公开(公告)号：US10883375B2

公开(公告)日：2021-01-05

申请号：US15483539

申请日：2017-04-10

Applicant: ANSALDO ENERGIA SWITZERLAND AG

Inventor： Urs Benz

IPC: F01D9/04 ,  F01D9/02 ,  F23R3/60 ,  F01D5/02 ,  F23R3/00 ,  F02C3/14 ,  F02C7/20 ,  F01D25/28

Abstract: A turboengine as disclosed includes an outer wall structure and an inner wall structure, wherein the inner wall structure is provided at a radially inner position with respect to the outer wall structure, and each of the wall structures has a surface, the surfaces being arranged facing each other in the radial direction. At least one guide vane member includes at least one airfoil, a radially inner end and a radially outer end. The inner wall structure and the outer wall structure are jointly provided as a vane carrier unit, wherein the inner wall structure and the outer wall structure are fixedly connected to each other by at least one bridging member extending between the inner wall structure and the outer wall structure.

公开(公告)号：US11629609B2

公开(公告)日：2023-04-18

申请号：US15081101

申请日：2016-03-25

Applicant: ANSALDO ENERGIA SWITZERLAND AG

Inventor： Frank Graf ,  Hans-Christian Mathews ,  Urs Benz ,  Fabien Fleuriot

IPC: F01D11/00 ,  F01D25/24 ,  F01D9/04 ,  F01D9/00 ,  F16J15/00 ,  F02C7/28 ,  F01D9/02 ,  F01D25/12

Abstract: The invention concerns a gas turbine having a picture frame, a first vane, and a sealing arrangement to seal a gap between the picture frame and the first vane, the sealing arrangement including two seals arranged in series between the picture frame and the first vane. In exemplary embodiments, one of the seals is a honeycomb seal, a dogbone seal, a hula seal or a piston seal and the other seal is a honeycomb seal, a dogbone seal, a hula seal or a piston seal. A method of supplying cooling fluid to the gap between the picture frame and the first vane is also disclosed.

公开(公告)号：US10590790B2

公开(公告)日：2020-03-17

申请号：US15081196

申请日：2016-03-25

Applicant: ANSALDO ENERGIA SWITZERLAND AG

Inventor： Hans-Christian Mathews ,  Urs Benz ,  Frank Graf

IPC: F01D11/00 ,  F01D25/12 ,  F23R3/60 ,  F01D9/02 ,  F02C7/28 ,  F01D9/04 ,  F23R3/00 ,  F16J15/06

Abstract: The invention concerns a conical hula seal wherein an inner part of the conical hula seal is closer to a conical hula seal longitudinal axis than an outer part of the conical hula seal, and wherein the conical hula seal extends in a circumferential direction relative to the conical hula seal longitudinal axis. A gas turbine which includes the conical hula seal is also disclosed, along with a method of operating a gas turbine which includes a conical hula seal that seals a gap between a first vane and a picture frame, the method including purging the gap with a cooling fluid.

公开(公告)号：US10544939B2

公开(公告)日：2020-01-28

申请号：US15446407

申请日：2017-03-01

Applicant: ANSALDO ENERGIA SWITZERLAND AG

Inventor： Andrea Ciani ,  John Philip Wood ,  Douglas Anthony Pennell ,  Ewald Freitag ,  Urs Benz ,  Andre Theuer

IPC: F23R3/16 ,  F23R3/20 ,  F23R3/28 ,  F02C9/32 ,  F02C9/34 ,  F02C9/26 ,  F23R3/46 ,  F23R3/34 ,  F23R3/36 ,  F02C6/00

Abstract: A burner for a combustion chamber of a gas turbine with a mixing and injection device, which includes a limiting wall that defines a gas-flow channel and at least two streamlined bodies. Each streamlined body extends in a first transverse direction into the gas-flow channel, and has two lateral surfaces that are arranged essentially parallel to the main-flow direction. The lateral surfaces are joined to one another at their upstream and downstream sides to form leading and trailing edges of the body, respectively. At least one of the streamlined bodies includes a mixing structure and at least one fuel nozzle at its trailing edge for introducing at least one fuel essentially parallel to the main-flow direction into the flow channel. At least two of the streamlined bodies have different lengths along the first transverse direction such that they may be used for a can combustor.

公开(公告)号：US10267522B2

公开(公告)日：2019-04-23

申请号：US14060931

申请日：2013-10-23

Applicant: ANSALDO ENERGIA SWITZERLAND AG

Inventor： Andrea Ciani ,  John Philip Wood ,  Douglas Anthony Pennell ,  Ewald Freitag ,  Urs Benz ,  Andre Theuer

IPC: F23R3/16 ,  F23R3/28 ,  F02C9/32 ,  F02C9/34 ,  F02C9/26 ,  F23R3/20 ,  F23R3/46 ,  F23R3/34 ,  F23R3/36 ,  F02C6/00

Abstract: The present invention relation to a burner for a combustion chamber of a gas turbine with a mixing and injection device. The mixing and injection device includes a limiting wall that defines a gas-flow channel and at least two streamlined bodies, each extending in a first transverse direction into the gas-flow channel. Each streamlined body has two lateral surfaces that are arranged essentially parallel to the main-flow direction, the lateral surfaces being joined to one another at their upstream side to form a leading edge of the body and joined at their downstream side to form a trailing edge of the body. Each streamlined body has a cross-section perpendicular to the first transverse direction that is shaped as a streamlined profile. At least one of the streamlined bodies is provided with a mixing structure and with at least one fuel nozzle located at its trailing edge for introducing at least one fuel essentially parallel to the main-flow direction into the flow channel, wherein at least two of the streamlined bodies have different lengths along the first transverse direction such that they may be used for a can combustor. The invention also relates to a method of using said burner in a gas turbine.

公开(公告)号：US10167739B2

公开(公告)日：2019-01-01

申请号：US15003729

申请日：2016-01-21

Applicant: ANSALDO ENERGIA SWITZERLAND AG

Inventor： Urs Benz ,  Paul Marlow ,  Jost Imfeld

IPC: F01D25/28 ,  F01D25/26 ,  F16D1/08

Abstract: A centering arrangement includes a ring-like inner part and a ring-like outer part, whereby the outer part surrounds the inner part in a concentric arrangement and with an interspace established between the outer part and the inner part, and whereby the outer part and the inner part are subject to a differential radial expansion. A centering contact element, procures a centering mechanical contact between the outer part and the inner part at a plurality of circumferentially distributed contact points, and is able to deform in order to compensate for differential radial expansion.

公开(公告)号：US10060352B2

公开(公告)日：2018-08-28

申请号：US14732070

申请日：2015-06-05

Applicant: Ansaldo Energia Switzerland AG

Inventor： Michael Thomas Maurer ,  Urs Benz ,  Felix Baumgartner

IPC: F02C1/00 ,  F02C7/18 ,  F23R3/00 ,  F02C3/04

CPC classification number: F02C7/18 ,  F02C3/04 ,  F05D2220/32 ,  F05D2260/201 ,  F05D2260/2212 ,  F23R3/002 ,  F23R2900/03044

Abstract: An impingement cooled wall arrangement includes a flow diverter arranged in the cooling flow path between the cooled wall and a sleeve to divert a cross flow away from a second aperture. The flow diverter extends in downstream direction of the cross flow beyond the second aperture with a first leg extending along one side of the second aperture in downstream direction of the cross flow and a second leg extending along the other side of the second aperture. No impingement cooling aperture is arranged in a first convective cooling section of the wall between the upstream end and downstream end of the flow diverter outside the section shielded by the diverter.

公开(公告)号：US11009232B2

公开(公告)日：2021-05-18

申请号：US15695510

申请日：2017-09-05

Applicant: ANSALDO ENERGIA SWITZERLAND AG

Inventor： Jost Imfeld ,  Paul Marlow ,  Oliver Konradt ,  Urs Benz

IPC: F23R3/00 ,  F23R3/60 ,  F23R3/50 ,  F23R3/42 ,  F01D25/26 ,  F01D25/28 ,  F02C3/14

Abstract: Combustor device having a twin-shell tubular casing including: an inner tubular member which extends roughly coaxial a longitudinal axis of the combustor device, delimits the combustion chamber and surrounds the burner; and an outer tubular housing which extends roughly coaxial outside of the inner tubular member. An intermediate supporting structure includes an outer annular supporting member, an inner annular supporting member, and a series of three or more oblong connecting beams angularly staggered about the longitudinal axis of combustor device in cantilever manner to stably connect the inner and outer annular supporting members.

公开(公告)号：US10920985B2

公开(公告)日：2021-02-16

申请号：US14947701

申请日：2015-11-20

Applicant: ANSALDO ENERGIA SWITZERLAND AG

Inventor： Xianfeng Gao ,  Urs Benz ,  Andre Theuer ,  Michael Düsing

IPC: F23R3/00 ,  F23R3/28 ,  F23C7/00 ,  F23R3/12 ,  F23R3/18 ,  F23R3/20 ,  F23R3/16 ,  F02C7/22

Abstract: A fuel lance is disclosed for injecting a gaseous and/or liquid fuel mixed with air into an axial hot gas flow flowing through a sequential combustor of a gas turbine, the fuel lance having at least one finger extending in a longitudinal direction into the axial hot gas flow of the gas turbine essentially perpendicular to the hot gas flow. The finger is configured as a streamlined body which has a streamlined cross-sectional profile. The body has two lateral surfaces essentially parallel to the axial hot gas flow. The body includes an enclosing outer wall having a longitudinally extending air plenum for the distributed introduction of air into the at least one finger. The air plenum is provided with a plurality of distributed impingement cooling holes, such that air exiting through the impingement cooling holes impinges on the inner side of the leading edge region of the body.

公开(公告)号：US10753214B2

公开(公告)日：2020-08-25

申请号：US15649938

申请日：2017-07-14

Applicant: ANSALDO ENERGIA SWITZERLAND AG

Inventor： Jost Imfeld ,  Hans-Christian Mathews ,  Urs Benz

IPC: F01D9/02 ,  F01D11/00 ,  F16J15/00 ,  F01D3/04 ,  F01D11/06 ,  F23R3/60 ,  F02C7/18 ,  F02C7/20

Abstract: A gas turbine unit having a combustor having a liner, a turbine, arranged downstream of the liner along a main flow gas direction and including a plurality of first stage vanes, a rotor cover support located inwardly of the vanes, and a sealing arrangement at a combustor to turbine interface, wherein the sealing arrangement includes a first dogbone seal extending between the rotor cover support and an inner downstream end of the liner or between the rotor cover support and a bulkhead located at the inner downstream end of the liner.