PRESSURE CONTROL FOR BIFURCATED FLOW OF A TURBINE ENGINE

An aircraft propulsion system (20) includes a turbine engine (22) having a propulsor rotor (60), an engine core (42) and a heat exchanger (86). The propulsor rotor (60) is configured to rotate about an axis (24) and direct a first air stream along a primary flowpath (44) that bypasses the engine cor...

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Bibliographische Detailangaben
Hauptverfasser:	TERWILLIGER, Neil J, EVANS, Simon W
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:	An aircraft propulsion system (20) includes a turbine engine (22) having a propulsor rotor (60), an engine core (42) and a heat exchanger (86). The propulsor rotor (60) is configured to rotate about an axis (24) and direct a first air stream along a primary flowpath (44) that bypasses the engine core (42) and direct a second air stream along a secondary flowpath (46) with a geometry extending at least eighty degrees about the axis (24). The turbine engine (22) is configured such that the first air stream enters the primary flowpath (44) at a first pressure and the second air stream enters the secondary flowpath (46) at a second pressure that is different than the first pressure. The engine core (42) is configured to drive rotation of the propulsor rotor (60). The heat exchanger (86) is disposed within the secondary flowpath (46).