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公开(公告)号：US20240011453A1
公开(公告)日：2024-01-11
申请号：US18035574
申请日：2021-11-03
申请人： SAFRAN NACELLES
摘要： The invention relates to an assembly for a turbine of a turbomachine with a longitudinal axis (X) comprising:
an exhaust cone (100) comprising an outer annular wall (102) for the flow of a primary airflow and an annular box arranged radially inside said outer annular wall (102), the annular box comprising an inner annular wall (104) arranged radially inside the outer annular wall of the exhaust cone,
an exhaust case arranged upstream of the exhaust cone, and
a connecting member (106) flexible in a radial direction, interposed longitudinally between the exhaust case and the exhaust cone (100), the connecting member being fastened to the exhaust case and to the inner annular wall (104), and
wherein the inner annular wall (104) is connected to the outer annular wall (102) by fastening means (112) configured to enable movements of the inner annular wall (104) in a circumferential direction and a longitudinal direction with respect to the outer annular wall (102).
Figure to be published with the abstract: FIG. 2-
公开(公告)号：US20230407814A1
公开(公告)日：2023-12-21
申请号：US18251965
申请日：2021-11-04
申请人： SAFRAN CERAMICS
发明人： Thomas VANDELLOS , Benoit CARRERE , Eric CONETE , Jean-Philippe JORET , Vincent DEVANLAY , Clément Marie Benoît ROUSSILLE
摘要： An assembly for a turbomachine with a longitudinal axis having an exhaust cone with an outer annular wall for the flow of a primary airflow and an annular box arranged radially inside the outer annular wall, an exhaust casing arranged upstream of and connected to the exhaust cone. One end of the outer annular wall or one end of the annular box may be free to move relative to and have no mechanical connection with the exhaust cone or the exhaust casing.
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公开(公告)号：US20190136718A1
公开(公告)日：2019-05-09
申请号：US15803514
申请日：2017-11-03
申请人： ROHR, INC.
CPC分类号： F01D25/30 , B60K13/04 , F01D9/02 , F01D25/24 , F01D25/28 , F01N13/1805 , F02K1/04 , F05D2300/50212
摘要： An exhaust assembly may include an exhaust body and a pivoting attachment feature. The exhaust body, such as a center body or a nozzle, may be configured to direct an annular exhaust stream exiting from a gas turbine engine. The pivoting attachment feature may be coupled the exhaust body and may be configured to pivotally couple the exhaust body to an engine flange. The pivoting attachment feature may be one of a plurality of attachment features circumferentially distributed around the exhaust body. The exhaust body may be a center body and the plurality of attachment features may be coupled to a radially inward surface the center body. The pivoting attachment feature may enable a degree of relative thermal expansion movement between the engine flange/turbine exhaust case and the exhaust body while mitigating detrimental thermal loads, according to various embodiments.
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4.发明申请公开(公告)号：US20180313268A1
公开(公告)日：2018-11-01
申请号：US15769060
申请日：2016-10-25
CPC分类号： F02C7/06 , F02K1/04 , F05D2260/30 , F05D2260/605 , F05D2260/608 , F05D2260/609
摘要： The invention relates to an aircraft turbine engine module (10), comprising a degassing tube (14) and an ejection cone (12). The tube end the cone comprise centring means engaging together. The invention also relates to a locating and adjusting tool for assembling said module.
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公开(公告)号：US20180245480A1
公开(公告)日：2018-08-30
申请号：US15757138
申请日：2016-08-30
CPC分类号： F01D25/243 , F01D21/045 , F01D25/265 , F02C7/20 , F02K1/04 , F05D2220/323 , F05D2240/14 , F05D2260/311 , F16D1/033 , F16D1/076 , F16L23/00 , F16L27/1012 , Y02T50/671
摘要： A propulsive assembly including a turbine engine configured to be fastened to an aircraft by means of a suspension, having certain casing portions suitable for being decoupled so as to attenuate certain bending modes of the turbine engine in the event of an incident, the propulsive assembly comprising at least first and second casing portions (33a, 22) extending axially one after another, one of said casing portions being cantilevered out relative to said suspension, wherein a first casing portion (33a) possesses a first fastener portion (41) connected rigidly to the body (43) of the first casing portion (33a) and a second fastener portion (42) connected more flexibly to the body (43) of the first casing portion (33a), and wherein the second casing portion (22) is fastened to the second fastener portion (42) of the first casing portion (33a) in a manner that is permanent, and to the first fastener portion (41) of the first casing portion (33a) in a manner that is releasable.
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公开(公告)号：US09863273B2
公开(公告)日：2018-01-09
申请号：US14914349
申请日：2014-08-21
申请人： SNECMA
CPC分类号： F01D25/16 , B64D27/16 , B64D27/26 , B64D2027/266 , F02C7/20 , F02K1/04 , F02K3/06 , F05D2220/323 , Y02T50/672
摘要： The invention relates to a bypass turbojet comprising an exhaust housing having a central hub (13) and connecting means (11) that can transmit the forces generated by the turbojet to the structure of the aircraft that it propels, said connection means being two arms extending radially from the central hub in order to cross the cold flow of said turbojet and being characterized in that they are secured to said central hub and positioned in a diametrically opposed manner in relation to each other. An additional connection means (14) extends between the hub (13) and the area (9) for securing the exhaust housing to the structure (12) of the aircraft in order to transmit the exceptional dimensioning loads, said connection means being on standby during normal use, without any transmission of force between said hub and said area.
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公开(公告)号：US09845727B2
公开(公告)日：2017-12-19
申请号：US11720463
申请日：2004-12-01
申请人： Gabriel L. Suciu , James W. Norris , Brian Merry
发明人： Gabriel L. Suciu , James W. Norris , Brian Merry
CPC分类号： F02C3/073 , F02K1/04 , F02K3/068 , F05D2300/603 , F05D2300/614 , Y02T50/672 , Y10T29/49346
摘要： A non-metallic tailcone (202) in a tip turbine engine includes a tapered wall structure disposed (208) about a central axis. The non-metallic tailcone is fastened to a structural frame (44) in the aft portion of the tip turbine engine. The tip turbine engine produces a first temperature gas stream from a first output source and a second temperature gas stream from a second output source. The second temperature gas stream is a lower temperature than the first temperature gas stream. The second temperature gas stream is discharged at an inner diameter of the tip turbine engine over an outer surface of the tailcone. Discharging the cooler second temperature gas stream at the inner diameter allows a non-metallic to be used to form the tailcone.
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公开(公告)号：US09676469B2
公开(公告)日：2017-06-13
申请号：US14249486
申请日：2014-04-10
申请人： Kent W. Benner
发明人： Kent W. Benner
CPC分类号： B64C1/069 , B64C1/12 , F02C7/00 , F02K1/04 , F05D2260/30 , F05D2300/224 , F05D2300/6033 , F16B5/0012 , F16B5/02 , F42B15/36 , Y02T50/672
摘要： A system includes an outer band, inner band, and a fastener. The outer band covers at least a portion of a first structure and has a first edge opposite a second edge. The second edge forms a first load redistribution ramp corresponding to a bend in the first structure. The inner band is positioned beneath a second structure and has a first surface opposite a second surface. The second surface forms a second load redistribution ramp corresponding to the bend in the first structure. A portion of the inner band adjacent to the second surface forms a curve around an edge of the second structure such that the second load redistribution ramp forms a wedge between the first structure and the second structure. The fastener couples the outer band, first structure, second structure, and inner band.
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公开(公告)号：US20160312662A1
公开(公告)日：2016-10-27
申请号：US14693114
申请日：2015-04-22
申请人： Rohr, Inc.
CPC分类号： F01D25/30 , F02K1/04 , F02K1/44 , F05D2220/32 , F05D2260/96 , F05D2300/177 , F05D2300/5021 , F05D2300/6033 , Y02T50/672
摘要： In various embodiments, center body assemblies are described herein. The center body assembly may include an attachment ring, a center body, and a cavity structure. The center body may be configured to be coupled to the attachment ring. The cavity structure may be configured to be coupled to the attachment ring. The cavity structure may be configured to be separated from the center body by a gap. The center body and the cavity structure may be configured to expand independently of each other in response to an increase in temperature. In various embodiments, the cavity structure may comprise a baffle. In various embodiments, the center body may comprise a baffle.
摘要翻译： 在各种实施例中，本文描述了中心体组件。 中心体组件可以包括附接环，中心体和空腔结构。 中心体可以被配置为联接到附接环。 空腔结构可以被配置为联接到附接环。 空腔结构可以被配置为通过间隙与中心体分离。 中心体和腔结构可以被配置为响应于温度的升高彼此独立地扩张。 在各种实施例中，空腔结构可以包括挡板。 在各种实施例中，中心体可包括挡板。
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公开(公告)号：US20160312657A1
公开(公告)日：2016-10-27
申请号：US14692158
申请日：2015-04-21
申请人： ROHR, INC.
发明人： DAVID C. BRICE
CPC分类号： F02K1/04 , F01D25/30 , F05D2230/232 , F05D2230/60 , F05D2250/283
摘要： An attachment feature for a structural panel may include a bracket arm with one or more flanges extending from the bracket arm. Each flange may have a lead ramp and a land. The structural panel may include a core sandwiched between two skins. The two skins may have portions which are cantilevered from the core. The lead ramps may guide the skins to the lands to align the structural panel with the attachment feature.
摘要翻译： 用于结构面板的附接特征可以包括具有从支架臂延伸的一个或多个凸缘的支架臂。 每个法兰可以具有引导斜坡和焊盘。 结构面板可以包括夹在两个表皮之间的芯。 两个表皮可以具有从芯部悬臂的部分。 引导斜面可以将皮肤引导到平台以将结构面板与附件特征对准。
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