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    Combustor arrangement for a gas turbine
    1.
    发明授权
    Combustor arrangement for a gas turbine 有权

    公开(公告)号：US10267525B2

    公开(公告)日：2019-04-23

    申请号：US14925527

    申请日：2015-10-28

    Applicant: ANSALDO ENERGIA SWITZERLAND AG

    Inventor： Douglas Anthony Pennell ,  Urs Benz ,  Adnan Eroglu ,  Ewald Freitag ,  Mirko Ruben Bothien ,  Andrea Ciani

    IPC: F23R3/06 ,  F23R3/34 ,  F23R3/36 ,  F23C6/04 ,  F23R3/28

    Abstract: A combustor arrangement for a gas turbine includes a first burner, a first combustion chamber, a mixer for admixing a dilution gas to the gases leaving the first combustion chamber during operation, a second burner, and a second combustion chamber arranged sequentially in a fluid flow connection. These elements of the combustor arrangement are arranged in a row to form a flow path extending between the first combustion chamber and the second burner. The combustor arrangement includes acentral lance body arranged inside the flow path and extending from the first burner through the first combustion chamber into the mixer and into the second burner, wherein the lance body includes a fuel duct for providing fuel for the first burner and/or for the second burner.

    Sequential combustion arrangement with dilution gas
    2.
    发明授权
    Sequential combustion arrangement with dilution gas 有权

    公开(公告)号：US10151487B2

    公开(公告)日：2018-12-11

    申请号：US14593032

    申请日：2015-01-09

    Applicant: ANSALDO ENERGIA SWITZERLAND AG

    Inventor： Michael Duesing ,  Ewald Freitag

    IPC: F23R3/34 ,  F02C3/30 ,  F23R3/04 ,  F23C6/04

    Abstract: The invention refers to a sequential combustor arrangement including a first combustor with a first burner for admitting a first fuel into a combustor inlet gas during operation and a first combustion chamber for burning the first fuel, a dilution gas admixer for admixing a dilution gas to the first combustor combustion products leaving the first combustion chamber, and a second burner for admixing a second fuel and a second combustion chamber. To assure good mixing over a wide operating range, the ratio of the pressure loss of the first combustor to the pressure loss of the dilution gas admixer is in the range of 1 to 6. The invention further refers to a gas turbine including such a sequential combustor arrangement as well as method for operating a gas turbine with such a sequential combustor arrangement.

    Gas turbine assembly and corresponding operating method
    3.
    发明授权
    Gas turbine assembly and corresponding operating method 有权

    公开(公告)号：US10774740B2

    公开(公告)日：2020-09-15

    申请号：US14048878

    申请日：2013-10-08

    Applicant: Ansaldo Energia Switzerland AG

    Inventor： Robert Marmilic ,  Jaan Hellat ,  Ewald Freitag ,  Adnan Eroglu

    IPC: F02C3/00 ,  F02C7/141 ,  F02C7/228 ,  F23R3/34

    Abstract: The invention relates to a gas turbine assembly which substantially includes at least one compressor, at least one first burner, at least one second burner that is connected downstream of the first burner, and at least one turbine that is connected downstream of the second burner. At least the first and second burner form a component of a tubular or quasi-tubular combustion chamber element in the flow direction of the combustion path of the burners. The combustion chamber element being closed or quasi-closed and extending between the compressor and the turbine. The combustion chamber elements are arranged around the rotor of the gas turbine assembly in the shape of a ring.

    Burner for a can combustor
    4.
    发明授权
    Burner for a can combustor 有权

    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.

    Burner for a combustion chamber of a gas turbine having a mixing and injection device
    5.
    发明授权
    Burner for a combustion chamber of a gas turbine having a mixing and injection device 有权

    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.

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