GAS TURBINE ENGINE COMPONENT WITH OPTIMIZED LEADING EDGE GEOMETRY

A gas turbine engine component is provided. The gas turbine engine component comprises a main body (54) having a leading edge (76) and a leading edge wall (56a) including an elongated transition portion (56b) extending between the leading edge (76) and a proximate flowpath surface (64) of the main b...

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Bibliographische Detailangaben
Hauptverfasser:	SWIFT, Anthony B, PRAISNER, Thomas J, LUTJEN, Paul M, JAROCHYM, Christopher M, BLANEY, Ken F, TATMAN, Neil L
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 component is provided. The gas turbine engine component comprises a main body (54) having a leading edge (76) and a leading edge wall (56a) including an elongated transition portion (56b) extending between the leading edge (76) and a proximate flowpath surface (64) of the main body (54). The elongated transition portion (56b) has an axial length that is greater than a radial height. A gas turbine engine (20) is also provided.