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公开(公告)号：US20180354638A1
公开(公告)日：2018-12-13
申请号：US15778954
申请日：2016-11-25
发明人： Romain Jean-Claude Ferrier , Romeo Brogna , Jackie Raymond Julien Prouteau , Nicolas Joseph Sirvin
CPC分类号： B64D33/02 , B64D2033/022 , B64D2033/0246 , B64D2033/0293 , F02C6/206 , F02C7/052 , F02C7/055 , F05D2220/325 , F05D2260/607 , Y02T50/671 , Y02T50/675
摘要： The invention relates to a turbomachine (24) of the «open rotor» type or a turboprop engine comprising a nacelle (26) defining an air inlet (28), a central hub (30) and an annular air intake section (32) surrounding the central hub (30) and opening into a air supply main section (34), with the central hub (30) comprising a central trap (36) having an aperture (38) for trapping the foreign objects in an air flow entering the turbomachine (24), and an air recovery channel (48) having a discharge end (48a), through which said air recovery channel (48) opens into the main section (34), provided on the central hub (30).
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公开(公告)号：US20170260903A1
公开(公告)日：2017-09-14
申请号：US15455532
申请日：2017-03-10
CPC分类号： F02C7/04 , F02C3/04 , F02C6/206 , F02C7/057 , F02K3/072 , F05D2220/325 , F05D2270/17
摘要： Air inlet duct of a turbine engine, in particular an aircraft turbine engine comprising a gas generator, which extends axially between the air inlet and the gas generator and has a first axial wall part and a second wall part which is angularly offset with respect to the first part, which duct is capable of causing, in a shedding region, shedding of the boundary layer formed by an air flow along the wall of the duct; and a device for controlling said shedding of the boundary layer, characterised in that the control device comprises an air-blowing pipe which opens via at least one air-injection opening which is directly upstream of the shedding region, the blowing pipe being connected to an air intake positioned upstream of said air-injection opening or in the shedding region and comprising an air compressor means between the air intake and the air-injection opening.
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公开(公告)号：US10054049B2
公开(公告)日：2018-08-21
申请号：US15323602
申请日：2015-07-02
CPC分类号： F02C7/04 , B64D2033/0226 , F02C7/057 , F05D2250/60 , F05D2270/17
摘要： An air guidance device for a turbomachine includes an air supply channel of a turbomachine engine. The supply channel has an upstream section and a downstream section connected together by a diverting section, the upstream section and the diverting section being connected together via an internal elbow and an external elbow. At the internal elbow, the internal surface has a groove extending longitudinally in the longitudinal direction of the supply channel and the longitudinal edges of which are widened in the direction of the downstream end of the upstream section of the supply channel.
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公开(公告)号：US11199108B2
公开(公告)日：2021-12-14
申请号：US17058433
申请日：2019-05-24
发明人： Romain Jean-Claude Ferrier , Sébastien Christophe Chalaud , Philippe Gérard Chanez , Lauren Davis , Bastien Pierre Verdier , Christian Sylvain Vessot
摘要： The outlet of a heat exchange circuit extending under a wall, such as a nacelle cowling of an aircraft engine, is divided into openings in the form of parallel slots which are elongated in the longitudinal direction and successively arranged in the transverse direction to divide the hot gas into streams while facilitating the circulation of fresh gas streams, originating from an external flow, on the intermediate laminates. The hot gas cannot fall back easily onto the outer face of the wall and risk damaging the wall, and the gas mixes more effectively with the fresh outdoor air. The openings are provided with nozzles flaring in the transverse direction and the downstream longitudinal direction to facilitate the mixing of the hot and cold gas streams.
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公开(公告)号：US10946975B2
公开(公告)日：2021-03-16
申请号：US15778954
申请日：2016-11-25
发明人： Romain Jean-Claude Ferrier , Romeo Brogna , Jackie Raymond Julien Prouteau , Nicolas Joseph Sirvin
摘要： A turbomachine of the «open rotor» type or a turboprop engine comprises a nacelle defining an air inlet, a central hub and an annular air intake section surrounding the central hub and opening into a air supply main section, with the central hub comprising a central trap having an aperture for trapping the foreign objects in an air flow entering the turbomachine, and an air recovery channel having a discharge end, through which said air recovery channel opens into the main section, is provided on the central hub.
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公开(公告)号：US10562638B2
公开(公告)日：2020-02-18
申请号：US16320264
申请日：2017-07-20
发明人： Frederic Paul Eichstadt , Nora El Ghannam , Romain Jean-Claude Ferrier , Antoine Elie Hellegouarch
摘要： The invention relates to a cradle (10) for an aircraft turbopropeller engine (12) of a substantially axial orientation, comprising a front arch (16) and a rear arch (18) extending transversely relative to said axial direction (A), said arches (16, 18) being open at their lower ends and connected to each other by at least one axial longeron (34) extending between said arches (16, 18), characterised in that the longeron (34) is arranged in an upper portion of the cradle (10) and is formed in a single piece with the front arch (16).
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公开(公告)号：US10415470B2
公开(公告)日：2019-09-17
申请号：US15455532
申请日：2017-03-10
摘要： Air inlet duct of a turbine engine, in particular an aircraft turbine engine comprising a gas generator, which extends axially between the air inlet and the gas generator and has a first axial wall part and a second wall part which is angularly offset with respect to the first part, which duct is capable of causing, in a shedding region, shedding of the boundary layer formed by an air flow along the wall of the duct; and a device for controlling said shedding of the boundary layer, characterised in that the control device comprises an air-blowing pipe which opens via at least one air-injection opening which is directly upstream of the shedding region, the blowing pipe being connected to an air intake positioned upstream of said air-injection opening or in the shedding region and comprising an air compressor means between the air intake and the air-injection opening.
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