PROPULSION ENGINE

An air intake for an open rotor engine including a propulsive blade array having a plurality of blades each having a gas washed surface extending radially outwardly relative to an axis or rotation from a root end to a tip. Intake has first and second circumferential walls extending about axis of rot...

Ausführliche Beschreibung

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Bibliographische Detailangaben
1. Verfasser:	STRETTON RICHARD GEOFFREY
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS AIRCRAFT ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT AVIATION BLASTING CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TOTRANSPORTATION COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS COSMONAUTICS EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS GAS-TURBINE PLANTS GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS INDEXING SCHEME FOR ASPECTS RELATING TONON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES ORJET-PROPULSION PLANTS INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUSSUBCLASSES OF CLASSES F01-F04 LIGHTING MECHANICAL ENGINEERING PARACHUTES PERFORMING OPERATIONS TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINSTCLIMATE CHANGE TRANSPORTING WEAPONS
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Beschreibung
Zusammenfassung:	An air intake for an open rotor engine including a propulsive blade array having a plurality of blades each having a gas washed surface extending radially outwardly relative to an axis or rotation from a root end to a tip. Intake has first and second circumferential walls extending about axis of rotation at a location downstream of propulsive blade array. First and second walls are spaced in a radial direction to define an annular passage with opening having a height dimension extending a portion of the way along propulsive blade array span. Intake further includes an annular lip arranged about axis of rotation at a radial distance such that lip bifurcates the annular passage at a height which separates a boundary layer flow portion of intake flow from a remainder of intake flow. Lip may define a collection scroll for foreign object debris and cooling air for the engine.