Interaction of Acoustic Waves with a Cryogenic Nitrogen Jet at Sub- and Supercritical Pressures
Abstract
Combustion instability has always been one of the most complex phenomena in liquid rocket engines, and therefore difficult to fully control particularly in designing large output rockets. These difficulties stem from the emergence of oscillatory combustion with large pressure amplitudes. In one classification, high-amplitude, low-frequency (< several hundred hertz) pressure variations (or chugging) due to combustion is understood to be coupled with the feed line and structural modes of oscillations. Chugging is responsive to system-type analysis. Another instability is characterized by high amplitudes and high frequencies (screaming), and can lead to local burnout of the combustion chamber walls and injector plates. This is caused by extreme heat-transfer rates brought about by high-frequency pressure and gas velocity fluctuations, see Harrje and Reardon.
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 23, 2001
- Accession Number
- ADA410897
Entities
People
- B. Chehroudi
- Doug Talley