TURBINE SHROUD COOLING

A turbine shroud segment (26) for a gas turbine engine (10) having an annular gas path (11) extending about an engine axis (L). The engine has a turbine rotor mounted for rotation about the axis and having a plurality of blades (20) extending into the gas path. The turbine shroud segment (26) includ...

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Bibliographic Details
Main Authors SYNNOTT, Remy, BIERNAT, Jacob, ENNACER, Mohammed, POTIFOROV, Andrey
Format Patent
LanguageEnglish
French
German
Published 13.04.2022
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:A turbine shroud segment (26) for a gas turbine engine (10) having an annular gas path (11) extending about an engine axis (L). The engine has a turbine rotor mounted for rotation about the axis and having a plurality of blades (20) extending into the gas path. The turbine shroud segment (26) includes a body extending axially between a leading edge (30) and a trailing edge (32) and circumferentially between a first and second lateral edges (34). The body has a radially outer surface (38) and a radially inner surface (36). The radially outer surface (38) includes a textured surface (56) exposed to a cooling flow. The radially inner surface (36) defines an outer flow boundary surface of the gas path next to a tip (28) of one of the blades (20). A cooling flow passageway (60) is defined in the body and extends axially between one or more cooling inlets (58) receiving the cooling flow from the textured surface (56) and one or more cooling outlets (62).
Bibliography:Application Number: EP20210201536