A PARAMETRIC STUDY OF SWIRL INLET PARTICLE SEPARATORS
Abstract
Helicopter turbine engines suffer extensive internal damage from the effects of foreign particles carried into the engine in the intake airstream. Many types of intake filters have already been designed to cope with this problem; however, none is entirely satisfactory. This report describes the investigation of this problem with the goal of producing an inlet particle separator which would be the optimum design for the problem; the resultant design must have high filtration efficiency, low airflow losses, and basic simplicity of concept. The study involved the two-dimensional simulation of the three-dimensional ingestion of particles by an actual inlet. This simulation was performed by using a two-dimensional, electrified inlet configuration in conjunction with a comprehensive computer program. Seven basic inlets were simulated, along with variations of several of the inlets. Various types of particles were represented in the simulation. The two basic trajectory influences were represented by airflow with and without helicopter rotor downwash. Complete procedural steps are given, along with a detailed account of the test results.
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 01, 1968
- Accession Number
- AD0834262
Entities
People
- Richard Darling
Organizations
- Boeing Rotorcraft Systems