Patent US4168939A successfully refreshed from Google Patents.
US4168939A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Acoustically swept rotor
Assignee: National Aeronautics and Space Administration
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Filing: 1977-09-08
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Granted: 1979-09-25
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Expires: 1997-09-08
Abstract
Abstract Impulsive noise reduction is provided in a rotor blade by "acoustically sweeping" the chord line from root to tip so that the acoustic radiation resulting from the summation of potential singularities used to model the flow about the blade tend to cancel for all times at an observation point in the acoustic far field.
Inventors
- 👤 Fredric H. Schmitz
- 👤 Donald A. Boxwell
- 👤 C. Rande Vause
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-04 08:06
CPC Classifications
B; B64; B64C; B64C27/00; B64C27/32; B64C27/46; B64C27/463
Claims Analysis
Total Claims: 8
Claim 1
Independent Claim
51 words
A rotor blade with nonlinear sweep for reducing impulsive noise having a quarter chord line that conforms to ##EQU2## where θ≡the sweep angle of the chord line, r≡the radial distance from the blade root to the chord line, R≡blade radius, M t =advancing tip Mach number, and K 1 =a constant.
Claim 2
Dependent Claim
51 words
A rotor blade with nonlinear sweep for reducing impulsive noise having a quarter chord line that conforms to ##EQU2## where θ≡the sweep angle of the chord line, r≡the radial distance from the blade root to the chord line, R≡blade radius, M t =advancing tip Mach number, and K 1 =a constant.
Claim 3
Dependent Claim
70 words
A rotor blade with nonlinear sweep having a root, a tip and a quarter chord line, said quarter chord line for at least the outer blade portion extending from the 70% station to the tip conforming to ##EQU3## where θ≡the sweep angle of the chord line, r≡the radial distance from the blade root to the chord line, R≡blade radius, M t =advancing tip Mach number, and K 1 =a constant.
Claim 4
Dependent Claim
70 words
A rotor blade with nonlinear sweep having a root, a tip and a quarter chord line, said quarter chord line for at least the outer blade portion extending from the 70% station to the tip conforming to ##EQU3## where θ≡the sweep angle of the chord line, r≡the radial distance from the blade root to the chord line, R≡blade radius, M t =advancing tip Mach number, and K 1 =a constant.
Claim 5
Dependent Claim
118 words
A helicopter rotor for reducing impulsive noise comprising a plurality of nonlinearly swept blades, said blades each having a root, a tip, and a quarter chord line, a hub with an axis of rotation, said roots being connected to said hub, the quarter chord line of each blade conforming to ##EQU4## where θ≡the sweep angle of the chord line, r≡the radial distance from the blade root to the chord line, R≡blade radius, M t =advancing tip Mach number, and K 1 =a constant, whereby when said blades and hub are rotated about said axis the aerodynamically generated acoustic radiation from blade sources tends to cancel in the acoustic far field the aerodynamically generated acoustic radiation from blade sinks.
Claim 6
Dependent Claim
118 words
A helicopter rotor for reducing impulsive noise comprising a plurality of nonlinearly swept blades, said blades each having a root, a tip, and a quarter chord line, a hub with an axis of rotation, said roots being connected to said hub, the quarter chord line of each blade conforming to ##EQU4## where θ≡the sweep angle of the chord line, r≡the radial distance from the blade root to the chord line, R≡blade radius, M t =advancing tip Mach number, and K 1 =a constant, whereby when said blades and hub are rotated about said axis the aerodynamically generated acoustic radiation from blade sources tends to cancel in the acoustic far field the aerodynamically generated acoustic radiation from blade sinks.
Claim 7
Independent Claim
65 words
The method of reducing impulsive noise in a helicopter rotor blade comprising the step of sweeping the quarter chord line of the blade continuously from root to tip nonlinearly in accordance with ##EQU5## where θ≡the sweep angle of the chord line, r≡the radial distance from the blade root to the chord line, R≡blade radius, M t =advancing tip Mach number, and K 1 =a constant.
Claim 8
Independent Claim
65 words
The method of reducing impulsive noise in a helicopter rotor blade comprising the step of sweeping the quarter chord line of the blade continuously from root to tip nonlinearly in accordance with ##EQU5## where θ≡the sweep angle of the chord line, r≡the radial distance from the blade root to the chord line, R≡blade radius, M t =advancing tip Mach number, and K 1 =a constant.
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USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1982-09-24 | 1983-03-26 | 1983-09-25 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1986-09-24 | 1987-03-26 | 1987-09-25 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1990-09-24 | 1991-03-26 | 1991-09-25 | $7700.00 | Window Closed / Lapsed |