US3823554A
Expired / Lapsed
US
⏱️ 0.0 years remaining
High speed valveless resonant pulse jet engine
Assignee: Individual
•
Filing: 1973-02-20
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Granted: 1974-07-16
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Expires: 1993-02-20
Abstract
Abstract A valveless resonent pulse jet engine particularly adapted to power target vehicles or pilotless aircraft at speeds of Mach 0.5 to Mach 1. This invention is an improved high-speed adaptation of my U.S. Pat. No. 3,517,510. The device of this invention continues to utilize a substantially cylindrical combustion chamber, a reduction cone and an exhaust tube, a multiplicity of reverse flow air fuel inlet tubes projecting through the reduction cone into the combustion chamber. Annular reverse flow vanes surround the bell mouth of the air inlet tubes thereby increasing static pressure at the air inlet as forward speed of the vehicle increases. An exhaust tube diffuser is employed in a similar fashion to assist the pulsating reverse flow of ambient air into the exhaust tube to increase thrust at high forward speeds.
Inventors
- 👤 J Melenric
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-09 02:03
CPC Classifications
F; F02; F02K; F02K7/00; F02K7/02; F02K7/04
Claims Analysis
Total Claims: 11
Claim 1
Independent Claim
198 words
A self starting valveless pulse jet engine comprising: a. a substantially cylindrical combustion chamber of circular cross section, b. an elongated substantially cylindrical exhaust tube of circular cross section projecting aft from said combustion chamber constructed and arranged on a common axis with the axis of said combustion chamber, c. a reduction cone intermediate said combustion chamber and said exhasut tube, d. a multiplicity of straight air and fuel inlet tubes constructed in a single axis configuration mounted in said reduction cone projecting into said combustion chamber, the construction and arrangement of the combustion chamber, exhaust tube, and air fuel intake tube combination places the axis of each said element substantially parallel with the axis of each other said element, e. an inlet tube bell mouth constructed in the respective intake ends of said air and fuel inlet tubes, f. a multiplicity of annular reverse flow vanes spaced from and substantially encircling said inlet tube bell mouth, said annular reverse flow vanes having an arcuate configuration adapted to entrap and deflect air into said inlet tube bell mouths, g. fuel supply means operably associated with said combustion chamber and, h. ignition means operably associated with said combustion chamber.
Claim 2
Dependent Claim
198 words
A self starting valveless pulse jet engine comprising: a. a substantially cylindrical combustion chamber of circular cross section, b. an elongated substantially cylindrical exhaust tube of circular cross section projecting aft from said combustion chamber constructed and arranged on a common axis with the axis of said combustion chamber, c. a reduction cone intermediate said combustion chamber and said exhasut tube, d. a multiplicity of straight air and fuel inlet tubes constructed in a single axis configuration mounted in said reduction cone projecting into said combustion chamber, the construction and arrangement of the combustion chamber, exhaust tube, and air fuel intake tube combination places the axis of each said element substantially parallel with the axis of each other said element, e. an inlet tube bell mouth constructed in the respective intake ends of said air and fuel inlet tubes, f. a multiplicity of annular reverse flow vanes spaced from and substantially encircling said inlet tube bell mouth, said annular reverse flow vanes having an arcuate configuration adapted to entrap and deflect air into said inlet tube bell mouths, g. fuel supply means operably associated with said combustion chamber and, h. ignition means operably associated with said combustion chamber.
Claim 3
Dependent Claim
87 words
The invention of claim 1 wherein said annular reverse flow vanes comprise: a. an intake section projecting forward said intake section being flared and of substantially greater diameter than said fuel and air inlet tubes, b. an arcuate reduction cone constructed in said annular reverse flow vanes projecting aft of said intake section, said arcuate reduction cone projecting aft at a progressively reduced diameter, said reverse flow vanes terminating in, c. a reverse flow lip projecting forward substantially in the direction of the inlet tube bell mouth.
Claim 4
Dependent Claim
55 words
The invention of claim 1 including: a. an exhaust tube nozzle secured to the aft end of said exhaust tube, and b. an exhaust tube diffuser secured to and encircling said exhaust tube nozzle, said exhaust tube diffuser constructed and arranged to reduce the rate of flow of ambiant air adjacent said exhaust tube nozzle.
Claim 5
Dependent Claim
61 words
The invention of claim 3 wherein said exhaust tube diffuser comprises: a. a diffuser inlet of substantially greater diameter than the diameter of said exhaust tube, b. a diffuser flow channel projecting aft at a progressively reduced diameter, and said exhaust tube diffuser terminating in c. a diffuser exhaust cone having a diameter less than the diameter of said diffuser inlet.
Claim 6
Dependent Claim
23 words
The invention of claim 1 wherein said combustion chamber includes a substantially flat forward wall normal to the axis of said exhaust tube.
Claim 7
Dependent Claim
21 words
The invention of claim 1 wherein the said air and fuel inlet tubes are substantially equiangular positioned in said combustion chamber.
Claim 8
Dependent Claim
28 words
The invention of claim 1 wherein the fuel supply means includes a convergent-divergent supersonic fuel nozzle positioned in the inlet end of said air and fuel inlet tubes.
Claim 9
Dependent Claim
27 words
The invention of claim 1 including a fuel nozzle positioned in substantially the center of said bellmouth at its juncture with said air and fuel inlet tube.
Claim 10
Dependent Claim
39 words
The invention of claim 5 wherein the said ignition means includes a spark plug positioned in the said forward wall at a position substantially in prolongation of the axis of one of the said air and fuel inlet tubes.
Claim 11
Dependent Claim
106 words
The invention of claim 1 wherein the dimensional proportions are relatively: a. the diameter of the combustion chamber is substantially twice the diameter of the exhaust tube, b. the combustion chamber, combustion chamber reduction cone, and exhaust tube combination is substantially fifteen (15) exhaust tube diameters in length, c. the length of each of the air and fuel inlet tubes is one-fourth ( 1/4 ) the length of the combustion chamber, combustion chamber reduction cone, and the exhaust tube combination, and d. the total cross-sectional intake area of the said air and fuel inlet tubes is one-third of the cross-sectional area of the said exhaust tube.
References Cited (Backward Citations)
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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) | 1977-07-15 | 1978-01-14 | 1978-07-16 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1981-07-15 | 1982-01-14 | 1982-07-16 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1985-07-15 | 1986-01-14 | 1986-07-16 | $7700.00 | Window Closed / Lapsed |