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Published byAugusta Stone Modified over 9 years ago
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Team 18: Design Optimization of a Supersonic Nozzle
Marc Linares Project Coordinator Alessandro Ciampitti Optimization Engineer Marco Robaina CFD Engineer Advisor: Prof. George S. Dulikravich
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Design Optimization of a Supersonic Nozzle
De Laval nozzle Convergent Section Throat Divergent Section
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Timeline for Presentation
Problem Statement Applications Optimization Goals Design Considerations Software Methods Manufacturing Validation Project Timeline Conclusion
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Problem Statement Non-uniformities of the flow at the nozzle exit due to upstream conditions & gradients Pressure Temperature Density Speed Shock wave development inside nozzle Difference of inlet stagnation pressure and exit pressure
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Applications Rocket Propulsion Wind Tunnel
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Motivation Global Approach
Supersonic wind tunnel test facilities improvements Optimized nozzle shape can maximize thrust force Ø Many countries are developing space programs Optimized nozzle will have minimum length & weight Global Approach
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Optimization Goals
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Minimize Flow Separation Avoid Shock Wave Development Back Flow
Divergent Section Length Weight Cost
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Exit-to-Throat Area Ratio
Maximize Exit Mach Number Exit Velocity Thrust Force Exit Flow Uniformity Exit-to-Throat Area Ratio
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Design Considerations
2-D/3-D flow Isentropic Quasi-One dimensional Euler equations non-viscous flow Navier-Stokes equations viscous turbulent flow Chemical properties are not considered Shock wave location Compressible flow Nozzle selection (feasibility) thttp://
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Design Alternative 1: Conical
Simple Design (feasibility) Manufacturing Simulation Optimization Constant half angle at divergent section Velocity components in flow
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Design Alternative 2: Bell
Most commonly used design Parabolic cone shape Half angle constantly changes Shorter length Efficient at design exit pressure bell nozzle
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Design Alternative 3: Dual Bell
Most difficult design of the three Altitude compensation (Ambient Pressure) Higher pressure: Wall inflection separates flow Lower pressure: Flow through entire geometry Higher overall efficiency for changes in pressure Lower efficiency at optimal pressure
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Software Modules Involved
Geometric Shape & Grid CFD Analysis Response Surface & Optimization
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Modeling SolidWorks/ANSYS Initial Designs (from previous work/designs)
Final Design (from optimization)
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CFD Analysis LOCI 2-D/3-D flow analysis Hot flow/cold flow
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Optimization Process ModeFrontier Optimization of nozzle parameters
Response Surface Evolutionary Based Algorithm Particle Swarm (PS) Optimal Solution
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Manufacturing Dimensional Analysis (small scale)
True scale versus model Plexiglas design Alternative Materials being considered
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Relevant Standards AS 9100 Quality management of aerospace industry
Created by SAE – Society of Automotive Engineers ASME Y14.5 Many standards are proprietary
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Validation Cold flow testing to be conducted with a compressed air cylinder Measuring devices: Thermocouples Pressure gauge
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Project Timeline & Responsibilities
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Summary: 8 Month Capstone Project
Develop a system for better performing supersonic nozzles Maximizing Mach Number & Flow Uniformity Minimizing Divergent Length & Flow Separation Use of different software programs Analysis & Optimization Manufacturing & Testing Standards Cold gas
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