SUPER-COOLED ICE IMPACT PROTECTION FOR A GAS TURBINE ENGINE

A gas turbine engine comprises a fan (23) mounted to rotate about a main longitudinal axis (9); an engine core (11), comprising in axial flow series a compressor (14), a combustor (16), and a turbine (19) coupled to the compressor through a shaft (26); a reduction gearbox (30) that receives an input...

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Bibliographische Detailangaben
Hauptverfasser:	Bousfield, Ian, MacDougall, Duncan
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	BLASTING ENGINE PLANTS IN GENERAL HEATING LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES NON-POSITIVE DISPLACEMENT PUMPS POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS PUMPS FOR LIQUIDS OR ELASTIC FLUIDS STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	A gas turbine engine comprises a fan (23) mounted to rotate about a main longitudinal axis (9); an engine core (11), comprising in axial flow series a compressor (14), a combustor (16), and a turbine (19) coupled to the compressor through a shaft (26); a reduction gearbox (30) that receives an input from the shaft and outputs drive to the fan so as to drive the fan at a lower rotational speed than the shaft; wherein the compressor comprises a first stage (ST1) at an inlet and a second stage (ST2), downstream of the first stage, comprising respectively a first rotor (R1) with a row of first blades (B1) and a second rotor (R2) with a row of second blades (B2), the first and second blades (B1, B2) comprising respective leading edges (50, 70), trailing edges (52, 72) and tips (54, 74), and wherein the ratio of a maximum leading edge radius (R1max) of the first blades (B1) to a maximum leading edge radius (R2max) of the second blades (B2) is greater than 2.8.