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公开(公告)号：EP3317585A1
公开(公告)日：2018-05-09
申请号：EP16738874.3
申请日：2016-06-30
发明人： MCNALLY, Joshua R. , PENNEL, Douglas , GAUTHIER, Donald , MATYS, Pawel , PASKIN, Marc , RUCK, Thomas R. , STUTTAFORD, Peter John , SAM, Bernard Tam-Yen , JORGENSEN, Stephen W.
摘要： Gas turbine combustion systems and fuel cartridge assemblies are provided. An exemplary combustion system may comprise a combustor including one or more components, such as a cylindrical combustion liner, a flow sleeve, a main mixer, a radial inflow swirler, a combustor dome, and a fuel cartridge assembly. An exemplary fuel cartridge assembly may comprise first and second fuel manifolds which are connected to respective fuel circuits which supply fuel, such as liquid fuel, through a plurality of fuel passages within the fuel cartridge assembly or to other locations within an associated combustor. The fuel cartridge assembly may further include a plurality of fuel injector tips located at a tip plate of the fuel cartridge assembly through which fuel may be supplied to an associated combustor.
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公开(公告)号：EP3221643A2
公开(公告)日：2017-09-27
申请号：EP15870609.3
申请日：2015-11-20
摘要： The present invention discloses a novel apparatus and way for reducing the recirculation zone at the inlet end of a combustor. The recirculation zone is reduced by altering the geometry of the inlet end through a tapering of the liner wall thickness and a tapering of the thermal barrier coating to reduce the bluff body effect at the combustion liner inlet end.
摘要翻译： 本发明公开了一种用于减少燃烧器入口端处的再循环区域的新颖设备和方法。 再循环区域通过改变入口端部的几何形状而减小，通过使衬里壁厚度逐渐变细并且使热障涂层变细以减小燃烧衬里入口端处的钝体效应。
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公开(公告)号：EP3317586B1
公开(公告)日：2020-11-04
申请号：EP16798552.2
申请日：2016-06-30
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公开(公告)号：EP3221643B1
公开(公告)日：2020-02-26
申请号：EP15870609.3
申请日：2015-11-20
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公开(公告)号：EP3317586A2
公开(公告)日：2018-05-09
申请号：EP16798552.2
申请日：2016-06-30
发明人： MCNALLY, Joshua R. , PENNEL, Douglas , GAUTHIER, Donald , MATYS, Pawel , PASKIN, Marc , RUCK, Thomas R. , STUTTAFORD, Peter John , SAM, Bernard Tam-Yen , JORGENSEN, Stephen W.
摘要： Systems and methods for dual-fuel operation of a gas turbine combustor are provided. An exemplary gas turbine combustor may comprise one or more components, such as a cylindrical combustion liner, a flow sleeve, a main mixer, a radial inflow swirler, a combustor dome, and a fuel cartridge assembly, one or more of which may be configured to supply either a gaseous or a liquid fuel to the combustion liner, depending on whether gaseous fuel operation or liquid fuel operation of the combustor is desired.
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6.发明公开AUTOMATED EXTENDED TURNDOWN OF A GAS TURBINE ENGINE COMBINED WITH INCREMENTAL TUNING TO MAINTAIN EMISSIONS AND DYNAMICS 审中-公开燃气涡轮发动机自动延长停机时间与增量调节组合以保持排放和动力
公开(公告)号：EP3250800A1
公开(公告)日：2017-12-06
申请号：EP16744269.8
申请日：2016-02-01
IPC分类号： F02C9/28
CPC分类号： F02C9/28 , F02C9/00 , F05D2260/80 , F05D2270/05
摘要： An auto-tune controller and tuning process implemented thereby for measuring and tuning the combustion dynamics and emissions of a GT engine, relative to predetermined upper limits, are provided. Initially, the tuning process includes monitoring the combustion dynamics of a plurality of combustors and emissions for a plurality of conditions. Upon determination that one or more of the conditions exceeds a predetermined upper limit, a fuel flow split to a fuel circuit on all of the combustors on the engine is adjusted by a predetermined amount. The control system continues to monitor the combustion dynamics and to recursively adjust the fuel flow split by the predetermined amount until the combustion dynamics and/or emissions are operating within a prescribed range of the GT engine. Additionally, a method of automated extended turndown of a GT engine to find a minimum load is provided.
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