Cooling Model Calibration in a Collaborative Turbine Preliminary Design Process Using the NASA Energy Efficient Engine Part II: 1D Turbine Modeling
Author:
Affiliation:
1. German Aerospace Center (DLR), Institute of Propulsion Technology, Turbine Department
2. German Aerospace Center (DLR), Institute of Propulsion Technology, Engine Department
Publisher
Gas Turbine Society of Japan
Link
https://www.jstage.jst.go.jp/article/jgpp/15/3/15_vol15no3tp04/_pdf
Reference27 articles.
1. Krumme, A. “Konzeption, Implementierung Und Anwendung Eines Automatisierten Aerothermodynamischen Vorentwurfsprozesses Fuer Axialturbinen”. Universitaet Kassel, 2015.
2. Grieb, H. Projektierung von Turboflugtriebwerken. Basel: Springer Basel, 2004. DOI: 10.1007/978- 3- 0348- 7938-5.
3. Holland, M. and Thake, T. “Rotor Blade Cooling in High Pressure Turbines”. In: Journal of Aircraft 17.6 (1980), pp. 412–418. DOI: 10.2514/3.44668.
4. Young, J. and Wilcock, R. “Modeling the Air-Cooled Gas Turbine: Part 2 - Coolant Flows and Losses”. In: Journal of Turbomachinery 124.2 (2002), pp. 214–221. DOI: 10 . 1115/1.1415038.
5. Torbidoni, L. and Horlock, J. “A New Method to Calculate the Coolant Requirements of a High-Temperature Gas Turbine Blade”. In: Journal of Turbomachinery 127.1 (2005), pp. 191–199. DOI: 10.1115/1.1811100.
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1. Cooling Model Calibration in a Collaborative Turbine Preliminary Design Process Using the NASA Energy Efficient Engine - Part I: 0D Performance Modeling;International Journal of Gas Turbine, Propulsion and Power Systems;2024
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