Development of a High-Temperature Nuclear-Radiation-Resistant Pneumatic Power System for Flight Vehicles
Abstract
The preliminary study for Phase II of the turbo compressor program was completed; a satisfactory configuration was established for a four-stage centrifugal compressor utilizing a single shaft. Three high-temperature (1,500 deg F) experimental test runs were conducted on the pilot portion of the Model X pressure regulator while experimental room temperature testing of the Model F relief valves also was completed with satisfactory results.
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 24, 1963
- Accession Number
- AD0419205
Entities
Organizations
- General Dynamics