variousmulti-hedral tip sections 28 a-28 f are illustrated. It should be understood that other tip sections which include multi-hedral sections will also benefit from the present invention. -
FIG. 6 illustrates a multi-hedral tip section 28 a which includes afirst segment 34 a which defines a first axis T1 a, asecond segment 36 a which defines a second axis T2 a and athird segment 38 a which defines a third axis T3 a. The second axis T2 a is transverse the first axis T1 a to define an anhedral between thefirst segment 34 a and thesecond segment 36 a. The third axis T3 a is transverse the second axis T2 a to define a second anhedral between thesecond segment 36 a and thethird segment 38 a. -
FIG. 7 illustrates amulti-hedral tip section 28 b as more fully described with regard toFIG. 4A and 4B . -
FIG. 8 illustrates amulti-hedral tip section 28 c, which essentially combinesFIG. 6 and 7 to include four sections. -
FIG. 9 illustrates amulti-hedral tip section 28 d, which includes asegment 40 d, which is generally parallel to thefirst segment 34 d. -
FIG. 10 illustrates a multi-hedral tip section 28 e, includes five segments to form a segmented arc. -
FIG. 11 illustrates amulti-hedral tip section 28 f, which is smooth. That is, themulti-hedral tip section 28 f includes an infinite number of segments to form the smooth arcuate tip section. - Although particular step sequences are shown, described, and claimed, it should be understood that steps may be performed in any order, separated or combined unless otherwise indicated and will still benefit from the present invention.
- The foregoing description is exemplary rather than defined by the limitations within. Many modifications and variations of the present invention are possible in light of the above teachings. The preferred embodiments of this invention have been disclosed, however, one of ordinary skill in the art would recognize that certain modifications would come within the scope of this invention. It is, therefore, to be understood that within the scope of the appended claims, the invention may be practiced otherwise than as specifically described. For that reason the following claims should be studied to determine the true scope and content of this invention.
Claims (18)
1. A rotary aerodynamic member comprising:
a first segment which defines a first axis;
a second segment which defines a second axis transverse said first axis; and
a third segment which defines a third axis transverse said second axis.
2. The rotary aerodynamic member as recited in claim 1 , wherein said first axis is defined parallel to a leading edge of said first segment.
3. The rotary aerodynamic member as recited in claim 1 , wherein said first axis is parallel to a trailing edge of said first segment.
4. The rotary aerodynamic member as recited in claim 1 , wherein said first axis is parallel to a feathering axis of said first segment.
5. The rotary aerodynamic member as recited in claim 1 , wherein said second axis extends at least partially above said first axis.
6. The rotary aerodynamic member as recited in claim 1 , wherein said second axis extends toward a first side of said first axis and said third axis extends toward a second side of said first axis.
7. The rotary aerodynamic member as recited in claim 1 , wherein said second axis extends toward a first side of said first axis and said third axis extends toward said first side of said first axis.
8. The rotary aerodynamic member as recited in claim 1 , wherein said second segment is a dihedral segment and said third segment is an anhedral segment.
9. The rotary aerodynamic member as recited in claim 1 , wherein said second segment and said third segment form a rotor blade tip section.
10. The rotary aerodynamic member as recited in claim 1 , wherein said second segment and said third segment form a propeller tip section.
11. The rotary aerodynamic member as recited in claim 1 , further comprising a fourth segment generally parallel to said first segment.
12. The rotary aerodynamic member as recited in claim 1 , wherein said second segment and said third segment are two of an infinite number of sections.
13. A rotor blade assembly comprising:
a first rotor blade segment which defines a first axis;
a second segment which defines a dihedral relative said first axis; and
a third segment which defines an anhedral relative said first axis.
14. The rotor blade assembly as recited in claim 13 , wherein said first rotor blade segment comprises a rotor blade root section.
15. The rotor blade assembly as recited in claim 13 , wherein said third rotor blade segment comprises a distal end of a rotor blade tip section.
16. The rotor blade assembly as recited in claim 13 , further comprising a fourth rotor blade segment between said second rotor blade segment and said third rotor blade segment.
17. A method of minimizing an influence of a tip vortex formed by a preceding rotary-wing upon a following rotary-wing comprising the step of:
(1) axially displacing a multiple of segments of the preceding and receding rotary-wings relative a first axis to axially displace a tip vortex formed by the preceding rotary-wing relative the following rotary-wing.
18. A method as recited in claim 17 , wherein step (1) further comprises the step of:
displacing at least one of the multiple of segments above the first axis and at least one of the multiple of segments below the first axis.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/869,799 US20050281676A1 (en) | 2004-06-16 | 2004-06-16 | Multi-hedral rotary wing |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/869,799 US20050281676A1 (en) | 2004-06-16 | 2004-06-16 | Multi-hedral rotary wing |
Publications (1)
Publication Number | Publication Date |
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US20050281676A1 true US20050281676A1 (en) | 2005-12-22 |
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ID=35480751
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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US10/869,799 Abandoned US20050281676A1 (en) | 2004-06-16 | 2004-06-16 | Multi-hedral rotary wing |
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US (1) | US20050281676A1 (en) |
Cited By (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20050158175A1 (en) * | 2004-01-21 | 2005-07-21 | Daniele Falchero | Two-sweep rotary wing blade with limited taper ratio |
US20060104812A1 (en) * | 2004-11-18 | 2006-05-18 | Sikorsky Aircraft Corporation | Mission replaceable rotor blade tip section |
WO2007102852A2 (en) | 2006-03-08 | 2007-09-13 | Sikorsky Aircraft Corporation | Rotor blade tip plan form |
WO2008155566A1 (en) * | 2007-06-21 | 2008-12-24 | Airbus Uk Limited | Winglet |
WO2009074528A2 (en) | 2007-12-10 | 2009-06-18 | Airbus Deutschland Gmbh | Wingtip extension for reduction of vortex drag in aircraft |
US20110024552A1 (en) * | 2008-04-25 | 2011-02-03 | Karem Aircraft, Inc. | Anhedral Tip Blades for Tiltrotor Aircraft |
US20110044796A1 (en) * | 2009-08-21 | 2011-02-24 | Rolls-Royce Plc | Fluidfoil tip vortex disruption |
CN104816827A (en) * | 2015-04-01 | 2015-08-05 | 天峋创新(北京)科技有限公司 | Low-induced-resistance helicopter rotor wing with sweepback anhedral wingtip |
US10053209B2 (en) | 2009-05-05 | 2018-08-21 | Aerostar Aircraft Corporation | Aircraft winglet design having a compound curve profile |
US10899440B2 (en) * | 2017-03-09 | 2021-01-26 | Sikorsky Aircraft Corporation | Rotor blade tip design for improved hover and cruise performance |
Citations (9)
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US141871A (en) * | 1873-08-19 | Improvement in screw-propellers | ||
US4822246A (en) * | 1988-07-19 | 1989-04-18 | Hsu Yun Tung | Fan for moving fluid axially and radially |
US5246344A (en) * | 1991-06-14 | 1993-09-21 | Westland Helicopters Limited | Helicopter rotor blade with improved performance characteristics |
US5588800A (en) * | 1994-05-31 | 1996-12-31 | Mcdonnell Douglas Helicopter Co. | Blade vortex interaction noise reduction techniques for a rotorcraft |
US5595475A (en) * | 1994-01-20 | 1997-01-21 | Ekato Ruhr- Und Mischtechnik Gmbh | Agitating element |
US5927948A (en) * | 1996-04-30 | 1999-07-27 | Gkn Westland Helicopters Limited | Propeller |
US5992793A (en) * | 1996-01-04 | 1999-11-30 | Gkn Westland Helicopters Limited | Aerofoil |
US6190132B1 (en) * | 1999-03-12 | 2001-02-20 | Advanced Technology Institute Of Commuter-Helicopter, Ltd. | Rotor blade for rotorcraft |
US6231308B1 (en) * | 1997-03-24 | 2001-05-15 | Advanced Technology Institute Of Commuter-Helicopter, Ltd. | Rotor blade for rotary wing aircraft |
-
2004
- 2004-06-16 US US10/869,799 patent/US20050281676A1/en not_active Abandoned
Patent Citations (10)
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US141871A (en) * | 1873-08-19 | Improvement in screw-propellers | ||
US4822246A (en) * | 1988-07-19 | 1989-04-18 | Hsu Yun Tung | Fan for moving fluid axially and radially |
US5246344A (en) * | 1991-06-14 | 1993-09-21 | Westland Helicopters Limited | Helicopter rotor blade with improved performance characteristics |
US5595475A (en) * | 1994-01-20 | 1997-01-21 | Ekato Ruhr- Und Mischtechnik Gmbh | Agitating element |
US5588800A (en) * | 1994-05-31 | 1996-12-31 | Mcdonnell Douglas Helicopter Co. | Blade vortex interaction noise reduction techniques for a rotorcraft |
US5588800B1 (en) * | 1994-05-31 | 2000-12-19 | Mcdonell Douglas Helicopter Co | Blade vortex interaction noise reduction techniques for a rotorcraft |
US5992793A (en) * | 1996-01-04 | 1999-11-30 | Gkn Westland Helicopters Limited | Aerofoil |
US5927948A (en) * | 1996-04-30 | 1999-07-27 | Gkn Westland Helicopters Limited | Propeller |
US6231308B1 (en) * | 1997-03-24 | 2001-05-15 | Advanced Technology Institute Of Commuter-Helicopter, Ltd. | Rotor blade for rotary wing aircraft |
US6190132B1 (en) * | 1999-03-12 | 2001-02-20 | Advanced Technology Institute Of Commuter-Helicopter, Ltd. | Rotor blade for rotorcraft |
Cited By (19)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20050158175A1 (en) * | 2004-01-21 | 2005-07-21 | Daniele Falchero | Two-sweep rotary wing blade with limited taper ratio |
US7331765B2 (en) * | 2004-01-21 | 2008-02-19 | Eurocopter | Two-sweep rotary wing blade with limited taper ratio |
US20060104812A1 (en) * | 2004-11-18 | 2006-05-18 | Sikorsky Aircraft Corporation | Mission replaceable rotor blade tip section |
US7246998B2 (en) * | 2004-11-18 | 2007-07-24 | Sikorsky Aircraft Corporation | Mission replaceable rotor blade tip section |
WO2007102852A2 (en) | 2006-03-08 | 2007-09-13 | Sikorsky Aircraft Corporation | Rotor blade tip plan form |
EP1991458A4 (en) * | 2006-03-08 | 2015-10-21 | Sikorsky Aircraft Corp | Rotor blade tip plan form |
US20100155541A1 (en) * | 2007-06-21 | 2010-06-24 | Airbus Uk Limited | Winglet |
US8366056B2 (en) * | 2007-06-21 | 2013-02-05 | Airbus Operations Limited | Winglet |
WO2008155566A1 (en) * | 2007-06-21 | 2008-12-24 | Airbus Uk Limited | Winglet |
WO2009074528A3 (en) * | 2007-12-10 | 2009-10-15 | Airbus Operations Gmbh | Wingtip extension for reduction of vortex drag in aircraft |
WO2009074528A2 (en) | 2007-12-10 | 2009-06-18 | Airbus Deutschland Gmbh | Wingtip extension for reduction of vortex drag in aircraft |
US20100294891A1 (en) * | 2007-12-10 | 2010-11-25 | Airbus Operations Gmbh | Wingtip extension for reduction of vortex drag in aircraft |
US9545997B2 (en) | 2007-12-10 | 2017-01-17 | Airbus Operations Gmbh | Wingtip extension for reducing wake vortices of aircraft |
US20110024552A1 (en) * | 2008-04-25 | 2011-02-03 | Karem Aircraft, Inc. | Anhedral Tip Blades for Tiltrotor Aircraft |
US8066219B2 (en) * | 2008-04-25 | 2011-11-29 | Karem Aircraft, Inc. | Anhedral tip blades for tiltrotor aircraft |
US10053209B2 (en) | 2009-05-05 | 2018-08-21 | Aerostar Aircraft Corporation | Aircraft winglet design having a compound curve profile |
US20110044796A1 (en) * | 2009-08-21 | 2011-02-24 | Rolls-Royce Plc | Fluidfoil tip vortex disruption |
CN104816827A (en) * | 2015-04-01 | 2015-08-05 | 天峋创新(北京)科技有限公司 | Low-induced-resistance helicopter rotor wing with sweepback anhedral wingtip |
US10899440B2 (en) * | 2017-03-09 | 2021-01-26 | Sikorsky Aircraft Corporation | Rotor blade tip design for improved hover and cruise performance |
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Legal Events
Date | Code | Title | Description |
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AS | Assignment |
Owner name: SIKORSKY AIRCRAFT CORPORATION, CONNECTICUT Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:EGOLF, THOMAS A.;MOFFITT, ROBERT C.;REEL/FRAME:015491/0149;SIGNING DATES FROM 20040609 TO 20040611 |
|
STCB | Information on status: application discontinuation |
Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION |