Patent US3727401A successfully refreshed from Google Patents.
US3727401A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Rotary turbine engine
Assignee: Individual
•
Filing: 1971-03-19
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Granted: 1973-04-17
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Expires: 1991-03-19
Abstract
Abstract Intake air undergoes two stage compression within a pair of coaxially mounted, counter-rotating rotors of a radial turbine engine and is tangentially discharged into a turbine mounted by one of the rotors. The air is heated and accelerated by discharge of combustion products from fuel burners mounted on the second stage compressor vanes in the other of the rotors to produce reaction thrust. Extensions of some of the second stage compressor vanes form discharge passages for the mixture of air and combustion products.
Inventors
- 👤 J Fincher
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-01 17:19
CPC Classifications
F; F04; F04D; F04D17/00; F04D17/02; F02; F02C; F02C3/00; F02C3/14; F02C3/16; F02C3/165
Claims Analysis
Total Claims: 7
Claim 1
Independent Claim
114 words
A gas turbine engine comprising a frame, a pair of counterrotating rotors rotatably mounted by the frame, one of said rotors being free-running, radial compressor means mounted by said rotors for two stage compression of an intake fluid, turbine blade means mounted by said one of the rotors for receiving the intake fluid discharged from the compressor means and combustion means mounted by the other of the rotors for heating the intake fluid during compression, said one of the rotors including an intake section through which the compressor means draws the intake fluid radially inward and a radially outer section mounting the turbine blade means in enclosing relation to the other of the rotors.
Claim 2
Dependent Claim
114 words
A gas turbine engine comprising a frame, a pair of counterrotating rotors rotatably mounted by the frame, one of said rotors being free-running, radial compressor means mounted by said rotors for two stage compression of an intake fluid, turbine blade means mounted by said one of the rotors for receiving the intake fluid discharged from the compressor means and combustion means mounted by the other of the rotors for heating the intake fluid during compression, said one of the rotors including an intake section through which the compressor means draws the intake fluid radially inward and a radially outer section mounting the turbine blade means in enclosing relation to the other of the rotors.
Claim 3
Dependent Claim
50 words
The combination of claim 1 wherein the other of the rotors includes a power delivery member on which said one of the rotors is rotationally supported, and a pair of end walls having inlet openings and projecting radially outward into the radially outer section of said one of the rotors.
Claim 4
Dependent Claim
60 words
The combination of claim 2 wherein said compressor means includes first stage compressor vanes mounted by the intake section of said one of the rotors, second stage compressor vanes mounted by the other of the rotors radially inwardly of the turbine blade means, and extensions on some of said second stage compressor vanes forming discharge passages for the intake fluid.
Claim 5
Dependent Claim
38 words
The combination of claim 3 wherein the combustion means includes thrust producing fuel burners mounted by the other of the rotors from which jets of combustion products are discharged into the intake fluid conducted by said discharge passages.
Claim 6
Dependent Claim
60 words
The combination of claim 1 wherein said compressor meAns includes first stage compressor vanes mounted by the intake section of said one of the rotors, second stage compressor vanes mounted by the other of the rotors radially inwardly of the turbine blade means, and extensions on some of said second stage compressor vanes forming discharge passages for the intake fluid.
Claim 7
Dependent Claim
38 words
The combination of claim 5 wherein the combustion means includes thrust producing fuel burners mounted by the other of the rotors from which jets of combustion products are discharged into the intake fluid conducted by said discharge passages.
References Cited (Backward Citations)
US1003708A
Cited
US1868143A
Cited
FR934755A
Cited
GB801281A
Cited
GB820337A
Cited
US3077075A
Cited
US3557551A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1976-04-16 | 1976-10-16 | 1977-04-17 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1980-04-16 | 1980-10-16 | 1981-04-17 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1984-04-16 | 1984-10-16 | 1985-04-17 | $7700.00 | Window Closed / Lapsed |