Three-dimensional CFD Analysis and Validation of Liquid Rocket Propulsion Components PDF Download
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Author: Hugh J. Thornburg
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Book Description
Author: Hugh J. Thornburg
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Book Description
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721568871
Category :
Languages : en
Pages : 26
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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: Rene Nardi Rezende
Publisher: SAE International
ISBN: 0768095425
Category : Technology & Engineering
Languages : en
Pages : 158
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Book Description
The great engineering achievement required to overcome most of the challenges and obstacles that prevented turning rocket design from art into science took place in Europe and the United States between the 1930s and the 1950s. With the vast majority of the engines currently in operation developed in the “pre-computer” age, there are new opportunities to update the design methodologies using technology that can now handle highly complex calculations fast. The space sector with an intense focus on efficiency is driving the need for updating, adapting or replacing the old modeling practices with new tools capable of reducing the volume of resources and the time required to complete simulations and analysis. This book presents an innovative parametric model applicable to the project of some elements of the liquid rocket thrust chamber with the level of detail and accuracy appropriate to the preliminary design phase. It addresses the operating characteristics and dimensioning of some thrust chamber elements through a set of equations and parameters, which include thrust or propellant characteristics. The model degree of sophistication was adjusted to the requirements of the Project Life Cycle Phase B, while also enabling quick analysis of new configurations from changes in initial project parameters.
Author:
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 638
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Author: J. M. Grenda
Publisher:
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Category :
Languages : en
Pages :
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Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722716806
Category :
Languages : en
Pages : 30
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Book Description
Pump CFD code validation tests were accomplished by obtaining nonintrusive flow characteristic data at key locations in generic current liquid rocket engine turbopump configurations. Data were obtained with a laser two-focus (L2F) velocimeter at scaled design flow. Three components were surveyed: a 1970's-designed impeller, a 1990's-designed impeller, and a four-bladed unshrouded inducer. Two-dimensional velocities were measured upstream and downstream of the two impellers. Three-dimensional velocities were measured upstream, downstream, and within the blade row of the unshrouded inducer. Brozowski, L. A. Unspecified Center NAS8-38864...
Author: Douglas S. Brocco
Publisher:
ISBN:
Category : Fluid dynamics
Languages : en
Pages : 125
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 704
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Author: American Institute of Aeronautics and Astronautics. Technical Information Service
Publisher:
ISBN:
Category : AIAA paper
Languages : en
Pages : 184
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Author: Andrew M. Brown
Publisher: Springer Nature
ISBN: 3031182073
Category : Technology & Engineering
Languages : en
Pages : 177
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Book Description
This is the first Structural Dynamics book focused on this indispensable aspect of liquid rocket engine design. This book begins by reviewing basic concepts in Structural Dynamics, including the free and forced response of SDOF and MDOF systems, along with some discussion of how numerical solutions are generated. The book then moves to a discussion of specific applications of these techniques in LREs, progressing from component level (turbomachinery and combustion devices), up through engine system models, and finally to integration with a launch vehicle. Clarifies specific topics including the Campbell and SAFE Diagrams for resonance identification in turbomachinery, the complications of component analysis in the pump side due to a host of complication factors such as acoustic/structure interaction, the "side-loads" fluid/structure interaction problem in overexpanded rocket nozzles, and competing methods for generation overall engine system interface loads. Includes specific examples for illustration while closing with rotordynamic analysis, dynamic data analysis, and vibroacoustics.
