US4185457A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Turbofan-ramjet engine
Assignee: RTX Corp
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Filing: 1976-01-28
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Granted: 1980-01-29
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Expires: 1996-01-28
Abstract
Abstract A turbofan-ramjet engine is provided with optional duct burning in the turbofan mode. A core engine is provided with a first annular passage therearound for directing airflow around the inlet of the core engine. A second annular passage having a fan directs air flow into the inlet of the core engine and said first annular passage. A third annular passage extends around the first and second annular passage with the first and third annular passage each directing their flow into a common annular combustion chamber. Variable vanes are provided in the first and third annular passages to provide for blocking off the passage or acting as swirl vanes depending on mode of operation. Blocking vanes are also provided in the annular exhaust passage of the core engine. Coannular nozzles are provided with one located at the exhaust of the core engine and an outer one located aft of the common annular combustion chamber. Air bleed means are provided for providing a positive pressure behind vanes in the first or third annular passage when either one is placed in its flow-blocking position to prevent undesired propagation of flame into that passage.
Inventors
- 👤 Sidney D. Parker
- 👤 Robert G. Carroll
- 👤 William L. Howell
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-06 10:45
CPC Classifications
F; F02; F02K; F02K7/00; F02K7/10; F02K7/16
Claims Analysis
Total Claims: 9
Claim 1
Independent Claim
265 words
A turbofan-ramjet engine having a core engine with a compressor section, burner section and turbine section, a first annular passage located around said core engine for directing airflow around the inlet of said core engine, a second annular passage located forwardly of the inlet of the core engine and said first annular passage for directing airflow thereinto, a fan positioned in said second annular passage, a third annular passage extending around said first and second annular passage, a common annular combustion chamber receiving the flow from said first and third annular passages, said core engine having a first nozzle means controlling the exhaust therefrom, said common annular combustion chamber having an annular nozzle means located around said first nozzle means for controlling the exhaust flow from said common annular combustion chamber, first movable vanes being positioned in said first passage, said first movable vanes being movable between a position where they block off flow through said first passage to a position where they act as swirl vanes for providing a desired angle of swirl flow into said common annular combustion chamber, means for placing said first movable vanes at a desired angle to obtain a desired swirl flow, second movable vanes being positioned in said third passage, said second movable vanes being movable between a position where they block off flow through said third passage to a position where they act as swirl vanes for providing a desired angle of swirl flow into said common annular combustion chamber, means for placing said second movable vanes at a desired angle to obtain a desired swirl flow.
Claim 2
Dependent Claim
265 words
A turbofan-ramjet engine having a core engine with a compressor section, burner section and turbine section, a first annular passage located around said core engine for directing airflow around the inlet of said core engine, a second annular passage located forwardly of the inlet of the core engine and said first annular passage for directing airflow thereinto, a fan positioned in said second annular passage, a third annular passage extending around said first and second annular passage, a common annular combustion chamber receiving the flow from said first and third annular passages, said core engine having a first nozzle means controlling the exhaust therefrom, said common annular combustion chamber having an annular nozzle means located around said first nozzle means for controlling the exhaust flow from said common annular combustion chamber, first movable vanes being positioned in said first passage, said first movable vanes being movable between a position where they block off flow through said first passage to a position where they act as swirl vanes for providing a desired angle of swirl flow into said common annular combustion chamber, means for placing said first movable vanes at a desired angle to obtain a desired swirl flow, second movable vanes being positioned in said third passage, said second movable vanes being movable between a position where they block off flow through said third passage to a position where they act as swirl vanes for providing a desired angle of swirl flow into said common annular combustion chamber, means for placing said second movable vanes at a desired angle to obtain a desired swirl flow.
Claim 3
Dependent Claim
39 words
A turbofan-ramjet engine as set forth in claim 1 wherein air bleed means connects the area forward of the first movable vanes to the area rearwardly of the second movable vanes to minimize recirculation from the common combustion chamber.
Claim 4
Dependent Claim
39 words
A turbofan-ramjet engine as set forth in claim 1 wherein air bleed means connects the area forward of the second movable vanes to the area rearwardly of the first movable vanes to minimize recirculation from the common combustion chamber.
Claim 5
Dependent Claim
39 words
A turbofan-ramjet engine as set forth in claim 2 wherein air bleed means connects the area forward of the second movable vanes to the area rearwardly of the first movable vanes to minimize recirculation from the common combustion chamber.
Claim 6
Independent Claim
168 words
A method of operating a turbofan-ramjet engine having a core engine and an annular fan duct and ram duct located therearound having a common annular combustion chamber, said core engine and said common combustion chamber each having means for controlling the flow therefrom, the steps of: (1) operating the engine for turbofan operation with no duct burning by (a) blocking the flow through said ram duct; (b) flowing air through said fan duct; and (c) controlling the flow from said common annular combustion chamber; (2) operating the engine for turbofan operation with duct burning by (a) providing burning within said common annular combustion chamber while swirling the air flowing through the fan duct at a desired angle of swirl; (3) operating the engine for ramjet operation by (a) blocking the flow through said core engine; (b) blocking the flow through said fan duct; and (c) providing burning within said common annular combustion chamber while swirling the air flowing through the ram duct at a desired angle of swirl.
Claim 7
Independent Claim
168 words
A method of operating a turbofan-ramjet engine having a core engine and an annular fan duct and ram duct located therearound having a common annular combustion chamber, said core engine and said common combustion chamber each having means for controlling the flow therefrom, the steps of: (1) operating the engine for turbofan operation with no duct burning by (a) blocking the flow through said ram duct; (b) flowing air through said fan duct; and (c) controlling the flow from said common annular combustion chamber; (2) operating the engine for turbofan operation with duct burning by (a) providing burning within said common annular combustion chamber while swirling the air flowing through the fan duct at a desired angle of swirl; (3) operating the engine for ramjet operation by (a) blocking the flow through said core engine; (b) blocking the flow through said fan duct; and (c) providing burning within said common annular combustion chamber while swirling the air flowing through the ram duct at a desired angle of swirl.
Claim 8
Dependent Claim
36 words
A method of operating a turbofan-ramjet engine as set forth in claim 5 including step (1)(d) air is directed just downstream of where the flow through said ram duct is blocked to provide a positive pressure.
Claim 9
Dependent Claim
36 words
A method of operating a turbofan-ramjet engine as set forth in claim 5 including step (3)(d) air is directed just downstream of where the flow through said fan duct is blocked to provide a positive pressure.
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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) | 1983-01-28 | 1983-07-30 | 1984-01-29 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1987-01-28 | 1987-07-30 | 1988-01-29 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1991-01-28 | 1991-07-30 | 1992-01-29 | $7700.00 | Window Closed / Lapsed |