公开(公告)号：US10174637B2

公开(公告)日：2019-01-08

申请号：US14835991

申请日：2015-08-26

Applicant: ANSALDO ENERGIA SWITZERLAND AG

Inventor： Jost Imfeld ,  Hans-Christian Mathews

IPC: F01D25/28

Abstract: The present invention concerning of a device for mounting or dismantling, replacement and maintenance of a can-combustor of a gas turbine engine including an assembly tool or assembly tool with additional frame having at least one lifting beam, at least one linear driver, wheels, at least one eccentric rolling hook for fixation of the gas turbine housing, optionally spacers for building the interface to the can-combustor, adapters, lifting points for the main crane. The eccentric rolling hook is connected to the gas turbine housing by giving in axial or quasi-axial direction a force for mounting or dismantling the can-combustor from the gas turbine housing.

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：US10851997B2

公开(公告)日：2020-12-01

申请号：US15725751

申请日：2017-10-05

Applicant: ANSALDO ENERGIA SWITZERLAND AG

Inventor： Jost Imfeld ,  Slawomir Swiatek ,  Oliver Konradt

IPC: F23R3/08 ,  F23C6/04 ,  F01D9/02 ,  F02C3/20 ,  F02C7/28 ,  F23R3/60

Abstract: A combustor device for a gas turbines engines includes first and a second tubular members telescopically fitted in axially sliding manner to one another with interposition of annular centering and sealing which include at least a centering annular shoulder and a sealing ring arranged coaxial to one another. The sealing ring is axially spaced apart from the centering annular shoulder so that an axial distance between the centering annular shoulder and the sealing ring is greater than a maximum axial movement allowed between the first and said second tubular members.

公开(公告)号：US10928068B2

公开(公告)日：2021-02-23

申请号：US15710096

申请日：2017-09-20

Applicant: ANSALDO ENERGIA SWITZERLAND AG

Inventor： Jost Imfeld ,  Paul Marlow

IPC: F23R3/00 ,  F23R3/16 ,  F23M20/00 ,  F23R3/50 ,  F02C3/04

Abstract: An annular Helmholtz damper for a gas turbine can combustor, the annular Helmholtz damper having an axis; an inner wall and an outer wall concentrically arranged with respect to the axis to define an annular damping volume arranged around a can combustor; a front and rear circumferential plates for closing the annular damping volume upstream and downstream; at least one intermediate circumferential plate arranged between the front and the rear plates for dividing the annular damping volume in a main and a secondary volume; and a plurality of intermediate drain holes passing the intermediate circumferential plate and configured for draining collected liquid from the main volume to the secondary volume.

公开(公告)号：US10393025B2

公开(公告)日：2019-08-27

申请号：US14851397

申请日：2015-09-11

Applicant: ANSALDO ENERGIA SWITZERLAND AG

Inventor： Wilhelm Reiter ,  Jost Imfeld ,  Marcos Escudero-Olano

IPC: F01D9/02 ,  F01D11/00 ,  F02C7/28 ,  F02C3/04 ,  F02C9/22 ,  F23R3/60

Abstract: A sealing arrangement is provided at the interface between a combustor and a turbine of a gas turbine. The turbine includes guiding vanes at its inlet. The guiding vanes are each mounted within the turbine at their outer diameter by means of rear outer diameter vane hook and are each at their inner diameter in sealing engagement by means of a front inner diameter vane tooth with a honeycomb seal arranged at the corresponding inner diameter part of the outlet of said combustor. The rear outer diameter vane hook allows a relative movement of the guiding vane in form of a rotation around the rear outer diameter vane hook. The sealing adapts the front inner diameter vane tooth and the corresponding honeycomb seal in their configuration to the rotating relative movement of the guiding vane, such that the compression of said honeycomb seal through transients of the gas turbine is reduced.

公开(公告)号：US10100688B2

公开(公告)日：2018-10-16

申请号：US15285887

申请日：2016-10-05

Applicant: ANSALDO ENERGIA SWITZERLAND AG

Inventor： Jost Imfeld ,  Roger Ernst ,  Laurent Fabien Laville

IPC: F01N1/02 ,  F23R3/42 ,  G10K11/16 ,  F23M20/00

Abstract: The present disclosure relates to gas turbines and to a damper assembly for a combustion chamber of a gas turbine. A damper assembly as disclosed herein may be adjusted to different frequencies during operation and/or deactivated for different operation regimes.

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：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.