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公开(公告)号：US20220349581A1
公开(公告)日：2022-11-03
申请号：US17860990
申请日：2022-07-08
摘要： In some embodiments, systems, apparatuses and methods are provided herein useful for spraying fuel in an augmented gas turbine engine. The embodiments may include a spray bar with a fuel injection aperture configured to inject a fuel jet into a fuel conduit; the fuel conduit having a fuel window to discharge the fuel jet into a core exhaust flow of an augmented gas turbine engine; a first channel directing a first air stream into the fuel conduit; and a second channel directing a second air stream into the fuel conduit. The first air stream and the second air stream cooperatively shape the fuel jet coming out of the fuel window.
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公开(公告)号：US11408610B1
公开(公告)日：2022-08-09
申请号：US17166477
申请日：2021-02-03
摘要： In some embodiments, systems, apparatuses and methods are provided herein useful for spraying fuel in an augmented gas turbine engine. The embodiments may include a spray bar with a fuel injection aperture to inject a fuel jet into a fuel conduit; the fuel conduit having a fuel window to discharge the fuel jet into a core exhaust flow of an augmented gas turbine engine; a first airflow conduit having a first orifice to discharge a first air stream into the core exhaust flow; and a second airflow conduit having a second orifice to discharge a second air stream into the core exhaust flow. The first orifice and the second orifice may be paired with the fuel window to cooperatively shape the fuel jet coming out of the fuel window.
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公开(公告)号：US11156156B2
公开(公告)日：2021-10-26
申请号：US16151728
申请日：2018-10-04
发明人： Lawrence Binek , Jesse R. Boyer , Om P. Sharma , Evan Butcher , Bryan G. Dods , Vijay Narayan Jagdale
摘要： A gas turbine engine is provided that includes a compressor section, a turbine section, and a unitary structure. The compressor section has at least one compressor rotor stage. The turbine section has at least one turbine rotor stage. The compressor rotor stage and the turbine rotor stage are in rotational communication with each other. The unitary structure includes an outer case portion, a combustor section, a turbine nozzle, and an exhaust duct. The unitary structure configured for attachment with the turbine section and compressor section.
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公开(公告)号：US10436117B2
公开(公告)日：2019-10-08
申请号：US14083040
申请日：2013-11-18
摘要： A fuel injection system for a gas turbine engine includes a vane in an airflow path within the gas turbine engine, the vane includes an air channel with an outlet in communication with the airflow path; and a fuel nozzle within the vane operable to inject fuel into the air channel to at least partially premix and prevaporize the fuel with a secondary airflow from within the vane in the air channel prior to entry into the airflow path through the outlet. A method of injecting fuel within a gas turbine engine includes at least partially premixing and prevaporizing fuel with a secondary airflow from within a vane in an air channel within the vane, the vane within an airflow path of the gas turbine engine.
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公开(公告)号：US10386073B2
公开(公告)日：2019-08-20
申请号：US15446451
申请日：2017-03-01
发明人： Andrea Ciani , John Philip Wood , Douglas Anthony Pennell , Ewald Freitag , Urs Benz , Andre Theuer
IPC分类号： F23R3/16 , F23R3/20 , F23R3/28 , F02C9/32 , F02C9/34 , F02C9/26 , F23R3/46 , F23R3/34 , F23R3/36 , F02C6/00
摘要： 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.
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公开(公告)号：US10371385B2
公开(公告)日：2019-08-06
申请号：US14955560
申请日：2015-12-01
发明人： Urs Benz , Andrea Ciani
摘要： A sequential burner for an axial gas turbine comprises: a burner body, which is designed as an axially extending hot gas channel and further comprises a fuel injection device, which extends into said burner body perpendicular to the axial direction. The manufacturing of the burner body is simplified and the fuel injection is stabilized by designing said fuel injection device as a mechanically stiff component, and fixing said fuel injection device to said burner body in order to keep it aligned with said burner body and to stiffen said burner body against creep.
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公开(公告)号：US10371057B2
公开(公告)日：2019-08-06
申请号：US15084177
申请日：2016-03-29
发明人： Kaspar Loeffel , Andre Theuer , Nico Biagioli , Alexey Stytsenko , Sergey Mylnikov , Igor Baibuzenko
摘要： Disclosed is a fuel injector device having a body with a leading edge and a trailing edge and defining a streamwise direction from the leading edge to the trailing edge, the fuel injector device body having a first wall and a second wall opposite the first wall, each wall extending between and including the leading edge and the trailing edge and the walls conjoining each other at the leading edge and the trailing edge, each wall having a streamwise extent and a crosswise extent, the walls further enclosing an internal space, at least one fluid plenum being provided within the internal space, the fluid plenum at least at one of an upstream end and/or a downstream end being delimited by an internal wall structure, wherein at least one surface of the wall structure is an inclined surface which forms an angle with the streamwise direction which is smaller than or equal to a maximum angle, wherein the maximum angle is 60°.
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公开(公告)号：US10337341B2
公开(公告)日：2019-07-02
申请号：US15292835
申请日：2016-10-13
发明人： Javier N. Johnson , Chris Bates , Eric Beach , Jorge I. Farah , Caleb N. Cross
摘要： An augmentor vane assembly includes an additively manufactured augmentor vane and a fuel line additively manufactured within the augmentor vane. A method of manufacture including additively manufacturing an augmentor vane having a wall that forms an internal volume therein; and additively manufacturing a fuel line within the augmentor vane that extends through the internal volume.
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公开(公告)号：US20180363905A1
公开(公告)日：2018-12-20
申请号：US16062066
申请日：2017-01-11
摘要： A fuel nozzle assembly includes a center body comprising an outer sleeve and an internal fuel passage defined within the outer sleeve. The internal fuel passage defines a fuel flow path within the center body and includes an inlet defined at an upstream end of the center body. The inlet is formed to receive fuel from a fuel supply. The fuel nozzle assembly also includes a plurality of vanes that extend radially outwardly from the outer sleeve and at least one of the vanes includes at least one fuel port that is in fluid communication with the internal fuel passage. At least one baffle extends radially into the internal fuel passage downstream from the inlet and upstream from the at least one fuel port such that the at least one baffle reduces fuel flow area within the fuel flow path upstream from the at least one fuel port.
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公开(公告)号：US10107501B2
公开(公告)日：2018-10-23
申请号：US14777685
申请日：2014-03-19
IPC分类号： F23R3/54 , F23R3/14 , F23R3/06 , F23R3/28 , F23C9/00 , F23M20/00 , F23R3/34 , F23R3/44 , F02C3/04 , F02C3/14 , F02C7/18 , F02C7/24 , F23R3/20 , F23R3/24
摘要： An object is to realize combustion flame which can further reduce the amount of NOx generation. A combustor (14) includes a pilot nozzle (40); a plurality of main nozzles (44) arranged apart from the pilot nozzle (40) in the circumferential direction on the outer peripheral side of the pilot nozzle (40) and configured to perform premix combustion; a combustor basket (34) surrounding the pilot nozzle (40) and each main nozzle (44); an outlet outer ring (50) provided at a tip end of the combustor basket (34); and a combustion liner (36) fitted, at an inner surface thereof, onto the outer periphery of the combustor basket (34) and surrounding the outlet outer ring (50). The outlet outer ring (50) is formed parallel to an inner wall surface (66) of the combustion liner (36).
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