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公开(公告)号：US6098407A
公开(公告)日：2000-08-08
申请号：US93371
申请日：1998-06-08
CPC分类号： F23C7/002 , F23D14/02 , F23D14/22 , F23C2900/07002 , F23D2206/10 , F23D2211/00
摘要： A premixing, tangential entry fuel injector (10) for a gas turbine engine features a secondary fuel-air injection insert (40) positively secured to a centerbody shell (38) by a braze joint (98). A secondary fuel supply tube (42), positively secured to both a centerbody base (36) and to the insert (40), is curved in at least two dimensions. In an exemplary embodiment, the tube is coiled into a spiral shape covering a single 360.degree. cycle. During engine operation, the centerbody expands axially in response to elevated temperatures in the engine's interior, causing the insert (40) to be displaced away from the base (36). The curvature of the tube allows the tube to flex slightly to accommodate the displacement. Ideally the curvature of the tube is such that the tube's natural frequency is well above the maximum vibratory frequency that the tube will experience during engine operation.
摘要翻译： 用于燃气涡轮发动机的预混合切向进入燃料喷射器（10）具有通过钎焊接头（98）主动固定到中心壳体（38）的二次燃料 - 空气注入插入件（40）。 固定在中心体基座（36）和插入件（40）两者上的辅助燃料供给管（42）至少在两个维度上弯曲。 在示例性实施例中，管被卷绕成覆盖单个360度循环的螺旋形状。 在发动机运转期间，中心体响应于发动机内部的升高的温度而轴向膨胀，导致插入件（40）远离基座（36）移动。 管的曲率允许管轻微弯曲以适应位移。 理想地，管的曲率使得管的固有频率远高于管在引擎操作期间将经历的最大振动频率。
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公开(公告)号：US07363763B2
公开(公告)日：2008-04-29
申请号：US10691790
申请日：2003-10-23
IPC分类号： F23R3/42
CPC分类号： F23R3/42 , F23R3/002 , F23R2900/03042 , F23R2900/03044 , Y02T50/675
摘要： A gas turbine engine combustor has forward bulkhead extending between inboard and outboard walls and cooperating therewith to define a combustor interior volume or combustion chamber. At least one of the walls has an exterior shell and an interior shell including a number of panels. Each panel has interior and exterior surfaces and a perimeter having leading and trailing edges and first and second lateral edges. A number of cooling passageways have inlets on the panel exterior surface and outlets on the panel interior surface. A rail protrudes from the exterior surface and is recessed from the leading edge along a majority of the leading edge.
摘要翻译： 燃气涡轮发动机燃烧器具有在内侧和外侧壁之间延伸的前隔板并与之协作以限定燃烧器内部容积或燃烧室。 至少一个壁具有外壳和包括多个面板的内壳。 每个面板具有内部和外部表面以及具有前缘和后缘以及第一和第二侧边缘的周边。 多个冷却通道在面板外表面上具有入口，并且在面板内表面上具有出口。 轨道从外表面突出，并沿着前缘的大部分从前缘凹陷。
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公开(公告)号：US20090293488A1
公开(公告)日：2009-12-03
申请号：US12037128
申请日：2008-02-26
IPC分类号： F02C1/00
CPC分类号： F23R3/42 , F23R3/002 , F23R2900/03042 , F23R2900/03044 , Y02T50/675
摘要： A gas turbine engine combustor has forward bulkhead extending between inboard and outboard walls and cooperating therewith to define a combustor interior volume or combustion chamber. At least one of the walls has an exterior shell and an interior shell including a number of panels. Each panel has interior and exterior surfaces and a perimeter having leading and trailing edges and first and second lateral edges. A number of cooling passageways have inlets on the panel exterior surface and outlets on the panel interior surface. The shell has a plurality of holes for directing air to a space between the shell and heat shield and adapted for preferentially directing said air toward leading edge portions of first stage vanes of a turbine section.
摘要翻译： 燃气涡轮发动机燃烧器具有在内侧和外侧壁之间延伸的前隔板并与之协作以限定燃烧器内部容积或燃烧室。 至少一个壁具有外壳和包括多个面板的内壳。 每个面板具有内部和外部表面以及具有前缘和后缘以及第一和第二侧边缘的周边。 多个冷却通道在面板外表面上具有入口，并且在面板内表面上具有出口。 壳体具有多个孔，用于将空气引导到壳体和隔热罩之间的空间，并且适于优先地将空气引向涡轮部分的第一级叶片的前缘部分。
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公开(公告)号：US6134780A
公开(公告)日：2000-10-24
申请号：US391992
申请日：1999-09-09
CPC分类号： F23C7/004 , F23R3/14 , F23D2211/00 , F23D2900/14021 , Y10T29/4932 , Y10T29/49826
摘要： A swirler 50 for a gas turbine engine combustor 10 has an outer wall 54, groupings 52 of vanes 42 attached to the outer wall, a centerbody 60 mechanically decoupled from the outer wall via the groupings of vanes so that the swirler can accommodate differential rates of thermal growth between the outer wall and the inner centerbody and vanes. Alternatively, the centerbody may be attached to one of the groupings of vanes to keep the centerbody from vibrating.
摘要翻译： 用于燃气涡轮发动机燃烧器10的旋流器50具有外壁54，附接到外壁的叶片42的组52，经由叶片组从机体上与外壁分离的中心体60，使得旋流器可以适应不同速率 外壁和内中心体和叶片之间的热生长。 或者，中心体可以附接到叶片组中的一个，以保持中心体不起振。
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公开(公告)号：US5996352A
公开(公告)日：1999-12-07
申请号：US995508
申请日：1997-12-22
CPC分类号： F23C7/004 , F23R3/14 , F23D2211/00 , F23D2900/14021 , Y10T29/4932 , Y10T29/49826
摘要： A swirler 50 for a gas turbine engine combustor 10 has an outer wall 54, groupings 52 of vanes 42 attached to the outer wall, a centerbody 60 mechanically decoupled from the outer wall via the groupings of vanes so that the swirler can accommodate differential rates of thermal growth between the outer wall and the inner centerbody and vanes. Alternatively, the centerbody may be attached to one of the groupings of vanes to keep the centerbody from vibrating.
摘要翻译： 用于燃气涡轮发动机燃烧器10的旋流器50具有外壁54，附接到外壁的叶片42的组52，经由叶片组从机体上与外壁分离的中心体60，使得旋流器可以适应不同速率 外壁和内中心体和叶片之间的热生长。 或者，中心体可以附接到叶片组中的一个，以保持中心体不起振。
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公开(公告)号：US08015829B2
公开(公告)日：2011-09-13
申请号：US12037128
申请日：2008-02-26
IPC分类号： F23R3/42
CPC分类号： F23R3/42 , F23R3/002 , F23R2900/03042 , F23R2900/03044 , Y02T50/675
摘要： A gas turbine engine combustor has forward bulkhead extending between inboard and outboard walls and cooperating therewith to define a combustor interior volume or combustion chamber. At least one of the walls has an exterior shell and an interior shell including a number of panels. Each panel has interior and exterior surfaces and a perimeter having leading and trailing edges and first and second lateral edges. A number of cooling passageways have inlets on the panel exterior surface and outlets on the panel interior surface. The shell has a plurality of holes for directing air to a space between the shell and heat shield and adapted for preferentially directing said air toward leading edge portions of first stage vanes of a turbine section.
摘要翻译： 燃气涡轮发动机燃烧器具有在内侧和外侧壁之间延伸的前隔板并与之协作以限定燃烧器内部容积或燃烧室。 至少一个壁具有外壳和包括多个面板的内壳。 每个面板具有内部和外部表面以及具有前缘和后缘以及第一和第二侧边缘的周边。 多个冷却通道在面板外表面上具有入口，并且在面板内表面上具有出口。 壳体具有多个孔，用于将空气引导到壳体和隔热罩之间的空间，并且适于优先地将空气引向涡轮部分的第一级叶片的前缘部分。
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公开(公告)号：US07093439B2
公开(公告)日：2006-08-22
申请号：US10147571
申请日：2002-05-16
CPC分类号： F23R3/002 , F23R3/06 , F23R3/60 , F23R2900/03041 , F23R2900/03042
摘要： The present invention relates to heat shield panels or liners to be used in combustors for gas turbine engines. The heat shield panels each comprise a hot side and a cold side and at least one isolated cooling chamber on the cold side. Each cooling chamber has a plurality of cooling film holes for allowing a coolant, such as air, to flow from the cold side to the hot side. A combustor having an arrangement of heat shield panels or liners is also described.
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