GAS TURBINE ENGINE AIRFOIL WITH EXTENDED LAMINAR FLOW

An apparatus is provided for a gas turbine engine. This engine apparatus includes an airfoil (46) extending spanwise along a span line from a base to a tip. The airfoil (46) extends laterally between a pressure side (54) and a suction side (56). The airfoil (46) extends longitudinally along a camber...

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Bibliographic Details
Main Authors MEDIC, Gorazd, JOLY, Michael M
Format Patent
LanguageEnglish
French
German
Published 29.05.2024
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
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Summary:An apparatus is provided for a gas turbine engine. This engine apparatus includes an airfoil (46) extending spanwise along a span line from a base to a tip. The airfoil (46) extends laterally between a pressure side (54) and a suction side (56). The airfoil (46) extends longitudinally along a camber line (58) from a leading edge (60) to a trailing edge (62). The airfoil (46) includes a first section (84B) and a second section (84C) arranged longitudinally between the first section (84B) and the trailing edge (62) along the camber line (58). An angle (64) between the camber line (58) and a reference plane (66; 72) changes according to a slope as the airfoil (46) extends longitudinally along the camber line (58). The slope in the second section (84C) is greater than the slope in the first section (84B).
Bibliography:Application Number: EP20230212567