-
公开(公告)号：US08882461B2
公开(公告)日：2014-11-11
申请号：US13230553
申请日：2011-09-12
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/304 , F05D2250/185 , F05D2260/202 , F05D2260/22141 , Y02T50/673 , Y02T50/676
摘要： An airfoil is provided for a gas turbine engine. The airfoil includes a pressure side wall; a suction side wall; an internal cavity defined between the pressure side wall and the suction side wall for receiving cooling air; and a cooling arrangement within the internal cavity. The cooling arrangement includes a first land extending to a first downstream end aft of the pressure side trailing edge, a second land extending to a second downstream end aft of the pressure side trailing edge, the first land and second land defining a first slot, a first divider positioned radially in between the first land and the second land to define a first passageway of the first slot and a second passageway of the first slot, a first pin positioned upstream and indexed to the first passageway, and a second pin positioned upstream and indexed to the second passageway.
摘要翻译： 提供一种用于燃气涡轮发动机的翼型件。 翼型件包括压力侧壁; 吸力侧壁; 限定在压力侧壁和吸力侧壁之间以接收冷却空气的内部空腔; 以及内部空腔内的冷却装置。 冷却装置包括延伸到压力侧后缘的第一下游端的第一焊盘，延伸到压力侧后缘的后部的第二下游端的第二焊盘，第一焊盘和第二焊盘限定第一槽， 第一分隔件径向地定位在第一平台和第二平台之间，以限定第一槽的第一通道和第一槽的第二通道，第一销定位在第一通道的上游并分配到第一通道上，第二销位于第二通道 索引到第二条通道。
-
2.发明申请公开(公告)号：US20130064639A1
公开(公告)日：2013-03-14
申请号：US13230553
申请日：2011-09-12
IPC分类号： F04D31/00
CPC分类号： F01D5/187 , F05D2240/304 , F05D2250/185 , F05D2260/202 , F05D2260/22141 , Y02T50/673 , Y02T50/676
摘要： An airfoil is provided for a gas turbine engine. The airfoil includes a pressure side wall; a suction side wall; an internal cavity defined between the pressure side wall and the suction side wall for receiving cooling air; and a cooling arrangement within the internal cavity. The cooling arrangement includes a first land extending to a first downstream end aft of the pressure side trailing edge, a second land extending to a second downstream end aft of the pressure side trailing edge, the first land and second land defining a first slot, a first divider positioned radially in between the first land and the second land to define a first passageway of the first slot and a second passageway of the first slot, a first pin positioned upstream and indexed to the first passageway, and a second pin positioned upstream and indexed to the second passageway.
摘要翻译： 提供一种用于燃气涡轮发动机的翼型件。 翼型件包括压力侧壁; 吸力侧壁; 限定在压力侧壁和吸力侧壁之间以接收冷却空气的内部空腔; 以及内部空腔内的冷却装置。 冷却装置包括延伸到压力侧后缘的第一下游端的第一焊盘，延伸到压力侧后缘的后部的第二下游端的第二焊盘，第一焊盘和第二焊盘限定第一槽， 第一分隔件径向地定位在第一平台和第二平台之间，以限定第一槽的第一通道和第一槽的第二通道，第一销定位在第一通道的上游并分配到第一通道上，第二销位于第二通道 索引到第二条通道。
-
公开(公告)号：US20100212324A1
公开(公告)日：2010-08-26
申请号：US12393729
申请日：2009-02-26
CPC分类号： F02C7/264 , F05D2260/201 , F23D2207/00 , F23R3/002 , F23R3/06 , F23R3/60 , F23R2900/00012 , F23R2900/03042 , F23R2900/03044 , 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 with the inner liner. The outer liner is a dual walled liner with a first wall and a second wall. The combustor includes a fuel igniter comprising a tip portion configured to ignite an air and fuel mixture in the combustion chamber and an igniter tube positioning the fuel igniter relative to the combustion chamber. The igniter tube includes a plurality of holes configured to direct cooling air toward the tip portion of the fuel igniter.
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，并与内衬形成燃烧室。 外衬套是具有第一壁和第二壁的双壁衬套。 燃烧器包括燃料点火器，该燃料点火器包括构造成点燃燃烧室中的空气和燃料混合物的顶端部分和点燃器管，其相对于燃烧室定位燃料点火器。 点火管包括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。
-
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。
-
-
-
搜索结果
4 条记录 (耗时 0.022 秒)
