Patents by Inventor Paul Marlow
Paul Marlow has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Combustor device for a gas turbine engine and gas turbine engine incorporating said combustor device
Patent number: 11009232Abstract: 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.Type: GrantFiled: September 5, 2017Date of Patent: May 18, 2021Assignee: ANSALDO ENERGIA SWITZERLAND AGInventors: Jost Imfeld, Paul Marlow, Oliver Konradt, Urs Benz -
Patent number: 10928068Abstract: 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.Type: GrantFiled: September 20, 2017Date of Patent: February 23, 2021Assignee: ANSALDO ENERGIA SWITZERLAND AGInventors: Jost Imfeld, Paul Marlow
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Patent number: 10787918Abstract: A gas turbine transition duct includes: an inner tubular body, defining a transition channel and having a first upstream end and a first downstream end for coupling to a can combustor and to a turbine section of a gas turbine assembly, respectively; an outer tubular body, arranged around the inner tubular body and having a second upstream end at the first upstream end of the inner tubular body and a second downstream end at the first downstream end of the inner tubular body; wherein a convective cooling channel is defined between the inner tubular body and the outer tubular body, the convective cooling channel having an inlet between the first downstream end and the second downstream end; and wherein the outer tubular body is continuous between the second upstream end and the second downstream end.Type: GrantFiled: August 18, 2017Date of Patent: September 29, 2020Assignee: ANSALDO ENERGIA SWITZERLAND AGInventors: Paul Marlow, Michael Maurer, Dalibor Vrbetic
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Patent number: 10167739Abstract: 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.Type: GrantFiled: January 21, 2016Date of Patent: January 1, 2019Assignee: ANSALDO ENERGIA SWITZERLAND AGInventors: Urs Benz, Paul Marlow, Jost Imfeld
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Publication number: 20180080652Abstract: 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.Type: ApplicationFiled: September 20, 2017Publication date: March 22, 2018Applicant: ANSALDO ENERGIA SWITZERLAND AGInventors: Jost IMFELD, Paul MARLOW
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COMBUSTOR DEVICE FOR A GAS TURBINE ENGINE AND GAS TURBINE ENGINE INCORPORATING SAID COMBUSTOR DEVICE
Publication number: 20180066848Abstract: 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.Type: ApplicationFiled: September 5, 2017Publication date: March 8, 2018Applicant: ANSALDO ENERGIA SWITZERLAND AGInventors: Jost IMFELD, Paul MARLOW, Oliver KONRADT, Urs BENZ -
Publication number: 20180051578Abstract: A gas turbine transition duct includes: an inner tubular body, defining a transition channel and having a first upstream end and a first downstream end for coupling to a can combustor and to a turbine section of a gas turbine assembly, respectively; an outer tubular body, arranged around the inner tubular body and having a second upstream end at the first upstream end of the inner tubular body and a second downstream end at the first downstream end of the inner tubular body; wherein a convective cooling channel is defined between the inner tubular body and the outer tubular body, the convective cooling channel having an inlet between the first downstream end and the second downstream end; and wherein the outer tubular body is continuous between the second upstream end and the second downstream end.Type: ApplicationFiled: August 18, 2017Publication date: February 22, 2018Applicant: ANSALDO ENERGIA SWITZERLAND AGInventors: Paul MARLOW, Michael MAURER, Dalibor VRBETIC
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Publication number: 20160215655Abstract: 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.Type: ApplicationFiled: January 21, 2016Publication date: July 28, 2016Applicant: General Electric Technology GmbHInventors: Urs BENZ, Paul MARLOW, Jost IMFELD
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Patent number: 9097119Abstract: A gas turbine is provided having a secondary combustion chamber and a first guide vane row of a low-pressure turbine, the row being arranged directly downstream of the chamber. The radially outer boundary of the secondary combustion chamber is formed by at least one outer wall segment, which is secured on at least one support element arranged radially outwardly. The flow path of the hot gases is bounded radially outwardly, in the region of the guide vane row, by an outer platform which is secured at least indirectly on at least one guide vane support. A substantially radially extending gap-shaped cavity having a width in the range of 1-25 mm in the axial direction in the inlet region is arranged between the wall segment and the outer platform. At least one step element, which reduces the width by at least 10% in at least one step, extending substantially perpendicularly to the direction of flow of the hot gas in the cavity, is arranged in the inlet region.Type: GrantFiled: November 4, 2012Date of Patent: August 4, 2015Assignee: ALSTOM TECHNOLOGY LTD.Inventors: Thomas Heinz-Schwarzmaier, Marc Widmer, Selma Zahirovic, Paul Marlow
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Patent number: 9074488Abstract: The invention refers to an arrangement for sealing an open cavity against hot gas entrainment. The open cavity is arranged between two axially adjacent stationary components limiting radially a hot gas path of a rotary flow machine, of which at least the downstream component carries at least one airfoil extending radially into said hot gas path. A multitude of air jets is directed into the open cavity such that hot gas flowing over the open cavity is prevented from penetrating into the open cavity completely. The invention has an arrangement of supply conduits for air jets which are directed into the open cavity with a jet momentum such that hot gas is induced not to enter the open cavity and forming at least one hot gas vortex close to the hot gas path within the open cavity and preventing hot gas from penetrating into the open cavity beyond the extension of the hot gas vortex.Type: GrantFiled: January 14, 2014Date of Patent: July 7, 2015Assignee: ALSTOM Technology LtdInventors: Paul Marlow, Selma Zahirovic, Robert Marmilic, Marc Widmer, Joerg Krückels
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Publication number: 20140197601Abstract: The invention refers to an arrangement for sealing an open cavity against hot gas entrainment. The open cavity is arranged between two axially adjacent stationary components limiting radially a hot gas path of a rotary flow machine, of which at least the downstream component carries at least one airfoil extending radially into said hot gas path. A multitude of air jets is directed into the open cavity such that hot gas flowing over the open cavity is prevented from penetrating into the open cavity completely. The invention has an arrangement of supply conduits for air jets which are directed into the open cavity with a jet momentum such that hot gas is induced not to enter the open cavity and forming at least one hot gas vortex close to the hot gas path within the open cavity and preventing hot gas from penetrating into the open cavity beyond the extension of the hot gas vortex.Type: ApplicationFiled: January 14, 2014Publication date: July 17, 2014Applicant: ALSTOM Technology LtdInventors: Paul MARLOW, Selma Zahirovic, Robert Marmilic, Marc Widmer, Joerg Krückels
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Patent number: 6038863Abstract: The burner arrangement for a gas turbine comprises at least one burner (2), which is arranged in the plenum of the gas turbine and leads with an inner injection space into a combustion chamber and to which compressed air is admitted on the outside from a compressor stage of the gas turbine. Furthermore, a fuel lance (9) for the alternative feeding of liquid and/or gaseous fuels is allocated to the burner (2), which fuel lance (9) has a central liquid-fuel tube (19) and a pilot gas tube (11) concentrically surrounding the liquid-fuel tube (19), the tubes (11, 19) ending in associated outlet openings (22, 23, 23a-c) in a lance head (12) at the tip of the fuel lance (9).Type: GrantFiled: December 3, 1997Date of Patent: March 21, 2000Assignee: Asea Brown Boveri AGInventors: Jakob Keller, Paul Marlow, Robin McMillan, Martin Valk
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Patent number: 5505588Abstract: A compressor for a gas turbine includes a gas seal chamber to seal the space between the guide vanes and the rotor vanes from ambient air. A seal casing is positioned at a radially inner side of the inlet casing adjacent to an inlet duct and the rotor blades with an annular gap between the seal casing and the rotor shaft. The annular gap communicates for air flow with the inlet duct. A plurality of ribs are mounted on the one or both of the seal casing and rotor shaft to extend into the annular gap to provide flow resistance. The seal casing defines therewithin a sealing air chamber is connected to the inlet space and the annular gap to permit air from the inlet space to flow to the annular gap and to the inlet duct.Type: GrantFiled: September 27, 1994Date of Patent: April 9, 1996Assignee: ABB Management AGInventors: Eduard Bruhwiler, Paul Marlow