Numerical Investigation on Multi-cycle Operation of Pulse Detonation Rocket Engine

Wei Fan,; Jianling Li,; Qiang Li,; Chuanjun Yan,

doi:10.1515/TJJ.2008.25.3.189

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Numerical Investigation on Multi-cycle Operation of Pulse Detonation Rocket Engine

Wei Fan, , Jianling Li, , Qiang Li, und Chuanjun Yan,

Veröffentlicht/Copyright: 1. September 2008

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Aus der Zeitschrift International Journal of Turbo and Jet Engines Band 25 Heft 3

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Fan,, Wei, Li,, Jianling, Li,, Qiang and Yan,, Chuanjun. "Numerical Investigation on Multi-cycle Operation of Pulse Detonation Rocket Engine" International Journal of Turbo and Jet Engines, vol. 25, no. 3, pp. 189-196. https://doi.org/10.1515/TJJ.2008.25.3.189

Fan,, W., Li,, J., Li,, Q. & Yan,, C. (). Numerical Investigation on Multi-cycle Operation of Pulse Detonation Rocket Engine. International Journal of Turbo and Jet Engines, 25(3), 189-196. https://doi.org/10.1515/TJJ.2008.25.3.189

Fan,, W., Li,, J., Li,, Q. and Yan,, C. () Numerical Investigation on Multi-cycle Operation of Pulse Detonation Rocket Engine. International Journal of Turbo and Jet Engines, Vol. 25 (Issue 3), pp. 189-196. https://doi.org/10.1515/TJJ.2008.25.3.189

Fan,, Wei, Li,, Jianling, Li,, Qiang and Yan,, Chuanjun. "Numerical Investigation on Multi-cycle Operation of Pulse Detonation Rocket Engine" International Journal of Turbo and Jet Engines 25, no. 3 (): 189-196. https://doi.org/10.1515/TJJ.2008.25.3.189

Fan, W, Li, J, Li, Q, Yan, C. Numerical Investigation on Multi-cycle Operation of Pulse Detonation Rocket Engine. International Journal of Turbo and Jet Engines. ;25(3): 189-196. https://doi.org/10.1515/TJJ.2008.25.3.189

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Published Online: 2008-09

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Artikel in diesem Heft

CONTENTS
Reduced-Order Model of a Mistuned Multi-Stage Bladed Rotor
Active and Passive Flow Control in a Turbine Cascade
Effects of Geometric and Structural Parameters on Coupled Bending Torsion Flutter in Turbo Machinery Blades
Turbomachine Shrouded Rotor Blade Forced Response Analysis
Numerical Investigation on Multi-cycle Operation of Pulse Detonation Rocket Engine
Determination of Performance and Parameters for Turboprop and Turboshaft Engine for Modification through Change of Gas Temperature Before Turbine
Performance Improvement of Gas Turbine Cycles
Characteristics of Supersonic Impinging Moist Air Jets

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https://doi.org/10.1515/TJJ.2008.25.3.189

Artikel in diesem Heft

CONTENTS
Reduced-Order Model of a Mistuned Multi-Stage Bladed Rotor
Active and Passive Flow Control in a Turbine Cascade
Effects of Geometric and Structural Parameters on Coupled Bending Torsion Flutter in Turbo Machinery Blades
Turbomachine Shrouded Rotor Blade Forced Response Analysis
Numerical Investigation on Multi-cycle Operation of Pulse Detonation Rocket Engine
Determination of Performance and Parameters for Turboprop and Turboshaft Engine for Modification through Change of Gas Temperature Before Turbine
Performance Improvement of Gas Turbine Cycles
Characteristics of Supersonic Impinging Moist Air Jets