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1. 发明授权

US09366144B2 Trailing edge cooling 有权
标题翻译：后缘冷却
公开(公告)号：US09366144B2
公开(公告)日：2016-06-14
申请号：US13424752
申请日：2012-03-20
申请人： Gary A. Zess , Brandon W. Spangler , Dominic J. Mongillo, Jr.
发明人： Gary A. Zess , Brandon W. Spangler , Dominic J. Mongillo, Jr.
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/304 , F05D2260/2212 , F05D2260/22141 , Y02T50/673 , Y02T50/676 , Y10T29/49337
摘要： An airfoil includes a leading edge, a trailing edge, a suction surface, a pressure surface, a cooling passageway, and a plurality of oblong pedestals. The suction surface and the pressure surface both extend axially between the leading edge and the trailing edge, as well as radially from a root section to a tip section of the airfoil. The cooling passageway is located between the suction surface and the pressure surface. The oblong pedestals connect the suction surface to the pressure surface at the trailing edge of the airfoil.
摘要翻译：翼型件包括前缘，后缘，吸力表面，压力表面，冷却通道和多个长方形基座。抽吸表面和压力表面两者都在前缘和后缘之间轴向延伸，并且从根部到径向从翼型的尖端部延伸。冷却通道位于吸力表面和压力表面之间。长方形基座将抽吸表面连接到翼型的后缘处的压力表面。

2. 发明授权

US06969232B2 Flow directing device 有权
标题翻译：导流装置
公开(公告)号：US06969232B2
公开(公告)日：2005-11-29
申请号：US10065484
申请日：2002-10-23
申请人： Gary A. Zess , Joel Wagner
发明人： Gary A. Zess , Joel Wagner
IPC分类号： F01D5/14 , F01D9/02 , F01D9/04 , F02C7/00 , F04D29/54 , F04D29/68
CPC分类号： F01D5/145 , F01D5/143 , F01D9/04 , F04D29/544 , F04D29/681 , F05D2250/14 , F05D2250/184 , F05D2250/71 , Y02T50/673 , Y10S415/914
摘要： A flow directing device of a gas turbine engine, comprising: an airfoil having a leading edge, trailing edge, suction side and pressure side; a wall abutting the airfoil; and a fillet between the airfoil and wall. The fillet has an enlarged section at the leading edge, along the suction and pressure sides, and towards the trailing edge. The device could be part of a vane segment. In addition to eliminating a horseshoe vortex, the device also reduces heat load on the airfoil by directing the cooler gas from the proximal end of the airfoil to the hotter gas at the medial section of the airfoil.
摘要翻译：一种燃气涡轮发动机的流动引导装置，包括：具有前缘，后缘，吸力侧和压力侧的翼型; 邻接翼面的墙壁; 和翼型与墙壁之间的圆角。圆角在前缘处具有放大的截面，沿着吸力和压力侧，并且朝向后缘。该装置可以是叶片段的一部分。除了消除马蹄形涡流之外，该装置还通过将较冷气体从翼型的近端引导到翼型的中间部分的较热的气体来减少翼型件的热负荷。

3. 发明授权

US06419446B1 Apparatus and method for inhibiting radial transfer of core gas flow within a core gas flow path of a gas turbine engine 有权
标题翻译：用于抑制燃气涡轮发动机的核心气体流动路径内的核心气体流的径向传递的装置和方法
公开(公告)号：US06419446B1
公开(公告)日：2002-07-16
申请号：US09468751
申请日：1999-12-21
申请人： William A. Kvasnak , Friedrich O. Soechting , Karen A. Thole , Gary A. Zess
发明人： William A. Kvasnak , Friedrich O. Soechting , Karen A. Thole , Gary A. Zess
IPC分类号： F01D904
CPC分类号： F01D9/041 , F01D5/145 , Y10S415/914
摘要： A method for inhibiting radial transfer of core gas flow away from a center radial region and toward the inner and outer radial boundaries of a core gas flow path within a gas turbine engine is provided that includes the steps of: (1) providing a flow directing structure that includes an airfoil that abuts a wall surface, said airfoil having a leading edge, a pressure side, and a suction side; and (2) increasing the velocity of the core gas flow in the area where the leading edge of the airfoil abuts the wall. Increasing the velocity of the core gas flow in the area where the leading edge of the airfoil abuts the wall impedes the formation of a pressure gradient along the surface of the airfoil that forces core gas from the center region of the core gas toward the wall. The apparatus includes apparatus for diverting core gas flow away from the area where the airfoil abuts the wall.
摘要翻译：提供了一种用于抑制核心气体流离开中心径向区域并朝向燃气涡轮发动机内的核心气体流动路径的内部和外部径向边界的径向转移的方法，其包括以下步骤：（1）提供流动导向包括邻接壁面的翼型的结构，所述翼型具有前缘，压力侧和吸力侧; 和（2）增加翼型件的前缘邻接壁的区域中的核心气流的速度。增加翼型件的前缘邻接壁的区域中的核心气流的速度阻碍沿着翼型的表面形成压力梯度，该压力梯度迫使核心气体从核心气体的中心区域朝向壁。该装置包括用于使核心气体流离开机翼抵靠壁的区域的装置。

4. 发明授权

US10100645B2 Trailing edge cooling configuration for a gas turbine engine airfoil 有权
公开(公告)号：US10100645B2
公开(公告)日：2018-10-16
申请号：US13584172
申请日：2012-08-13
申请人： Scott D. Lewis , Gary A. Zess
发明人： Scott D. Lewis , Gary A. Zess
IPC分类号： F01D5/18 , F01D5/28
摘要： An airfoil for a gas turbine engine includes pressure and suction surfaces provided by pressure and suction walls that extend in a radial direction and are joined at a leading edge and a trailing edge. A cooling passage is arranged between the pressure and suction walls and extends to the trailing edge. Elongated pedestals are arranged in the cooling passage and interconnect the pressure and suction walls. The elongated pedestals are spaced apart from one another in the radial direction and extend from a plane to the trailing edge. A metering pedestal includes at least a portion that is arranged between the plane and the trailing edge. The portion is provided between adjacent elongated pedestals in the radial direction.

5. 发明申请

US20140044555A1 TRAILING EDGE COOLING CONFIGURATION FOR A GAS TURBINE ENGINE AIRFOIL 审中-公开
标题翻译：用于气体涡轮发动机空气涡轮的跟踪边缘冷却配置
公开(公告)号：US20140044555A1
公开(公告)日：2014-02-13
申请号：US13584172
申请日：2012-08-13
申请人： Scott D. Lewis , Gary A. Zess
发明人： Scott D. Lewis , Gary A. Zess
IPC分类号： F01D5/18
CPC分类号： F01D5/18 , F01D5/187 , F01D5/288 , F05D2230/90 , F05D2240/127 , F05D2240/304 , F05D2260/2212 , F05D2260/22141 , Y02T50/676 , Y10T29/49341
摘要： An airfoil for a gas turbine engine includes pressure and suction surfaces provided by pressure and suction walls that extend in a radial direction and are joined at a leading edge and a trailing edge. A cooling passage is arranged between the pressure and suction walls and extends to the trailing edge. Elongated pedestals are arranged in the cooling passage and interconnect the pressure and suction walls. The elongated pedestals are spaced apart from one another in the radial direction and extend from a plane to the trailing edge. A metering pedestal includes at least a portion that is arranged between the plane and the trailing edge. The portion is provided between adjacent elongated pedestals in the radial direction.
摘要翻译：用于燃气涡轮发动机的翼型件包括由在径向方向上延伸并在前缘和后缘连接的压力和吸力壁提供的压力和吸力表面。冷却通道设置在压力和吸力壁之间并延伸到后缘。细长的基座布置在冷却通道中并互连压力和吸力壁。细长基座在径向上彼此间隔开并且从平面延伸到后缘。计量基座包括布置在平面和后缘之间的至少一部分。该部分在径向方向上设置在相邻的细长基座之间。

6. 发明申请

US20130251538A1 TRAILING EDGE COOLING 有权
标题翻译：拖车边缘冷却
公开(公告)号：US20130251538A1
公开(公告)日：2013-09-26
申请号：US13424752
申请日：2012-03-20
申请人： Gary A. Zess , Brandon W. Spangler , Dominic J. Mongillo, JR.
发明人： Gary A. Zess , Brandon W. Spangler , Dominic J. Mongillo, JR.
IPC分类号： F02C7/12 , B23P15/02 , F01D5/18
CPC分类号： F01D5/187 , F05D2240/304 , F05D2260/2212 , F05D2260/22141 , Y02T50/673 , Y02T50/676 , Y10T29/49337
摘要： An airfoil includes a leading edge, a trailing edge, a suction surface, a pressure surface, a cooling passageway, and a plurality of oblong pedestals. The suction surface and the pressure surface both extend axially between the leading edge and the trailing edge, as well as radially from a root section to a tip section of the airfoil. The cooling passageway is located between the suction surface and the pressure surface. The oblong pedestals connect the suction surface to the pressure surface at the trailing edge of the airfoil.
摘要翻译：翼型件包括前缘，后缘，吸力表面，压力表面，冷却通道和多个长方形基座。抽吸表面和压力表面两者都在前缘和后缘之间轴向延伸，并且从根部到径向从翼型的尖端部延伸。冷却通道位于吸力表面和压力表面之间。长方形基座将抽吸表面连接到翼型的后缘处的压力表面。

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