Обзор методик расчета турбонасосного агрегата авиационного назначения, работающего на жидком водороде

Abstract

The article explores the prospects of using liquid hydrogen as an alternative environmentally friendly fuel for aircraft engines, with a focus on the challenges of designing turbopump assemblies (TPAs) for cryogenic fuel systems. It analyzes key differences between aviation TPAs and rocket engine TPAs, including lower fuel consumption, wider operating ranges, higher rotational speeds, and extended service life. The need for new calculation methods for TPA flow paths, considering aviation-specific requirements, is substantiated. The paper presents the results of a systematic analysis of existing models, refinement of liquid hydrogen flow parameters, and preliminary CFD simulations in ANSYS CFX. The importance of modern CAE/CAM technologies and product lifecycle management (PLM) tools for accelerating the development of advanced hydrogen-powered engines that meet energy efficiency and environmental safety requirements is emphasized.