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1.发明申请GAS TURBINE ENGINE COMBUSTOR LINER PANEL WITH SYNERGISTIC COOLING FEATURES 审中-公开燃气涡轮发动机配备有协同冷却功能的衬板公开(公告)号：US20170003027A1
公开(公告)日：2017-01-05
申请号：US15106032
申请日：2015-01-30
发明人： Stanislav Kostka , Frank J. Cunha , James B. Hoke , Timothy S. Snyder , Albert K. Cheung , Christos Adamopoulos
CPC分类号： F23R3/005 , F02C7/18 , F02K1/822 , F05D2260/20 , F05D2260/201 , F23R3/007 , F23R3/06 , F23R2900/00017 , F23R2900/03041 , F23R2900/03044 , F23R2900/03045 , Y02T50/675
摘要： A liner panel for a combustor of a gas turbine engine includes a multiple of heat transfer augmentors. At least one of the multiple of heat transfer augmentors includes a cone shaped pin.
摘要翻译： 用于燃气涡轮发动机的燃烧器的衬板包括多个传热增强器。 多个传热增强器中的至少一个包括锥形销。
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公开(公告)号：US20170045226A1
公开(公告)日：2017-02-16
申请号：US14826463
申请日：2015-08-14
摘要： A combustor liner for a gas turbine is provided. The combustor liner comprises a wall and a plurality of airflow injection holes in the wall arranged in a circumferentially-extending row, the plurality of airflow injection holes including a plurality of circular first airflow injection holes and at least one non-circular second airflow injection hole.
摘要翻译： 提供了一种用于燃气轮机的燃烧器衬套。 所述燃烧器衬套包括壁和沿所述壁布置成沿圆周方向延伸的排中的多个气流注入孔，所述多个气流注入孔包括多个圆形第一气流注入孔和至少一个非圆形第二气流注入孔 。
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公开(公告)号：US10480787B2
公开(公告)日：2019-11-19
申请号：US14669206
申请日：2015-03-26
摘要： A cooled wall for lining a combustor of a gas turbine engine includes an annular outer wall defining a radial passage extending therethrough, an inner wall spaced radially from the outer wall to define an axial channel in fluid communication with the radial passage, and a connecting wall joining the inner wall to the outer wall. A method of making the cooled wall includes providing a three-dimensional computer model of the cooled wall, depositing a uniform thickness layer of material on a substrate, using a laser or electron beam to melt or sinter the material to form a cross section, repeating the depositing and cross section steps to form the cooled wall, and heat treating the cooled wall.
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公开(公告)号：US20170059161A1
公开(公告)日：2017-03-02
申请号：US14836117
申请日：2015-08-26
CPC分类号： F23R3/16 , F02C6/06 , F02C6/08 , F02C7/12 , F02C7/18 , F02C9/18 , F05D2220/32 , F05D2240/35 , F05D2260/20 , F23C9/08 , F23C2900/09001 , F23R3/002 , F23R3/02 , F23R3/04 , F23R3/42 , F23R3/425 , F23R3/44 , F23R3/46 , F23R3/48 , F23R3/50 , F23R3/52 , F23R3/54 , F23R3/56 , F23R3/58
摘要： An air extraction port at a combustor of a gas turbine engine includes a port inlet at a combustor case of the combustor having an inlet area, a port outlet having a final area, and a fluid passage extending from the port inlet to the port outlet to convey an airflow, the port inlet sized and configured to extract the airflow from the combustor case at the same nominal upstream Mach number with a tolerance of +/−0.05.
摘要翻译： 燃气涡轮发动机的燃烧器处的空气抽出口包括在燃烧器壳体处的具有入口区域的端口入口，具有最终区域的端口出口和从端口入口延伸到端口出口的流体通道 传送气流，端口入口的尺寸和构造可以在相同标称上游马赫数处从燃烧器壳体提取气流，其公差为+/- 0.05。
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公开(公告)号：US20160281986A1
公开(公告)日：2016-09-29
申请号：US14669206
申请日：2015-03-26
CPC分类号： F23R3/002 , B22F3/1055 , B22F5/009 , B22F2003/1057 , B33Y10/00 , B33Y50/02 , B33Y80/00 , F23R3/007 , F23R3/06 , F23R3/50 , F23R2900/00018 , F23R2900/03042 , F23R2900/03043 , Y02T50/675
摘要： A cooled wall for lining a combustor of a gas turbine engine includes an annular outer wall defining a radial passage extending therethrough, an inner wall spaced radially from the outer wall to define an axial channel in fluid communication with the radial passage, and a connecting wall joining the inner wall to the outer wall. A method of making the cooled wall includes providing a three-dimensional computer model of the cooled wall, depositing a uniform thickness layer of material on a substrate, using a laser or electron beam to melt or sinter the material to form a cross section, repeating the depositing and cross section steps to form the cooled wall, and heat treating the cooled wall.
摘要翻译： 用于衬套燃气涡轮发动机的燃烧器的冷却壁包括限定通过其延伸的径向通道的环形外壁，与外壁径向间隔开的内壁，以限定与径向通道流体连通的轴向通道，以及连接壁 将内壁连接到外壁。 制造冷却壁的方法包括提供冷却壁的三维计算机模型，使用激光或电子束在衬底上沉积均匀的厚度的材料层以熔化或烧结材料以形成横截面，重复 沉积和横截面步骤以形成冷却的壁，并且对冷却的壁进行热处理。
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公开(公告)号：US10670267B2
公开(公告)日：2020-06-02
申请号：US14826463
申请日：2015-08-14
摘要： A combustor liner for a gas turbine is provided. The combustor liner comprises a wall and a plurality of airflow injection holes in the wall arranged in a circumferentially-extending row, the plurality of airflow injection holes including a plurality of circular first airflow injection holes and at least one non-circular second airflow injection hole.
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公开(公告)号：US10514169B2
公开(公告)日：2019-12-24
申请号：US14826463
申请日：2015-08-14
摘要： A combustor liner for a gas turbine is provided. The combustor liner comprises a wall and a plurality of airflow injection holes in the wall arranged in a circumferentially-extending row, the plurality of airflow injection holes including a plurality of circular first airflow injection holes and at least one non-circular second airflow injection hole.
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公开(公告)号：US10024538B2
公开(公告)日：2018-07-17
申请号：US14836117
申请日：2015-08-26
IPC分类号： F23R3/02 , F23R3/16 , F02C7/18 , F23R3/00 , F23R3/42 , F02C6/06 , F02C7/12 , F23R3/04 , F23C9/08 , F23R3/58 , F23R3/46 , F23R3/52 , F23R3/56 , F23R3/54 , F23R3/50 , F23R3/48 , F02C6/08 , F02C9/18 , F23R3/44
摘要： An air extraction port at a combustor of a gas turbine engine includes a port inlet at a combustor case of the combustor having an inlet area, a port outlet having a final area, and a fluid passage extending from the port inlet to the port outlet to convey an airflow, the port inlet sized and configured to extract the airflow from the combustor case at the same nominal upstream Mach number with a tolerance of +/−0.05.
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公开(公告)号：US20170044979A1
公开(公告)日：2017-02-16
申请号：US14826502
申请日：2015-08-14
CPC分类号： F02C3/14 , F02C7/232 , F05D2220/32 , F05D2240/35 , F23R3/04 , F23R3/10 , Y02T50/675
摘要： A gas turbine engine is provided. The engine includes a combustor configured at a combustor angle relative to an engine axis and a pre-diffuser configured to supply air to the combustor and configured at a diffuser angle relative to the engine axis, wherein the diffuser angle is greater than the combustor angle. A method of manufacturing a gas turbine engine includes installing a combustor at a combustor angle relative to an engine axis and installing a pre-diffuser at a diffuser angle relative to the engine axis, wherein the diffuser angle is greater than the combustor angle. A gas turbine engine includes a pre-diffuser configured at an angle of between 8° and 10° relative to an engine axis.
摘要翻译： 提供燃气涡轮发动机。 发动机包括构造成相对于发动机轴线以燃烧器角度的燃烧器和预扩散器，该预扩散器构造成向燃烧器提供空气并且相对于发动机轴线以扩散器角度构造，其中扩散器角度大于燃烧器角度。 一种制造燃气涡轮发动机的方法包括以相对于发动机轴线的燃烧器角度安装燃烧器并相对于发动机轴线以扩散器角度安装预扩散器，其中扩散器角度大于燃烧器角度。 燃气涡轮发动机包括相对于发动机轴线以8°和10°之间的角度构造的预扩散器。
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