METHOD FOR MAKING A THROAT INSERT FOR ROCKET THRUSTERS
Assignee
NORTHROP GRUMMAN SPACE & MISSION SYSTEMS CORP.
Filed
Aug 22, 1997
Granted
Oct 24, 2000
Location
VERDES CA US
Abstract
A thruster rocket engine throat insert (12) has a thin walled shell (54) made from a high strength, oxidation resistant material. The shell (54) having a throat (48) of reduced cross-section and a radially extending annular stiffening ring (60) located at the throat (48). A casing (56) made from a material having a thermal conductivity at least 10 times greater than that of shell (54) is molded around an outer surface (58) of shell (54) and has a generally cylindrical exterior surface (59). Shell (54) resists yielding and oxidation caused by the extreme temperatures of rocket fuel combustion products passing through the throat insert (12), while the casing (56) acts to efficiently transfer heat from the shell (54).
Source: Google Patents
35 USC §181 Secrecy Order
Imposed
May 28, 1998
Rescinded
Dec 8, 1999
Duration
1 year, 6 months
Inventor
- 1DALE L. HOOK
Record Details
- Patent number
- US 6134781
- Application
- 08916379
- Aerospace match
- Yes
- Dataset source
- 35 USC §181 SO records
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