Is this project an undergraduate, graduate, or faculty project?
Undergraduate
Project Type
group
Campus
Daytona Beach
Authors' Class Standing
Gus Gatti, Senior Nico Guido, Senior
Lead Presenter's Name
Gus Gatti
Lead Presenter's College
DB College of Engineering
Faculty Mentor Name
Mark Ricklick
Abstract
A propulsion system featuring two mixed-flow low-bypass turbofan engines (LBTF) and one ramjet engine was designed to satisfy a specified mission, which included a supersonic cruise at Mach 2.5 and a hypersonic dash at Mach 5 under ramjet power. A preliminary constraint and mission analysis was performed to determine each of the engine's performance characteristics and define the thermal cycle. Subsonic and supersonic inlets were designed, and the diffuser flow health was validated using Sovran and Klomp plots for both engines. Nozzles were designed for both engines, and viscous, angularity, and pressure losses were considered. Compressor and turbine stages were designed using the free-vortex principle, and preliminary blade geometry and velocity triangles were defined for each stage of the LBTF. The effect of internal vs external compression was explored for both inlets, and a new internal compression inlet will be designed for the ramjet to control size and losses. The finalized supersonic LBTF inlet resulted in an adiabatic efficiency of 90.2%. The two LBTF engines produced a combined 682.4 KN of Sea Level Static (SLS) thrust, and the ramjet produced 669.5 KN of thrust at the design point Mach 5 cruise.
Did this research project receive funding support (Spark, SURF, Research Abroad, Student Internal Grants, Collaborative, Climbing, or Ignite Grants) from the Office of Undergraduate Research?
No
Hypersonic Propulsion System Design
A propulsion system featuring two mixed-flow low-bypass turbofan engines (LBTF) and one ramjet engine was designed to satisfy a specified mission, which included a supersonic cruise at Mach 2.5 and a hypersonic dash at Mach 5 under ramjet power. A preliminary constraint and mission analysis was performed to determine each of the engine's performance characteristics and define the thermal cycle. Subsonic and supersonic inlets were designed, and the diffuser flow health was validated using Sovran and Klomp plots for both engines. Nozzles were designed for both engines, and viscous, angularity, and pressure losses were considered. Compressor and turbine stages were designed using the free-vortex principle, and preliminary blade geometry and velocity triangles were defined for each stage of the LBTF. The effect of internal vs external compression was explored for both inlets, and a new internal compression inlet will be designed for the ramjet to control size and losses. The finalized supersonic LBTF inlet resulted in an adiabatic efficiency of 90.2%. The two LBTF engines produced a combined 682.4 KN of Sea Level Static (SLS) thrust, and the ramjet produced 669.5 KN of thrust at the design point Mach 5 cruise.