HIGH SPEED PROPULSION: ENGINE DESIGN - INTEGRATION AND THERMAL MANAGEMENT

From September 13 to September 16, 2010

von Karman Institute, Rhode-St-Genèse, Belgium

Hypersonic systems will provide a revolution in commercial transport, space access, and military missions. The objective of this RTO lecture series is to provide clear engineering guidelines. Following the keynote lecture, turbine based cycles will be introduced, including variable cycles. A rocket-ramjet combined cycle engine is then proposed. A lecture on detonation propulsion will focus on fundamental properties; various design concepts with their theoretical and measured performances.

The first lecture of the second day will demonstrate the design process of a ramjet intake by an example for Mach 4 to 6. The second lecture will present engineering models of the aerodynamics and propulsion to evaluate the cruise flight performance of future long range missiles with special attention to vehicle-engine integration. The third presentation will address the combined thermal loading due to the aerodynamic heating as well as reactive gas dynamics from the propulsion unit. Thermal equilibrium conditions of the structural parts will be evaluated with and without active cooling. The fourth lecture will be dedicated to the specific design of the scramjet intakes.

The third day will be dedicated to scramjets and dual mode operation. The first lecture will present design rules on the isolator and nozzle. The next two presentations will present the experimental experience on self-ignition, stabilization and blow-out/blow-off of the combustion in the high-speed combustion chamber with Mach numbers at the entrance from 2 to 5, using different fuels. Additionally, the results of an experimental study of a full scramjet model operating on kerosene will be reported at Mach numbers 5 and 6 for flow parameters close to in-flight conditions.

The fourth lecture will focus on the estimation of the heat loads on a scramjet or a dual-mode ramjet. Solutions to sustain such high energy will be proposed and how to combine materials, cooling techniques and system requirements.

The final day will start with the overall system analysis of scramjets, considering what is the optimum number of engine modules; comparison between fixed or movable geometry; effect of engine mass and size to on-trajectory-performance of an air-breathing space launcher. The second lecture will present an overview on EU funded research programs. The third lecture will present the major achievements and lessons learned from the Sanger II project, with emphasis on the selection of the combined cycle engine, propulsion operational modes. The last lecture will review the LEA program and its contributions to address key technologies considering potential future extensions. In few lectures the audience will be invited to participate performing some calculations, remember to bring your pocket calculator with you.

The directors of this VKI/RTO Lecture Series are Dr. J. Steelant (European Space Agency) and Prof. G. Paniagua (von Karman Institute).

TIMETABLE

Monday 13 September, 2010

• 08:45    Registration
• 09:15    Welcome Address
  J. Muylaert, Director, von Karman Institute for Fluid Dynamics, Belgium
• 09:30    Keynote lecture: Engineering approach of engine /  airframe integration for reusable space transportation systems
  P.W. Sacher, Consultant, Germany
• 11:15    The mission defines the cycle: turbojet, turbofan and  variable cycle engines for high speed propulsion
  J. Kurzke, Consultant, Germany
• 14:00    Rocket based cycles
  T. Hiraiwa, Jaxa, Japan
• 15:45    Pulsed detonation propulsion
  S. Frolov, Semenov Institute, Russia
• 17:00    Reception

Tuesday 14 September, 2010

• 09:00    Ramjets: intake design
  T. Cain, GDL, United Kingdom
• 10:45    Ramjets: airframe integration
  J.L. Moerel, TNO, The Netherlands
• 14:00    Ramjets: thermal management
  R. Veraar, TNO, The Netherlands
• 15:45    Scramjet: intake design
  M. Smart, University of Queensland, Australia

Wednesday 15 September, 2010

• 09:00    Scramjets: isolator design
  M. Smart
• 09:40    Scramjets: nozzle design
  T. Cain
• 10:45    Features gas dynamic processes in combustion chambers of ramjet/scramjet
  M. Goldfeld, ITAM, Russia
• 14:00    Experimental investigations of combustion cambers of ramjet/scramjet
  M. Goldfeld
• 15:45    Scramjets: Thermal Management
  M. Bouchez, MBDA, France

Thursday 16 September, 2010

• 09:00    Structural design of dual-mode ramjets and associated system issues
  M. Bouchez
• 10:45    Hypersonic technology developments with EU co-funded projects
  J. Steelant, ESTEC-ESA, The Netherlands
• 14:00    The engineering design of engine / airframe integration for the SÄNGER fully reusable space transportation system
  P.W. Sacher
• 15:45    LEA program contribution to general development methodology for dual-mode ramjet (DMR) powered vehicles
  F. Falempin, MBDA, France
• 17:00     End of Lecture Series

Lunch will be taken from 12h30 to 14h00. Coffee breaks are scheduled each morning and afternoon.

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Location : von Karman Institute for Fluid Dynamics, Rhode-St-Genèse, Belgium

From 13.09.2010 to 16.09.2010