Rocket Engine Evaluation of Erosion and Char as Functions of Fabric Orientation for Silica-Reinforced Nozzle Materials.
Abstract
Thirty-five silica reinforced ablative specimens were evaluated as nozzle sections of a storable propellant (nitrogen tetroxide and a blend of 50-percent unsymmetrical dimethyl hydrazine and 50-percent hydrazine) rocket engine. Testing was performed at an oxidant-to-fuel ratio of 1. 6, a chamber pressure of 100 psia (689 kN/sq meters), an initial throat diameter of 7.82 inches (19. 8 cm), and a run duration of 150 seconds. Both oxidant-to-fuel ratio and chamber pressure were maintained constant during the test firing. Ten materials and five fabric orientations were evaluated. Quartz reinforcement was determined to have the greatest resistance to erosion, but a low-cost silica powder-filled material was also high in erosion resistance. For most of the materials tested, a fabric orientation of 60 deg to the nozzle centerline resulted in low char depths and high resistance to erosion. A 0 deg helix angle used for the rosette layup resulted in delaminations and severe erosion. The fabric layup angle to the gas stream should be minimized to minimize char depth and reduce engine weight. A 0 deg angle cannot be used because of delaminations; however, a rosette layup gives the effect of minimum angle to the gas stream.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1969
- Accession Number
- ADA306886
Entities
People
- Arthur M. Shinn Jr.
- Donald A. Peterson
- Jerry M. Winter
Organizations
- Glenn Research Center