METHOD OF VARYING AN ANNULAR FAN EXIT AREA OF A GAS TURBINE ENGINE

A method of varying an annular fan exit area of a gas turbine engine (10) comprising the step of asymmetrically adjusting a first flap assembly segment (44A ... 44D) relative a second flap assembly segment to adjust an annular fan exit throat area.

Saved in:
Bibliographic Details
Main Authors WINTER, Michael, HANSON, Russell B
Format Patent
LanguageEnglish
French
German
Published 12.06.2019
Subjects
BLASTING
COMBUSTION ENGINES
HEATING
HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
JET-PROPULSION PLANTS
LIGHTING
MECHANICAL ENGINEERING
WEAPONS
Online AccessGet full text

Cover

More Information
Summary:A method of varying an annular fan exit area of a gas turbine engine (10) comprising the step of asymmetrically adjusting a first flap assembly segment (44A ... 44D) relative a second flap assembly segment to adjust an annular fan exit throat area.
Bibliography:Application Number: EP20180215689