CPC F02C 7/36 (2013.01) [F16H 57/082 (2013.01); F05D 2200/14 (2013.01); F05D 2220/323 (2013.01); F05D 2260/40311 (2013.01); F05D 2300/501 (2013.01); F16H 2057/02043 (2013.01)] | 20 Claims |
1. A gas turbine engine for an aircraft comprising:
an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor;
a fan located upstream of the engine core, the fan comprising a plurality of fan blades; and
a gearbox arranged to receive an input from a gearbox input shaft portion of the core shaft and to output drive to the fan so as to drive the fan at a lower rotational speed than the core shaft, wherein:
a geared engine performance parameter is defined as:
the fan tip loading being defined as dH/Uttip2, where dH is an enthalpy rise across the fan and Uttip is the velocity of the fan tip, and
the geared engine performance parameter is in a range of 4200 to 16000.
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