公开(公告)号：US07341427B2

公开(公告)日：2008-03-11

申请号：US11306221

申请日：2005-12-20

申请人： Andrew David Farmer ,  Bangalore Aswatha Nagaraj ,  Wenfeng Lu ,  Ching-Pang Lee ,  Joseph Michael Guentert

发明人： Andrew David Farmer ,  Bangalore Aswatha Nagaraj ,  Wenfeng Lu ,  Ching-Pang Lee ,  Joseph Michael Guentert

IPC分类号： F04D9/02

CPC分类号： F01D5/288 ,  F01D9/041 ,  F05D2220/31 ,  F05D2230/21 ,  F05D2230/31 ,  F05D2230/90 ,  F05D2260/95 ,  F05D2300/15 ,  F05D2300/611

摘要： A gas turbine engine nozzle segment and process for producing such a nozzle segment to exhibit improved durability and aerodynamic performance. The process produces a nozzle segment having at least one vane between and interconnecting a pair of platforms. The nozzle segment is cast from a gamma prime-strengthened nickel-base superalloy, on whose surface is thermal sprayed an environmental coating formed of a MCrAlX-type coating material. The surface of the environmental coating is then worked to cause the coating to have a surface finish of less than 2.0 micrometers Ra. Cooling holes are then drilled in the nozzle segment, after which an oxidation-resistant coating is applied on the smoothed surface of the nozzle segment so as to maintain an outermost surface on the nozzle segment having surface finish of less than 2.0 micrometers Ra.

摘要翻译： 一种燃气涡轮发动机喷嘴段和用于生产这种喷嘴段的工艺，以显示出改善的耐久性和空气动力性能。 该过程产生具有在一对平台之间并互连的至少一个叶片的喷嘴段。 喷嘴段由伽马强化镍基超级合金铸造，其表面被热喷涂为由MCrAlX型涂层材料形成的环境涂层。 然后对环境涂层的表面进行加工，使涂层的表面光洁度小于2.0微米。 然后在喷嘴段中钻出冷却孔，然后在喷嘴段的平滑表面上施加耐氧化涂层，以便保持表面光洁度小于2.0微米Ra的喷嘴段上的最外表面。

公开(公告)号：US07140835B2

公开(公告)日：2006-11-28

申请号：US10956299

申请日：2004-10-01

申请人： Ching-Pang Lee ,  Baolan Shi ,  Wenfeng Lu ,  Joseph Michael Guentert ,  Steven Robert Brassfield

发明人： Ching-Pang Lee ,  Baolan Shi ,  Wenfeng Lu ,  Joseph Michael Guentert ,  Steven Robert Brassfield

IPC分类号： F01D9/02

CPC分类号： F01D5/187 ,  F05D2240/81 ,  Y02T50/671 ,  Y02T50/673 ,  Y02T50/676

摘要： A turbine nozzle includes a hollow vane joined to opposite inner and outer bands. The inner band includes a forward lip under the leading edge of the vane, an aft lip under the trailing edge of the vane, and a mounting flange spaced therebetween. An impingement bore extends obliquely and aft from the base of the mounting flange under a corner of the inner band toward the aft lip for impingement cooling thereof.

摘要翻译： 涡轮喷嘴包括连接到相对的内部和外部带的中空叶片。 内带包括在叶片的前缘下方的前唇，在叶片的后缘下方的后唇，以及间隔开的安装凸缘。 冲击孔从安装凸缘的底部在内带的角部向后缘倾斜地向后延伸，用于冲​​击冷却。

公开(公告)号：US07371046B2

公开(公告)日：2008-05-13

申请号：US11160010

申请日：2005-06-06

申请人： Ching-Pang Lee ,  Joseph Michael Guentert ,  James Robert Bailey

发明人： Ching-Pang Lee ,  Joseph Michael Guentert ,  James Robert Bailey

IPC分类号： F04D29/54

CPC分类号： F01D5/143 ,  F05D2240/121 ,  F05D2240/122 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2240/80 ,  Y02T50/673

摘要： A turbine airfoil may be a rotating blade having a single platform, or a stationary nozzle having a pair of platforms. The airfoil body has pressure and suction sidewalls extending between leading and trailing edges. A compound fillet is disposed between the airfoil body and at least one of the platforms. The compound fillet includes a concave first fillet having a first radius, and a concave second fillet having a second, greater radius. The second fillet extends from the leading edge downstream along the suction sidewall and terminates at a point upstream of the trailing edge. The second fillet may also extend downstream from the leading edge along the pressure sidewall.

摘要翻译： 涡轮机翼片可以是具有单个平台的旋转叶片或具有一对平台的固定喷嘴。 机翼本体具有在前缘和后缘之间延伸的压力和吸力侧壁。 在翼型件本体和至少一个平台之间设置复合内圆角。 复合圆角包括具有第一半径的凹入的第一圆角和具有第二较大半径的凹入的第二圆角。 第二圆角从前缘沿着吸力侧壁向下游延伸，并终止在后缘上游的一个点处。 第二圆角也可以沿着压力侧壁从前缘的下游延伸。

公开(公告)号：US20080080968A1

公开(公告)日：2008-04-03

申请号：US11538273

申请日：2006-10-03

申请人： Joseph Michael Guentert ,  Ching-Pang Lee

发明人： Joseph Michael Guentert ,  Ching-Pang Lee

IPC分类号： F01D25/26

CPC分类号： F01D25/246 ,  F01D11/005 ,  F05D2240/57

摘要： A method for assembling a gas turbine engine is provided. The method includes providing a turbine nozzle including an outer band and an inner band, wherein each band includes a leading edge, a trailing edge, and a body extending therebetween. At least one of the outer band and the inner band has at least one radial tab extending outward therefrom. The method also includes coupling at least one seal between at least one of the radial tabs extending from the outer band and the inner band and a respective leading edge of the outer and inner band. The method also includes positioning at least one non-planar seal support against at least one portion of the seal.

摘要翻译： 提供一种用于组装燃气涡轮发动机的方法。 该方法包括提供包括外带和内带的涡轮喷嘴，其中每个带包括前缘，后缘和在其间延伸的本体。 外带和内带中的至少一个具有从其向外延伸的至少一个径向突片。 该方法还包括在从外带和内带延伸的至少一个径向突片和外带和内带的相应前缘之间联接至少一个密封件。 该方法还包括将至少一个非平面密封支撑件定位在密封件的至少一部分上。