ROTOR BLADE AND CORRESPONDING GAS TURBINE

The present disclosure is directed to a rotor blade (100) for a gas turbine engine (10). The rotor blade (100) includes a platform (106) comprising a radially inner surface (168), an undulating radially outer surface (166), a leading edge portion (126), a trailing edge portion (128), a pressure-side...

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Bibliographic Details
Main Authors HOGBERG, Nicholas Alvin, BENSON, Adebukola Oluwaseun, ZHANG, Xiuzhang James
Format Patent
LanguageEnglish
French
German
Published 26.05.2021
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
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Summary:The present disclosure is directed to a rotor blade (100) for a gas turbine engine (10). The rotor blade (100) includes a platform (106) comprising a radially inner surface (168), an undulating radially outer surface (166), a leading edge portion (126), a trailing edge portion (128), a pressure-side slash face (130), and a suction-side slash face (132). An airfoil (108) extends outwardly from the undulating radially outer surface (166) of the platform (106) to an airfoil tip (112). A connection portion (102, 104) extends radially inwardly from the radially inner surface (168) of the platform (106). The platform (106), the airfoil (108), and the connection portion (102, 104) collectively define a cooling circuit (140) extending from an inlet (146) in the connection portion (102, 104) through the airfoil (108) to a plurality of outlet plena (124, 124(a), 124(b)) in the platform (108). Two or more outlet plena (124, 124(a), 124(b)) of the plurality of outlet plena (124, 124(a), 124(b)) are spaced equidistant from the undulating radially outer surface (166) of the platform (106).
Bibliography:Application Number: EP20170151244