EP 2904210 A2 20150812 - GAS TURBINE ENGINE WITH FORWARD MOMENT ARM
Title (en)
GAS TURBINE ENGINE WITH FORWARD MOMENT ARM
Title (de)
GASTURBINENMOTOR MIT VORWÄRTSHEBELARM
Title (fr)
TURBINE À GAZ À BRAS DE LEVIER AVANT
Publication
Application
Priority
- US 201261708240 P 20121001
- US 201361789275 P 20130315
- US 2013062104 W 20130927
Abstract (en)
[origin: WO2014099085A2] A gas turbine engine includes a plurality of fan blades rotatable about an axis, wherein each of the plurality of fan blades includes a leading edge. The gas turbine engine also includes turbine section includes an aft most turbine blade having a trailing edge and a geared architecture driven by the turbine section for rotating the plurality of fan blades about the axis. A center of gravity of the gas turbine engine is located a first axial distance from the trailing edge of the aft most turbine blade that is between about 35% and about 75% of a total length between the leading edge of the plurality of fan blades and the trailing edge of the aft most turbine blade.
IPC 8 full level
F01D 5/14 (2006.01); F01D 25/28 (2006.01); F02C 7/00 (2006.01); F02C 7/20 (2006.01); F02K 3/06 (2006.01)
CPC (source: EP)
F01D 25/28 (2013.01); F02C 7/20 (2013.01); F02K 3/06 (2013.01); F05D 2260/4031 (2013.01); Y02T 50/60 (2013.01)
Designated contracting state (EPC)
AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR
Designated extension state (EPC)
BA ME
DOCDB simple family (publication)
WO 2014099085 A2 20140626; WO 2014099085 A3 20140918; BR 112015006820 A2 20170704; BR 112015006820 B1 20221206; CA 2884976 A1 20140626; CA 2884976 C 20180306; EP 2904210 A2 20150812; EP 2904210 A4 20151202; JP 2015534622 A 20151203; JP 6027250 B2 20161116
DOCDB simple family (application)
US 2013062104 W 20130927; BR 112015006820 A 20130927; CA 2884976 A 20130927; EP 13865250 A 20130927; JP 2015533317 A 20130927