Gas turbine unit for hypersonic aircraft - has axial compressor and blower replaced by tangential blower

摘要

The turbo-drive unit (1) involves thrust prodn. units (3) and gas outlet channels (16). A basic drive unit (2) has a front-sided ring-shaped combustion device (4), followed by a drum turbine (5) with connected running roller (6), and inner counterflow channels (8). A first outlet mass flows through a counterflow channel (8) and is heated in the combustion device (4). It then flows into the drum turbine (5) connected to the running roller (6) by a connecting plate carrying the main bearing. A tongue in the counterflow channel divides the input mass into first and second inlet masses, and first and second outlet masses. USE/ADVANTAGE - To reduce noise levels in supersonic aircraft turbo-drive units.