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Dana Lattibeaudiere February 21, 2008 Propulsion Nozzle Design Injectors

Dana Lattibeaudiere February 21, 2008 Propulsion Nozzle Design Injectors. Assistance from Nicole Wilcox & Stephen Bluestone . Nozzle Design . CEA code Addition Pe /Pc ratio as input – varied Pc, O/F for each prop Output parameters: c*, ɛ , γ , Tc , M, a Assumption:

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Dana Lattibeaudiere February 21, 2008 Propulsion Nozzle Design Injectors

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  1. Dana LattibeaudiereFebruary 21, 2008PropulsionNozzle DesignInjectors Assistance from Nicole Wilcox & Stephen Bluestone AAE 450 Spring 2008

  2. Nozzle Design • CEA code Addition • Pe/Pc ratio as input – varied Pc, O/F for each prop • Output parameters: c*, ɛ, γ, Tc, M, a • Assumption: • Exit Pressure = 48,263 Pa – Reason: Find ɛ AAE 450 Spring 2008

  3. Injectors: • What are those? Who cares? • Cost: ~30% of total engine cost • Recommendations: • Liquid Propellants: • unlike, impinging type of injector • Hybrid Propellants: • Injects ox directly down the port • 91 – 93 % combustion efficiency • Injects ox into a pre-combustion chamber AAE 450 Spring 2008 Propulsion

  4. Backup Slides EXAMPLE: Selected this chamber pressure and O/F = 3 for LOX/LH2 case because there wasn’t much of a loss in Isp as Pc increased. Addition of mass is something we wanted to avoid. AAE 450 Spring 2008 Propulsion

  5. References • Humble, R. W., Henry, G. N., Larson, W. J., Space Propulsion Analysis and Design, McGraw-Hill, New York, NY, 1995. • Sutton, G. P., Rocket Propulsion Elements, Wiley & Sons, INC., New York, NY, 2001. AAE 450 Spring 2008

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