Three-dimensional Computational Fluid Dynamics Analysis of a Rocket-based Combined-cycle Engine in Ejector Mode PDF Download
Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download Three-dimensional Computational Fluid Dynamics Analysis of a Rocket-based Combined-cycle Engine in Ejector Mode PDF full book. Access full book title Three-dimensional Computational Fluid Dynamics Analysis of a Rocket-based Combined-cycle Engine in Ejector Mode by Douglas S. Brocco. Download full books in PDF and EPUB format.
Author: Douglas S. Brocco
Publisher:
ISBN:
Category : Fluid dynamics
Languages : en
Pages : 125
Get Book Here
Book Description
Author: Douglas S. Brocco
Publisher:
ISBN:
Category : Fluid dynamics
Languages : en
Pages : 125
Get Book Here
Book Description
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721568871
Category :
Languages : en
Pages : 26
Get Book Here
Book Description
The GTX program at NASA Glenn Research Center is designed to develop a launch vehicle concept based on rocket-based combined-cycle (RBCC) propulsion. Experimental testing, cycle analysis, and computational fluid dynamics modeling have all demonstrated the viability of the GTX concept, yet significant technical issues and challenges still remain. Our research effort develops a unique capability for dynamic CFD simulation of complete high-speed propulsion devices and focuses this technology toward analysis of the GTX response during critical mode transition events. Our principal attention is focused on Mode 1/Mode 2 operation, in which initial rocket propulsion is transitioned into thermal-throat ramjet propulsion. A critical element of the GTX concept is the use of an Independent Ramjet Stream (IRS) cycle to provide propulsion at Mach numbers less than 3. In the IRS cycle, rocket thrust is initially used for primary power, and the hot rocket plume is used as a flame-holding mechanism for hydrogen fuel injected into the secondary air stream. A critical aspect is the establishment of a thermal throat in the secondary stream through the combination of area reduction effects and combustion-induced heat release. This is a necessity to enable the power-down of the rocket and the eventual shift to ramjet mode. Our focus in this first year of the grant has been in three areas, each progressing directly toward the key initial goal of simulating thermal throat formation during the IRS cycle: CFD algorithm development; simulation of Mode 1 experiments conducted at Glenn's Rig 1 facility; and IRS cycle simulations. The remainder of this report discusses each of these efforts in detail and presents a plan of work for the next year. Edwards, Jack R. and McRae, D. Scott and Bond, Ryan B. and Steffan, Christopher (Technical Monitor) Glenn Research Center NASA/CR-2003-212193, E-13796, NAS 1.26:212193
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 36
Get Book Here
Book Description
Author: James R. DeBonis
Publisher:
ISBN:
Category : Fluid dynamics
Languages : en
Pages : 24
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 28
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 14
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages :
Get Book Here
Book Description
A new concept for the low speed propulsion mode in rocket based combined cycle (RBCC) engines has been developed as part of the NASA GTX program. This concept, called the independent ramjet stream (IRS) cycle, is a variation of the traditional ejector ramjet (ER) design and involves the injection of hydrogen fuel directly into the air stream, where it is ignited by the rocket plume. Experiments and computational fluid dynamics (CFD) are currently being used to evaluate the feasibility of the new design. In this work, a Navier-Stokes code valid for general reactive flows is applied to the model engine under cold flow, ejector ramjet, and IRS cycle operation. Pressure distributions corresponding to cold-flow and ejector ramjet operation are compared with experimental data. The engine response under independent ramjet stream cycle operation is examined for different reaction models and grid sizes. The engine response to variations in fuel injection is also examined. Mode transition simulations are also analyzed both with and without a nitrogen purge of the rocket. The solutions exhibit a high sensitivity to both grid resolution and reaction mechanism, but they do indicate that thermal throat ramjet operation is possible through the injection and burning of additional fuel into the air stream. The solutions also indicate that variations in fuel injection location can affect the position of the thermal throat. The numerical simulations predicted successful mode transition both with and without a nitrogen purge of the rocket; however, the reliability of the mode transition results cannot be established without experimental data to validate the reaction mechanism.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 22
Get Book Here
Book Description
Author: Shaye Yungster
Publisher:
ISBN:
Category : Chemical equilibrium
Languages : en
Pages : 20
Get Book Here
Book Description
Author: Jeff S. Noall
Publisher:
ISBN:
Category : Computational aerodynamics [etc.]
Languages : en
Pages : 125
Get Book Here
Book Description
