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公开(公告)号:EP3401514A1
公开(公告)日:2018-11-14
申请号:EP18171660.6
申请日:2018-05-09
IPC分类号: F01D25/16 , F16C27/04 , F16F15/023
CPC分类号: F01D25/164 , F01D25/20 , F02C7/06 , F05D2220/32 , F05D2240/50 , F05D2240/53 , F05D2260/96 , F05D2260/98 , F16C27/045 , F16C2360/23 , F16F15/0237 , F16K15/00
摘要: A fluid damping structure is provided that includes a damper ring. The damper ring includes an annular body, a plurality of fluid check valves (122), and at least one fluid stop (124). The annular body extends circumferentially around an axial centerline, and is defined by a first end surface (88), a second end surface (90), an outer radial surface (92), and an inner radial surface (94). The outer radial surface (92) and the inner radial surface (94) extend axially from the first end surface (88) toward the second end surface (90). The body includes one or more check valve passages (104). Each check valve passage (104) extends axially from an open end (106) disposed at the first end surface (88) inwardly toward the second end surface (90), and is disposed between the inner radial surface (94) and the outer radial surface (92). An inlet aperture (112) extends between each check valve passage (104) and the outer radial surface (92), and an outlet aperture (114) extends between each check valve passage (104) and the inner radial surface (94). Each fluid check valve (122) is disposed in a check valve passage (104). The at least one fluid stop (124) is configured to prevent fluid exit from the open end (106) of each check valve passage (104).
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公开(公告)号:EP2975227B1
公开(公告)日:2018-10-03
申请号:EP15173238.5
申请日:2015-06-23
CPC分类号: F01D25/18 , B01D45/16 , F02C7/06 , F05D2220/32 , F05D2260/98
摘要: A gas turbine engine includes a lubrication system for distributing lubricant throughout the engine. The lubrication system includes a breather assembly that receives air and lubricant from various other components of the lubrication system. The breather assembly includes a baffle that redirects air and lubricant received by the breather assembly.
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公开(公告)号:EP3187414B1
公开(公告)日:2018-08-01
申请号:EP16204975.3
申请日:2016-12-19
申请人: GE Avio S.r.l.
发明人: ALTAMURA, Paolo
IPC分类号: B64C11/38
CPC分类号: F16H57/0486 , B64C11/38 , F01D25/18 , F02C7/36 , F02K3/02 , F05D2260/40311 , F05D2260/98 , F16C3/023 , F16H1/28 , F16H57/043
摘要: An oil transfer unit (1) feeds oil into a moving, rotating tube (2) extending along an axis (5); the unit (1) is provided with a support plate (11) transversal to the axis (11) and a sleeve (28), which is angularly fixed with respect to the support plate (11), it is configured to be coupled in a sliding and watertight way to a terminal section of the inlet (20) of said tube (2) and has at least one chamber (32, 33) for transferring oil into said terminal section of the inlet (20); the unit is also equipped with at least two tubular bodies (29, 30, 31), which project axially from the support plate (11), define between them an annular channel (37,38) communicating with the chamber (32,33) and join the sleeve (28) to the support plate (11) in a watertight manner and with clearances so as to leave freedom of orientation of the sleeve (28) around any direction orthogonal to the axis (5).
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公开(公告)号:EP3343010A1
公开(公告)日:2018-07-04
申请号:EP18150209.7
申请日:2018-01-03
发明人: SHERIDAN, William G.
CPC分类号: F02C7/36 , F02C3/107 , F02K3/06 , F05D2220/323 , F05D2240/62 , F05D2260/4031 , F05D2260/40311 , F05D2260/98 , F16H1/20 , F16H57/0423 , F16H57/0457 , F16H57/0495
摘要: A gas turbine engine (100) comprises a fan drive turbine (46) driving a shaft (108). The shaft (108) engages a gear reduction (105). The gear reduction (105) drives a fan rotor (102) at a speed that is less than the speed of the fan drive turbine (46). The gear reduction (105) is a non-epicyclic gear reduction.
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公开(公告)号:EP3278885A3
公开(公告)日:2018-06-20
申请号:EP17183460.9
申请日:2017-07-27
发明人: FILES, Jay C.
CPC分类号: B08B9/0322 , B08B9/04 , B08B9/0495 , F01D25/002 , F02B77/04 , F02B2077/045 , F05D2230/72 , F05D2260/607 , F05D2260/98 , Y02T50/675
摘要: A method is provided involving a gas turbine engine system (20). The method includes configuring a plug (32) within a fluid passage (24) in the gas turbine engine system (20), where the plug (32) is between first and second portions (34, 36) of the fluid passage (24). Material (28) is removed from an interior surface (30) of the fluid passage (24) in the first portion (34) of the fluid passage (24) to provide removed material (28), where the plug (32) substantially prevents the removed material (28) from entering the second portion (36) of the fluid passage (24). The removed material (28) is directed out of the fluid passage (24). The plug (32) is removed from the fluid passage (24).
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公开(公告)号:EP3327316A1
公开(公告)日:2018-05-30
申请号:EP17202520.7
申请日:2017-11-20
发明人: Venter, Gideon
CPC分类号: F16C33/6681 , F01D25/16 , F01D25/18 , F02C7/36 , F05D2240/53 , F05D2260/40311 , F05D2260/98 , F16C19/362 , F16C2360/23 , F16H57/0424 , F16H57/0482 , F16H57/08
摘要: Es wird eine Vorrichtung (21) mit einem drehfesten ersten Bauteil (27) und einem zumindest bereichsweise mit dem ersten Bauteil (27) drehbar verbundenen zweiten Bauteil (28) beschrieben. Hydraulikfluid ist über das erste Bauteil (27) und das zweite Bauteil (28) zu Schmierstellen führbar, wobei eine Schnittstelle (29) zwischen den Bauteilen (27, 28) einen ersten Überleitungsbereich (32) und einen zweiten, in axialer Erstreckung der Bauteile (27, 28) zu dem ersten Überleitungsbereich (32) beabstandeten Überleitungsbereich (56, 57) aufweist. Der erste Überleitungsbereich (32) ist im Betrieb mit einem Druck beaufschlagt, der größer als ein Druck ist, mit dem der zweite Überleitungsbereich (56, 57) im Betrieb beaufschlagt ist. Im Bereich der Schnittstelle (29) ist in axialer Erstreckung der Bauteile (27, 28) zwischen dem ersten Überleitungsbereich (32) und dem zweiten Überleitungsbereich (56, 57) eine Dichteinrichtung (31) angeordnet, die im Bereich einer einer Oberfläche (35 bzw. 36) des ersten Bauteiles (27) oder des zweiten Bauteiles (28) zugewandten Oberfläche (36 bzw. 35) des zweiten Bauteiles (28) oder des ersten Bauteiles (27) mit wenigstens einem Gewindebereich (62, 63) ausgebildet ist.
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公开(公告)号:EP3309371A1
公开(公告)日:2018-04-18
申请号:EP17182094.7
申请日:2017-07-19
发明人: LEFEBVRE, Guy
CPC分类号: F02C7/36 , B64D27/10 , B64D35/04 , F01D5/026 , F01D15/12 , F01D25/18 , F02C3/08 , F02C3/10 , F02C3/107 , F02C3/113 , F02C3/145 , F02C6/206 , F02C7/32 , F02K3/06 , F05D2220/32 , F05D2220/323 , F05D2220/324 , F05D2220/329 , F05D2230/70 , F05D2230/72 , F05D2240/61 , F05D2250/36 , F05D2260/31 , F05D2260/36 , F05D2260/40 , F05D2260/4031 , F05D2260/40311 , F05D2260/98 , F16H57/0495 , Y02T50/671
摘要: A multi-spool gas turbine engine (10) comprises a low pressure (LP) spool (20) and a high pressure (HP) spool (40). The LP spool (20) and the HP spool (40) are independently rotatable about an axis (17). The LP spool (20) has an LP compressor (22) and an LP turbine (21). The HP spool (40) has an HP turbine (41) and an HP compressor (42). The LP compressor (22) is axially positioned between the HP compressor (42) and an accessory gear box (AGB) (50). The AGB (50) is drivingly connected to the HP spool (40) through the center of the LP compressor (22).
摘要翻译: 多管式燃气涡轮发动机(10)包括低压(LP)阀芯(20)和高压(HP)阀芯(40)。 LP线轴(20)和HP线轴(40)可围绕轴线(17)独立旋转。 LP线轴(20)具有LP压缩机(22)和LP涡轮(21)。 HP阀芯(40)具有HP涡轮机(41)和HP压缩机(42)。 LP压缩机(22)轴向定位在HP压缩机(42)和附件齿轮箱(AGB)(50)之间。 AGB(50)通过LP压缩机(22)的中心与HP滑阀(40)驱动连接。
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公开(公告)号:EP3282104A1
公开(公告)日:2018-02-14
申请号:EP17179631.1
申请日:2017-07-04
CPC分类号: F16N19/003 , B29C64/106 , B29K2995/0005 , B29L2031/712 , B33Y10/00 , B33Y70/00 , B33Y80/00 , F01D21/003 , F01D25/18 , F01M11/12 , F02C7/06 , F05D2220/323 , F05D2230/30 , F05D2260/98 , F16N2250/18 , G01F23/263 , Y02T50/671
摘要: L'invention concerne un réservoir (30) d'huile équipant une turbomachine, notamment un turboréacteur d'avion. Le réservoir (30) comprend une chambre intérieure (36) contenant l'huile de la turbomachine ; une paroi (42) avec une surface interne (40) entourant la chambre intérieure (36); et un dispositif capacitif de mesure de niveau d'huile. Le dispositif comprend au moins une électrode (38), éventuellement deux électrodes (38) parallèles formant la surface interne (40). Ces électrodes (38) baignent dans l'huile pour en mesurer le niveau en effectuant une mesure de capacité électrique. L'invention propose également procédé de réalisation d'un réservoir (3) où les électrodes (30) sont imprimées contre la paroi (42).
摘要翻译: 本发明涉及一种装备涡轮机的油(30),包括飞机涡轮喷气发动机。 储存器(30)包括含有涡轮机械的油的内腔室(36) 具有围绕所述内室(36)的内表面(40)的壁(42); 和一个用于测量油位的电容式装置。 该装置包括至少一个电极(38),可能包括形成内表面(40)的两个平行电极(38)。 将这些电极(38)浸入油中以通过执行电容测量来测量水平。 本发明还提出了一种制造储存器(3)的方法,其中电极(30)被印刷在壁(42)上。
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公开(公告)号:EP3277938A1
公开(公告)日:2018-02-07
申请号:EP16729299.4
申请日:2016-04-01
发明人: CHALAUD, Sébastien
CPC分类号: F02C7/14 , F01D25/18 , F01M5/002 , F02C7/06 , F02C7/185 , F02C7/224 , F04C18/16 , F04C23/005 , F04C25/00 , F04C28/08 , F04C28/125 , F04C2270/80 , F05D2260/213 , F05D2260/98 , F05D2270/301 , F05D2270/303 , F05D2270/3062 , F25B9/02 , F25B41/04 , Y02T50/676
摘要: The invention relates to a turbine engine such as a turbojet engine or a turboprop engine of an aircraft, comprising at least one oil circuit (8) and means (16) for cooling the oil of said circuit (8), the cooling means (16) comprising a refrigerant circuit (17) provided with a first heat exchanger (18) capable of exchanging heat between the refrigerant and the air and forming a condenser, a second heat exchanger (19) capable of exchanging heat between the refrigerant and the oil of the oil circuit and forming an evaporator, an expander (20), a compressor (21) and first control means (31) capable of controlling the pressure of the refrigerant entering the first exchanger (18).
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公开(公告)号:EP3276147A1
公开(公告)日:2018-01-31
申请号:EP17185332.8
申请日:2016-04-04
CPC分类号: F01D25/18 , F02C7/06 , F02C7/36 , F05D2260/40 , F05D2260/40311 , F05D2260/406 , F05D2260/98 , F16H1/28 , F16H57/04 , F16H57/0427 , F16H57/043 , F16H57/0486 , F16L25/10 , F16L37/50
摘要: A transfer coupling comprises a static component (41) and a rotatable component (42) arranged in co-axial alignment. The static component (41) includes a first number of ports (41 a) and the rotatable component (42) includes a second number of ports (42a). The ports are arranged in a common circumferential plane and are configured and arranged, in use, to homogenise a flow area for a fluid being transferred through the ports (41 a, 42a) and thereby create a homogenous volume flow. The packing factor of ports on at least one of the components is at least 40%.
摘要翻译: 传送联接器包括以同轴对齐方式布置的静态部件(41)和可旋转部件(42)。 静态部件(41)包括第一数量的端口(41a),并且可旋转部件(42)包括第二数量的端口(42a)。 端口布置在共同的圆周平面中,并且在使用中被配置和布置成使通过端口(41a,42a)传送的流体的流动区域均匀化并且由此产生均匀的体积流量。 至少一个组件上的端口的装箱系数至少为40%。
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