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公开(公告)号：US08959928B2
公开(公告)日：2015-02-24
申请号：US13452152
申请日：2012-04-20
CPC分类号： F02C7/20 , F01D25/24 , Y10T29/49229 , Y10T403/18
摘要： The positioning arrangement comprises at least one pair of complimentary rounded recesses, each recess being provided on the mating face of the corresponding component. One ball is positioned between each pair of complementary recesses.
摘要翻译： 定位装置包括至少一对互补的圆形凹槽，每个凹槽设置在相应部件的配合面上。 一个球位于每对互补凹槽之间。
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公开(公告)号：US20120227415A1
公开(公告)日：2012-09-13
申请号：US13452152
申请日：2012-04-20
IPC分类号： F02C7/20
CPC分类号： F02C7/20 , F01D25/24 , Y10T29/49229 , Y10T403/18
摘要： The positioning arrangement comprises at least one pair of complimentary rounded recesses, each recess being provided on the mating face of the corresponding component. One ball is positioned between each pair of complementary recesses.
摘要翻译： 定位装置包括至少一对互补的圆形凹槽，每个凹槽设置在相应部件的配合面上。 一个球位于每对互补凹槽之间。
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公开(公告)号：US20060218925A1
公开(公告)日：2006-10-05
申请号：US11095663
申请日：2005-04-01
申请人： Lev Prociw , Aleksandar Kojovic , Harris Shafique
发明人： Lev Prociw , Aleksandar Kojovic , Harris Shafique
IPC分类号： F02C7/22
CPC分类号： F23R3/283 , F02C7/222 , F23D11/107 , F23K5/06
摘要： A gas turbine engine internal fuel manifold has a plurality of airblast fuel nozzles in communication with an air source such that nozzle core air does not pass through the manifold.
摘要翻译： 燃气涡轮发动机内部燃料歧管具有与空气源连通的多个喷气燃料喷嘴，使得喷嘴芯空气不通过歧管。
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公开(公告)号：US09400104B2
公开(公告)日：2016-07-26
申请号：US13630439
申请日：2012-09-28
CPC分类号： F23D11/383 , F23D11/107 , F23D2900/00016 , F23R3/28 , F23R2900/00004
摘要： A fuel injector nozzle assembly includes a body extending along an axis and a core swirl plug positioned at least partially within the body. The core swirl plug has a flow modifying structure configured to swirl fuel at a location upstream from a distal end of the nozzle assembly.
摘要翻译： 燃料喷射器喷嘴组件包括沿着轴线延伸的主体和至少部分地位于主体内的核心旋塞。 核心涡旋塞具有流动改变结构，其构造成在喷嘴组件的远端上游的位置处使燃料旋转。
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公开(公告)号：US07533531B2
公开(公告)日：2009-05-19
申请号：US11095663
申请日：2005-04-01
CPC分类号： F23R3/283 , F02C7/222 , F23D11/107 , F23K5/06
摘要： A gas turbine engine internal fuel manifold assembly including an annular fuel distribution member defining at least one fuel flow passage therein, and a plurality of fuel nozzles having spray tips mounted to the fuel distribution member. the spray tips are in fuel flow communication with the fuel flow passage, and each fuel nozzle has at least one core airflow passage extending through a center thereof between the spray tip and an air inlet defined in the fuel nozzle.
摘要翻译： 一种燃气涡轮发动机内部燃料歧管组件，包括在其中限定至少一个燃料流动通道的环形燃料分配构件和具有安装到燃料分配构件上的喷雾尖端的多个燃料喷嘴。 喷嘴与燃料流路连通燃料流，每个燃料喷嘴具有至少一个核心气流通道，其延伸穿过喷嘴和燃料喷嘴中限定的空气入口之间的中心。
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公开(公告)号：US20080006641A1
公开(公告)日：2008-01-10
申请号：US11061608
申请日：2005-02-22
申请人： Lev Prociw , Aleksandar Kojovic
发明人： Lev Prociw , Aleksandar Kojovic
IPC分类号： F17C1/00
CPC分类号： F02C7/20 , F01D25/24 , Y10T29/49229 , Y10T403/18
摘要： The positioning arrangement comprises at least one pair of complimentary rounded recesses, each recess being provided on the mating face of the corresponding component. One ball is positioned between each pair of complementary recesses.
摘要翻译： 定位装置包括至少一对互补的圆形凹槽，每个凹槽设置在相应部件的配合面上。 一个球位于每对互补凹槽之间。
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公开(公告)号：US06745571B2
公开(公告)日：2004-06-08
申请号：US10421751
申请日：2003-04-24
IPC分类号： F23R306
CPC分类号： F23R3/005 , F02C7/08 , F05D2260/201 , F23R3/26 , F23R2900/00016 , F23R2900/03044
摘要： A method of combustor cycle air flow adjustment for a gas turbine engine according to the present invention solves the problem of a higher flame temperature in the combustor, thereby affecting the emission levels when a heat-recuperated air flow cycle is used to increase the compressed air temperature. In low emission combustors this impact is severe because emission levels are significantly dependent on the primary combustion zone flame temperature. The method of the present invention includes a step of changing a geometry of an air flow passage and thereby changing distribution of a total air mass flow between an air mass flow for combustion and an air mass flow for cooling in order to ensure that flame temperature in a primary combustion zone of a combustor are maintained substantially the same whether the gas turbine engine is manufactured to operate as a simple air flow cycle engine or as a heat-recuperated air flow cycle engine. In an embodiment of the present invention, the changing of the geometry of the air flow passage by changing the number and size of perforations in an impingement cooling skin so that with minimal changes the impingement cooling skin serves duel purposes both as a cooling device for cooling the combustor wall and as a valve means for combustor cycle air flow adjustment, which makes the method simple and economical.
摘要翻译： 根据本发明的用于燃气涡轮发动机的燃烧器循环空气流量调节方法解决了燃烧器中火焰温度较高的问题，从而当使用热回收空气流循环来增加压缩空气时影响排放水平 温度。 在低排放燃烧器中，这种影响是严重的，因为排放水平显着取决于主燃烧区火焰温度。 本发明的方法包括改变空气流路的几何形状，从而改变用于燃烧的空气质量流与冷却空气质量流之间的总空气质量流的分布，以确保火焰温度在 无论燃气涡轮发动机是否被制造成作为简单的气流循环发动机或作为热回收空气流循环发动机来操作，燃烧器的主燃烧区域保持基本相同。 在本发明的一个实施例中，通过改变冲击冷却皮肤中的穿孔的数量和尺寸来改变空气流动通道的几何形状，使得在最小变化的情况下，冲击冷却皮肤作为用于冷却的冷却装置的决斗 燃烧器壁和用于燃烧器循环空气流量调节的阀装置，这使得该方法简单和经济。
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公开(公告)号：US06536201B2
公开(公告)日：2003-03-25
申请号：US09733051
申请日：2000-12-11
申请人： Peter Stuttaford , Bernhard Fischer , David Edwin Cowburn , Saeid Oskooei , Michael Andrew Fryer , Aleksandar Kojovic , Jeffrey Scott Acton
发明人： Peter Stuttaford , Bernhard Fischer , David Edwin Cowburn , Saeid Oskooei , Michael Andrew Fryer , Aleksandar Kojovic , Jeffrey Scott Acton
IPC分类号： F02G0300
CPC分类号： F23R3/005 , F01D5/00 , F01D25/26 , F02C7/18 , F05D2260/201 , F23R2900/03044
摘要： The present invention is directed to a combustor/turbine successive dual cooling arrangement in which the combustor has a one-piece hot combustor wall and front and rear cold combustor walls, and cooling air is forced under pressure through perforations in the cold combustor walls and impinges on the annular front and rear sections of the hot combustor wall for the backside cooling of the hot combustor wall. The exhaust combustor backside cooling air is directed to gain access to the hot end of the engine, that is, the turbine section, to cool the turbine components. The combustor/turbine successive dual cooling arrangement according to the present invention enables all the air typically used to cool the hot end of the engine downstream of the combustor, to be used as combustor backside cooling as well, to significantly reduce the amount of air needed for combustor and turbine cooling. Moreover, all the exhaust combustor backside cooling air must be used for turbine cooling and is never ingested into the combustion chamber, thereby avoiding negatively affecting the engine combustion emissions.
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公开(公告)号：US07805948B2
公开(公告)日：2010-10-05
申请号：US11300477
申请日：2005-12-15
IPC分类号： F02C7/20
摘要： An assembly for sealingly mounting a device in a hole in a pressure vessel casing, the assembly transferring a load produced by pressurized fluid to the casing and retaining the stem to the casing.
摘要翻译： 一种用于将装置密封地安装在压力容器壳体中的孔中的组件，该组件将由加压流体产生的负载传递到壳体并将杆保持在壳体上。
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公开(公告)号：US07712313B2
公开(公告)日：2010-05-11
申请号：US11843236
申请日：2007-08-22
IPC分类号： F02C1/00
CPC分类号： F02C7/222
摘要： In the fuel nozzle, the fuel is circulated in a helical path around the interface of a stem of the fuel nozzle and a flange for increase the cooling.
摘要翻译： 在燃料喷嘴中，燃料以围绕燃料喷嘴的杆的界面的螺旋路径和用于增加冷却的凸缘循环。
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