VARIABLE COMPRESSION AIR INTAKES FOR AIRCRAFT PROPULSION SYSTEMS AND METHODS FOR VARYING COMPRESSION OF AIR INTAKE

To provide techniques regarding air intakes for propulsion systems of aerospace vehicles that operate in a wide Mach range.SOLUTION: A propulsion system 100 for an aircraft includes an engine 102 having a central axis. A cowl 104 surrounds the engine 102 and includes a cowl lip 106. A compression ra...

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Bibliographische Detailangaben
Hauptverfasser:	THOMAS R SMITH, MATTHEW J ROODE
Format:	Patent
Sprache:	eng ; jpn
Schlagworte:	AEROPLANES AIR INTAKES FOR JET-PROPULSION PLANTS AIRCRAFT ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT AVIATION BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS COSMONAUTICS EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS GAS-TURBINE PLANTS HEATING HELICOPTERS HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MECHANICAL ENGINEERING PARACHUTES PERFORMING OPERATIONS TRANSPORTING WEAPONS
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Beschreibung
Zusammenfassung:	To provide techniques regarding air intakes for propulsion systems of aerospace vehicles that operate in a wide Mach range.SOLUTION: A propulsion system 100 for an aircraft includes an engine 102 having a central axis. A cowl 104 surrounds the engine 102 and includes a cowl lip 106. A compression ramp 108 is at a distance from the cowl lip 106. An inlet is formed by the cowl lip 106 and the compression ramp 108. The compression ramp 108 is non-planar. The compression ramp 108 is movable relative to the cowl lip 106 to vary compression of an inlet airflow 112 through the inlet.SELECTED DRAWING: Figure 2 【課題】広いマッハ範囲で作動可能な、航空宇宙機の推進システムのための吸気口に関する技術を提供する。【解決手段】航空機のための推進システム１００が、中央軸を有するエンジン１０２を含む。カウル１０４がエンジン１０２を取り囲んでおり、カウルリップ部１０６を含む。圧縮斜面１０８が、カウルリップ部１０６から間隔を空けられている。入口が、カウルリップ部１０６及び圧縮斜面１０８によって形成される。圧縮斜面１０８は非平面的である。圧縮斜面１０８は、入口を流過する入口空気流１１２の圧縮を変更するために、カウルリップ部１０６に対して可動である。【選択図】図２