US3864907A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Step cylinder combustor design
Assignee: United States Department of the Air Force
•
Filing: 1973-11-05
•
Granted: 1975-02-11
•
Expires: 1993-11-05
Abstract
Abstract A supersonic combustion ramjet having a combustor including at least two constant area combustor chamber-sections or stages disposed in open communication between the ramjet inlet and expansion nozzle, and further each incorporating a combustion stabilizing step configuration and a separate fuel injector for respectively and selectively adding heat to the pair of constant area-chambers to control the heat addition to the subsonic or supersonic mode.
Inventors
- 👤 Edward T Curran
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-26 18:02
CPC Classifications
F; F02; F02K; F02K7/00; F02K7/10
Claims Analysis
Total Claims: 5
Claim 1
Independent Claim
179 words
In a ramjet engine having a main duct member, an air inlet and an expansion nozzle-forming structure; combustor chamber means incorporated in said duct member and comprising; a plurality of substantially cylindrically-shaped, combustor chamber-sections disposed in direct and continuous alignment with each other and in open communication between said air inlet and expansion nozzle-forming structure, each combustor chambersections being formed into a constant area configuration and respectively increasing in size in the downstream direction to thereby provide for the periodic, non-divergent and relatively even expansion of flow in separate stages and in all directions inherently ensuring better fuel-air mixing and thus the more efficient combustion thereof; separate combustion stability means inherently incorporated with and disposed at or near the upstream end of each of said combustor chamber-sections; and individually actuatable, heat-adding means positioned immediately upstream of each said combustor stability means, and selectively and individually operable to add varying amounts of heat to said combustor chamber means to thereby provide a positive, built-in control and regulation of the speed being inherently produced during the operation of said ramjet engine.
Claim 2
Dependent Claim
179 words
In a ramjet engine having a main duct member, an air inlet and an expansion nozzle-forming structure; combustor chamber means incorporated in said duct member and comprising; a plurality of substantially cylindrically-shaped, combustor chamber-sections disposed in direct and continuous alignment with each other and in open communication between said air inlet and expansion nozzle-forming structure, each combustor chambersections being formed into a constant area configuration and respectively increasing in size in the downstream direction to thereby provide for the periodic, non-divergent and relatively even expansion of flow in separate stages and in all directions inherently ensuring better fuel-air mixing and thus the more efficient combustion thereof; separate combustion stability means inherently incorporated with and disposed at or near the upstream end of each of said combustor chamber-sections; and individually actuatable, heat-adding means positioned immediately upstream of each said combustor stability means, and selectively and individually operable to add varying amounts of heat to said combustor chamber means to thereby provide a positive, built-in control and regulation of the speed being inherently produced during the operation of said ramjet engine.
Claim 3
Dependent Claim
29 words
In a ramjet engine as in claim 1, wherein said separate combustion stability means each comprise a step formed at the upstream end of each of said combustor-chamber sections.
Claim 4
Dependent Claim
180 words
In a ramjet engine as in claim 2; and relatively elongated, center body means centrally disposed in said combustor chamber means along the longitudinal axis of said main duct member and incorporating a spike diffuser element at the front end thereof disposed at and through the air inlet, and a center body member extending between said spike diffuser element and the expansion nozzle-forming structure; said center body member comprising a plurality of substantially cylindrical, center body elements respectively decreasing in diameter in the downstream direction to thereby incorporate and form each of said combustion stability steps at the junctures between adjacent center body elements, and further respectively define each of the said combustor chambers into a constant area configuration disposed in circumferential relation around the corresponding center body element and progressively increasing in size in the downstream direction to thereby ensure both non-divergent flow coupled with the addition of heat by said individually actuatable, heat-adding means in one or more selected stages to positively promote more efficient combustion and the mode of control to either the supersonic or subsonic range.
Claim 5
Dependent Claim
63 words
In a ramjet engine as in claim 1, wherein said main duct member comprises a missile having a main fuel tank and combined payload and spike inlet diffuser member, and said combustor chamber means comprises a series of three combustion stability steps and combustor chamber-sections annularily disposed between a supporting structure surrounding said fuel tank and the outside wall of said duct member.
References Cited (Backward Citations)
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1978-02-10 | 1978-08-12 | 1979-02-11 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1982-02-10 | 1982-08-12 | 1983-02-11 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1986-02-10 | 1986-08-12 | 1987-02-11 | $7700.00 | Window Closed / Lapsed |