Integrated Thermal Management System Design for Advanced Propulsion System

De Cang Lou; Wen Guo; Zhi Guo Wang; Yong Hong Wang

doi:10.4028/www.scientific.net/AMM.232.723

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Dynamic Stress Intensity Factor Computation by Using Xfem Formulation
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HomeApplied Mechanics and MaterialsApplied Mechanics and Materials Vol. 232Integrated Thermal Management System Design for...

Integrated Thermal Management System Design for Advanced Propulsion System

Abstract:

Thermal management system (TMS) design is considered to be a key technology for advanced aero engines and supersonic or hypersonic propulsion systems. In this paper, the concepts of coupling flow and thermodynamic networks are proposed for TMS design. In this method, the propulsion system is considered to be a zero-dimensional flow system. Components, subsystems and hence the entire engine system can be modelled using some basic flow and thermodynamics networks. The platform for TMS design, ThermalM, is developed based on this model. As an example, modelling for a Turbine Based Combined Cycle (TBCC) thermal management system is described. Performance of the fuel heat exchanger in the network is discussed in detail. With the TMS design technology, performance of the advanced propulsion system can be analysed.

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Periodical:

Applied Mechanics and Materials (Volume 232)

Pages:

723-729

DOI:

https://doi.org/10.4028/www.scientific.net/AMM.232.723

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Online since:

November 2012

Authors:

De Cang Lou, Wen Guo, Zhi Guo Wang, Yong Hong Wang

Keywords:

Flow Networks, Thermal Management System, Thermal Protection System, Thermodynamics Networks, Turbine Based Combined Cycle (TBCC)

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References

[1] AIAA Air Breathing Propulsion Technical Committee, THE VERSATILE AFFORDABLE ADVANCED TURBINE ENGINES (VAATE) INITIATIVE, January, (2006).

Google Scholar

[2] David E. Glass*, N. Ronald Merski, and Christopher E. Glass. Airframe Research and Technology for Hypersonic Airbreathing Vehicles. NASA Langley Research Center, Hampton, VA 23681 AIAA-2002-5137.

DOI: 10.2514/6.2002-5137

Google Scholar

[3] Marc BOUCHEZ. PTAH-SOCAR Fuel-cooled Composite Materials Structure for Dual-Mode Ramjet and Liquid Rocket Engines. MBDA France AIAA-2004-3653.

DOI: 10.2514/6.2004-3653

Google Scholar

[4] Marvin R. Glickstein, Robert J. Bengston. Applications of Endothermic Reaction Technology to HSCT and AST. NASA/CR-2005-213133.

Google Scholar

[5] Traci, R. M. et al., Integrated thermal management of a hybrid electric vehicle, J. Magnetics, IEEE Transactions. Vol. 35, Jan. 1999, pp.479-483.

DOI: 10.1109/20.738455

Google Scholar

[6] P. L. Moses, K. A. Bouchard, R. F. Vause, S. Z. Pinckney. An Airbreathing Launch Vehicle Design with Turbine-Based Low-Speed Propulsion and Dual Mode Scramjet High-Speed Propulsion. NASA Langley Research Center, Hampton, VA AIAA-99-4948.

DOI: 10.2514/6.1999-4948

Google Scholar