Patent US4620303A successfully refreshed from Google Patents.
Patent US4917332A successfully refreshed from Google Patents.
US4917332A
Expired / Lapsed
US
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Wingtip vortex turbine
Assignee: National Aeronautics and Space Administration
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Filing: 1988-10-28
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Granted: 1990-04-17
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Expires: 2008-10-28
Abstract
Abstract A means for extracting rotational energy from the vortex created at aircraft wing tips which consists of a turbine with blades located in the crossflow of the vortex and attached downstream of the wingtip. The turbine 30 has blades 40, 41, 42 and 43 attached to a core 45. When the aircraft is in motion, rotation of core 45 transmits energy to a centrally attached shaft 50. The rotational energy thus generated may be put to use within the airfoil 20 or aircraft fuselage 10.
Inventors
- 👤 James C. Patterson, Jr.
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-31 12:48
CPC Classifications
B; B64; B64C; B64C23/00; B64C23/06; B64C23/065; Y; Y02; Y02T; Y02T50/00; Y02T50/10
Claims Analysis
Total Claims: 10
Claim 1
Independent Claim
183 words
An apparatus for reducing induced drag on an aircraft by attenuating a lift-induced vortex and for extracting energy from the vortex, the apparatus comprising: a moving vehicle; lift-producing surface means on said vehicle inducing a naturally-occurring wingtip vortex having a crossflow, said lift producing surface means having a leading edge, a trailing edge and a wingtip chord; turbine means, positioned on the lift-producing surface means so that it is driven solely by said wingtip vortex crossflow with no power being derived from freestream airflow, for reducing induced drag on the moving vehicle by attenuating the lift-induced vortex and extracting rotational energy from said vortex, said turbine means further having a position adjacent to and aft of said wingtip chord, said turbine means having turbine blades with a blade diameter greater than 60% and less than 160% of said wingtip chord, said turbine blades positioned in the crossflow of the wingtip vortex occurring outside the vortex core, providing energy for utilization within the aircraft without any thrust penalty to the vehicle propulsion system, and means for utilizing said rotational energy within said moving vehicle.
Claim 2
Independent Claim
183 words
An apparatus for reducing induced drag on an aircraft by attenuating a lift-induced vortex and for extracting energy from the vortex, the apparatus comprising: a moving vehicle; lift-producing surface means on said vehicle inducing a naturally-occurring wingtip vortex having a crossflow, said lift producing surface means having a leading edge, a trailing edge and a wingtip chord; turbine means, positioned on the lift-producing surface means so that it is driven solely by said wingtip vortex crossflow with no power being derived from freestream airflow, for reducing induced drag on the moving vehicle by attenuating the lift-induced vortex and extracting rotational energy from said vortex, said turbine means further having a position adjacent to and aft of said wingtip chord, said turbine means having turbine blades with a blade diameter greater than 60% and less than 160% of said wingtip chord, said turbine blades positioned in the crossflow of the wingtip vortex occurring outside the vortex core, providing energy for utilization within the aircraft without any thrust penalty to the vehicle propulsion system, and means for utilizing said rotational energy within said moving vehicle.
Claim 3
Dependent Claim
28 words
An apparatus as in claim 1 wherein said means for utilizing said rotational energy is shaft means associated with and actuated by rotational motion of said turbine means.
Claim 4
Dependent Claim
13 words
An apparatus as in claim 2 wherein said moving vehicle is an aircraft.
Claim 5
Dependent Claim
14 words
An apparatus as in claim 3 wherein said blade means are cambered blade means.
Claim 6
Dependent Claim
36 words
An apparatus as in claim 3 wherein said blade means, having tips and roots, have chords which are tapered such that the chords of said blade means are smaller at the tips than at the roots.
Claim 7
Dependent Claim
14 words
An apparatus as in claim 5 wherein said blade means are cambered blade means.
Claim 8
Dependent Claim
28 words
An apparatus as in claim 3 wherein the force produced by said blade means is coupled to said shaft, providing means for transfer of energy to said shaft.
Claim 9
Dependent Claim
24 words
An apparatus as in claim 3 wherein said blade means are oriented at an angle of attack such that airstream-turbine blade interference is minimized.
Claim 10
Dependent Claim
33 words
An apparatus as in claim 1 wherein said means for utilizing said rotational energy within said moving vehicle is a generator located at the center of said turbine and within said vortex core.
References Cited (Backward Citations)
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1993-04-16 | 1993-10-16 | 1994-04-17 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1997-04-16 | 1997-10-16 | 1998-04-17 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2001-04-16 | 2001-10-16 | 2002-04-17 | $7700.00 | Window Closed / Lapsed |