BLADE OUTER AIR SEAL WITH CIRCUMFERENTIAL HOOK ASSEMBLY

A gas turbine engine (20) includes a compressor section (24) and a turbine section (28). The turbine section (28) includes at least one rotor and at least one blade (102) extending radially outwardly from the rotor to a radially outer tip (103). A blade outer air seal (104) is positioned radially ou...

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Bibliographische Detailangaben
Hauptverfasser:	CLARK, Thomas E, BARKER, William M, WHITNEY, Daniel J
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	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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Beschreibung
Zusammenfassung:	A gas turbine engine (20) includes a compressor section (24) and a turbine section (28). The turbine section (28) includes at least one rotor and at least one blade (102) extending radially outwardly from the rotor to a radially outer tip (103). A blade outer air seal (104) is positioned radially outwardly of the radially outer tip (103) of the blade (102). The blade outer air seal (104) has forward and aft hooks (106,108), and the forward and aft hooks (106,108) are supported on forward and aft seal hooks (112,114) of an attachment block (110). The blade outer air seal forward and aft hooks (106,108) extend at angles (α) relative to an upper surface (300) of a web (109) that is between 20 and 70 degrees. A method is also disclosed.