Andere Kunden interessierten sich auch für
![Detonation Propagation Through Ducts in a Pulsed Detonation Engine]( "Detonation Propagation Through Ducts in a Pulsed Detonation Engine")
Detonation Propagation Through Ducts in a Pulsed Detonation Engine63,99 €![Direct Initiation Through Detonation Branching in a Pulsed Detonation Engine]( "Direct Initiation Through Detonation Branching in a Pulsed Detonation Engine")
Direct Initiation Through Detonation Branching in a Pulsed Detonation Engine63,99 €![Heat Transfer Experiments on a Pulse Detonation Driven Combustor]( "Heat Transfer Experiments on a Pulse Detonation Driven Combustor")
Heat Transfer Experiments on a Pulse Detonation Driven Combustor64,99 €![Fuel Composition Analysis of Endothermically Heated Jp-8 Fuel for Use in a Pulse Detonation Engine]( "Fuel Composition Analysis of Endothermically Heated Jp-8 Fuel for Use in a Pulse Detonation Engine")
Fuel Composition Analysis of Endothermically Heated Jp-8 Fuel for Use in a Pulse Detonation Engine63,99 €![Computational Analysis of Geometric Effects on Strut Induced Mixing in a Scramjet Combustor]( "Computational Analysis of Geometric Effects on Strut Induced Mixing in a Scramjet Combustor")
Computational Analysis of Geometric Effects on Strut Induced Mixing in a Scramjet Combustor64,99 €![Rubidium Recycling in a High Intensity Short Duration Pulsed Alkali Laser]( "Rubidium Recycling in a High Intensity Short Duration Pulsed Alkali Laser")
Rubidium Recycling in a High Intensity Short Duration Pulsed Alkali Laser64,99 €![Operational Characteristics of a Rotating Detonation Engine Using Hydrogen and Air]( "Operational Characteristics of a Rotating Detonation Engine Using Hydrogen and Air")
Operational Characteristics of a Rotating Detonation Engine Using Hydrogen and Air63,99 €
It has been proposed that the implementation of a pulsed detonation combustor in a high-bypass turbofan engine would result in an engine that is both more efficient and more reliable. The validity of the performance claims are evaluated based on a comparison between the baseline and hybrid turbofans as modeled in the Numerical Propulsion System Simulation (NPSS). The engine cycle of the baseline high-bypass turbofan is evaluated and compared using both the Aircraft Engine Design System (AEDsys) and NPSS programs. The baseline engine agreed to within 1% on the net thrust calculation and specific fuel consumption between the two programs. Differences are traceable to the variation in specific heat models and to different methods of calculating temperature across the turbine and compressor components. The hybrid pulsed detonation engine model shares a common architecture with the baseline turbofan model. Inlet mass flow and core mass flow are maintained, but the combustor of the baseline engine is replaced with a pulsed detonation combustor for the hybrid engine. The effect of detonation on the core airflow is calculated using a closed form solution of the Chapman-Jouguet Mach number with a total energy correction applied. Cycle time is calculated to provide a reasonable estimate of frequency for the user input geometry. Effects of sub-component design choices within the pulsed detonation combustor are evaluated using simple parametric studies. These studies are used to select an optimal architecture for the combustor. The effects of detonation are accounted for by applying pressure and temperature losses to the fluid exiting the combustor. A parametric study was performed to demonstrate what level of loss continues to yield a more efficient engine. Results show improvement in thrust specific fuel consumption with careful selection of combustor design parameters. There is a definite level of acceptable loss that if surpassed makes pulsed detonation combustion a good
Hinweis: Dieser Artikel kann nur an eine deutsche Lieferadresse ausgeliefert werden.
Hinweis: Dieser Artikel kann nur an eine deutsche Lieferadresse ausgeliefert werden.