US3783618A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Aerodynamic engine system
Assignee: Individual
•
Filing: 1972-03-29
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Granted: 1974-01-08
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Expires: 1992-03-29
Abstract
Abstract A lift-fan engine system of small size but strong lifting power which comprises a lift-fan having a plurality of fan blades each formed by an inner-fan blade portion gradually twisted toward its outside and a turbo-fan blade portion incorporated with the inner-fan blade portion at its outer end. At the boundary between the inner-fan and turbo-fan blade portions is provided a first shroud segment of the turbo-fan blade portion and beneath it is provided a second shroud segment. By radially mounting the fan blades as constructed in the above by means of their root portions on a fan or rotor disc, the first and second shroud segment of the respective fan blades are adjoined with the first and second shroud segments of adjacent fan blades so as to constitute a first ring and a second ring between which a passage of the high-temperature gas is formed.
Inventors
- 👤 O Kawamura
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-28 10:30
CPC Classifications
F; F02; F02K; F02K3/00; F02K3/02; F02K3/025; F02K3/04; F02K3/068
Claims Analysis
Total Claims: 8
Claim 1
Independent Claim
229 words
An aerodynamic engine system comprising a lift fan assembly having a rotatable disc, a plurality of fan blades, each constituted of an inner fan blade portion and an integral outer turbo-fan blade portion, said plurality of blades being connected at their inner ends to said disc and being radially outwardly directed therefrom, each of said fan blades being gradually twisted from its inner to its outer end and being provided with a notch in the turbo-fan blade portion for forming a nozzle exhaust-gas guiding fin member and an auxiliary fin member, a set of first shroud segments and a set of second shroud segments integrally formed on opposed surfaces of each fan blade and in substantially perpendicular relation thereto, said set of first shroud segments and said set of second shroud segments being radially spaced from one another and positioned on each said fan blade to delimit said exhaust-gas guiding fin member from said auxiliary fin member and respectively connected to sets of first and second shroud segments on adjacent fan blades to form therewith first and second rings defining a passage for flow of high temperature fluids, burner means for producing hightemperature fluid gases, and nozzle means disposed adjacent to said burner means for supplying said high-temperature fluid gases from said burner means to a predetermined circumferential portion of the passage defined by said first and second rings.
Claim 2
Dependent Claim
229 words
An aerodynamic engine system comprising a lift fan assembly having a rotatable disc, a plurality of fan blades, each constituted of an inner fan blade portion and an integral outer turbo-fan blade portion, said plurality of blades being connected at their inner ends to said disc and being radially outwardly directed therefrom, each of said fan blades being gradually twisted from its inner to its outer end and being provided with a notch in the turbo-fan blade portion for forming a nozzle exhaust-gas guiding fin member and an auxiliary fin member, a set of first shroud segments and a set of second shroud segments integrally formed on opposed surfaces of each fan blade and in substantially perpendicular relation thereto, said set of first shroud segments and said set of second shroud segments being radially spaced from one another and positioned on each said fan blade to delimit said exhaust-gas guiding fin member from said auxiliary fin member and respectively connected to sets of first and second shroud segments on adjacent fan blades to form therewith first and second rings defining a passage for flow of high temperature fluids, burner means for producing hightemperature fluid gases, and nozzle means disposed adjacent to said burner means for supplying said high-temperature fluid gases from said burner means to a predetermined circumferential portion of the passage defined by said first and second rings.
Claim 3
Dependent Claim
15 words
A system according to claim 1, wherein said nozzle means comprise a plurality of nozzles.
Claim 4
Dependent Claim
14 words
A system according to claim 1, wherein said nozzle means comprises a single nozzle.
Claim 5
Dependent Claim
29 words
A system according to cLaim 1, wherein said nozzle means comprise nozzle guide vanes, each formed with a plurality of passages for cooling of the vanes by circulating fluid.
Claim 6
Dependent Claim
14 words
A system according to claim 4, wherein the nozzle guide vanes comprise cooling fins.
Claim 7
Dependent Claim
16 words
A system according to claim 1, wherein said disc is journalled for rotation on a shaft.
Claim 8
Dependent Claim
45 words
A system according to claim 1 in combination with a V/STOL aircraft, said system being installed in a horizontal section of the wing of the aircraft, and means for introducing bleed air, and/or exhaust gas to said burner means through the intermediary of valve means.
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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) | 1977-01-07 | 1977-07-09 | 1978-01-08 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1981-01-07 | 1981-07-09 | 1982-01-08 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1985-01-07 | 1985-07-09 | 1986-01-08 | $7700.00 | Window Closed / Lapsed |