MISTUNED ROTORS FOR GAS TURBINE ENGINES

A mistuned rotor for a gas turbine engine includes a plurality of airfoils (112, 114) and each airfoil has a span (S) that extends from 0% at a root to 100% at a tip, a chord (CH) that extends from 0% at a leading edge (206) to 100% at a trailing edge (208) and a pressure side opposite a suction sid...

Full description

Saved in:
Bibliographic Details
Main Authors REPP, John, GEBRE-GIORGIS, Yoseph, NOLCHEFF, Nick, GUNARAJ, John A
Format Patent
LanguageEnglish
French
German
Published 11.09.2024
Subjects
BLASTING
ENGINE PLANTS IN GENERAL
HEATING
LIGHTING
MACHINES OR ENGINES IN GENERAL
MECHANICAL ENGINEERING
NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES
NON-POSITIVE DISPLACEMENT PUMPS
POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS
PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
STEAM ENGINES
WEAPONS
Online AccessGet full text

Cover

More Information
Summary:A mistuned rotor for a gas turbine engine includes a plurality of airfoils (112, 114) and each airfoil has a span (S) that extends from 0% at a root to 100% at a tip, a chord (CH) that extends from 0% at a leading edge (206) to 100% at a trailing edge (208) and a pressure side opposite a suction side. The pressure side of each airfoil has a pressure side surface shape and the suction side of each airfoil has a suction side surface shape based on an operating state of the rotor. Each airfoil has the same suction side surface shape between 10% and 90% of the chord and between 80% and 100% of the span at a first state. At least one first airfoil has a different suction side surface shape between 10% and 90% of the chord and between 80% and 100% of the span than at least one second airfoil at a static state of the rotor. A method of manufacturing a mistuned rotor includes determining a second working shape and a third working shape for at least one of the suction or pressure side surface that are different from each other.
Bibliography:Application Number: EP20190207318