公开(公告)号：EP3019758B1

公开(公告)日：2018-10-24

申请号：EP14755154.3

申请日：2014-07-11

申请人： Ansaldo Energia S.p.A.

发明人： PISTONE, Valerio

IPC分类号： F16B37/12

CPC分类号： F23R3/007 ,  F16B21/04 ,  F16B37/122 ,  F23M5/04 ,  F23R3/60 ,  F23R2900/00017

摘要： A gas turbine combustion chamber includes a casing (2), a plurality of thermally insulating tiles (7) and at least one reversible fastening device (10), which fixes one of the respective tiles (7) to an inner face (3a, 4a) of the casing (2). The reversible fastening device includes: a supporting body (13), fixed to an outer face (3b, 4b) of the casing (2) and having a locking seat (18) and an opening (21) for access to the locking seat (18) from the inside of the casing (2) through a wall (3, 4) of the casing (2); a threaded bushing (12) insertable inside the locking seat (18) so as to receive a screw (30) through the wall (3, 4) from the inside of the casing (2); and at least one locking member (14), configured to releasably lock the bushing (12; 112; 212) inside the locking seat (18; 118; 218).

公开(公告)号：EP2957833B1

公开(公告)日：2018-10-24

申请号：EP15170874.0

申请日：2015-06-05

申请人： Rolls-Royce Corporation ,  Rolls-Royce North American Technologies, Inc.

发明人： Taylor, Todd S. ,  Petty, Jack D. ,  Froemming, Kenneth W.

IPC分类号： F23R3/02 ,  F23R3/04 ,  F23R3/50

CPC分类号： F23R3/002 ,  F23R3/02 ,  F23R3/04 ,  F23R3/045 ,  F23R3/06 ,  F23R3/16 ,  F23R3/50 ,  F23R2900/00017 ,  F23R2900/03041 ,  Y02T50/675 ,  Y10T29/49236

摘要： A combustor for use in a gas turbine engine includes a chute and a combustion liner defining a combustion chamber and a chute-receiving aperture that extends through the combustion liner. The chute extends through the chute-receiving aperture of the combustion liner and defines a passageway sized to convey air from an environment outside the combustion chamber through the combustion liner into the combustion chamber.

公开(公告)号：EP3039344B1

公开(公告)日：2018-08-08

申请号：EP14839726.8

申请日：2014-06-30

申请人： United Technologies Corporation

发明人： WILLIAMS, Alexander W. ,  MAX, Seth A. ,  LYONS, Christopher B.

IPC分类号： F23R3/28 ,  F02C7/22

CPC分类号： F23R3/12 ,  F23R3/14 ,  F23R3/286 ,  F23R3/60 ,  F23R2900/00017 ,  Y02T50/675

摘要： A swirler for a combustor of a gas turbine engine includes a swirler outer body with a male snap component and/or female snap component of a snap-fit interface defined around a swirler central longitudinal axis. A bulkhead assembly for a combustor of a gas turbine engine includes a swirler mounted to a bulkhead support shell through a snap-fit interface.

公开(公告)号：EP1798475B1

公开(公告)日：2018-08-08

申请号：EP06125952.9

申请日：2006-12-12

申请人： KAWASAKI JUKOGYO KABUSHIKI KAISHA

发明人： ODA, Takeo ,  NINOMIYA, Hiroyuki ,  OGATA, Hideki

IPC分类号： F23R3/14 ,  F23R3/28 ,  F23D11/38 ,  F23R3/34

CPC分类号： F23R3/14 ,  F23C2900/07022 ,  F23D11/383 ,  F23D2900/00008 ,  F23D2900/11101 ,  F23R3/283 ,  F23R3/286 ,  F23R3/343 ,  F23R2900/00017 ,  F23R2900/00019 ,  Y02T50/675

摘要： A fuel spraying apparatus of a gas turbine engine includes a first fuel spraying section configured to spray fuel for diffusion combustion and a second fuel spraying section configured to spray fuel for premixed combustion. The second fuel spraying section is disposed so as to surround the first fuel spraying section. The apparatus further includes an air curtain generating section disposed between the first fuel spraying section and the second fuel spraying section. The air curtain generating section is configured to generate an air curtain which defines an outer edge of a diffusion combustion area in a combustion chamber.

公开(公告)号：EP3330040A1

公开(公告)日：2018-06-06

申请号：EP17204478.6

申请日：2017-11-29

申请人： General Electric Company

发明人： MOGLE II, Thomas Alan ,  KOLVICK, Sandra Beverly ,  SMITH, Troy Lee

IPC分类号： B23P19/02 ,  B25B27/02 ,  F01D25/28

CPC分类号： F01D25/285 ,  B25B27/023 ,  F05D2230/70 ,  F05D2260/83 ,  F23R3/002 ,  F23R3/44 ,  F23R2900/00017

摘要： This disclosure provides tools for installing and removing a combustion liner (30, 350) in a combustion casing (22, 310). A mounting frame (110) has fasteners (130, 140) positioned circumferentially around an end casing surface of the combustion casing (22, 310) and removably attaches the mounting frame (110) to the combustion casing (22, 310). A positioning member (150) has pushing surfaces and pulling surfaces distributed circumferentially around the combustion liner (30, 350). An axial positioning mechanism (200) engages the mounting frame (110) and the positioning member (150) along a common axis. The axial positioning mechanism (200) incrementally positions the positioning member (150) relative to the mounting frame (110) by adjusting a positioning distance between the mounting frame (110) and the positioning member (150).

公开(公告)号：EP2203682B1

公开(公告)日：2018-04-04

申请号：EP08804351.8

申请日：2008-09-18

申请人： General Electric Technology GmbH

发明人： TSCHUOR, Remigi ,  HÄHNLE, Hartmut ,  SCHNEIDER, Lothar ,  MARKOVIC, Alen

IPC分类号： F23R3/00

CPC分类号： F23R3/002 ,  B23P6/002 ,  B23P2700/13 ,  F23R2900/00017 ,  F23R2900/00019 ,  F23R2900/03042 ,  F23R2900/03044

公开(公告)号：EP3278027A1

公开(公告)日：2018-02-07

申请号：EP16711857.9

申请日：2016-03-29

申请人： NUOVO PIGNONE TECNOLOGIE SRL

发明人： PUCCI, Egidio ,  PROVENZALE, Michele

IPC分类号： F23M5/04 ,  F23R3/00 ,  F23R3/60

CPC分类号： F23R3/002 ,  F23R3/60 ,  F23R2900/00017

摘要： A gas turbine combustor is disclosed, comprising: a combustor liner; a combustor casing, at least partly housing the combustor liner, and a liner support arrangement. The liner support arrangement comprises individual support elements located between the combustor liner and the combustor casing. Each support element comprises a liner support member fixed to the combustor liner and a casing support member fastened to the combustor casing. Each casing support member comprises a casing stop seat fixed on the combustor casing and a replaceable casing stop, detachably coupled to the casing stop seat.

公开(公告)号：EP2952813B1

公开(公告)日：2017-12-27

申请号：EP15169991.5

申请日：2015-05-29

申请人： Rolls-Royce North American Technologies, Inc.

发明人： Vetters, Daniel Kent

IPC分类号： F23R3/50

CPC分类号： F23R3/007 ,  F23M5/04 ,  F23M2900/05002 ,  F23R3/44 ,  F23R3/50 ,  F23R3/60 ,  F23R2900/00017 ,  Y10T29/49233

摘要： A combustor for use in a gas turbine engine and methods for assembling the same are disclosed. The combustor includes an outer case and a combustion liner. The combustion liner is arranged radially inward of the outer case. The combustion liner is arranged to define an annular combustion chamber.

公开(公告)号：EP2154431B1

公开(公告)日：2017-07-26

申请号：EP09167590.0

申请日：2009-08-11

申请人： General Electric Technology GmbH

发明人： Tschuor, Remigi ,  Hähnle, Hartmut ,  Rüdel, Uwe

IPC分类号： F23R3/00 ,  F23R3/50 ,  F23R3/54

CPC分类号： F23R3/54 ,  F23R3/002 ,  F23R3/50 ,  F23R2900/00017 ,  F23R2900/00018 ,  F23R2900/03044

公开(公告)号：EP3098429A4

公开(公告)日：2017-03-22

申请号：EP15769123

申请日：2015-02-17

申请人： MITSUBISHI HEAVY IND LTD

发明人： UENO YOSHIHIKO ,  FURUYA SHOJIRO

IPC分类号： F02K7/10 ,  F02C7/00 ,  F02C7/042 ,  F02K7/18 ,  F23R3/22

CPC分类号： F23R3/22 ,  F02C7/042 ,  F02K7/10 ,  F02K7/18 ,  F05D2220/10 ,  F05D2220/80 ,  F05D2260/99 ,  F23R3/60 ,  F23R2900/00015 ,  F23R2900/00017 ,  Y02T50/671

摘要： A jet engine includes an inlet (11) which takes in air and a combustor (12) which combusts fuel with the air. The combustor (12) has an injector (20), a plurality of flame stabilizers (21, 22) and a vanishment section (31). The injector (20) injects the fuel. The plurality of flame stabilizers (21, 22) can maintain the flame (F) used for combustion in the combustor (12). The vanishment section (31) is provided to cover the dent of the first flame stabilizer (21) which is situated on the side near to the inlet in the plurality of flame stabilizers (21, 22), and vanishes with the passage of time in the flight.

摘要翻译： 喷气式发动机包括吸入空气的入口（11）和使燃料与空气燃烧的燃烧器（12）。 燃烧器（12）具有喷射器（20），多个火焰稳定器（21,22）和消失部分（31）。 喷射器（20）喷射燃料。 多个火焰稳定器（21,22）可以保持用于在燃烧器（12）中燃烧的火焰（F）。 该消失部31设置成覆盖位于多个火焰稳定器21,22中靠近入口一侧的第一火焰稳定器21的凹陷，并且随着时间的推移而消失 飞行。