#GE AVIO SRL [IT]

FUEL SUPPLY SYSTEM FOR A COMBUSTOR

A fuel supply system (100) for a combustion section (114) of a turbine engine (10). The turbine engine (10) including a heat source (110). The fuel supply system (100) comprising a first fuel supply (…

DRIVE·Apr 22·1 min read

F02C3/22 GE AVIO SRL [IT]

METHOD AND APPARATUS FOR CALIBRATING A TORQUE SENSOR OF AN AIRCRAFT ENGINE

Input is received. A conformance is determined. When conformance is determined, a raw torque is measured from a torque sensor at an engine; the raw torque is calibrated using the torque sensor paramet…

DRIVE·Nov 26·1 min read

B64F5/60 GE AVIO SRL [IT]

HYDROGEN FUEL SYSTEM

A fuel system for a vehicle having an engine is provided. The fuel system including: a fuel tank for holding a hydrogen fuel in a liquid phase; a fuel delivery assembly extending from the fuel tank to…

DRIVE·Nov 12·1 min read

B64D37/30 GE AVIO SRL [IT]

GAS TURBINE ENGINES WITH A FUEL CELL ASSEMBLY

An aircraft engine (300) is provided. The aircraft engine includes a compressor section (302) including a compressor (308) and a turbine section (304) downstream of the compressor section (302). The t…

DRIVE·Aug 20·2 min read

F02C1/06 GE AVIO SRL [IT]

EPICYCLIC GEARING WITH PRESS-FIT COLLAR WITH REDUCED EDGE CONTACT STRESS CONCENTRATIONS

An apparatus and method for reducing edge contact stress concentrations in a press-fit. The apparatus and method of the present disclosure specifically provide for a press-fit collar having a channel …

DRIVE·Aug 6·1 min read

F01D15/12 GE AVIO SRL [IT]

METHOD AND APPARATUS FOR CONTROLLING FUEL FLOW INTO AN AIRCRAFT ENGINE

Based upon measured resistances, a first delta curve and second delta curve are selected. A first fuel valve position (FVP) is received from a first position sensor (102), and the first FVP is applied…

DRIVE·Jul 16·1 min read

B64D37/34 GE AVIO SRL [IT]

COMBUSTOR ASSEMBLY FOR A GAS TURBINE ENGINE

A combustor assembly (80) for a gas turbine engine (10) is provided. The combustor assembly (80) generally includes a liner (82, 84) at least partially defining a combustion chamber (88) and having an…

DRIVE·Aug 7·2 min read

F01D25/30 GE AVIO SRL [IT]

Low pressure turbine provided with splitters at the last stator array

A low pressure turbine, in particular for a gas turbine engine, extends along an axis (3), has an annular conduit (6) for guiding a gas flow and is provided with a plurality of stator arrays of blades…

DRIVE·Nov 19·1 min read

F01D1/04 GE AVIO SRL [IT]