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公开(公告)号：US12129795B2
公开(公告)日：2024-10-29
申请号：US17598987
申请日：2020-03-19
CPC分类号： F02C7/057 , B64D33/02 , F02C7/042 , F05D2260/50
摘要： An air inlet duct or a nacelle of an aircraft propulsion assembly includes an annular body and an annular air inlet lip with two coaxial annular walls, inner and outer, respectively. The inner wall defining a portion of an inner annular surface of the air inlet duct and the outer wall defining a portion of an outer annular surface of the air inlet duct. A control system translates the lip from a first position, in which the lip is attached to the body, to a second position, in which the lip is axially separated from the body. An annular row of grilles is translatably secured to the lip. The grilles are housed inside the body in the first position and extended from the body in order for an air flow entering the air inlet duct to pass therethrough in the second position.
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公开(公告)号：US20240247611A1
公开(公告)日：2024-07-25
申请号：US18158690
申请日：2023-01-24
发明人： Trevor H. Wood , Michael J. McMahon
CPC分类号： F02C7/042 , F02C7/057 , F05D2220/323 , F05D2240/12 , F05D2260/60 , F05D2260/96
摘要： A turboprop engine includes a main nacelle body, a rotatable hub provided on the main nacelle body, a plurality of propellers connected to the rotatable hub, and a nacelle extension coupled to the main nacelle body, the nacelle extension including at least one wall defining an air intake inlet. The air intake inlet is movable in an airflow axis with respect to a trailing edge of a propeller in the plurality of propellers to vary a distance between the air intake inlet and the trailing edge of the propeller during various phases of operation of the turboprop engine.
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公开(公告)号：US11993408B2
公开(公告)日：2024-05-28
申请号：US17415395
申请日：2019-12-04
IPC分类号： B64U20/10 , B64D7/00 , F01D5/14 , F01D9/02 , F01D17/16 , F02C3/04 , F02C7/042 , F02K3/06 , F04D19/00 , F04D29/18 , F04D29/54
CPC分类号： B64U20/10 , B64D7/00 , F01D5/141 , F01D9/02 , F01D17/162 , F02C3/04 , F02C7/042 , F02K3/06 , F04D19/002 , F04D29/181 , F04D29/544 , F05D2220/3217 , F05D2220/323 , F05D2240/12 , F05D2250/711 , F05D2250/712 , F05D2260/96
摘要： A bladed disc for masking a moving disc of a jet engine, including blades, each blade including a pressure-side wall and a suction-side wall that meet at a leading-edge and at a trailing edge, and wherein each blade has a pressure-side wall and a suction-side wall each including a concave zone and a convex zone that are at a distance from the leading-edge and from the trailing edge and are spaced apart from one another, these concave zones and these convex zones each extending over the majority of the height of the blade, the concave zone of the pressure-side wall is opposite the convex zone of the suction-side wall, the concave zone of the suction-side wall is opposite the convex zone of the pressure-side wall.
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公开(公告)号：US20240092495A1
公开(公告)日：2024-03-21
申请号：US18368922
申请日：2023-09-15
申请人： Rohr, Inc.
发明人： Imad D. Ghandour , Timothy Gormley
摘要： An assembly is provided for an aircraft. This assembly includes a variable area inlet for an aircraft propulsion system. The variable area inlet includes an inlet structure, an inlet door, an inner inlet passage and an outer inlet passage. The inlet door is configured to move outward from a closed position to an open position. The inlet door is configured to close the outer inlet passage when the inlet door is in the closed position. The inlet door is configured to open the outer inlet passage when the inlet door is in the open position. The inner inlet passage extends into the variable area inlet from a leading edge of the inlet structure. The outer inlet passage extends into the inlet structure to the inner inlet passage.
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公开(公告)号：US11919654B2
公开(公告)日：2024-03-05
申请号：US17817749
申请日：2022-08-05
发明人： Eray Akcayoz
CPC分类号： B64D33/02 , F02C7/042 , B64D2033/0293 , F05D2220/323 , F05D2250/51
摘要： An aircraft engine, has: an inlet leading to a compressor section, the inlet extending circumferentially around a central axis; an annular inlet duct extending circumferentially around the central axis, the annular inlet duct having a duct inlet fluidly connected to an environment outside of the aircraft engine and a duct outlet fluidly connected to the inlet, the duct outlet extending circumferentially around the central axis; and a flow restrictor located within the annular inlet duct, the flow restrictor extending across the annular inlet duct, being movable within the annular inlet duct along a circumferential direction relative to the central axis in response to a fluid pressure differential on opposed sides of the flow restrictor.
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6.发明公开公开(公告)号：US20240002036A1
公开(公告)日：2024-01-04
申请号：US18250914
申请日：2021-10-28
摘要： An air intake for an aircraft propulsion assembly extending along a longitudinal axis and comprising a turbine engine that comprises a primary flow path and a secondary flow path for respectively guiding a primary air flow and a secondary air flow during a thrust, and thrust reversal means for changing the secondary airflow into a reverse airflow during a thrust reversal. The air intake comprising a peripheral external enclosure comprising, in each plane radial to the axis, a point of maximum curvature for detaching the reverse airflow, an osculating circle defining a radius of curvature that is defined at each of the points of maximum curvature. The average value of the radii of curvature being less than a product of 0.028 times an internal radius of the intake at the fan.
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公开(公告)号：US20230417182A1
公开(公告)日：2023-12-28
申请号：US18247852
申请日：2021-10-01
申请人： SAFRAN NACELLES
摘要： Disclosed is an air intake of a turbine engine nacelle extending along an axis in which a flow of air circulates from upstream to downstream, the air intake extending annularly about the axis, the air intake having a movable upstream portion and a stationary downstream portion, at least one controllable movement member for moving the movable upstream portion between a retracted position and an extended position in order to enable circulation of an air flow passing between the movable upstream portion and the stationary downstream portion, at least one de-icing circuit having at least one circulation channel fluidically connecting the movable upstream portion and a hot air source, the circulation channel having at least one non-telescopic upstream pipe and at least one telescopic downstream member.
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公开(公告)号：US20230374940A1
公开(公告)日：2023-11-23
申请号：US18248211
申请日：2021-10-18
CPC分类号： F02C7/042 , F02K3/06 , F02C7/18 , F05D2220/323 , F05D2250/90
摘要： A turbojet engine, having a primary duct and a secondary duct surrounding the primary duct, a row of guide vanes extending in the secondary duct downstream of a fan, at least one servo extending in the secondary duct downstream of the guide vanes and housed in a profiled casing, and at least one air sampling scoop located in the region of the casing and equipped with a control valve. Where at least one guide vane located in the vicinity of the casing has a variable geometry zone, the geometry of which can be adjusted during operation.
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公开(公告)号：US11808207B1
公开(公告)日：2023-11-07
申请号：US17817758
申请日：2022-08-05
发明人： Eray Akcayoz
CPC分类号： F02C7/057 , F01D17/08 , F01D17/141 , F02C7/042 , F05D2270/3015
摘要： An aircraft engine, has: an inlet extending circumferentially around a central axis; an annular inlet duct having a duct inlet fluidly connected to an environment outside of the aircraft engine and a duct outlet fluidly connected to the inlet; a flow restrictor extending across the annular inlet duct and being movable within the annular inlet duct; an actuator engaged to the flow restrictor and operable to move the flow restrictor; and a controller operatively connected to at least one sensor and the actuator, the controller having a processing unit and a computer-readable medium operatively connected to the processing unit and containing instructions for: receiving a signal indicative of a pressure difference between opposite sides of the flow restrictor; and powering the actuator to move the flow restrictor with the actuator from a first position to a second position offset from the first position as a function of the pressure difference.
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公开(公告)号：US11725581B2
公开(公告)日：2023-08-15
申请号：US17358957
申请日：2021-06-25
申请人： Rohr, Inc.
发明人： Timothy Gormley
摘要： An assembly for an aircraft propulsion system includes a variable area inlet with a fixed structure and a moveable structure. The variable area inlet is configured to open and close an airflow inlet passage into the aircraft propulsion system. The moveable structure is configured to move axially along a centerline between an aft position and a forward position. The moveable structure includes an inlet lip structure and a deflector. When the moveable structure is in the aft position, the airflow inlet passage is closed, and the deflector is at least partially recessed into the fixed structure. When the moveable structure is in the forward position, the airflow inlet passage is opened axially between an aft end of the inlet lip structure and a forward end of the fixed structure, and a forward end of the deflector is disposed axially at the forward end of the fixed structure.
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