-
公开(公告)号：US07008185B2
公开(公告)日：2006-03-07
申请号：US10375415
申请日：2003-02-27
申请人： Jonathan Jordan Peterman , Andrew Charles Powis , Ronald Eugene McRae, Jr. , Jonathan Philip Clarke , Robert Alan Frederick , Edward Eugene Gibler , Brian David Keith
发明人： Jonathan Jordan Peterman , Andrew Charles Powis , Ronald Eugene McRae, Jr. , Jonathan Philip Clarke , Robert Alan Frederick , Edward Eugene Gibler , Brian David Keith
CPC分类号： F01D5/189 , F01D9/041 , F05D2240/81 , F05D2250/70 , F05D2260/201 , F05D2260/30 , Y02T50/67 , Y02T50/676
摘要： A turbine nozzle bifurcated impingement baffle includes axially forward and aft chambers with a gap therebetween, impingement holes through forward and aft baffle walls of the forward and aft chambers respectively, and a plenum chamber in fluid flow communication with the forward and aft chambers. An exemplary embodiment of the bifurcated impingement baffle further includes a single cooling air inlet to the plenum chamber enclosed within a plenum chamber enclosure the plenum chamber. A sealing plate is mounted between and sealed to the plenum chamber enclosure and the forward and aft chambers. The sealing plate has forward and aft inlet apertures disposed between the plenum chamber and the forward and aft chambers respectively. Forward and aft end plates cap radially inner ends of the forward and aft chambers. An outlet aperture in the forward end plate has an interstage seal cavity feed tube disposed therethrough.
摘要翻译： 涡轮喷嘴分叉冲击挡板包括轴向前后空间，其间具有间隙，冲击孔分别通过前后舱的前后挡板壁和与前室和后室流体连通的增压室。 分叉式冲击挡板的示例性实施例还包括一个单独的冷却空气入口，该冷却空气入口封闭在包围增压室的增压室内。 密封板安装在密封室之间并密封到增压室外壳和前后室。 密封板具有分别设置在增压室和前后室之间的前后入口孔。 前端和后端板盖住前后室的径向内端。 前端板中的出口孔具有穿过其设置的级间密封腔供给管。
-
2.发明授权Gas turbine engine turbine nozzle segment with a single hollow vane having a bifurcated cavity 有权燃气涡轮发动机涡轮喷嘴段具有单个空心叶片，其具有分叉腔公开(公告)号：US06969233B2
公开(公告)日：2005-11-29
申请号：US10375585
申请日：2003-02-27
申请人： Andrew Charles Powis , Ronald Eugene McRae, Jr. , Jonathan Philip Clarke , Jonathan Jordan Peterman , Robert Alan Frederick , Edward Eugene Gibler , Brian David Keith
发明人： Andrew Charles Powis , Ronald Eugene McRae, Jr. , Jonathan Philip Clarke , Jonathan Jordan Peterman , Robert Alan Frederick , Edward Eugene Gibler , Brian David Keith
CPC分类号： F01D5/189 , B22C21/14 , F05D2240/12 , F05D2240/81 , F05D2260/201 , F05D2260/22141 , Y02T50/67 , Y02T50/671 , Y02T50/676
摘要： A turbine nozzle segment includes a single hollow airfoil extending radially between radially outer and inner band segments. The airfoil has an airfoil wall with pressure and suction sides extending axially between leading and trailing edges of the airfoil. The airfoil wall surrounds a bifurcated cavity and a bifurcating rib extends through the bifurcated cavity and between the pressure and suction sides of the airfoil wall dividing the bifurcated cavity into forward and aft cavities. A stiffening rib extends radially outwardly from and along a radially outer surface of the outer band segment and axially and circumferentially from a pressure side forward corner of the outer band segment to the bifurcating rib. The outer and inner band segments, the bifurcating rib, and the stiffening rib are integral and made from a unitary one-piece casting.
摘要翻译： 涡轮喷嘴段包括在径向外部段和内部带段之间径向延伸的单个中空翼型件。 翼型件具有翼型壁，其压力和吸力侧面在翼型的前缘和后缘之间轴向延伸。 翼型壁围绕分叉的空腔并且分叉肋延伸穿过分叉的空腔，并且在翼型壁的压力和吸力侧之间延伸，将分叉腔分成前后空腔。 加强筋从外带段的径向外表面径向向外延伸，并且从外带段的压力侧前角轴向和周向延伸到分叉肋。 外带和内带段，分叉肋和加强筋是整体的，由一体式单件铸件制成。
-
公开(公告)号：US06932568B2
公开(公告)日：2005-08-23
申请号：US10375441
申请日：2003-02-27
申请人： Andrew Charles Powis , Ronald Eugene McRae, Jr. , Jonathan Philip Clarke , Jonathan Jordan Peterman , Robert Alan Frederick , Edward Eugene Gibler , Brian David Keith
发明人： Andrew Charles Powis , Ronald Eugene McRae, Jr. , Jonathan Philip Clarke , Jonathan Jordan Peterman , Robert Alan Frederick , Edward Eugene Gibler , Brian David Keith
CPC分类号： F01D9/041 , B22C21/14 , E05Y2900/402 , F01D5/189 , F01D25/246 , F05D2240/12 , F05D2240/81 , F05D2260/201 , F05D2260/22141 , F05D2260/30 , Y02T50/67 , Y02T50/676
摘要： A turbine nozzle segment includes at least one hollow airfoil extending radially between radially outer and inner band segments, a clockwise open hook on a clockwise end at an aft end of the outer band segment, and counter-clockwise open hook on a counter-clockwise end at the aft end of the outer band segments. An exemplary embodiment of the turbine nozzle segment includes a load stop extending radially outwardly from the outer band segment. At least one aftwardly facing load face is at the aft end of the nozzle segment at the outer band segment. The clockwise open hook is C-shaped and the counter-clockwise open hook is a shiplap hook. Another embodiment of the turbine nozzle segment has only one hollow airfoil with an airfoil wall surrounding a bifurcated cavity divided into forward and aft cavities by a bifurcating rib extending between pressure and suction sides of the airfoil wall.
摘要翻译： 涡轮喷嘴段包括至少一个在径向外带段和内带段之间径向延伸的中空翼型件，在外带段的后端处的顺时针端部上的顺时针打开的钩子，以及逆时针方向的逆时针方向的开口钩 在外带段的后端。 涡轮喷嘴段的示例性实施例包括从外带段径向向外延伸的负载停止。 至少一个面向前的负载面处于外带段处的喷嘴段的后端。 顺时针打开的钩子是C形的，逆时针打开的钩子是一个shiplap钩子。 涡轮喷嘴段的另一个实施例仅具有一个中空翼型件，其翼型壁围绕通过在翼型件壁的压力侧和抽吸侧之间延伸的分叉肋分成前部和后部空腔的分叉空腔。
-
公开(公告)号：US07007488B2
公开(公告)日：2006-03-07
申请号：US10885147
申请日：2004-07-06
申请人： Robert Joseph Orlando , Thomas Ory Moniz , John Christopher Brauer , Ian Francis Prentice , Erich Alois Krammer , James Patrick Dolan , Robert Alan Frederick
发明人： Robert Joseph Orlando , Thomas Ory Moniz , John Christopher Brauer , Ian Francis Prentice , Erich Alois Krammer , James Patrick Dolan , Robert Alan Frederick
IPC分类号： F02C7/12
摘要： A gas turbine engine includes a compressor powered by a turbine. The turbine includes a nozzle having vanes extending between outer and inner bands. Each vane includes an internal cooling plenum and a bypass tube extending through the bands. First and second manifolds surround the outer band and are disposed in flow communication with the plenums and bypass tubes, respectively. A bleed circuit joins the compressor to the manifolds for providing pressurized air thereto. A control valve modulates airflow to the first manifold and in turn through the cooling plenums of the vanes.
摘要翻译： 燃气涡轮发动机包括由涡轮机供电的压缩机。 涡轮机包括具有在外带和内带之间延伸的叶片的喷嘴。 每个叶片包括一个内部冷却通风室和一个延伸穿过该带的旁通管。 第一和第二歧管围绕外部带并分别设置成与集气室和旁通管流动连通。 泄放回路将压缩机连接到歧管，以向其提供加压空气。 控制阀调节到第一歧管的气流，并依次通过叶片的冷却增压室。
-
公开(公告)号：US06769865B2
公开(公告)日：2004-08-03
申请号：US10104211
申请日：2002-03-22
IPC分类号： F01D906
CPC分类号： F01D9/04 , F01D25/12 , F05D2240/55 , F05D2240/81 , F05D2260/201 , Y02T50/676
摘要： A turbine nozzle includes hollow nozzle vanes mounted between outer and inner bands. The inner band includes an integral skirt around the perimeter thereof. A backing sheet of a honeycomb seal is mounted to the skirt to define a cavity therein. The inner band includes supply apertures for providing cooling air into the cavity, and the skirt includes forward and aft purge holes for discharging the cooling air therefrom. During operation, the air channeled through the cavity cools the backside of the inner band and is then discharged through the purge holes.
摘要翻译： 涡轮喷嘴包括安装在外带和内带之间的中空喷嘴叶片。 内带包括围绕其周边的整体裙部。 蜂窝密封件的背衬片安装到裙部以在其中限定空腔。 内带包括用于向空腔提供冷却空气的供应孔，并且裙部包括用于从其排出冷却空气的前吹气孔和后吹扫孔。 在操作过程中，通过空腔引导的空气冷却内带的背面，然后通过吹扫孔排出。
-
公开(公告)号：US06629817B2
公开(公告)日：2003-10-07
申请号：US09899305
申请日：2001-07-05
IPC分类号： F01D518
CPC分类号： F01D5/186 , Y10T29/49339 , Y10T29/49341
摘要： An airfoil for a gas turbine engine including an inflection that facilitates enhancing film cooling of the airfoil, without adversely affecting aerodynamic efficiency of airfoil is described. The airfoil includes a generally concave first sidewall and a generally convex second sidewall joined at a leading edge and at a trailing edge of the airfoil. A plurality of cooling openings extend between an internal cooling chamber and an external surface of the first sidewall. One cooling opening extends from the cooling chamber into the inflection at a relatively shallow injection angle with respect the airfoil external surface.
摘要翻译： 描述了一种用于燃气涡轮发动机的翼型件，其包括有助于增强翼型件的薄膜冷却的拐点，而不会不利地影响翼型件的空气动力学效率。 翼型件包括大致凹入的第一侧壁和在翼型件的前缘和后缘处连接的大致凸形的第二侧壁。 多个冷却开口在内部冷却室和第一侧壁的外表面之间延伸。 一个冷却开口以相对于翼型件外表面的相对浅的注入角度从冷却室延伸到拐点。
-
-
-
-
-
搜索结果
6 条记录 (耗时 0.052 秒)