Hypersonic Air-Breathing Propulsion: Emerging Technologies and Cycles 17 August - 18 August 2019 JW Marriott, Indianapolis, Indiana
- Conference Rate: $700
- Early Member Rate: $500
- Standard Member Rate: $600
High-speed air-breathing propulsion is becoming more prevalent. The standard approaches involve turbojets, scramjets, and turbine-based combined cycle systems. Emerging cycles include the Japanese ATREX engine (Air Turbo Ramjet Engine with eXpander cycle) and the air-breathing rocket engine, which rely on pre-cooling the air with heat exchangers. Additional emerging cycles include pressure gain cycles (Pulse Detonation Engines and Rotating Detonation Engines), Mass Injection Pre-Combustion Cooling (MIPCC), Oxy-Boost that injects oxygen during the cycle, and turbo-ramjets in which the air bypasses the turbojet at high speeds and the afterburner is treated as a ramjet. This course is designed to explore these cycles and bring a theoretical understanding of how to apply them and what performance advantages they might have.
- High-speed air-breathing propulsion basics
- Overview of multiple combined cycle propulsion systems
- Overview of analysis techniques used in high-speed air-breathing propulsion
- Air-Turbo Rocket engine cycle
- Pressure Gain Cycles
- Airframe Integration
- Vehicle concept examples
Who Should Attend
The course is oriented toward aerospace conceptual designers and analysts interested in the application of hypersonic air-breathing to hypersonic cruise and access to space missions. This would include but is not limited to aircraft designers, propulsion engineers, systems engineers, and aerodynamicists.
- Learn the cycles and performance for emerging high-speed air-breathing propulsion concepts
- Learn the cycle and performance for air-breathing rocket engines
- Learn about pressure gain combustion processes and how they can fit into high-speed air-breathing propulsion cycles
- Learn the cycle and performance for cycle modifications like the Turbo-Ramjet, Mass Injection Pre-Combustion Cooling (MIPCC), and Oxy-Boost (oxygen injection into the combustion chamber)
- Learn the benefits of each in their application to hypersonic cruise and launch vehicles
- Learn high-speed propulsion integration
- Learn about vehicles concepts that exemplify various high-speed air-breathing propulsion concepts
Course Presented by the High-Speed Air-breathing Propulsion Technical Committee
Dr. John Bossard has over 25 years of experience in aerospace and advanced-technology industries, and has served in technical, management and executive leadership positions for Aerojet, CFD Research, KT Engineering, and Orion Propulsion. He specializes in Turbine Based Combined Cycle (TBCC) engines, particularly the Air Turbo Rocket (ATR) cycle.
Dr. Graham Candler uses computational fluid dynamics to study high-temperature reacting flows and hypersonic flows and is particularly interested in how the relaxation of internal energy modes and finite-rate chemical reactions interact with fluid motion. Applications of this work include the analysis of planetary entry spacecraft heat shields, hypersonic boundary layer transition, and the effects of chemical reactions on aerodynamics. Dr. Candler works closely with experimentalists to validate high-enthalpy flow models by careful comparison to shock tunnel data. Recently, Candler's research group has been working to extend computational methods to complex geometries for application to future scramjet-powered hypersonic aircraft. These tools were used to design an inward-turning inlet for an upcoming sounding rocket flight experiment of a Mach 10 vehicle.
Eric Donovan is a thermal management system development engineer with Rolls-Royce Libertyworks. He has worked on large and small development engine demonstrator programs. He also has experience designing and building cooling equipment for high energy applications.
Michael Karam is the chief functional engineer for high Mach applications at Rolls-Royce. His technical skill set includes gas turbine performance and operability, conceptual cycle design, and multidisciplinary optimization. Karam holds six patents for a range of gas turbine applications including hybrid-electric and open rotors.
Dr. Daniel E. Paxson is an aerospace research engineer with the NASA John H. Glenn Research Center, Research and Engineering Directorate. He earned his B.E. degree in mechanical engineering from Vanderbilt University and his M.S. and Ph.D. degrees at Rensselaer Polytechnic Institute. Since graduation, Dan has been at NASA conducting both experimental and analytical research in the areas of unsteady fluid mechanics, and gasdynamic-based propulsion and power systems. While there he has developed simulation, design, and optimization software, and designed or aided the design and operation of experimental rigs for wave rotor technology, active combustion instability control, high speed fuel valve systems, pulsed ejectors, pulsed (pressure-gain) combustors, pulse detonation engines, and rotating detonation engines. His simulation software has been used extensively by government, industry, and academic research groups. He has published more than 90 peer reviewed papers, of which 24 are in journals. Dan is an Associate Fellow in the American Institute of Aeronautics and Astronautics (AIAA). He serves as vice chair on the AIAA High Speed Air Breathing Propulsion Technical Committee, and he serves on the AIAA Pressure Gain Combustion Technical Committee. He is also a member of the JANNAF Pressure Gain Combustion Working Group, and has served as a subject matter expert for DARPA, DOE, and the Air Force.