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Design of High Heat Release Slinger Combustor with Rapid Acceleration Requirement
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English
Abstract
Reliable turbojet engine ignition and rapid acceleration at high combustor heat release rates have recently gained in importance for drone and missile applications. These requirements are imposed due to the necessity to minimize engine size and booster needs. Because of the mission and flight envelope, the combustor must also be capable of high-altitude variable Mach number and windmill starts. Design and development of a 10 lb/s airflow combustor delivering in excess of 12 × 106 Btu/h-ft3-atm (1.22 kW/m3 Pa) is described. Pyrotechnic devices are used for ignition and acceleration. Optimized fuel scheduling combined with efficient combustor and fuel slinger characteristics have demonstrated engine start and acceleration to maximum power in less than 5 s at sea-level conditions.
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Authors
Citation
Rogo, C. and Trauth, R., "Design of High Heat Release Slinger Combustor with Rapid Acceleration Requirement," SAE Technical Paper 740167, 1974, https://doi.org/10.4271/740167.Also In
References
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