Performance Prediction of a Ducted Rocket Combustor [microform]
Title | Performance Prediction of a Ducted Rocket Combustor [microform] PDF eBook |
Author | Robert Alan Stowe |
Publisher | National Library of Canada = Bibliothèque nationale du Canada |
Pages | 420 |
Release | 2001 |
Genre | |
ISBN | 9780612654341 |
Performance Prediction of a Ducted Rocket Combustor
Title | Performance Prediction of a Ducted Rocket Combustor PDF eBook |
Author | |
Publisher | |
Pages | |
Release | 2001 |
Genre | |
ISBN |
Modelling Combustor Performance of a Ducted Rocket
Title | Modelling Combustor Performance of a Ducted Rocket PDF eBook |
Author | R. A. Stowe |
Publisher | |
Pages | |
Release | 2000 |
Genre | |
ISBN |
Modelling and Flow Visualization of Mixing in a Ducted Rocket Combustor
Title | Modelling and Flow Visualization of Mixing in a Ducted Rocket Combustor PDF eBook |
Author | R. A. Stowe |
Publisher | |
Pages | |
Release | 1998 |
Genre | |
ISBN |
User's Manual for Rocket Combustor Interactive Design (Roccid) and Analysis Computer Program. Volume 2
Title | User's Manual for Rocket Combustor Interactive Design (Roccid) and Analysis Computer Program. Volume 2 PDF eBook |
Author | National Aeronautics and Space Administration (NASA) |
Publisher | Createspace Independent Publishing Platform |
Pages | 586 |
Release | 2018-08-04 |
Genre | |
ISBN | 9781724704665 |
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...
User's Manual for Rocket Combustor Interactive Design (Roccid) and Analysis Computer Program. Volume 1
Title | User's Manual for Rocket Combustor Interactive Design (Roccid) and Analysis Computer Program. Volume 1 PDF eBook |
Author | National Aeronautics and Space Administration (NASA) |
Publisher | Createspace Independent Publishing Platform |
Pages | 94 |
Release | 2018-07-17 |
Genre | |
ISBN | 9781722858841 |
The user's manual for the rocket combustor interactive design (ROCCID) computer program is presented. The 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 easily be added. The analysis model in ROCCID can account for the influence 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...
Scaling in a Ducted Rocket Combustor
Title | Scaling in a Ducted Rocket Combustor PDF eBook |
Author | |
Publisher | |
Pages | 24 |
Release | 1998 |
Genre | |
ISBN |
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.