US4150540A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Rocket nozzle system
Assignee: United States Department of the Air Force
•
Filing: 1977-04-14
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Granted: 1979-04-24
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Expires: 1997-04-14
Abstract
Abstract An improved rocket nozzle system having a closure insulator located adjacent the combustion chamber of a rocket engine. The closure insulator has formed as an integral part thereof a plurality of nozzles. Each of the nozzles has incorporated therein a throat insert of pyrolized graphite cloth laminate and a consumable washer. The entire closure insulator assembly including nozzles is transfer molded as one piece into a steel housing. The housing is mounted on the combustion chamber thereby providing an effective nozzle system which is reliably operable under high temperature operation.
Inventors
- 👤 Harold A. Krayenbuhl
- 👤 Gene Dolgonas
- 👤 Charles J. Rogers
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-01 09:14
CPC Classifications
F; F02; F02K; F02K9/00; F02K9/08; F02K9/30; F02K9/97; F02K9/974; Y; Y10; Y10S; Y10S60/00; Y10S60/909
Claims Analysis
Total Claims: 3
Claim 1
Independent Claim
143 words
A rocket nozzle system comprising a supporting structure, said supporting structure having at least one nozzle formed as an integral part thereof, said nozzle having an entrance section and an exit section, a throat located intermediate said entrance and exit sections of said nozzle, a throat insert formed of a pyrolized graphite cloth laminate secured within said throat section of said nozzle, a washer of predetermined thickness being located between said throat insert and said entrance section of said nozzle, said washer being consumable at temperatures greater than approximately 700° F. and yet capable of withstanding a temperature of approximately 320° F. and a pressure of approximately 7000 psi with a resultant maximum reduction of said predetermined thickness of approximately 15 percent and a steel housing encompassing said supporting structure, said supporting structure being transfer molded as one piece into said steel housing.
Claim 2
Dependent Claim
143 words
A rocket nozzle system comprising a supporting structure, said supporting structure having at least one nozzle formed as an integral part thereof, said nozzle having an entrance section and an exit section, a throat located intermediate said entrance and exit sections of said nozzle, a throat insert formed of a pyrolized graphite cloth laminate secured within said throat section of said nozzle, a washer of predetermined thickness being located between said throat insert and said entrance section of said nozzle, said washer being consumable at temperatures greater than approximately 700° F. and yet capable of withstanding a temperature of approximately 320° F. and a pressure of approximately 7000 psi with a resultant maximum reduction of said predetermined thickness of approximately 15 percent and a steel housing encompassing said supporting structure, said supporting structure being transfer molded as one piece into said steel housing.
Claim 3
Dependent Claim
33 words
A rocket nozzle system as defined in claim 1 wherein said washer is made of the combination of two forms of a long chain synthetic polymer, fibrous binder particles and short length fibers.
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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) | 1982-04-23 | 1982-10-23 | 1983-04-24 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1986-04-23 | 1986-10-23 | 1987-04-24 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1990-04-23 | 1990-10-23 | 1991-04-24 | $7700.00 | Window Closed / Lapsed |