公开(公告)号：US20240240563A1

公开(公告)日：2024-07-18

申请号：US18618367

申请日：2024-03-27

申请人： MTU Aero Engines AG

发明人： Andreas HARTUNG ,  Markus SCHLEMMER ,  Daniel THEURICH ,  Adam KOSCSO

IPC分类号： F01D5/10

CPC分类号： F01D5/10 ,  F05D2250/221 ,  F05D2250/241 ,  F05D2260/96

摘要： A damper ring (1) for reducing unwanted vibrations of a blisk (2), which damper ring (1) is disposable at the radially inner side of a blade ring (3) of the blisk (2). The damper ring (1) features at least one damper element (4) configured to dissipate vibrational energy of the blisk (2) and/or to transfer vibrational modes of the blisk into vibrational modes different from the vibrational modes of the blisk. The invention also relates to a blisk (2) and to a turbomachine (13).

公开(公告)号：US11753958B2

公开(公告)日：2023-09-12

申请号：US17633834

申请日：2020-08-06

申请人： Safran Aircraft Engines

发明人： Simon Nicolas Morliere ,  Stéphane Pierre Guillaume Blanchard ,  Nicolas Jean-Marc Marcel Beauquin

IPC分类号： F01D25/12 ,  F01D11/24 ,  F01D25/14 ,  F01D25/28 ,  F02C7/18

CPC分类号： F01D11/24 ,  F01D25/12 ,  F01D25/14 ,  F01D25/28 ,  F02C7/18 ,  F05D2220/323 ,  F05D2250/241 ,  F05D2260/201 ,  F05D2260/30

摘要： The present invention relates to a device for cooling, using air jets, an external casing of a turbomachine, comprising a housing for supplying air to cooling tubes of said casing, the housing being provided with an attachment device on the external casing. According to the invention, said attachment device comprises two upstream ball joint retention devices which each connect the housing to the external casing.

公开(公告)号：US20190240725A1

公开(公告)日：2019-08-08

申请号：US16314341

申请日：2017-06-07

申请人： SAFRAN AIRCRAFT ENGINES

发明人： Coralie Cinthia Guerard ,  Vincent Marc Herb ,  Jun Ni ,  Joseph Toussaint Tami Lizuzu ,  Matthieu Jean Luc Vollebregt

IPC分类号： B22C9/10 ,  B22C9/04 ,  B22C9/24 ,  F01D5/18

CPC分类号： B22C9/10 ,  B22C9/04 ,  B22C9/24 ,  F01D5/187 ,  F05D2250/241

摘要： The present disclosure is generally directed to a core configured for the manufacturing of a turbine engine blade by lost-wax casting. The core includes a first convex curved outer face and a second concave curved outer face. The first and second faces have a plurality of recesses, each recess including a spherical portion.

公开(公告)号：US09982628B2

公开(公告)日：2018-05-29

申请号：US14771243

申请日：2014-02-11

申请人： UNITED TECHNOLOGIES CORPORATION

发明人： Gary D Roberge

IPC分类号： F02K1/82 ,  F01D25/08 ,  F01D25/28 ,  F01D25/30 ,  F02C7/18 ,  F23R3/00 ,  F01D25/24 ,  F01D25/26 ,  F02C7/20

CPC分类号： F02K1/822 ,  F01D25/08 ,  F01D25/243 ,  F01D25/26 ,  F01D25/28 ,  F01D25/30 ,  F02C7/18 ,  F02C7/20 ,  F05D2230/642 ,  F05D2250/241 ,  F05D2260/30 ,  F23R3/005 ,  Y02T50/675

摘要： The exhaust system (60) includes an exhaust flow path liner (62) surrounded and supported by a plurality of structural duct segments (64, 70). Pluralities of links (84) are secured to and extend between the duct segments (64, 70) and the liner (62). A duct end (88) of the link includes a lock member (96) having a diameter greater than a width of the stem (86). The lock member (96) is configured to be secured within a capture nest (98) defined between and within adjacent junction flanges (76, 80} of the structural duct segments {64, 70) when the segments (64, 70) are secured to each other to secure the segments (64, 70) together. A catch member (100) at an opposed end of the link (84) is secured to a capture node (102) at the exhaust liner (62).

公开(公告)号：US09957812B2

公开(公告)日：2018-05-01

申请号：US14302659

申请日：2014-06-12

申请人： IHI Corporation

发明人： Yoji Okita ,  Shu Fujimoto ,  Chiyuki Nakamata

IPC分类号： F01D5/00 ,  F01D5/18 ,  F23R3/00

CPC分类号： F01D5/187 ,  F01D5/189 ,  F05D2250/241 ,  F05D2250/294 ,  F05D2260/201 ,  F05D2260/2212 ,  F23R3/002 ,  F23R3/005 ,  F23R2900/03042 ,  F23R2900/03044 ,  F23R2900/03045

摘要： The present invention relates to an impingement cooling mechanism (1) that ejects a cooling gas (G) toward a cooling target (2) from a plurality of impingement holes (4) formed in an opposing member (3) that is arranged opposite the cooling target (2). Turbulent flow promoting portions (6) are provided in the flow path of a crossflow (CF), which is a flow that is formed by the cooling gas (G) after being ejected from the impingement holes (4). The turbulent flow promoting portions (6) are constituted so that a turbulent flow is promoted from the upstream side to the downstream side of the crossflow (CF).

公开(公告)号：US09951623B2

公开(公告)日：2018-04-24

申请号：US14801103

申请日：2015-07-16

申请人： MTU Aero Engines AG

发明人： Andreas Hartung ,  Frank Stiehler ,  Martin Pernleitner

IPC分类号： F01D5/06 ,  F01D5/16 ,  F01D5/22 ,  F01D9/04 ,  F01D5/14 ,  F01D1/02

CPC分类号： F01D5/06 ,  F01D1/02 ,  F01D5/142 ,  F01D5/16 ,  F01D5/22 ,  F01D9/041 ,  F05D2220/32 ,  F05D2240/129 ,  F05D2240/30 ,  F05D2250/241 ,  F05D2260/961 ,  F05D2300/607 ,  Y02T50/671

摘要： A blade cascade for a gas turbine, which has a first group with at least two, in particular at least three, first blade arrangements of the same type to one another, on which first element arrangements that are identical to one another and have at least one first element are movably mounted; and a second group with at least two, in particular at least three, second blade arrangements, which are of the same type to one another and are of different type from the first blade arrangements, on which second element arrangements, which are identical to one another and have at least one second element are movably mounted, wherein first and second element arrangements are different from each other.

公开(公告)号：US20170335695A1

公开(公告)日：2017-11-23

申请号：US15458257

申请日：2017-03-14

申请人： MTU Aero Engines AG

发明人： Markus Schlemmer ,  Gerhard-Heinz Roesele ,  Andreas Hartung

IPC分类号： F01D5/26 ,  F01D5/30 ,  F01D5/14 ,  F01D5/16

CPC分类号： F01D5/26 ,  F01D5/147 ,  F01D5/16 ,  F01D5/3061 ,  F04D29/668 ,  F05D2220/32 ,  F05D2240/30 ,  F05D2250/22 ,  F05D2250/221 ,  F05D2250/241 ,  F05D2260/96 ,  F16F7/10

摘要： A turbomachine blade assembly including a turbomachine blade (1), in particular for a gas turbine, and at least one tuning element container including a housing (10) attached to the turbomachine blade and an insert (20) disposed in a recess (11) of this housing. A wall (20; 21) of the insert spaces apart two first cavities (31), which each accommodate at least one tuning element (40) provided for impacting contact with the housing (10) and the insert (20).

公开(公告)号：US09598974B2

公开(公告)日：2017-03-21

申请号：US13775806

申请日：2013-02-25

申请人： PRATT & WHITNEY CANADA CORP.

发明人： Eugene Gekht ,  Terrence Lucas ,  Thomas Francis Haslam-Jones ,  Danny Mills ,  Guy Bouchard

IPC分类号： F01D11/24 ,  F01D25/12

CPC分类号： F01D11/24 ,  F01D25/12 ,  F01D25/14 ,  F05D2220/321 ,  F05D2240/11 ,  F05D2250/241 ,  F05D2250/711 ,  F05D2260/201 ,  Y02T50/676

摘要： A gas turbine engine includes an annular plenum defined with an outer skin and a perforated inner skin for receiving selective air flow to impinge a support case which supports shrouds of the rotor assemblies of the engine therein for active tip clearance control of the rotor assemblies. In one embodiment a bobbin-type transfer tube for supplying cooling air into the plenum, is provided between an outer case of the engine an the plenum such that the thermally induced relative movement of the outer case and the plenum is permitted.

公开(公告)号：US20160377166A1

公开(公告)日：2016-12-29

申请号：US15132620

申请日：2016-04-19

申请人： United Technologies Corporation

发明人： William G. Sheridan

IPC分类号： F16H57/04 ,  F16H57/08 ,  F02K3/02 ,  F16H1/28

CPC分类号： F16H57/0479 ,  F01D25/162 ,  F01D25/166 ,  F02C3/107 ,  F02C7/36 ,  F05D2240/53 ,  F05D2240/54 ,  F05D2250/241 ,  F05D2260/40311 ,  F05D2260/98 ,  F16H1/28 ,  F16H57/043 ,  F16H57/0471 ,  F16H57/0486 ,  F16H57/082 ,  F16H2057/085 ,  Y02T50/671

摘要： A gear system for a geared turbofan engine includes a sun gear, a planet gear supported in a carrier and engaged to the sun gear, a forward journal bearing and an aft journal bearing both supporting the planet gear. The carrier includes a forward wall supporting the forward journal bearing and an aft wall supporting the aft journal bearing. A ring gear is engaged to the planet gear. A geared turbofan engine is also disclosed.

摘要翻译： 用于齿轮传动涡扇发动机的齿轮系统包括太阳齿轮，支撑在载体中并与太阳齿轮啮合的行星齿轮，前轴颈轴承和支承行星齿轮的后轴颈轴承。 载体包括支撑前轴颈轴承的前壁和支撑后轴颈轴承的后壁。 环形齿轮接合到行星齿轮。 还公开了一种齿轮涡扇发动机。

公开(公告)号：US20160024945A1

公开(公告)日：2016-01-28

申请号：US14801264

申请日：2015-07-16

申请人： MTU Aero Engines AG

发明人： Frank Stiehler ,  Martin Pernleitner ,  Andreas Hartung

IPC分类号： F01D5/30 ,  F01D9/02 ,  F01D5/12

CPC分类号： F01D5/30 ,  F01D5/16 ,  F01D5/22 ,  F01D5/26 ,  F05D2250/241 ,  F05D2260/961 ,  F05D2300/607 ,  F16F15/00 ,  Y02T50/671

摘要： The present invention relates to a turbomachine blade (100; 200) with a base element, which has a blade part (1) for flow diversion and a blade root (2), a first guide (110; 210), fixed on the base element, in which a first element (111; 211) is movably guided, and a second guide (120; 220), fixed on the base element, in which a second element (121; 221) is movably guided, wherein a dynamic of the first element in the first guide and a dynamic of the second element in the second guide are designed differently, and the first guide (110; 210) is arranged in a half, nearer to the base root, of a radial height (H) of the base element, and the second guide is arranged in a half, more remote from the blade root, of the radial height of the base element.

摘要翻译： 技术领域本发明涉及一种具有基座元件的涡轮机叶片（100; 200），其具有用于分流的叶片部分（1）和叶片根部（2），固定在基座上的第一引导件（110; 210） 元件，其中第一元件（111; 211）可移动地被引导;以及第二引导件（120; 220），固定在所述基座元件上，第二元件（121; 221）可移动地被引导，其中， 第一引导件中的第一元件和第二引导件中的第二元件的动态被设计为不同，并且第一引导件（110; 210）布置在径向高度（H）的更靠近基部根部的一半中， 并且第二引导件布置在基部元件的径向高度的一半，更远离叶片根部。