Modelling Combustor Performance Of A Ducted Rocket PDF Download

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Scaling in a Ducted Rocket Combustor

Scaling in a Ducted Rocket Combustor
Author:
Publisher:
Total Pages: 24
Release: 1998
Genre:
ISBN:
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In a project to demonstrate several of the key technologies of an air-breathing propulsion unit for a medium-range air-launched missile, experiments are to be conducted on an essential component of such a unit: the ducted rocket combustor. Existing test facilities will use hardware smaller than those of the missiles of interest, so that test results on small-scale models will have to be scaled up to the larger full-sized combustors. This report details the derivation of the relevant dimensionless parameters used in the scaling process and shows how the scaling has been applied in the past to experimental data from various types of combustors. The scaling procedure is called PD-scaling, which requires that geometric similarity be maintained and that the product of the static pressure in the combustor and the length scale be held constant between the model and the full-scale combustors. Inlet velocities, fuel type, air/fuel ratios, and inlet temperatures must also be kept constant. Finally, the report shows how PD-scaling should be applied to the ducted rocket combustor tests.

Modelling and Water Tunnel Visualization of Air

Modelling and Water Tunnel Visualization of Air
Author:
Publisher:
Total Pages: 67
Release: 1999
Genre:
ISBN:
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The Defence Research Establishment Valcartier (DREV) in Canada and the TNO Prins Maurits Laboratory, Netherlands, have undertaken a collaborative activity (Integral Rocket Ramjet Demonstration Program - IRRDP) to demonstrate several of the key technologies of an air-breathing propulsion unit for a medium-range air-launched missile. An essential component of the propulsion system is the ducted rocket combustor, and as part of its development, experiments were conducted at TNO's direct-connect combustion test facility using existing sub-scale combustor hardware. To make the best use of the limited number of tests that could be carried out, a test matrix had to be carefully developed to determine which geometries and test conditions should be considered. This document presents much of the information used to develop this test matrix, to understand the phenomena investigated by other researchers, and identify which parameters were the most important for good air/fuel and combustor performance. Research work described includes visualization of flowfield within a model combustor in a water tunnel to better understand the air/fuel mixing, including flow stability; computational fluid dynamic modelling of the flow fields inside the combustor to determine whether the modelling was representative of the water tunnel tests; and modelling of additional combustor geometries.

User's Manual for Rocket Combustor Interactive Design (Roccid) and Analysis Computer Program. Volume 2

User's Manual for Rocket Combustor Interactive Design (Roccid) and Analysis Computer Program. Volume 2
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
Total Pages: 586
Release: 2018-08-04
Genre:
ISBN: 9781724704665
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The appendices A-K to the user's manual for the rocket combustor interactive design (ROCCID) computer program are presented. This includes installation instructions, flow charts, subroutine model documentation, and sample output files. The ROCCID program, written in Fortran 77, provides a standardized methodology using state of the art codes and procedures for the analysis of a liquid rocket engine combustor's steady state combustion performance and combustion stability. The ROCCID is currently capable of analyzing mixed element injector patterns containing impinging like doublet or unlike triplet, showerhead, shear coaxial and swirl coaxial elements as long as only one element type exists in each injector core, baffle, or barrier zone. Real propellant properties of oxygen, hydrogen, methane, propane, and RP-1 are included in ROCCID. The properties of other propellants can be easily added. The analysis models in ROCCID can account for the influences of acoustic cavities, helmholtz resonators, and radial thrust chamber baffles on combustion stability. ROCCID also contains the logic to interactively create a combustor design which meets input performance and stability goals. A preliminary design results from the application of historical correlations to the input design requirements. The steady state performance and combustion stability of this design is evaluated using the analysis models, and ROCCID guides the user as to the design changes required to satisfy the user's performance and stability goals, including the design of stability aids. Output from ROCCID includes a formatted input file for the standardized JANNAF engine performance prediction procedure. Muss, J. A. and Nguyen, T. V. and Johnson, C. W. Unspecified Center NASA-CR-187110, NAS 1.26:187110 NAS3-25556; RTOP 582-01-21...

Liquid Rocket Engine

Liquid Rocket Engine
Author: Rene Nardi Rezende
Publisher: SAE International
Total Pages: 158
Release: 2018-11-15
Genre: Technology & Engineering
ISBN: 0768095425
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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.