DEMONSTRATION OF AN ADVANCED TRANSPIRATION-COOLED THRUST CHAMBER
Abstract
An advanced transpiration-cooled thrust chamber concept has been tested extensively with both N2O4 and ClF3 as coolants. This concept utilizes stacked ultra-thin (0.001 to 0.020 in.) platelets to form a porous combustion chamber wall. Each platelet contains precise flow control channels which meter the coolant flow to the cooled surface and prevent the formation and growth of local hot spots. To demonstrate feasibility of the concept, two completely transpiration cooled chambers were fabricated and tested. A total of 121 tests were made with the N2O4-cooled chamber (stainless steel) for a cumulative firing duration of 3076.7 seconds. Ninety-six tests were made at the 100 lb thrust level and 25 tests at the 1000 lb thrust level. The cumulative firing duration for the ClF3-cooled chamber (nickel) was 219.2 seconds. Thirteen tests were made at the 100 lb thrust level and 16 tests were made at the 1000 lb thrust level. Thermal data obtained during these tests indicate that, aside from injector streaking effects, the TRANSPIRE system operated as designed. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 31, 1967
- Accession Number
- AD0385085
Entities
People
- Albert L. Blubaugh
- Edward J. Zisk
Organizations
- Aerojet Rocketdyne Holdings