APPARATUS COMPRISING A VANE ARRAY STRUCTURE

A vane array structure (20) for a gas turbine engine (94) includes a first platform (22), a second platform (24), a plurality of vanes (26A, 26B) and a flowpath (28). Each of the vanes (26A, 26B) extends across the flowpath (28) between the first platform (22) and the second platform (24). The vanes...

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Bibliographische Detailangaben
Hauptverfasser:	KANDASAMY, Vijay, DUONG, Hien
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 vane array structure (20) for a gas turbine engine (94) includes a first platform (22), a second platform (24), a plurality of vanes (26A, 26B) and a flowpath (28). Each of the vanes (26A, 26B) extends across the flowpath (28) between the first platform (22) and the second platform (24). The vanes (26A, 26B) include a first vane (26A) and a second vane (26B) disposed longitudinally next to the first vane (26A) along the flowpath (28). The first vane (26A) includes a first airfoil (58A) and a first recess (60A). The first airfoil (58A) extends spanwise between a first end (64A) at the first platform (22) and a second end (66A) at the second platform (24). The first airfoil (58A) extends chordwise between a leading edge (52A) and a trailing edge (50A). The first airfoil (58A) extends laterally between a first side (72A) and a second side (74A). The first recess (60A) projects spanwise into the first airfoil (58A) from the first end (64A). The first recess (60A) projects chordwise into the first airfoil (58A) from the trailing edge (50A).