TRANSPIRATION COOLING AND FLOW-SEPARATION CONTROL BY GASEOUS INJECTION IN A POROUS NOZZLE
Abstract
Transpiration cooling and flow-separation control by gaseous injection in a porous-wall rocket nozzle were evaluated in a pilot-scale study. Gaseous oxygen and hydrogen were used as propellants in a nominal 1000-lb-thrust system. Gaseous hydrogen was injected through a 1/4-in.thick, porous, nozzle liner fabricated from 5micron-particle-size sintered stainless steel, and with an expansion ratio of 25. The convergent and throat sections of this nozzle were severely eroded in the first test due to cracking of the liner. Eight subsequent tests were conducted on a modified nozzle which utilized the porous liner in the divergent section only. Transpiration cooling was 100% effective at an injectant/total propellant ratio of 0.028. A significant exhaust jet deflection was achieved by asymmetric mass addition in one test before a control malfunction caused nozzle burnout. A mathematical analysis of heat transfer and fluid flow in porous media is derived and the computer solution of the resulting equations is presented in terms of parameters of interest to nozzle designers. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1961
- Accession Number
- AD0263458
Entities
People
- A.w. Magnusson
- B. Misra
- W.r. Thompson
Organizations
- Aerojet Rocketdyne Holdings