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 (102) having a liquid fuel, a second fuel supply (104) ha...

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 parameters to produce a calibrated torque value, non-torque par...

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 turbine section (304) includes a turbine having turbine b...

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 to the first delta curve to obtain a first offset. A se...

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 and a plurality of rotor arrays of blades; the last of ...