97 research outputs found
Fluid mechanics approach to acoustic liner design
Fluid mechanics approach to acoustic liner desig
Nonlinear Aspects of Combustion Instability in Liquid Propellant Rocket Motors. Second Yearly Progress Report for the Period 1 June 1961 to 31 May 1962
Combustion instability in liquid-propellant rocket engine
Recommended from our members
(Air flow patterns within buildings)
As Annex 20 enters the final year, deliverables in the form of reports, guidelines, and data formats are nearing completion. The Reporting Guidelines for the Measurement of Air Flows and Related Factors in Buildings will be published by the AIVC next month and was presented to the research community at the 11th AIVC Conference. Measurement guidelines and state-of-the-art equipment descriptions are part of a comprehensive manual, Measurement Techniques Related to Air Flow Patterns Within Buildings -- An Application Guide, in the final stages of preparation in Part 2 of Annex 20, together with reports on how to estimate the effects of flow through large openings, as well as contaminant movements in buildings. The Measurement Manual will include the latest information from the AIVC. The next AIVC Conference, in Ottawa, September 1991, will feature more than 12 presentations of Annex 20 results, including the information from Part 1 which has focused on the detailed air flow patterns in a variety of single-room configurations. Both complex modelling (including CFD) and detailed measurements have been completed, and it is now desirable that added tests be made in the next months by the University of Illinois, BERL, representing the US in Part 1 for the first time
Nonlinear Aspects of Combustion Instability in Liquid Propellant Rocket Motors Sixth Yearly Progress Report, 1 Jun. 1965 - 31 May 1966
Nonlinear aspects of combustion instability in liquid propellant rocket motor
High speed hydrogen/graphite interaction
Various aspects of a research program on high speed hydrogen/graphite interaction are presented. Major areas discussed are: (1) theoretical predictions of hydrogen/graphite erosion rates; (2) high temperature, nonequilibrium hydrogen flow in a nozzle; and (3) molecular beam studies of hydrogen/graphite erosion
Combustion contribution to noise in jet engines
The relative importance of combustion as a source of noise in a flow regime representative of a subsonic jet engine exhaust was investigated. The combustion noise source characteristics were obtained from pressure and temperature fluctuation measurements in the combustor and exhaust nozzle. The similarity between the fluctuations in this source region and the far field noise were compared. In the jet exhaust velocity range between 450 and 660 ft/sec investigated in detail, the frequencies of dominant pressure and temperature fluctuations in the combustor were also the frequencies of the dominant far field noise. The overall noise levels were 14 to 20 dB higher than from a corresponding clean jet in the same velocity range. Thus it seemed clear that the unsteadiness associated with the combustion process was responsible for the dominant noise in the far field. A simple analysis to predict the far field noise due to the internal pressure fluctuations causing exit plane velocity fluctuations produced trends closely resembling the measured results, but under predicted the far field noise over the spectral range examined. The possible reason for the higher far field noise is direct transmission of acoustic waves through the nozzle, which was not accounted for in the prediction scheme
Combustion instability research Summary report, 1970
Combustion instability in liquid rocket engine
Summary of combustion instability research at Princeton University, 1969
Control and causes of combustion instability in rocket engine
Recommended from our members
HEAT TRANSFER IN OSCILLATING FLOW. Second Progress Report for the Period October 1, 1959-September 30, 1960. Aeronautical Engineering Report No. 483-b
The investigation of heat transfer in oscillating flow was continued. A series of tests to further investigate the dependence of heat transfer on various parameters was made for three locations of the heat-transfer section along the duct at several harmonic frequencies with pressure amplitudes varying from 0.4 steady-state pressure to zero. (W.L.H.
Discussion: “Convective Heat Transfer in a Gas-Fired Pulsating Combustor” (Hanby, V. I., 1969, ASME J. Eng. Power, 91, pp. 48–52)
- …