Patent US4133173A successfully refreshed from Google Patents.
US4133173A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Ducted rockets
Assignee: United States Department of the Navy
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Filing: 1977-06-13
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Granted: 1979-01-09
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Expires: 1997-06-13
Abstract
Abstract The overall efficiency of a reaction engine having primary and secondary combustion chambers is greatly improved by reducing the primary exhaust velocity to subsonic speed. This is accomplished in a preferred embodiment by using an exhaust tube downstream of the primary nozzle. A tube diameter of about six times that of the primary throat diameter and a tube length of about five to ten times that of the tube diameter is considered optimum.
Inventors
- 👤 Klaus C. Schadow
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-07 11:51
CPC Classifications
F; F02; F02K; F02K7/00; F02K7/10; F02K7/105; Y; Y10; Y10S; Y10S60/00; Y10S60/917
Claims Analysis
Total Claims: 8
Claim 1
Independent Claim
149 words
The method of improving efficiency of rocket engines having a primary and a secondary combustion chamber including the step of: burning a solid propellant in a primary chamber to produce combustion products; placing a nozzle at the open end of the primary chamber through which the combustion products of the primary chamber must flow; maintaining a supersonic flow of the combustion products through the nozzle; slowing the supersonic flow to subsonic after it has passed through the nozzle, but prior to its entrance in the secondary chamber; restricting the subsonic flow so that it travels parallel to the secondary chamber axis when it enters the secondary chamber; and restricting the flow of ram air as it enters the secondary chamber so that it travels parallel to the secondary chamber axis, so that it limits the mixing process between the ram air and combustion products to one of diffusion only.
Claim 2
Independent Claim
149 words
The method of improving efficiency of rocket engines having a primary and a secondary combustion chamber including the step of: burning a solid propellant in a primary chamber to produce combustion products; placing a nozzle at the open end of the primary chamber through which the combustion products of the primary chamber must flow; maintaining a supersonic flow of the combustion products through the nozzle; slowing the supersonic flow to subsonic after it has passed through the nozzle, but prior to its entrance in the secondary chamber; restricting the subsonic flow so that it travels parallel to the secondary chamber axis when it enters the secondary chamber; and restricting the flow of ram air as it enters the secondary chamber so that it travels parallel to the secondary chamber axis, so that it limits the mixing process between the ram air and combustion products to one of diffusion only.
Claim 3
Dependent Claim
25 words
The method of claim 1 wherein said solid propellant includes boron and the said products of combustion comprise a fuel rich mixture including boron particles.
Claim 4
Dependent Claim
27 words
The method of claim 1 wherein said solid propellant includes a high mass fraction of metal and said products of combustion contain unreacted gaseous and particulate fuels.
Claim 5
Dependent Claim
12 words
The method of claim 3 wherein said metal consists essentially of Boron.
Claim 6
Dependent Claim
131 words
In a ducted rocket having primary and secondary combustion chambers, the improvement comprising: said primary chamber having a nozzle from which combustion products exit to said secondary chamber; means for maintaining a supersonic flow through the nozzle in said primary chamber; an elongated tube attached to the nozzle in said primary chamber for slowing the combustion products to subsonic speed prior to emerging in the secondary chamber and shaped to restrict the direction of combustion products flow to be parallel to the axis of the secondary chamber; and means for providing ram air into the secondary chamber traveling parallel to the axis of the secondary chamber so as to limit the mixing with the combustion products to that due to diffusion only and where the combustion products are at subsonic speeds.
Claim 7
Dependent Claim
131 words
In a ducted rocket having primary and secondary combustion chambers, the improvement comprising: said primary chamber having a nozzle from which combustion products exit to said secondary chamber; means for maintaining a supersonic flow through the nozzle in said primary chamber; an elongated tube attached to the nozzle in said primary chamber for slowing the combustion products to subsonic speed prior to emerging in the secondary chamber and shaped to restrict the direction of combustion products flow to be parallel to the axis of the secondary chamber; and means for providing ram air into the secondary chamber traveling parallel to the axis of the secondary chamber so as to limit the mixing with the combustion products to that due to diffusion only and where the combustion products are at subsonic speeds.
Claim 8
Dependent Claim
10 words
Apparatus according to claim 5 wherein said tube is cylindrical.
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) | 1982-01-08 | 1982-07-10 | 1983-01-09 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1986-01-08 | 1986-07-10 | 1987-01-09 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1990-01-08 | 1990-07-10 | 1991-01-09 | $7700.00 | Window Closed / Lapsed |