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公开(公告)号：US11506143B2
公开(公告)日：2022-11-22
申请号：US16477063
申请日：2018-01-11
摘要： The invention relates to a concentric gas flow mixer in a multiple-flow turbomachine, comprising a nominally cylindrical upstream part and a downstream part having outer and inner lobes distributed peripherally around the tower of said mixer, characterised in that it comprises at least one modified lobe having a wall thickness, in at least one area, which is different from the other lobes, so as to modify the vibratory response of said mixer.
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公开(公告)号：US11085398B2
公开(公告)日：2021-08-10
申请号：US16351031
申请日：2019-03-12
申请人： Rohr, Inc.
发明人： Michael Aten , Adam Saunders , Gary E. Bowman
摘要： A exhaust nozzle assembly comprises a nozzle that extends about an axial centerline and includes an exhaust nozzle flange; an radially inner surface that comprises an axially forward inner surface; a noise attenuating structure; a through hole inlet formed in the axially forward inner surface; a through hole outlet formed in the axially rear inner surface. The nozzle assembly also includes a radially outer surface that is radially separated from the radially inner surface by a nozzle cavity, where engine core air enters the nozzle cavity from the through hole inlet and exits the nozzle cavity axially downstream of the hole inlet via the through hole outlet.
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公开(公告)号：US11053890B2
公开(公告)日：2021-07-06
申请号：US15580496
申请日：2016-06-10
发明人： Mario Cesar De Sousa , Benoit Argemiro Matthieu Debray , Dominique Michel Fouquet , Gregory Ghosarossian-Prillieux , Frederic Noel
摘要： The invention relates to an assembly comprising: a turbomachine exhaust case (110) that includes an external sleeve and an internal sleeve inside the former, both sleeves extending concentrically about a turbomachine axis, and also includes a plurality of arms extending radially between the sleeves; and an annular part (130) that is centered about the axis, is mounted on one sleeve of the exhaust case, and is located downstream of the exhaust case in the direction in which the air flows inside the turbomachine; the assembly is characterized in that the annular part and the sleeve of the exhaust case on which the annular part is mounted each have a circumferential thread (131, 115), said threads cooperating with each other in order to allow the annular part to be screwed onto the sleeve of the exhaust case.
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公开(公告)号：US10954834B2
公开(公告)日：2021-03-23
申请号：US16057300
申请日：2018-08-07
摘要： Systems and methods for an exhaust system for a gas turbine engine are provided. The method includes: receiving a primary exhaust fluid in a primary manifold; receiving a secondary cooling fluid in a secondary plenum; directing the primary exhaust fluid through a plurality of eductor primary flow paths associated with a respective plurality of ducts spaced circumferentially about a primary manifold, the plurality of eductor primary flow paths extending through the secondary plenum; and mixing the primary exhaust fluid and the secondary cooling fluid in a mixing chamber associated with a respective one of the plurality of ducts to create a mixed fluid flow.
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公开(公告)号：US10927791B2
公开(公告)日：2021-02-23
申请号：US16359152
申请日：2019-03-20
发明人： Andre Julien , Jean Thomassin , Maxime Courtois , Bruno Villeneuve , Richard Ullyott , Serge Dussault , Luc Dionne , Serge Lafortune , Anthony Jones , Behzad Hagshenas , David H. Menheere
IPC分类号： F02K1/38 , B64D41/00 , F01C1/22 , F02K5/00 , F02C5/00 , F02C7/14 , F02C7/18 , F02B63/04 , F02B63/06 , F02B67/04 , F01C21/18 , F01N3/05 , F01P5/02 , F01P11/10 , F02B53/02 , F02K1/82 , F02B53/00
摘要： An engine assembly for an aircraft, including an internal combustion engine having a liquid coolant system in fluid communication with a heat exchanger, an exhaust duct in fluid communication with air passages of the heat exchanger, a fan in fluid communication with the exhaust duct for driving a cooling air flow through the air passages of the heat exchanger and into the exhaust duct, and an intermediate duct in fluid communication with an exhaust of the engine and having an outlet positioned within the exhaust duct downstream of the fan and upstream of the outlet of the exhaust duct. The outlet of the intermediate duct is spaced inwardly from a peripheral wall of the exhaust duct. The engine assembly may be configured as an auxiliary power unit. A method of discharging air and exhaust gases in an auxiliary power unit having an internal combustion engine is also discussed.
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公开(公告)号：US20200378339A9
公开(公告)日：2020-12-03
申请号：US16105159
申请日：2018-08-20
摘要： The invention proposes an assembly for a rear of a dual-flow turbomachine (10) having a longitudinal axis (X), comprising: a secondary nozzle (110) defined about the longitudinal axis (X), said secondary nozzle being configured to eject a mixture of the flows coming from a secondary vein (Vs) and a primary vein (Vp) of the turbomachine (10), the secondary nozzle being of convergent-divergent form with a neck (112) corresponding to a minimal cross-cross-section of the secondary nozzle (110), a heating system located on at least one portion of the internal circumference of the secondary nozzle longitudinally in the region of the neck and/or upstream from the neck (112).
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公开(公告)号：US10794329B2
公开(公告)日：2020-10-06
申请号：US15366876
申请日：2016-12-01
摘要： An exhaust plume cooling device for cooling an exhaust gas plume to reduce deleterious heat effects on impinged and surrounding surfaces. The device is supportable in a position downstream of an exhaust nozzle of an exhaust gas plume-producing engine and configured to periodically interrupt the flow of exhaust gases by injecting fluid into the exhaust plume zone.
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公开(公告)号：US10760527B2
公开(公告)日：2020-09-01
申请号：US15019341
申请日：2016-02-09
发明人： Guy Lefebvre , Nicolas Grivas , Richard Bouchard , Denis Leclair , Eric Durocher
摘要： An exhaust mixer for a gas turbine engine includes an annular wall having upstream end adapted to be fastened to an engine case and a downstream end forming a plurality of inner and outer mixer lobes. A support member interconnects at least a number of the inner lobes, and includes a circumferentially extending stiffener ring located radially inwardly from the inner lobes and a series of circumferentially spaced apart mixer struts radially extending from the inner lobes to the stiffener ring. The mixer struts have a radial length at least equal to a width of a main gas path defined between the inner lobes and the exhaust cone such that the mixer struts extend entirely through the main gas path. The stiffener ring being fixed solely to the mixer struts such as to float with respect to the exhaust cone and permit relative movement therebetween.
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公开(公告)号：US20200240359A1
公开(公告)日：2020-07-30
申请号：US16745606
申请日：2020-01-17
发明人： Pascal GARDES , Guillaume SEGUIN , Laurent TIZAC , Fabien MENOU , Frédéric RIDRAY , Benoit ORTEU , Romain CUSSET
摘要： A turbofan having a nacelle comprising a slider translatable between an advanced position and a retracted position to open a window between a duct and the exterior, a plurality of blades, each one rotatable on the slider between a stowed position and a deployed position, and a maneuvering system that moves each blade and comprises, for each blade, a shaft rotatable on the slider and on which the blade is fixed, and a toothed sector fixed to the shaft, and a toothed arc rotatable on the slider about a longitudinal axis, where the teeth of the toothed arc mesh with the teeth of each toothed sector, a cam, as one with the toothed arc, and a groove, as one with a fixed structure, which receives the cam and where, when the slider moves, the cam follows the groove and rotates the toothed arc.
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公开(公告)号：US20200011333A1
公开(公告)日：2020-01-09
申请号：US16398878
申请日：2019-04-30
申请人： ROLLS-ROYCE plc
摘要： A gas turbine engine has an engine core and a bypass duct. A fan drives the flow through the bypass duct. A bypass efficiency is defined as the efficiency of the fan compression of the bypass flow. The bypass efficiency is a function of the bypass flow rate at a given set of conditions. The bypass flow rate at the optimum bypass efficiency is appreciably lower than the maximum bypass flow rate at the given conditions. This results in increased design flexibility and improved overall engine performance.
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