TRANSPIRATION-FILM COOLING STUDY USING SPIRAL-WOUND-RIBBON NOZZLES.
Abstract
This report describes the work conducted to establish the feasibility of using the spiral-wound-ribbon type structure for a transpiration-film cooled nozzle. An analysis was developed and a computer program was written for transpiration-film cooling, which considered the three-dimensional effects within the wall structure. A bench test program was conducted which provided experimentation performance data of the transpiration cooling of a grooved ribbon structure. The use of the grooved ribbon structure, along with a unique single-wire thermocouple technique, permitted obtaining actual wall temperature measurements without interferring with the coolant flow passages. Axisymmetric convergent-divergent nozzles were designed, fabricated, and tested up to 500 psi and 3600 R gas stream conditions. The spiral winding and bonding results, along with the test results, indicate that this type of construction isf feasible for rocket cooling applications. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1966
- Accession Number
- AD0487187
Entities
People
- A. Robert Nagy Jr.
- George A. Yankura
- John E. Ahern