FAN BLADES FOR GAS TURBINE ENGINES WITH REDUCED STRESS CONCENTRATION AT LEADING EDGE

Title:

FAN BLADES FOR GAS TURBINE ENGINES WITH REDUCED STRESS CONCENTRATION AT LEADING EDGE

Document Type and Number:

WIPO Patent Application WO/2014/133613

Kind Code:

A3

Abstract:

A light weight fan blade for a gas turbine engine is disclosed. The disclosed fan blade has an increased chord length at a transition section between the inner edge or single tooth attachment portion of the fan blade that connects to the rotor disk and the airfoil. Increasing the chord length at the transition section substantially reduces the stress concentration when the fan blade is operated under normal operating conditions. Reducing the stress concentration enables engineers to design lighter fan blades and larger fan blades for larger gas turbine engines. By increasing the size of gas turbine engines, additional thrust can be provided without adding additional engines to the aircraft.

Inventors:

LATTANZIO SANTIAGO (US)
AMOO OLALEYE M (US)

Application Number:

PCT/US2013/072987

Publication Date:

December 24, 2014

Filing Date:

December 04, 2013

Export Citation:

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Assignee:

UNITED TECHNOLOGIES CORP (US)

International Classes:

F01D5/30

Foreign References:

US20110229334A1	2011-09-22
US20120003100A1	2012-01-05
US6004101A	1999-12-21
US20110182740A1	2011-07-28
US20070031259A1	2007-02-08
US20040076521A1	2004-04-22
US20130064669A1	2013-03-14

Other References: