Accession Number : AD0866555
Title : Propulsion System Flow Stability Program (Dynamic). Part IX. Combustion Instability Model Program Description and Parametric Study Results.
Descriptive Note : Final technical rept. 1 Oct 68-1 Dec 69 on Phase 2,
Corporate Author : NORTH AMERICAN ROCKWELL CORP LOS ANGELES CA LOS ANGELES DIV
Personal Author(s) : Dix, Donald M. ; Smith, George E.
Report Date : FEB 1970
Pagination or Media Count : 68
Abstract : Part IX describes a theoretical investigation of combustion instability in aircraft engine augmentors. Included is a general description of the analytical model and its digital computer solution. The model determines the frequencies, amplitudes, and spatial distributions of self-excited pressure oscillations in an afterburner or duct burner. The results of a parametric investigation of combustion instability in two turbojet afterburners are also reported. Good agreement between computed and observed trends has confirmed the conceptual validity of the analytical model. The parametric study also confirmed the utility of the computer programs in evaluating design modifications for suppressing or eliminating combustion instability. The computer programs are recommended for use now in engine design projects, but more advanced treatment of some of the input quantities, in conjunction with experimental data, will doubtlessly refine the accuracy of the solution. (Author)
Descriptors : (*RECONNAISSANCE AIRCRAFT, TURBOJET ENGINES), (*TURBOJET ENGINES, AXIAL FLOW COMPRESSORS), (*AXIAL FLOW COMPRESSORS, FLOW SEPARATION), STABILITY, SCREAMING COMBUSTION, SENSITIVITY, TURBINE PARTS, INTERFACES, AFTERBURNERS, MATHEMATICAL MODELS, COMPUTER PROGRAMS, FLOW FIELDS, ADVANCED WEAPONS.
Subject Categories : Patrol and Reconnaissance Aircraft
Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE