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公开(公告)号：US09957889B2
公开(公告)日：2018-05-01
申请号：US14463031
申请日：2014-08-19
CPC分类号： F02C7/045 , F02C7/042 , F02K3/06 , F05D2220/323 , F05D2260/96
摘要： An aeroengine is provided with a splitter apparatus disposed in a section of an inlet duct. The splitter apparatus can be actuated from a stowed position to a deployed position to allow splitter(s) to selectively move from out of the inlet flow to a position extending into the inlet duct to divide the inlet flow into multiple passages.
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公开(公告)号：US09951690B2
公开(公告)日：2018-04-24
申请号：US14463077
申请日：2014-08-19
CPC分类号： F02C7/045 , F01D17/143 , F01D17/146 , F02C7/042 , F05D2260/963 , Y02T50/672
摘要： An aeroengine has an inlet system which includes at least one deformable wall disposed adjacent a peripheral wall of an inlet duct and a plurality of acoustic cells attached to a back side in fluid communication through respective holes in the at least one deformable wall with an inlet duct air flow. The at least one deformable wall selectively forms part of the peripheral wall of the inlet duct when in an undeployed position and selectively forms a curved profile projecting into the inlet duct to reduce line-of-sight noise propagation through the inlet duct.
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公开(公告)号：US10221764B2
公开(公告)日：2019-03-05
申请号：US14462981
申请日：2014-08-19
摘要： A variable geometry inlet system of an aircraft engine includes an inlet duct. The inlet duct includes at least first and second sections moveable between extended and retracted positions such that the inlet duct defines a variable axial length of an inlet in controlling noise.
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公开(公告)号：US10054050B2
公开(公告)日：2018-08-21
申请号：US14463114
申请日：2014-08-19
摘要： An aeroengine has an inlet system with a forward end with respect to a flight direction. The inlet system includes a main inlet duct for selectively directing a first air flow from a forward main intake opening of the main inlet duct to a compressor rotor, the forward main intake opening being defined at the forward end of the inlet system and a secondary inlet duct for directing a second air flow from a secondary intake opening of the secondary inlet duct to the compressor rotor only when the main inlet duct is closed. A control apparatus is provided for selecting the first and second air flow to enter into the compressor rotor.
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公开(公告)号：US11661887B2
公开(公告)日：2023-05-30
申请号：US17319439
申请日：2021-05-13
CPC分类号： F02C7/045 , F02C7/042 , B64D2033/0206 , B64D2033/0286 , F01D17/143 , F02K3/025 , F02K3/04 , F02K3/06 , F02K3/068 , F05D2250/311 , F05D2250/712 , F05D2250/90 , F05D2260/96
摘要： A variable geometry inlet system of an aircraft engine includes an inlet duct. The inlet duct includes at least first and second sections moveable between extended and retracted positions such that the inlet duct defines a variable axial length of an inlet passage for selective flight conditions. The inclusion of acoustic treatment may assist in controlling noise.
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公开(公告)号：US11066993B2
公开(公告)日：2021-07-20
申请号：US16256097
申请日：2019-01-24
摘要： A variable geometry inlet system of an aircraft engine includes an inlet duct. The inlet duct includes at least first and second sections moveable between extended and retracted positions such that the inlet duct defines a variable axial length of an inlet passage for selective flight conditions. The inclusion of acoustic treatment may assist in controlling noise.
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