Three Dimensional Numerical Simulation Of Rocket Based Combined Cycle Engine Response During Mode Transition Nasa Cr 2003 212193 Nat
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Three Dimensional Numerical Simulation Of Rocket Based Combined Cycle Engine Response During Mode Transition Nasa Cr 2003 212193 Nat
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Author : United States. National Aeronautics and Space Administration
language : en
Publisher:
Release Date : 2003*
Three Dimensional Numerical Simulation Of Rocket Based Combined Cycle Engine Response During Mode Transition Nasa Cr 2003 212193 Nat written by United States. National Aeronautics and Space Administration and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2003* with categories.
Three Dimensional Numerical Simulation Of Rocket Based Combined Cycle Engine Response During Mode Transition Events
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Author : National Aeronautics and Space Administration (NASA)
language : en
Publisher: Createspace Independent Publishing Platform
Release Date : 2018-06-20
Three Dimensional Numerical Simulation Of Rocket Based Combined Cycle Engine Response During Mode Transition Events written by National Aeronautics and Space Administration (NASA) and has been published by Createspace Independent Publishing Platform this book supported file pdf, txt, epub, kindle and other format this book has been release on 2018-06-20 with categories.
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
Three Dimensional Numerical Simulation Of Rocket Based Combined Cycle Engine Response During Mode Transition Events
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Author :
language : en
Publisher:
Release Date : 2003
Three Dimensional Numerical Simulation Of Rocket Based Combined Cycle Engine Response During Mode Transition Events written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2003 with categories.
Three Dimensional Computational Fluid Dynamics Analysis Of A Rocket Based Combined Cycle Engine In Ejector Mode
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Author : Douglas S. Brocco
language : en
Publisher:
Release Date : 2000
Three Dimensional Computational Fluid Dynamics Analysis Of A Rocket Based Combined Cycle Engine In Ejector Mode written by Douglas S. Brocco and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2000 with Fluid dynamics categories.
Reynolds Averaged Navier Stokes Analysis Of The Flow Through A Model Rocket Based Combined Cycle Engine With An Independently Fueled Ramjet Stream
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Author :
language : en
Publisher:
Release Date : 2003
Reynolds Averaged Navier Stokes Analysis Of The Flow Through A Model Rocket Based Combined Cycle Engine With An Independently Fueled Ramjet Stream written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2003 with categories.
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.
Analysis Of A Rocket Based Combined Cycle Engine During Rocket Only Operation
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Author :
language : en
Publisher:
Release Date : 1998
Analysis Of A Rocket Based Combined Cycle Engine During Rocket Only Operation written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1998 with categories.
Performance Of An Axisymmetric Rocket Based Combined Cycle Engine During Rocket Only Operation Using Linear Regression Analysis
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Author :
language : en
Publisher:
Release Date : 1998
Performance Of An Axisymmetric Rocket Based Combined Cycle Engine During Rocket Only Operation Using Linear Regression Analysis written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1998 with categories.
Analysis Of A New Rocket Based Combined Cycle Engine Concept At Low Speed
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Author : National Aeronautics and Space Administration (NASA)
language : en
Publisher: Createspace Independent Publishing Platform
Release Date : 2018-06-15
Analysis Of A New Rocket Based Combined Cycle Engine Concept At Low Speed written by National Aeronautics and Space Administration (NASA) and has been published by Createspace Independent Publishing Platform this book supported file pdf, txt, epub, kindle and other format this book has been release on 2018-06-15 with categories.
An analysis of the Independent Ramjet Stream (IRS) cycle is presented. The IRS cycle is a variation of the conventional ejector-Ramjet, and is used at low speed in a rocket-based combined-cycle (RBCC) propulsion system. In this new cycle, complete mixing between the rocket and ramjet streams is not required, and a single rocket chamber can be used without a long mixing duct. Furthermore, this concept allows flexibility in controlling the thermal choke process. The resulting propulsion system is intended to be simpler, more robust, and lighter than an ejector-ramjet. The performance characteristics of the IRS cycle are analyzed for a new single-stage-to-orbit (SSTO) launch vehicle concept, known as "Trailblazer." The study is based on a quasi-one-dimensional model of the rocket and air streams at speeds ranging from lift-off to Mach 3. The numerical formulation is described in detail. A performance comparison between the IRS and ejector-ramjet cycles is also presented. Yungster, S. and Trefny, C. J. Glenn Research Center NASA/TM-1999-209393, NAS 1.15:209393, E-11824, AIAA Paper 99-2393, ICOMP-99-05
Rocket Based Combined Cycle Engine Technology Development
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Author : James R. DeBonis
language : en
Publisher:
Release Date : 1996
Rocket Based Combined Cycle Engine Technology Development written by James R. DeBonis and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1996 with Fluid dynamics categories.
Validation Of The Ncc Code For Staged Transverse Injection And Computations For A Rbcc Combustor
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Author : National Aeronautics and Space Administration (NASA)
language : en
Publisher: Createspace Independent Publishing Platform
Release Date : 2018-06-12
Validation Of The Ncc Code For Staged Transverse Injection And Computations For A Rbcc Combustor written by National Aeronautics and Space Administration (NASA) and has been published by Createspace Independent Publishing Platform this book supported file pdf, txt, epub, kindle and other format this book has been release on 2018-06-12 with categories.
The NCC code was validated for a case involving staged transverse injection into Mach 2 flow behind a rearward facing step. Comparisons with experimental data and with solutions from the FPVortex code was then used to perform computations to study fuel-air mixing for the combustor of a candidate rocket based combined cycle engine geometry. Comparisons with a one-dimensional analysis and a three-dimensional code (VULCAN) were performed to assess the qualitative and quantitative performance of the NCC solver.Ajmani, Kumud and Liu, Nan-SueyGlenn Research CenterINJECTION; COMBUSTION CHAMBERS; BACKWARD FACING STEPS; ROCKET-BASED COMBINED-CYCLE ENGINES; SUPERSONIC SPEED; SPACECRAFT PROPULSION