Investigation of Feasibility of Integral Gas Turbine Engine Solid Particle Inlet Separators. Phase 1. Feasibility Study and Design

Abstract

Abstract : Helicopter operations from unimproved landing sites have demonstrated the vulnerability of unprotected gas turbine engines to sand and dust ingestion. As an interim solution, engine inlet filtration or particle separator devices have been added to engines and aircraft that were already designed and developed. However, there is a need for particle separators designed to be integral with the engine from its conception to minimize penalties in engine performance, weight, maintainability, and reliability. The objective of this program is to conduct a two-phase investigation of particle separators intended to be an integral part of future advanced-technology gas turbine engines. Eight particle separator concepts were determined to be feasible, and preliminary design study layout drawings were prepared for each. Design information for three of the concepts was obtained from organizations that have been active in the field of particle separation; a review of current separator designs led to the development of a new concept; and the rest were formulated by Pratt + Whitney Aircraft. The eight separator concepts were evaluated with respect to each other for each of ten rating factors. The two most promising concepts, 'semi-reverse flow' and 'powered mixed-flow,' were selected for feasibility demonstration. Test hardware was then designed to experimentally evaluate the two selected concepts.