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Fabrication process for combustion chamber/nozzle assembly
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 2001 |
| Description | An integral, lightweight combustion chamber/nozzle assembly for a rocket engine has a refractory metal shell defining a chamber of generally frusto-conical contour. The shell communicates at its smaller end with a rocket body, and terminates at its larger end in a generally contact contour, which is open at its terminus and which serves as a nozzle for the rocket engine. The entire inner surface of the refractory metal shell has a thermal and oxidation barrier layer applied thereto. An ablative silica phenolic insert is bonded to the exposed surface of the thermal and oxidation barrier layer. The ablative phenolic insert provides a chosen inner contour for the combustion chamber and has a taper toward the open terminus of the nozzle. A process for fabricating the integral, lightweight combustion chamber/nozzle assembly is simple and efficient, and results in economy in respect of both resources and time. |
| File Size | 413471 |
| Page Count | 7 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20080004644 |
| Archival Resource Key | ark:/13960/t5m955m2v |
| Language | English |
| Publisher Date | 2001-10-30 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Propulsion And Power Fabrication Rocket Nozzles Patents Refractory Metals Metal Shells Rocket Engines Combustion Chambers Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Patent |
