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公开(公告)号：US06892543B2
公开(公告)日：2005-05-17
申请号：US10436272
申请日：2003-05-13
申请人： Tomoyoshi Nakae
发明人： Tomoyoshi Nakae
CPC分类号： F23R3/06 , F23R3/14 , F23R3/26 , Y02T50/675
摘要： A gas turbine combustor that controls flow rate of air flowing into a primary combustion zone for controlling a local fuel-air ratio comprises no sliding portion that is liable to cause sticking or biting of components operating in high temperature, thereby providing a simple, reliable and efficient combustor and a combustion control method thereof. The gas turbine combustor comprising a liner provided in a combustor case and a bypass duct provided in the liner and enabling a control of flow rate of air supplied into a primary combustion zone via a swirler by causing a portion of the air to pass through the bypass duct, further comprises a float, made of a magnetic substance, provided in the bypass duct so as to open and close the bypass duct by the position of movement of the float and an electromagnetic coil provided outside of the combustor case corresponding to the position of the float so as to move the float.
摘要翻译： 控制流入主燃烧区域的空气流量用于控制局部燃料空气比的燃气轮机燃烧器不包括易于引起在高温下运行的部件的粘着或咬合的滑动部分，从而提供简单，可靠和可靠的 高效燃烧器及其燃烧控制方法。 燃气轮机燃烧器包括设置在燃烧器壳体中的衬套和设置在衬套中的旁路管道，并且能够通过使一部分空气通过旁路来控制通过旋流器供应到主燃烧区域的空气的流量 管道，还包括设置在旁路管道中的由磁性体制成的浮子，以便通过浮子的运动位置和设置在燃烧器壳体外部的电磁线圈来打开和关闭旁路管道，该电磁线圈对应于位于 浮动以移动浮子。
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2.发明申请Heat exchanging wall, gas turbine using the same, and flying body with gas turbine engine 有权换热墙，采用相同的燃气轮机，带燃气轮机的飞机公开(公告)号：US20050047932A1
公开(公告)日：2005-03-03
申请号：US10912565
申请日：2004-08-06
CPC分类号： F23R3/002 , F23R3/005 , F23R2900/03043 , F28F3/02 , F28F3/022 , F28F13/12 , Y02T50/675
摘要： A heat exchange wall include a base plate; a plurality of first protrusions distributedly provided on a surface of the base plate, and a plurality of second protrusions distributedly provided on the base plate surface. The height of the second protrusion in a normal direction of the base plate is desirably less than ½ of a height of the first protrusion in the normal direction. The height of the second protrusion in the normal direction is desirably between {fraction (1/20)} and ¼ of the height of the first protrusion in the normal direction. More desirably, the height of the second protrusion in the normal direction is {fraction (1/10)} of the height of the first protrusion in the normal direction.
摘要翻译： 热交换壁包括基板; 多个第一突起分布设置在基板的表面上，多个第二突起分布设置在基板表面上。 第二突起在基板的法线方向上的高度优选小于第一突起在法线方向的高度的1/2。 第二突起在法线方向的高度优选为{法线方向的第一突起的高度的1/20〜1/4，更优选地，第二突起在法线方向的高度为{分数（ 第一突起在正常方向的高度的1/10。
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3.发明授权Heat exchanging wall, gas turbine using the same, and flying body with gas turbine engine 有权换热墙，采用相同的燃气轮机，带燃气轮机的飞机公开(公告)号：US07694522B2
公开(公告)日：2010-04-13
申请号：US10912565
申请日：2004-08-06
CPC分类号： F23R3/002 , F23R3/005 , F23R2900/03043 , F28F3/02 , F28F3/022 , F28F13/12 , Y02T50/675
摘要： A heat exchange wall include a base plate; a plurality of first protrusions distributedly provided on a surface of the base plate, and a plurality of second protrusions distributedly provided on the base plate surface. The height of the second protrusion in a normal direction of the base plate is desirably less than ½ of a height of the first protrusion in the normal direction. The height of the second protrusion in the normal direction is desirably between 1/20 and ¼ of the height of the first protrusion in the normal direction. More desirably, the height of the second protrusion in the normal direction is 1/10 of the height of the first protrusion in the normal direction.
摘要翻译： 热交换壁包括基板; 多个第一突起分布设置在基板的表面上，多个第二突起分布设置在基板表面上。 第二突起在基板的法线方向上的高度优选小于第一突起在法线方向的高度的1/2。 第二突起在法线方向的高度优选为第一突起的高度在正常方向的1/20和1/4之间。 更优选地，第二突起在法线方向上的高度是第一突起在法线方向上的高度的1/10。
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4.发明授权System and method for controlling combustion in gas turbine with annular combustor 有权用于控制带有环形燃烧器的燃气轮机燃烧的系统和方法公开(公告)号：US07024862B2
公开(公告)日：2006-04-11
申请号：US10448452
申请日：2003-05-30
申请人： Yoshiaki Miyake , Tomoyoshi Nakae
发明人： Yoshiaki Miyake , Tomoyoshi Nakae
IPC分类号： F02C9/00
CPC分类号： F23N5/203 , F23N1/022 , F23N5/003 , F23N2025/10 , F23N2900/05003 , F23R3/26 , F23R3/50 , Y02T50/677
摘要： A gas turbine system composed of a gas turbine engine and a controller. The gas turbine engine includes an annular combustor, and a turbine driven by combustion gas from the annular combustor to rotate on a longitudinal centerline axis of the gas turbine engine. The annular combustor is comprised of an outer casing, a liner disposed in the outer casing, and a plurality of dilution air regulators introducing dilution air into the liner. The plurality of dilution air regulators are circumscribed about the longitudinal centerline axis and spaced apart at substantially equal intervals. The controller controls the plurality of dilution air regulators to individually adjust dilution air flows through the plurality of dilution air regulators into the liner.
摘要翻译： 一种由燃气涡轮发动机和控制器组成的燃气轮机系统。 燃气涡轮发动机包括环形燃烧器和由来自环形燃烧器的燃烧气体驱动的涡轮机，以在燃气涡轮发动机的纵向中心线轴线上旋转。 环形燃烧器由外壳，设置在外壳中的衬套和多个稀释空气调节器构成，所述稀释空气调节器将稀释空气引入到衬套中。 多个稀释空气调节器围绕纵向中心线轴线被间隔开并以基本相等的间隔间隔开。 控制器控制多个稀释空气调节器以单独调节通过多个稀释空气调节器进入衬管的稀释空气流。
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公开(公告)号：US5918459A
公开(公告)日：1999-07-06
申请号：US917466
申请日：1997-08-26
申请人： Tomoyoshi Nakae
发明人： Tomoyoshi Nakae
CPC分类号： F23R3/26 , F05B2250/41
摘要： An annular type gas turbine combustor which can regulate air flow distribution without being influenced by high temperature flames and with a desired fuel-air ratio for reducing the generation of NO.sub.x etc. A slide duct (10), for regulating air flow distribution, is disposed slidably in an axial direction at a terminal end of a diffuser (1). And as the slide duct (10) is moved, air flow supplied downstream to a swirler (4) is regulated so as to obtain a desired fuel-air ratio.
摘要翻译： 一种可以调节空气流量分布而不受高温火焰影响并具有用于减少NOx的产生的期望的燃料空气比的环形燃气轮机燃烧器。设置用于调节气流分布的滑动管道（10） 在扩散器（1）的末端可滑动地沿轴向滑动。 并且当滑动导管（10）移动时，供应到旋流器（4）下游的空气流被调节以获得期望的燃料 - 空气比。
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