HOT FIRING EVALUATION OF SPIRAL WOUND RIBBON STRUCTURES FOR TRANSPIRATION/FILM COOLING.
Quarterly progress rept. no. 2, 1 Jul-30 Sep 66,
MARQUARDT CO VAN NUYS CA
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The work reported in this report consisted of continuation of the design analysis and fabrication of the test engine components. Checkout operations of the modified grooving and spiral winding tooling are nealy complete in preparation for fabrication of the test structures. The stress analysis and mechanical testing of the Inconel 718 ribbon structures has provided data for evaluation of the structural integrity of the cooled test engine component. A compatibility test of refractory metals in hot N2O4 vapor indicates that certain of the refractory metals may be suitable as the second material for fabrication of the spiral wound ribbon structure. Most of the test engine components have been fabricated in preparation for the test operations to begin in the next quarter. Author
- Rocket Engines