GAS TURBINE ENGINE CORE FLOW DEBRIS CLEANER

An assembly (200) of a gas turbine engine (20) includes a low pressure compressor (44), a high pressure compressor (52), an intermediate case (45) between the low pressure compressor (44) and the high pressure compressor (52), and a cleaning apparatus (70) having an annular arrangement (400) about t...

Full description

Saved in:
Bibliographic Details
Main Author MULDOON, Marc J
Format Patent
LanguageEnglish
French
German
Published 18.10.2023
Subjects
BLASTING
ENGINE PLANTS IN GENERAL
HEATING
LIGHTING
MACHINES OR ENGINES IN GENERAL
MECHANICAL ENGINEERING
NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES
STEAM ENGINES
WEAPONS
Online AccessGet full text

Cover

More Information
Summary:An assembly (200) of a gas turbine engine (20) includes a low pressure compressor (44), a high pressure compressor (52), an intermediate case (45) between the low pressure compressor (44) and the high pressure compressor (52), and a cleaning apparatus (70) having an annular arrangement (400) about the intermediate case (45). A core flow path (C) is defined through the low pressure compressor (44), the intermediate case (45), and the high pressure compressor (52). The annular arrangement (400) includes a scroll portion (300) configured to extract debris from an airstream at an outer diameter wall (204) of the core flow path (C) and return the airstream to the core flow path (C).
Bibliography:Application Number: EP20230167810