Pilot Gas Generator Ignition of Liquid Storable Fuels in a High Speed Air Stream

摘要

A study was performed to determine some of the combustion and flow characteristics associated with piloted ignition of liquid hydrocarbons injected directly into a supersonic air stream. Experiments were performed in a direct connect constant area combustor supplied by a Mach 2 air stream at a static pressure level of 1 atmosphere and at total temperatures ranging from ambient (530 R) to approximately 3300 R. The fuel was liquid hexane and was injected laterally into the flow through piloted and non-piloted injector configurations. Measurements include penetrations, combustor wall static pressure distributions and property profiles at two axial stations downstream of the injection point. It was found that autoignition and stable combustion occurs for total temperatures above about 2600 R. For temperatures below this limit minimum piloting requirements were established and it was found that the pilot mass flows needed for sustained combustion were small compared to the main fuel and air flow rates. Comparison with available theory indicates combustion efficiencies greater than 90% were obtaained. (Author)