NOZZLE SYSTEM DEVELOPMENT FOR HYBRID PROPULSION SYSTEM (U)
Abstract
Development of a hybrid propulsion concept has created the requirement for a lightweight nozzle system capable of withstanding gas temperature in excess of 6200 F with condensible soilds in excess of 25% by weight for operation longer than 30 seconds. A series of nozzle material test firings illustrated that tungsten impregnated with copper nozzle provided the best service. This led to the possibility that a transpiration effect or mass transfer cooling was being realized. A test program is now in process making use of pressure-driven liquid metal cooling through tungsten and graphite matrices subjected to a plasma-arc heat source. Tests indicate that liquid metal transpiration coolants, through a tungsten matrix coupled with nozzle inlet sacrificial materials, allow the possibility of longtime operation of a self-contained nozzle system suitable for hybrid or solid propellant rocket propulsion motors. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 01, 1961
- Accession Number
- AD0328004
Entities
People
- A.t. Robinson
- G.j. Wydra
- R.l. Mcalexander
Organizations
- Naval Air Weapons Station China Lake