HIGHLY LOADED INLET DUCT IN A GEARED TURBOFAN

A gas turbine engine (10) comprises an inlet duct (50) to guide a core engine flow (A) to a compressor (14) and an engine section stator (52) arranged in the inlet duct (50) upstream of the compressor (14) comprising a plurality of vanes (54) with respective leading edges (64) defining a first annul...

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Bibliographische Detailangaben
1. Verfasser:	Bousfield, Ian
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS
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Beschreibung
Zusammenfassung:	A gas turbine engine (10) comprises an inlet duct (50) to guide a core engine flow (A) to a compressor (14) and an engine section stator (52) arranged in the inlet duct (50) upstream of the compressor (14) comprising a plurality of vanes (54) with respective leading edges (64) defining a first annulus area (A1) in the inlet duct (50), a mid-span leading edge point (66) of the engine section stator vanes (54) being arranged at a first radius (R1). The compressor (14) comprises a first rotor (60) with a row of first blades (62) with respective leading edges (68) defining a second annulus area (A2); a mid-span leading edge point (70) of the compressor first blades (62) being arranged at a second radius (R2) and at an axial distance (L) from the engine section stator vane mid-span leading edge point (66). The ratio (A2/A1) of the second annulus area (A2) to the first annulus area (A1) is equal or greater than 0.75, and the ratio (ΔR /L) of a difference (ΔR) between the first radius (R1) and the second radius (R2) to the axial distance (L) is equal or greater than 0.23.