Method for making a throat insert for rocket thrusters
US6134781A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Aug 22, 1997 |
| Grant date | Oct 24, 2000 |
| Priority date | — |
| Expiry date | Aug 22, 2017 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49346
- WIPO fieldMachine tools
- WIPO sectorMechanical engineering
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: USPTO / EPO open patent data. Objective bibliographic and citation counts.