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公开(公告)号：US09038395B2
公开(公告)日：2015-05-26
申请号：US13434618
申请日：2012-03-29
CPC分类号： F23R3/06 , F23R3/16 , F23R2900/00017 , F23R2900/00018 , Y02T50/675 , Y10T29/49323
摘要： A combustor for a turbine engine is provided. The combustor includes a first liner and a second liner forming a combustion chamber with the first liner, the combustion chamber configured to receive an air-fuel mixture for combustion therein. The first liner defining an air admission hole for directing a first jet of pressurized air into the combustion chamber, and the air admission hole may have a non-circular shape. The combustor further includes an insert positioned within the air admission hole to guide the first jet through the air admission hole and into the combustion chamber.
摘要翻译： 提供了一种用于涡轮发动机的燃烧器。 燃烧器包括第一衬套和形成具有第一衬套的燃烧室的第二衬套，燃烧室被配置为容纳用于在其中燃烧的空气 - 燃料混合物。 所述第一衬套限定用于将第一喷射加压空气引导到所述燃烧室中的进气孔，并且所述进气孔可以具有非圆形形状。 燃烧器还包括位于进气孔内的插入件，以引导第一射流通过进气孔并进入燃烧室。
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公开(公告)号：US20130255265A1
公开(公告)日：2013-10-03
申请号：US13434618
申请日：2012-03-29
CPC分类号： F23R3/06 , F23R3/16 , F23R2900/00017 , F23R2900/00018 , Y02T50/675 , Y10T29/49323
摘要： A combustor for a turbine engine is provided. The combustor includes a first liner and a second liner forming a combustion chamber with the first liner, the combustion chamber configured to receive an air-fuel mixture for combustion therein. The first liner defining an air admission hole for directing a first jet of pressurized air into the combustion chamber, and the air admission hole may have a non-circular shape. The combustor further includes an insert positioned within the air admission hole to guide the first jet through the air admission hole and into the combustion chamber.
摘要翻译： 提供了一种用于涡轮发动机的燃烧器。 燃烧器包括第一衬套和形成具有第一衬套的燃烧室的第二衬套，燃烧室被配置为容纳用于在其中燃烧的空气 - 燃料混合物。 所述第一衬套限定用于将第一喷射加压空气引导到所述燃烧室中的进气孔，并且所述进气孔可以具有非圆形形状。 燃烧器还包括位于进气孔内的插入件，以引导第一射流通过进气孔并进入燃烧室。
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公开(公告)号：US09062884B2
公开(公告)日：2015-06-23
申请号：US13116897
申请日：2011-05-26
CPC分类号： F23R3/045 , F23R3/06 , Y02T50/675 , Y10T29/49348
摘要： A combustor is provided for a turbine engine. The combustor includes a first liner having a first hot side and a first cold side; a second liner having a second hot side and a second cold side, the second hot side and the first hot side forming a combustion chamber therebetween. The combustion chamber is configured to receive an air-fuel mixture for combustion therein. The combustor further includes an insert having a body portion extending through the first liner and terminating at a tip, the body portion configured to direct air flow into the combustion chamber. The insert further includes a cooling hole defined in the body portion and configured to direct a first portion of the air flow toward the tip as cooling air.
摘要翻译： 为涡轮发动机提供燃烧器。 燃烧器包括具有第一热侧和第一冷侧的第一衬里; 具有第二热侧和第二冷侧的第二衬里，所述第二热侧和所述第一热侧在其间形成燃烧室。 燃烧室构造成容纳用于在其中燃烧的空气 - 燃料混合物。 燃烧器还包括具有主体部分的插入件，该主体部分延伸穿过第一衬套并终止于尖端，主体部分构造成引导空气流入燃烧室。 插入件还包括限定在主体部分中的冷却孔，其构造成将空气流的第一部分朝向尖端作为冷却空气。
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公开(公告)号：US20120297778A1
公开(公告)日：2012-11-29
申请号：US13116897
申请日：2011-05-26
CPC分类号： F23R3/045 , F23R3/06 , Y02T50/675 , Y10T29/49348
摘要： A combustor is provided for a turbine engine. The combustor includes a first liner having a first hot side and a first cold side; a second liner having a second hot side and a second cold side, the second hot side and the first hot side forming a combustion chamber therebetween. The combustion chamber is configured to receive an air-fuel mixture for combustion therein. The combustor further includes an insert having a body portion extending through the first liner and terminating at a tip, the body portion configured to direct air flow into the combustion chamber. The insert further includes a cooling hole defined in the body portion and configured to direct a first portion of the air flow toward the tip as cooling air.
摘要翻译： 为涡轮发动机提供燃烧器。 燃烧器包括具有第一热侧和第一冷侧的第一衬里; 具有第二热侧和第二冷侧的第二衬里，所述第二热侧和所述第一热侧在其间形成燃烧室。 燃烧室构造成容纳用于在其中燃烧的空气 - 燃料混合物。 燃烧器还包括具有主体部分的插入件，该主体部分延伸穿过第一衬套并终止于尖端，主体部分构造成引导空气流入燃烧室。 插入件还包括限定在主体部分中的冷却孔，其构造成将空气流的第一部分朝向尖端作为冷却空气。
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公开(公告)号：US09010123B2
公开(公告)日：2015-04-21
申请号：US12843750
申请日：2010-07-26
CPC分类号： F23R3/06 , F23R2900/00018 , F23R2900/03282 , Y02T50/675 , Y10T29/53
摘要： A combustor for a turbine engine is provided. The combustor includes a first liner having a first hot side and a first cold side; a second liner having a second hot side and a second cold side, the second hot side and the first hot side forming a combustion chamber therebetween, the combustion chamber configured to receive an air-fuel mixture for combustion therein; and an insert including a body portion extending through the first liner, a shoulder circumscribing the body portion and abutting the first hot side, and an inlet portion coupled to the body portion and abutting the first cold side such that the inlet portion and the shoulder capture the second liner therebetween to retain the insert.
摘要翻译： 提供了一种用于涡轮发动机的燃烧器。 燃烧器包括具有第一热侧和第一冷侧的第一衬里; 具有第二热侧和第二冷侧的第二衬套，所述第二热侧和所述第一热侧在其间形成燃烧室，所述燃烧室被配置为容纳用于在其中燃烧的空气 - 燃料混合物; 以及插入件，其包括延伸穿过所述第一衬垫的主体部分，限定所述主体部分并邻接所述第一热侧的台阶，以及联接到所述主体部分并抵靠所述第一冷侧的入口部分，使得所述入口部分和所述肩部抓住 其间的第二衬垫保持插入物。
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公开(公告)号：US20120017596A1
公开(公告)日：2012-01-26
申请号：US12843750
申请日：2010-07-26
CPC分类号： F23R3/06 , F23R2900/00018 , F23R2900/03282 , Y02T50/675 , Y10T29/53
摘要： A combustor for a turbine engine is provided. The combustor includes a first liner having a first hot side and a first cold side; a second liner having a second hot side and a second cold side, the second hot side and the first hot side forming a combustion chamber therebetween, the combustion chamber configured to receive an air-fuel mixture for combustion therein; and an insert including a body portion extending through the first liner, a shoulder circumscribing the body portion and abutting the first hot side, and an inlet portion coupled to the body portion and abutting the first cold side such that the inlet portion and the shoulder capture the second liner therebetween to retain the insert.
摘要翻译： 提供了一种用于涡轮发动机的燃烧器。 燃烧器包括具有第一热侧和第一冷侧的第一衬里; 具有第二热侧和第二冷侧的第二衬套，所述第二热侧和所述第一热侧在其间形成燃烧室，所述燃烧室被配置为容纳用于在其中燃烧的空气 - 燃料混合物; 以及插入件，其包括延伸穿过所述第一衬垫的主体部分，限定所述主体部分并邻接所述第一热侧的台阶，以及联接到所述主体部分并抵靠所述第一冷侧的入口部分，使得所述入口部分和所述肩部抓住 其间的第二衬垫保持插入物。
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公开(公告)号：US20100095680A1
公开(公告)日：2010-04-22
申请号：US12256246
申请日：2008-10-22
IPC分类号： F02C5/02
CPC分类号： F23R3/06 , F23R3/002 , F23R3/60 , F23R2900/00017 , F23R2900/03041 , F23R2900/03044 , Y02T50/675
摘要： A dual wall structure for a combustor of a gas turbine engine including an inner liner and an outer liner coupled to a combustor dome and defining a combustion chamber there between. Each of the inner liner and the outer liner include an outer wall and an inner wall. Each of the outer walls includes a plurality of impingement holes formed therein for allowing a coolant to flow therethrough. Each of the inner walls is coupled to the outer wall and a combustor dome and includes a plurality of heat shield panels. Each of the plurality of heat shield panels extends a longitudinal length of the combustor chamber and includes a plurality of side rails, an aft rail and a forward flange that when coupled to the outer wall defines a single cavity there between. A plurality of cavities being formed by the plurality of heat shield panels.
摘要翻译： 一种用于燃气涡轮发动机的燃烧器的双壁结构，其包括内衬和联接到燃烧器圆顶并且在其之间限定燃烧室的外衬套。 内衬套和外衬套中的每一个包括外壁和内壁。 每个外壁包括形成在其中的多个冲击孔，用于允许冷却剂流过其中。 每个内壁联接到外壁和燃烧器圆顶并且包括多个隔热板。 多个隔热屏板中的每一个延伸了燃烧室的纵向长度，并且包括多个侧轨，后轨和前凸缘，当与外壁连接时，它们之间形成单个空腔。 由多个隔热板形成的多个空腔。
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公开(公告)号：US20110120133A1
公开(公告)日：2011-05-26
申请号：US12623773
申请日：2009-11-23
IPC分类号： F23D14/46
CPC分类号： F23R3/002 , F23R2900/00012
摘要： A combustor for a turbine engine is provided. The combustor includes a first liner and a second liner forming a combustion chamber. The combustion chamber is configured to receive an air-fuel mixture for combustion therein and having a longitudinal axis that defines axial and radial directions. The first liner is a first dual walled liner having a first hot wall facing the combustion chamber and a first cold wall that forms a first liner cavity with the first hot wall, the first liner cavity having first and second ends. A first liner seal is configured to seal the second end of the first liner cavity and to accommodate relative movement of the first hot wall and first cold wall generally in the axial and radial directions.
摘要翻译： 提供了一种用于涡轮发动机的燃烧器。 燃烧器包括形成燃烧室的第一衬里和第二衬套。 燃烧室被配置为接收用于在其中燃烧的空气 - 燃料混合物并且具有限定轴向和径向方向的纵向轴线。 第一衬垫是具有面向燃烧室的第一热壁的第一双壁衬套和与第一热壁形成第一衬里腔的第一冷壁，第一衬里腔具有第一和第二端。 第一衬里密封件被配置为密封第一衬里腔的第二端并且容纳通常在轴向和径向方向上的第一热壁和第一冷壁的相对运动。
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公开(公告)号：US08726631B2
公开(公告)日：2014-05-20
申请号：US12623622
申请日：2009-11-23
CPC分类号： F23R3/60 , F02C7/264 , F05D2260/201 , F23R2900/00012 , Y02T50/671 , Y02T50/675
摘要： A combustor for a gas turbine engine includes an inner liner and an outer liner circumscribing the inner liner and forming a combustion chamber therewith. The outer liner is a dual walled liner with a first wall and a second wall. A fuel igniter includes a tip portion configured to ignite an air and fuel mixture in the combustion chamber. An igniter support assembly positions the fuel igniter relative to the combustion chamber. The igniter support assembly defines a plurality of holes configured to direct cooling air toward the tip portion of the fuel igniter. The igniter support assembly includes first and second floating seals that are configured to accommodate radial and axial relative movements.
摘要翻译： 用于燃气涡轮发动机的燃烧器包括内衬和限定内衬的外衬套，并与其形成燃烧室。 外衬套是具有第一壁和第二壁的双壁衬套。 燃料点火器包括被配置为点燃燃烧室中的空气和燃料混合物的末端部分。 点火器支撑组件相对于燃烧室定位燃料点火器。 点火器支撑组件限定了构造成将冷却空气朝向燃料点火器的尖端部分引导的多个孔。 点火器支撑组件包括构造成适应径向和轴向相对运动的第一和第二浮动密封件。
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公开(公告)号：US09021812B2
公开(公告)日：2015-05-05
申请号：US13560876
申请日：2012-07-27
CPC分类号： F23R3/14 , F23R3/60 , Y02T50/675 , Y10T29/49323
摘要： A combustor dome and heat-shield assembly comprises a heat-shield having a first opening therethrough. A swirler extends through the first opening and captures the heat-shield. A dome having a second opening therethrough and has an upstream side and a downstream side. The swirler extends through the second opening from the downstream side to the upstream side to capture the heat-shield on the downstream side, and a retaining clip engages the swirler to secure the swirler and the heat-shield on the dome.
摘要翻译： 燃烧器穹顶和隔热罩组件包括具有穿过其中的第一开口的隔热罩。 旋流器延伸穿过第一开口并捕获隔热罩。 具有通过其的第二开口并具有上游侧和下游侧的圆顶。 旋流器从下游侧延伸到第二开口到上游侧，以在下游侧捕获隔热罩，并且保持夹与旋流器接合以将旋流器和隔热罩固定在圆顶上。
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