TURBINE SHROUD COOLING

A turbine shroud segment for a gas turbine engine having an annular gas path extending about an engine axis. The engine has a turbine rotor mounted for rotation about the axis and having a plurality of blades extending into the gas path. The turbine shroud segment includes a body extending axially b...

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Bibliographische Detailangaben
Hauptverfasser:	SYNNOTT, Remy, BIERNAT, Jacob, ENNACER, Mohammed, POTIFOROV, Andrey
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	A turbine shroud segment for a gas turbine engine having an annular gas path extending about an engine axis. The engine has a turbine rotor mounted for rotation about the axis and having a plurality of blades extending into the gas path. The turbine shroud segment includes a body extending axially between a leading edge and a trailing edge and circumferentially between a first and second lateral edges. The body has a radially outer surface and a radially inner surface. The radially outer surface includes a textured surface exposed to a cooling flow. The radially inner surface defines an outer flow boundary surface of the gas path next to a tip of one of the blades. A cooling flow passageway is defined in the body and extends axially between one or more cooling inlets receiving the cooling flow from the textured surface and one or more cooling outlets.