Partially-metallic blade for a gas turbine

A lightweight, impact-resistant gas turbine blade (110), such as an aircraft engine fan blade, has a metal solid section (114), composite or structural/syntactic foam segments (116), and metal solid spars (118) all attached together to define an airfoil portion (124). The solid section includes the...

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Bibliographische Detailangaben
Hauptverfasser:	BACHRACH, WILLIAM ELLIOT, INGLING, THEODORE ROBERT, HOWARD, WALTER DOUGLAS
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	BLASTING CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TOTRANSPORTATION ENGINE PLANTS IN GENERAL GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS HEATING LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINSTCLIMATE CHANGE WEAPONS
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Beschreibung
Zusammenfassung:	A lightweight, impact-resistant gas turbine blade (110), such as an aircraft engine fan blade, has a metal solid section (114), composite or structural/syntactic foam segments (116), and metal solid spars (118) all attached together to define an airfoil portion (124). The solid section includes the leading edge (126), blade tip (136), and trailing edge (128). The segments (116) together are bounded in part by the solid section near the leading edge, blade tip, and trailing edge. The solid spars (118) separate and are attached to the segments (116).