To ensure the tightness of the turbopump assemblies within the engines of aircraft when exposed to high vibration loads

Abstract

The paper deals with the problems of ensuring the tightness of the turbo-pump unit (TNA) and the turbopump hydraulic unit (TNGA) of the canned fuel system (TS) of a dynamically high-loaded aircraft engine (LA). The purpose of the work is to study the influence of various factors on the tightness of TNA, TNGA under the influence of vibration and the development of criteria for ensuring tightness. Taking into account the influence on the tightness of the aggregates of many factors that are not possible to take into account in the calculations, experimental methods of research are used in the work. According to the experimental points, the criterion dependence of fuel leaks on the radial backlash of the rotor is constructed and the  transition  zone  of  the units from the hermetic to the    non-hermetic state is distinguished. Design and production of TNA, TNGA with application of the developed criteria provided reliable tightness of units at influence of vibrations and increased reliability of products with their application.