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公开(公告)号：US4315405A
公开(公告)日：1982-02-16
申请号：US98173
申请日：1979-11-28
CPC分类号： F23R3/04
摘要： The airflow into a gas turbine engine combustion chamber e.g. through the primary air inlet and the dilution air inlets is directionally controlled by airflow directing inserts located in the air inlets. The inserts preferably comprise an open-ended cellular honeycomb structure.
摘要翻译： 进入燃气涡轮发动机燃烧室的气流，例如 通过主空气入口和稀释空气入口由位于空气入口中的气流引导插入件定向地控制。 插入件优选地包括开放式泡孔蜂窝结构。
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公开(公告)号：US20060117755A1
公开(公告)日：2006-06-08
申请号：US10635482
申请日：2003-08-07
申请人： Michael Spooner , Anthony Pidcock , Desmond Close
发明人： Michael Spooner , Anthony Pidcock , Desmond Close
IPC分类号： F23R3/42
CPC分类号： F23R3/002
摘要： A wall element (29) for a wall structure (21) of a gas turbine engine combustor (15). The wall element (29) comprises a main member (36) with an upstream edge region (30) and a downstream edge region (31). A plurality of heat removal members (38) are provided on the main member (36). The downstream edge (35) of the wall element and/or the downstream facing surface of the heat removal members closest to the downstream edge (35) are provided with a thermally resistant coating.
摘要翻译： 一种用于燃气涡轮发动机燃烧器（15）的壁结构（21）的壁元件（29）。 壁元件（29）包括具有上游边缘区域（30）和下游边缘区域（31）的主构件（36）。 多个散热构件（38）设置在主构件（36）上。 壁元件的下游边缘（35）和/或最靠近下游边缘（35）的散热构件的下游侧表面设置有耐热涂层。
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公开(公告)号：US07000397B2
公开(公告)日：2006-02-21
申请号：US11020167
申请日：2004-12-27
IPC分类号： F23R3/04
CPC分类号： F23R3/04 , F23R3/002 , F23R2900/03041 , F23R2900/03045
摘要： A wall element for use as part of an inner wall of a gas turbine engine combustor wall structure is of cast construction and includes a plurality of cooling apertures provided therethrough and formed during the casting process. The cooling apertures may be located in positions where they could not be conventionally formed by laser drilling.
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公开(公告)号：US06708499B2
公开(公告)日：2004-03-23
申请号：US10079403
申请日：2002-02-22
IPC分类号： F23R360
CPC分类号： F23R3/04 , F23R3/002 , F23R2900/03041 , F23R2900/03045
摘要： A wall element for use as part of an inner wall of a gas turbine engine combustor wall structure is of cast construction and includes a plurality of cooling apertures provided therethrough and formed during the casting process. The cooling apertures may be located in positions where they could not be conventionally formed by laser drilling.
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公开(公告)号：US06408628B1
公开(公告)日：2002-06-25
申请号：US09703666
申请日：2000-11-02
IPC分类号： F02C100
CPC分类号： F23R3/002 , F23R2900/03044
摘要： A wall element (29A, 29B) for a combustor (20) of a gas turbine engine (10). The wall element (29A, 29B) defines an axis. In use, the axis is arranged generally parallel to the principal axis of the engine (10). In one aspect, the length of the wall element (29B) along the axis is at least substantially 20% of the length of the wall element (29B) transverse to the axis. In another aspect, the wall element (29A, 29B) has a first pair of opposite edges extending transverse to the axis and a second pair of opposite edges (48, 50) extending transverse to the first pair, at least one of the second pair of edges (48, 50) being angled relative to the axis of the wall element (29A, 29B).
摘要翻译： 一种用于燃气涡轮发动机（10）的燃烧器（20）的壁元件（29A，29B）。 壁元件（29A，29B）限定一个轴线。 在使用中，轴线大致平行于发动机（10）的主轴布置。 一方面，沿着轴线的壁元件（29B）的长度至少基本上是横向于轴线的壁元件（29B）的长度的20％。 在另一方面，壁元件（29A，29B）具有横向于轴线延伸的第一对相对边缘和横向于第一对延伸的第二对相对边缘（48,50），第二对中的至少一个 的边缘（48,50）相对于壁元件（29A，29B）的轴线成角度。
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公开(公告)号：US4561257A
公开(公告)日：1985-12-31
申请号：US634453
申请日：1984-07-26
CPC分类号： F23D11/008 , F23R3/10 , F23R3/30 , F23D2900/11001 , Y02T50/675
摘要： A gas turbine engine combustion apparatus for vaporizing fuel comprises a flame tube having an upstream end wall in which are located a number of flow guides having associated fuel ducts. In operation, fuel and air flow through the U-shaped duct in each guide and the fuel flows onto the inside of the end wall which acts as a vaporizing surface. The exterior of the end wall is cooled by a flow of air from the engine compressor. The invention avoids the need of vaporizing tubes within the flame tube.
摘要翻译： 用于蒸发燃料的燃气涡轮发动机燃烧装置包括具有上游端壁的火焰管，其中位于具有相关联的燃料管道的多个流动引导件中。 在操作中，燃料和空气流过每个引导件中的U形管道，燃料流入作为汽化表面的端壁内侧。 端壁的外部由来自发动机压缩机的空气流冷却。 本发明避免了在火焰管内蒸发管的需要。
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公开(公告)号：US06666025B2
公开(公告)日：2003-12-23
申请号：US09784162
申请日：2001-02-16
IPC分类号： F23R300
CPC分类号： F23R3/002
摘要： A wall element (29) for a wall structure (21) of a gas turbine engine combustor (15). The wall element (29) comprises a main member (36) with an upstream edge region (30) and a downstream edge region (31). A plurality of heat removal members (38) are provided on the main member (36). The downstream edge (35) of the wall element and/or the downstream facing surface of the heat removal members closest to the downstream edge (35) are provided with a thermally resistant coating.
摘要翻译： 一种用于燃气涡轮发动机燃烧器（15）的壁结构（21）的壁元件（29）。 壁元件（29）包括具有上游边缘区域（30）和下游边缘区域（31）的主构件（36）。 多个散热构件（38）设置在主构件（36）上。 壁元件的下游边缘（35）和/或最靠近下游边缘（35）的散热构件的下游侧表面设置有耐热涂层。
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公开(公告)号：US07181914B2
公开(公告)日：2007-02-27
申请号：US10602610
申请日：2003-06-25
申请人： Anthony Pidcock , Desmond Close
发明人： Anthony Pidcock , Desmond Close
CPC分类号： F23R3/04
摘要： A gas turbine engine pre-diffuser 40 is generally annular, including radially inner and radially outer walls 40 and 42 and a generally cylindrical midline 48 defined between the walls. The pre-diffuser 40 includes a central member 46 which forces air flowing through the pre-diffuser 40 to separate, initially to be directed away from the midline 48 before subsequently being allowed to diffuse back towards the midline 48. The majority of the diffusion takes place on the walls of the central member and is thus in an inner region of the annulus of air ejected from the pre-diffuser to pass to the combustor. Any boundary losses therefore do not significantly effect air at the extremities of this annulus, this air being destined for the annuli of the combustor and requiring relatively high energy levels.
摘要翻译： 燃气涡轮发动机预扩散器40通常是环形的，包括径向内部和径向外壁40和42以及限定在壁之间的大致圆柱形的中线48。 预扩散器40包括中心构件46，该中心构件46迫使流过预扩散器40的空气分开，最初被引导离开中线48，之后允许其向中线48向后扩散。 扩散的大部分发生在中心构件的壁上，因此在从预扩散器喷出的空气环空的内部区域中传递到燃烧器。 因此，任何边界损失都不会显着影响这个环的末端的空气，这种空气注定为燃烧器的环形，并且需要较高的能量水平。
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公开(公告)号：US07080516B2
公开(公告)日：2006-07-25
申请号：US10742811
申请日：2003-12-23
申请人： Anthony Pidcock , Desmond Close
发明人： Anthony Pidcock , Desmond Close
CPC分类号： F04D29/541 , F23R3/04
摘要： A gas diffusion arrangement (22) for a gas turbine engine (10) is disclosed. The gas diffusion arrangement (22) has an inlet (26) and an outlet (28) for the gas, and comprises diffusion means (32) having an upstream region (38) and a downstream region (40). Distribution means (41) is arranged between the downstream region (40) and the outlet (28) to distribute the gas into a desired flow pattern. The area ratio of the cross-sectional area of the downstream region (40) to the cross-sectional area of the upstream region (38) is greater than 1.5 to 1.
摘要翻译： 公开了一种用于燃气涡轮发动机（10）的气体扩散装置（22）。 气体扩散装置（22）具有用于气体的入口（26）和出口（28），并且包括具有上游区域（38）和下游区域（40）的扩散装置（32）。 分配装置（41）布置在下游区域（40）和出口（28）之间，以将气体分布成期望的流动模式。 下游区域（40）的横截面面积与上游区域（38）的截面积的面积比大于1.5比1。
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公开(公告)号：US20050034399A1
公开(公告)日：2005-02-17
申请号：US10880463
申请日：2004-07-01
申请人： Anthony Pidcock , Desmond Close
发明人： Anthony Pidcock , Desmond Close
CPC分类号： F23R3/60 , F23R3/002 , F23R2900/03041
摘要： A double wall structure (22) for a combustor (15) of a gas turbine engine (10) comprising an inner wall (28) and an outer wall (27), the inner wall (28) comprising a plurality of main tiles (50), the main tiles (50) are secured to the outer wall (27) by a securing means (35), wherein the inner wall (28) further comprises a plurality of edge tiles (52) which are secured to the outer wall (27) by securing means (35), each edge tile (52) overlapping at least one edge (30, 31, 54, 61) of a main tile (50) thereby further securing the main tiles (50) to the outer wall (27).
摘要翻译： 一种用于包括内壁（28）和外壁（27）的燃气涡轮发动机（10）的燃烧器（15）的双壁结构（22），所述内壁（28）包括多个主瓦片（50） ），主瓦片（50）通过固定装置（35）固定到外壁（27），其中内壁（28）还包括多个边缘瓦片（52），其固定到外壁 通过固定装置（35），每个边缘瓦片（52）与主瓦片（50）的至少一个边缘（30,31,54,61）重叠，从而进一步将主瓦片（50）固定到外壁 27）。
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