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Languages : en
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MULTIPLE-CYCLE SIMULATION OF A PULSE DETONATION ENGINE EJECTOR... NASA
Author:
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Category :
Languages : en
Pages :
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Publisher:
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Category :
Languages : en
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Multiple-Cycle Simulation of a Pulse Detonation Engine Ejector
Author: S. Yungster
Publisher:
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Category :
Languages : en
Pages : 18
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 18
Book Description
MULTIPLE-CYCLE SIMULATION OF A PULSE DETONATION ENGINE EJECTOR... NASA/TM--2002-211888... NATIONAL AERONAUTICS AND SPACE ADMINISTRATION... O
Author:
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Category :
Languages : en
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Publisher:
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Category :
Languages : en
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Multiple-cycle Simulation of a Pulse Detonation Engine Ejector
Author: Shaye Yungster
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Category :
Languages : en
Pages : 10
Book Description
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Category :
Languages : en
Pages : 10
Book Description
Thrust Augmentation Measurements Using a Pulse Detonation Engine Ejector
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721571031
Category :
Languages : en
Pages : 34
Book Description
The present NASA GRC-funded three-year research project is focused on studying PDE driven ejectors applicable to a hybrid Pulse Detonation/Turbofan Engine. The objective of the study is to characterize the PDE-ejector thrust augmentation. A PDE-ejector system has been designed to provide critical experimental data for assessing the performance enhancements possible with this technology. Completed tasks include demonstration of a thrust stand for measuring average thrust for detonation tube multi-cycle operation, and design of a 72-in.-long, 2.25-in.-diameter (ID) detonation tube and modular ejector assembly. This assembly will allow testing of both straight and contoured ejector geometries. Initial ejectors that have been fabricated are 72-in.-long-constant-diameter tubes (4-, 5-, and 6-in.-diameter) instrumented with high-frequency pressure transducers. The assembly has been designed such that the detonation tube exit can be positioned at various locations within the ejector tube. PDE-ejector system experiments with gaseous ethylene/ nitrogen/oxygen propellants will commence in the very near future. The program benefits from collaborations with Prof. Merkle of University of Tennessee whose PDE-ejector analysis helps guide the experiments. The present research effort will increase the TRL of PDE-ejectors from its current level of 2 to a level of 3. Santoro, Robert J. and Pal, Sibtosh Glenn Research Center NASA/CR-2003-212191, NAS 1.26:212191, E-13794
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721571031
Category :
Languages : en
Pages : 34
Book Description
The present NASA GRC-funded three-year research project is focused on studying PDE driven ejectors applicable to a hybrid Pulse Detonation/Turbofan Engine. The objective of the study is to characterize the PDE-ejector thrust augmentation. A PDE-ejector system has been designed to provide critical experimental data for assessing the performance enhancements possible with this technology. Completed tasks include demonstration of a thrust stand for measuring average thrust for detonation tube multi-cycle operation, and design of a 72-in.-long, 2.25-in.-diameter (ID) detonation tube and modular ejector assembly. This assembly will allow testing of both straight and contoured ejector geometries. Initial ejectors that have been fabricated are 72-in.-long-constant-diameter tubes (4-, 5-, and 6-in.-diameter) instrumented with high-frequency pressure transducers. The assembly has been designed such that the detonation tube exit can be positioned at various locations within the ejector tube. PDE-ejector system experiments with gaseous ethylene/ nitrogen/oxygen propellants will commence in the very near future. The program benefits from collaborations with Prof. Merkle of University of Tennessee whose PDE-ejector analysis helps guide the experiments. The present research effort will increase the TRL of PDE-ejectors from its current level of 2 to a level of 3. Santoro, Robert J. and Pal, Sibtosh Glenn Research Center NASA/CR-2003-212191, NAS 1.26:212191, E-13794
Thrust Augmentation Measurements Using a Pulse Detonation Engine Ejector
Author:
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Category :
Languages : en
Pages : 24
Book Description
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Category :
Languages : en
Pages : 24
Book Description
Development of a Gas-Fed Pulse Detonation Research Engine
Author: R. J. Litchford
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Category : Detonation waves
Languages : en
Pages : 52
Book Description
Publisher:
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Category : Detonation waves
Languages : en
Pages : 52
Book Description
Thrust Augmentation Measurements Using a Pulse Detonation Engine Ejector ... Nasa/cr--2003-212191 ... National Aeronautics and Space Administr
Author: United States. National Aeronautics and Space Administration
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Category :
Languages : en
Pages :
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Category :
Languages : en
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Monthly Catalog of United States Government Publications
Author:
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Category : Government publications
Languages : en
Pages : 1102
Book Description
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Category : Government publications
Languages : en
Pages : 1102
Book Description
Multiple Cycle Detonation Experiments During the Development of a Pulse Detonation Engine
Author: Michael J. Aarnio
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Category :
Languages : en
Pages :
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Publisher:
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Category :
Languages : en
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