Patent US3269119A successfully refreshed from Google Patents.
US3269119A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Turbo-jet powerplant with toroidal combustion chamber
Assignee: Individual
•
Filing: 1964-05-07
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Granted: 1966-08-30
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Expires: 1984-05-07
Abstract
No abstract record available.
Inventors
- 👤 Nathan C Price
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-26 12:39
CPC Classifications
F; F01; F01D; F01D9/00; F01D9/02; F01D9/023; F01D21/00; F01D21/04; F01D21/045; F01D5/00; F01D5/02; F01D5/027; F02; F02C; F02C3/00; F02C3/04; F02C3/06; F02C3/073; F23; F23R; F23R3/00; F23R3/42; F23R3/52; Y; Y02; Y02T; Y02T50/00; Y02T50/60
Claims Analysis
Total Claims: 2
Claim 1
Independent Claim
137 words
A TURBO-JET POWERPLANT COMPRISING, A COMPRESSOR ROTOR SECTION, A TURBINE ROTOR SECTION DRIVINGLY CONNECTED TO SAID COMPRESSOR ROTOR SECTION FOR DRIVING THEREOF A TOROIDAL COMBUSTOR LOCATED BETWEEN THE COMPRESSOR AND TURBINE ROTOR SECTIONS, FIRST FLOW DIRECTING MEANS EXTEND ING FORWARD TANGENTIALLY FROM THE RADIAL OUTER PORTION OF SAID COMBUSTION TO ADJACENT THE AFT END OFTHE COMPRESSOR ROTOR SECTION FOR INTRODUCING THE COMPRESSOR FLUID DISCHARGE INTO THE COMBUSTOR, SECOND FLOW DIRECTING MEANS EXTENDING AFTWARD TANGENTIALLY FROM THE RADIAL OUTER PORTION OF SAID COMBUSTOR TO ADJACENT THE FORWARD END OF THE TURBINE ROTOR SECTION FOR INTRODUCING COMBUSTION GASES INTO THE TURBINE ROTOR SECTION, AND A RADIALLY EXTENDING CONTINUOUS ANNULAR CHANNEL LOCATED CIRCUMFERENTIALLY AROUND THE RADIAL INNER PORTION OF THE TOROID COMBUSTOR FORMING A FUEL DELIVERY DISCHARGE MEANS FOR DISCHARGING FUEL INTO THE COMBUSTOR IN A RADIAL ANNULAR SPRAY PATTERN.
Claim 2
Dependent Claim
137 words
A TURBO-JET POWERPLANT COMPRISING, A COMPRESSOR ROTOR SECTION, A TURBINE ROTOR SECTION DRIVINGLY CONNECTED TO SAID COMPRESSOR ROTOR SECTION FOR DRIVING THEREOF A TOROIDAL COMBUSTOR LOCATED BETWEEN THE COMPRESSOR AND TURBINE ROTOR SECTIONS, FIRST FLOW DIRECTING MEANS EXTEND ING FORWARD TANGENTIALLY FROM THE RADIAL OUTER PORTION OF SAID COMBUSTION TO ADJACENT THE AFT END OFTHE COMPRESSOR ROTOR SECTION FOR INTRODUCING THE COMPRESSOR FLUID DISCHARGE INTO THE COMBUSTOR, SECOND FLOW DIRECTING MEANS EXTENDING AFTWARD TANGENTIALLY FROM THE RADIAL OUTER PORTION OF SAID COMBUSTOR TO ADJACENT THE FORWARD END OF THE TURBINE ROTOR SECTION FOR INTRODUCING COMBUSTION GASES INTO THE TURBINE ROTOR SECTION, AND A RADIALLY EXTENDING CONTINUOUS ANNULAR CHANNEL LOCATED CIRCUMFERENTIALLY AROUND THE RADIAL INNER PORTION OF THE TOROID COMBUSTOR FORMING A FUEL DELIVERY DISCHARGE MEANS FOR DISCHARGING FUEL INTO THE COMBUSTOR IN A RADIAL ANNULAR SPRAY PATTERN.
References Cited (Backward Citations)
US2944397A
Cited
US2856755A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1969-08-29 | 1970-02-28 | 1970-08-30 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1973-08-29 | 1974-02-28 | 1974-08-30 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1977-08-29 | 1978-02-28 | 1978-08-30 | $7700.00 | Window Closed / Lapsed |