A GAS TURBINE ENGINE AND AIR INTAKE ASSEMBLY

A gas turbine engine and air intake assembly comprises an intake passage (26) extending between an inlet highlight (A) at a first end and an upstream face (C) of a fan 13 at a second end and comprising in flow series an intake lip (34), a most upstream portion of which defines the intake highlight (...

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Bibliographische Detailangaben
Hauptverfasser:	Green, Jeffrey, Gonzalez-Gutierrez, Gabriel, Sgro, Domenico
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 and air intake assembly comprises an intake passage (26) extending between an inlet highlight (A) at a first end and an upstream face (C) of a fan 13 at a second end and comprising in flow series an intake lip (34), a most upstream portion of which defines the intake highlight (A) and a most downstream portion of which defines a throat (T), a diffuser (35) with sectional area broadening towards the fan (13); and a straight conditioning duct (36), arranged immediately upstream of the fan (13). The camber line (32) of the intake passage (26) intersects the engine main axis (11) at an intersecting point (X) upstream of the fan (13) and the camber line (32) is parallel to the engine main axis (11) in the straight conditioning duct (36).