Accession Number : AD0866556
Title : Propulsion System Flow Stability Program (Dynamic). Part X. Combustion Instability Model Program User's Manual.
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) : Smith, George E. ; Bastress, E. Karl
Report Date : FEB 1970
Pagination or Media Count : 292
Abstract : This volume (Part X) contains detailed descriptions and operating instructions for two computer programs, HLMHLT and REFINE. Together, these programs comprise a numerical method of solution of a model of combustion instability in aircraft engine afterburners and duct burners. The model was developed in Phase 1 and is described in AFAPL-TR-68-142, Part XII, Unsteady Combustion in Duct Burners, Propulsion System Flow Program (Dynamic), Phase 1, Final Technical Report. Computer program HLMHLT consists of a general acoustics analysis of cylindrical and annular ducts with heat addition and with acoustic losses (or gains) at the boundaries. This program is applicable to a wide variety of problems, including those involving unsteady combustion. Computer program REFINE determines the effects of unsteady combustion and through-flow on the basic acoustic characteristics of the duct. These effects are used to modify the results of the acoustics analysis provided by Program HLMHLT. (Author)
Descriptors : (*RECONNAISSANCE AIRCRAFT, TURBOJET ENGINES), (*TURBOJET ENGINES, AXIAL FLOW COMPRESSORS), (*AXIAL FLOW COMPRESSORS, FLOW SEPARATION), STABILITY, SCREAMING COMBUSTION, TURBINE PARTS, AFTERBURNERS, FLOW FIELDS, ACOUSTICS, MATHEMATICAL MODELS, SUBROUTINES, COMPUTER LOGIC, COMPUTER PROGRAMS, INSTRUCTION MANUALS, ADVANCED WEAPONS.
Subject Categories : Patrol and Reconnaissance Aircraft
Computer Programming and Software
Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE