Accession Number : AD0821853
Title : CALCULATION OF PRESSURE LOSSES IN JET ENGINE COMBUSTION CHAMBERS (K VYPOCTU TLAKOVE ZTRATY SPALOVACICH KOMOR PROUDOVYCH MOTORU).
Descriptive Note : Unedited rough draft translation.
Corporate Author : FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OH
Personal Author(s) : Schurek, O.
Report Date : 01 MAY 1967
Pagination or Media Count : 11
Abstract : Flow coefficients are derived for air injected into combustion chambers by air streams directed parallel to and at right angles to the perforated metal jacket. Experiments are described with apparatus consisting of two parallel tubes intersected by a plate 1.2 mm thick with holes drilled in varying ratios of diameter to total plate area. Air flow was regulable and the pressure was gauged before and after passing through the perforated plate. Ten sizes of perforation were tested beginning at 5 mm diameter, and a graph relates sizes to the coefficient of air flow through the openings at five graduated velocities. Calculations are given and formulas derived for all phases of the experiments, and the conclusion is reached that pressure loss cannot be reduced by raising the ratio of aperture diameter to jacket thickness. Similar tests with the air flow directed parallel to the perforated jacket demonstrated a flow coefficient about 5% higher than when the air stream was directed at right angles to the jacket, which agrees roughly with tests made in operating combustion chambers. (Author)
Descriptors : (*JET ENGINES, COMBUSTION CHAMBERS), (*COMBUSTION CHAMBER GASES, PRESSURE), GAS FLOW, ATTENUATION, SECONDARY FLOW, VELOCITY, ORIFICES, NUMERICAL ANALYSIS, CZECHOSLOVAKIA.
Subject Categories : Combustion and Ignition
Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE