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公开(公告)号：US08522557B2
公开(公告)日：2013-09-03
申请号：US12004399
申请日：2007-12-20
申请人： Robert W. Dawson , Roland Liebe
发明人： Robert W. Dawson , Roland Liebe
IPC分类号： F02C1/00
CPC分类号： F23R3/06 , F05B2260/20
摘要： The invention relates to a cooling channel for a component conveying hot gas for the purposes of conveying a coolant along a direction of flow with a downstream and an upstream side, with a plurality of inlet apertures for a coolant, with a number of inlet apertures that vary their configuration at least partly among themselves is arranged at least in one section of the cooling channel. As a result, the heat-transfer coefficient is substantially increased at points particularly requiring cooling and therefore the cooling is substantially improved. The cooling channel is characterized by a particularly low pressure loss. Furthermore, a combustion chamber with a cooling channel of this type is specified.
摘要翻译： 本发明涉及一种用于输送热气体的部件的冷却通道，用于沿着具有下游侧和上游侧的流动方向输送冷却剂，具有多个用于冷却剂的入口孔，多个入口孔 至少部分地在它们之间改变它们的构造至少布置在冷却通道的一个部分中。 结果，在特别需要冷却的点处，传热系数显着增加，因此冷却得到显着改善。 冷却通道的特征在于特别低的压力损失。 此外，具有这种类型的冷却通道的燃烧室。
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公开(公告)号：US20090272124A1
公开(公告)日：2009-11-05
申请号：US12004399
申请日：2007-12-20
申请人： Robert W. Dawson , Roland Liebe
发明人： Robert W. Dawson , Roland Liebe
CPC分类号： F23R3/06 , F05B2260/20
摘要： The invention relates to a cooling channel for a component conveying hot gas for the purposes of conveying a coolant along a direction of flow with a dowrnstream and an upstream side, with a plurality of inlet apertures for a coolant, with a number of inlet apertures that vary their configuration at least partly among themselves is arranged at least in one section of the cooling channel. As a result, the heat-transfer coefficient is substantially increased at points particularly requiring cooling and therefore the cooling is substantially improved. The cooling channel is characterized by a particularly low pressure loss. Furthermore, a combustion chamber with a cooling channel of this type is specified
摘要翻译： 本发明涉及一种用于输送热气体的部件的冷却通道，用于沿着具有下游和上游侧的流动方向输送冷却剂，具有多个用于冷却剂的入口孔，多个入口孔具有多个入口孔， 至少部分地在它们之间改变它们的构造至少布置在冷却通道的一个部分中。 结果，在特别需要冷却的点处，传热系数显着增加，因此冷却得到显着改善。 冷却通道的特征在于特别低的压力损失。 此外，具有这种类型的冷却通道的燃烧室
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3.发明授权Gas turbine engine transitions comprising closed cooled transition cooling channels 有权燃气轮机发动机转换包括封闭冷却的过渡冷却通道公开(公告)号：US07827801B2
公开(公告)日：2010-11-09
申请号：US11350562
申请日：2006-02-09
IPC分类号： F02C1/00
CPC分类号： F23R3/04 , F01D9/023 , F01D25/12 , F05D2260/205
摘要： A transition (200) for a gas turbine engine (100) comprises a transition wall (201) comprising cooling channels (213L, 213R, 223L, 223R) that are adapted to pass a cooling fluid, such as compressed air from a compressor (102) during operation of the gas turbine engine (100) so as to cool combusted hot gases passing through the transition (200). For each cooling channel (213L, 213R, 223L, 223R), respective entry ports (212L, 212L, 222L, 222R) and exit ports (214L, 214R, 224L, 224R) are arranged so as to obtain a performance improvement based upon pressure differentials between the respective entry and exit ports. In various embodiments, a scoop (220) is associated with an entry port (222L, 222R) so as to establish a more elevated pressure differential in the respective cooling channel (223L, 223R). An entry port (330a-h) may be positioned offset relative to a lower-positioned exit port (340a-h) so as to so minimize or eliminate intake of heated airflow from a respective nearby exit port (340a-h). Such offset positioning may be based on the airflow paths and cooling requirements at selected high-temperature operating conditions.
摘要翻译： 用于燃气涡轮发动机（100）的过渡（200）包括过渡壁（201），其包括冷却通道（213L，213R，223L，223R），其适于使冷却流体例如来自压缩机（102）的压缩空气 ）在燃气涡轮发动机（100）的操作期间，以便冷却通过过渡（200）的燃烧的热气体。 对于每个冷却通道（213L，213R，223L，223R），设置各个入口（212L，212L，222L，222R）和出口（214L，214R，224L，224R），以便基于压力获得性能改进 相应入口和出口之间的差异。 在各种实施例中，勺子（220）与入口端口（222L，222R）相关联，以便在相应的冷却通道（223L，223R）中建立更高的压力差。 入口端口（330a-h）可以相对于下定位的出口（340a-h）定位成偏移，以便使相应的邻近出口（340a-h）的加热气流的吸入最小化或消除。 这种偏移定位可以基于所选择的高温操作条件下的气流路径和冷却要求。
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4.发明授权公开(公告)号：US07600370B2
公开(公告)日：2009-10-13
申请号：US11440820
申请日：2006-05-25
申请人： Robert W. Dawson
发明人： Robert W. Dawson
CPC分类号： F01D9/023 , F02C7/12 , F05D2240/12 , F23R3/26
摘要： A plenum (210) in a gas turbine engine mid-frame section (200) comprises one or more annular flow splitters (240) spaced from an inboard annular wall (232) that partition air flow flowing from a compressor into two or more portions of flow having different vectors. This provides for an improved balancing between supplying air to compression chamber intakes more directly and to transitions to aid in convective cooling. When an annular diffuser (202) is spaced between the compressor and the plenum (210), the flow splitters (240) may provide an additional diffusion action. When no annular diffuser is so provided, the flow splitters (452, 454, 456) are effective to diffuse the air flow. Embodiments include those in which an annular diffuser (304) is relatively shorter and there is a longer axial expanse in the plenum (320) for flow splitters (350, 352, 354, 356).
摘要翻译： 燃气涡轮发动机中框架部分（200）中的集气室（210）包括与内侧环形壁（232）间隔开的一个或多个环形分流器（240），其将从压缩机流动的空气流分隔成两个或更多个部分 流量有不同的向量。 这提供了更直接地将空气供应到压缩室入口并且转变以帮助对流冷却的改进的平衡。 当环形扩散器（202）在压缩机和增压室（210）之间间隔开时，分流器（240）可以提供额外的扩散作用。 当没有设置环形扩散器时，分流器（452,454,456）有效地扩散空气流。 实施例包括其中环形扩散器（304）相对更短并且在用于分流器（350,352,354,356）的增压室（320）中具有较长轴向膨胀的实施例。
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5.发明申请公开(公告)号：US20120015311A1
公开(公告)日：2012-01-19
申请号：US12835960
申请日：2010-07-14
CPC分类号： F23R3/343 , F23C9/006 , F23C2202/40 , F23N1/002 , F23N2037/02 , F23R3/28 , F23R3/346 , F23R2900/00013 , F23R2900/00015 , F23R2900/03282
摘要： A burner for a gas combustor and a method of operating the burner are disclosed. The burner includes a front surface area divided into a plurality of subareas and inlets arranged on the front surface area such that each subarea is encircled by at least four inlets and such that during operation of the burner, a gas recirculation in the combustor is facilitated corresponding to each subarea.
摘要翻译： 公开了一种用于气体燃烧器的燃烧器和操作燃烧器的方法。 燃烧器包括被分成多个分区和前排表面区域的入口的前表面区域，使得每个子区域被至少四个入口环绕，并且使得在燃烧器的操作期间燃烧器中的气体再循环对应于 到每个分区。
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6.发明授权Transition support system for combustion transition ducts for turbine engines 有权用于涡轮发动机燃烧过渡管道的过渡支撑系统公开(公告)号：US08001787B2
公开(公告)日：2011-08-23
申请号：US11711823
申请日：2007-02-27
CPC分类号： F01D9/023 , F01D11/005 , F01D25/12 , F02C7/28
摘要： A transition duct support system for a transition duct that channels hot gases from a combustor exit to a gas turbine inlet of a turbine engine. The transition duct support system includes a transition support frame formed from a body positioned around a transition duct body at an outlet transition section. The transition support frame may include a first inner surface aligned with and positioned proximate to portion of the outlet transition section that is positioned at an oblique angle relative to the outer wall of the transition duct body to limit linear movement of the transition duct body in a first direction. The transition support frame may also include a second inner surface positioned at an oblique angle to limit linear movement of the transition duct body in a second direction opposite the first direction.
摘要翻译： 用于过渡管道的过渡管道支撑系统，其将来自燃烧器出口的热气体引导到涡轮发动机的燃气涡轮机入口。 过渡管道支撑系统包括过渡支撑框架，该过渡支撑框架由位于出口过渡部分处的过渡管道主体周围的主体形成。 过渡支撑框架可以包括与出口过渡部分的一部分对准并定位成靠近过渡管体本体的外壁的倾斜角度的第一内表面，以限制过渡管体的线性移动 第一个方向 过渡支撑框架还可以包括以倾斜角度定位的第二内表面，以限制过渡管体在与第一方向相反的第二方向上的线性运动。
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公开(公告)号：US06244220B1
公开(公告)日：2001-06-12
申请号：US09317504
申请日：1999-05-24
申请人： Robert W. Dawson
发明人： Robert W. Dawson
IPC分类号： A01K3106
CPC分类号： A01K31/06
摘要： A bird cage (20) includes a centrally disposed bird receiving structure (30) and inwardly sloping sides (28) which in combination cause birds to face inward and thereby defecate away from the bird receiving structure. These features make the cleaning of the bird cage easier. In a preferred embodiment, the bird cage also includes a removable top portion (24) which is selectively connected to a bottom portion (22). Since the top portion can be removed from the bottom portion, cleaning of the bird cage is simplified. In a preferred embodiment, the bird cage does not include a conventional door.
摘要翻译： 鸟笼（20）包括集中设置的鸟类接收结构（30）和向内倾斜的侧面（28），其组合地使鸟类面向内部，从而使其远离鸟类接收结构排出。 这些功能使鸟笼的清洁更容易。 在优选实施例中，鸟笼还包括可选择地连接到底部部分（22）的可移除顶部部分（24）。 由于顶部可以从底部移除，所以可以简化鸟笼的清洁。 在优选实施例中，鸟笼不包括常规门。
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8.发明申请TRANSITION SUPPORT SYSTEM FOR COMBUSTION TRANSITION DUCTS FOR TURBINE ENGINES 审中-公开用于涡轮发动机燃烧过渡管的过渡支撑系统公开(公告)号：US20110192171A1
公开(公告)日：2011-08-11
申请号：US13087534
申请日：2011-04-15
IPC分类号： F02C7/20
CPC分类号： F01D9/023 , F01D11/005 , F01D25/12 , F02C7/28
摘要： A transition duct support system for a transition duct that channels hot gases from a combustor exit to a gas turbine inlet of a turbine engine. The transition duct support system includes a transition support frame formed from a body positioned around a transition duct body at an outlet transition section. The transition support frame may include a first inner surface aligned with and positioned proximate to portion of the outlet transition section that is positioned at an oblique angle relative to the outer wall of the transition duct body to limit linear movement of the transition duct body in a first direction. The transition support frame may also include a second inner surface positioned at an oblique angle to limit linear movement of the transition duct body in a second direction opposite the first direction.
摘要翻译： 用于过渡管道的过渡管道支撑系统，其将来自燃烧器出口的热气体引导到涡轮发动机的燃气涡轮机入口。 过渡管道支撑系统包括过渡支撑框架，该过渡支撑框架由位于出口过渡部分处的过渡管道主体周围的主体形成。 过渡支撑框架可以包括与出口过渡部分的一部分对准并定位成靠近过渡管体本体的外壁的倾斜角度的第一内表面，以限制过渡管体的线性移动 第一个方向 过渡支撑框架还可以包括以倾斜角度定位的第二内表面，以限制过渡管体在与第一方向相反的第二方向上的线性运动。
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公开(公告)号：US07886517B2
公开(公告)日：2011-02-15
申请号：US11801306
申请日：2007-05-09
CPC分类号： F01D9/023 , F05D2260/201 , F23R3/002 , F23R2900/03044
摘要： Embodiments of a transition (400) of the present invention comprise a cooling channel (20, 30, 410) defined in part by an outer wall (23) and an inner wall (24). The cooling channel (20, 30, 410) also comprises lateral side walls (33, 34). Two or more subdomains (AA, BB, A, B1, B2, C1, C2, D) of impingement jets (25, 35) are provided through the outer wall (23), and one or more metering outlets (26, 36, 37, 38) is provided through the inner wall (24), all communicating with a respective channel (20, 30, 410). The impingement jets of each respective subdomain are designed to supply cooling fluid to one of the one or more metering outlets. Further to the impingement jets (25, 35) their size, shape, spacing, and arrangement with regard to the metering outlet (26, 36, 37, 38) are such that a desired cooling of the inner wall (24) is provided during normal gas turbine operations through advantageous impingement cooling at points along the surface of the inner wall (24) that defines the cooling channel (20, 30, 410).
摘要翻译： 本发明的过渡（400）的实施例包括部分由外壁（23）和内壁（24）限定的冷却通道（20,30,410）。 冷却通道（20,30,410）还包括横向侧壁（33,34）。 冲击射流（25,35）的两个或多个子域（AA，BB，A，B1，B2，C1，C2，D）通过外壁（23）提供，并且一个或多个计量出口（26,36， 37,38）通过内壁（24）设置，全部与相应的通道（20,30,410）连通。 每个子域的冲击射流被设计成将冷却流体供应到一个或多个计量出口中的一个。 除了冲击射流（25,35）之外，它们相对于计量出口（26,36,37,38）的尺寸，形状，间距和布置使得在内壁（24）期间的期望的冷却是在 正常的燃气轮机操作通过在限定冷却通道（20,30,410）的内壁（24）的表面的点处的有利冲击冷却。
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公开(公告)号：US07810334B2
公开(公告)日：2010-10-12
申请号：US11581164
申请日：2006-10-13
申请人： Johan Hsu , Andrew G. McQuiggan , Robert W. Dawson
发明人： Johan Hsu , Andrew G. McQuiggan , Robert W. Dawson
CPC分类号： F01D9/023 , F05D2250/74
摘要： A transition duct having an inlet opening and an outlet opening and a body portion extending between the inlet and outlet openings at respective inlet and outlet ends. The inlet opening defines a generally circular cross-section for the body portion and has a geometric center, and the outlet opening defines a generally rectangular arc-like cross-section. The body portion has an internal profile substantially in accordance with coordinate values X, Y and Z at an angle θ, as set forth in Table 1, where each of the X, Y and Z coordinate values are taken at a sweep angle θ passing through the section origin and measured from a first plane defined by the inlet end and increasing toward a second plane defined by the outlet end.
摘要翻译： 一个具有入口和出口的过渡管道以及在相应入口和出口端处在入口和出口之间延伸的主体部分。 入口开口限定了用于主体部分的大致圆形的横截面并且具有几何中心，并且出口开口限定了大致矩形的弧形横截面。 如图1所示，主体部分具有基本上按照角度θ的坐标值X，Y和Z的内部轮廓，其中X，Y和Z坐标值中的每一个以扫掠角度＆amp; 穿过截面原点并从由入口端限定的第一平面测量并且朝向由出口端限定的第二平面增加。
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