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1. 发明申请

US20120177503A1 COMPONENT COOLING CHANNEL 有权
标题翻译：组件冷却通道
公开(公告)号：US20120177503A1
公开(公告)日：2012-07-12
申请号：US12985553
申请日：2011-01-06
申请人： Ching-Pang Lee , John J. Marra , Gary B. Merrill , Benjamine E. Heneveld , Jill Klinger
发明人： Ching-Pang Lee , John J. Marra , Gary B. Merrill , Benjamine E. Heneveld , Jill Klinger
IPC分类号： F01D5/18 , F28F7/00
CPC分类号： F01D5/18 , F01D5/187 , F05D2240/304 , F05D2250/13 , F05D2260/2214 , F28F3/048 , F28F7/02
摘要： A cooling channel (36, 36B) cools an exterior surface (40 or 42) or two opposed exterior surfaces (40 and 42). The channel has a near-wall inner surface (48, 50) with a width (W1). Interior side surfaces (52, 54) may converge to a reduced channel width (W2). The near-wall inner surface (48, 50) may have fins (44) aligned with a coolant flow (22). The fins may highest at mid-width of the near-wall inner surface. A two-sided cooling channel (36) may have two near-wall inner surfaces (48, 50) parallel to two respective exterior surfaces (40, 42), and may have an hourglass shaped transverse sectional profile. The tapered channel width (W1, W2) and the fin height profile (56A, 56B) increases cooling flow (22) into the corners (C) of the channel for more uniform and efficient cooling.
摘要翻译：冷却通道（36,36B）冷却外表面（40或42）或两个相对的外表面（40和42）。通道具有宽度（W1）的近壁内表面（48,50）。内侧表面（52,54）可以会聚到减小的通道宽度（W2）。近壁内表面（48,50）可以具有与冷却剂流（22）对准的翅片（44）。翅片在近壁内表面的中间宽度处可能最高。双面冷却通道（36）可以具有两个平行于两个相应的外表面（40,42）的近壁内表面（48,50），并且可以具有沙漏形横截面轮廓。锥形通道宽度（W1，W2）和翅片高度轮廓（56A，56B）将冷却流（22）增加到通道的拐角（C），以实现更均匀和有效的冷却。

2. 发明授权

US08764394B2 Component cooling channel 有权
标题翻译：组件冷却通道
公开(公告)号：US08764394B2
公开(公告)日：2014-07-01
申请号：US12985553
申请日：2011-01-06
申请人： Ching-Pang Lee , John J. Marra , Gary B. Merrill , Benjamin E. Heneveld , Jill Klinger
发明人： Ching-Pang Lee , John J. Marra , Gary B. Merrill , Benjamin E. Heneveld , Jill Klinger
IPC分类号： F01D5/18 , F28F3/04 , F28F7/02
CPC分类号： F01D5/18 , F01D5/187 , F05D2240/304 , F05D2250/13 , F05D2260/2214 , F28F3/048 , F28F7/02
摘要： A cooling channel (36, 36B) cools an exterior surface (40 or 42) or two opposed exterior surfaces (40 and 42). The channel has a near-wall inner surface (48, 50) with a width (W1). Interior side surfaces (52, 54) may converge to a reduced channel width (W2). The near-wall inner surface (48, 50) may have fins (44) aligned with a coolant flow (22). The fins may highest at mid-width of the near-wall inner surface. A two-sided cooling channel (36) may have two near-wall inner surfaces (48, 50) parallel to two respective exterior surfaces (40, 42), and may have an hourglass shaped transverse sectional profile. The tapered channel width (W1, W2) and the fin height profile (56A, 56B) increases cooling flow (22) into the corners (C) of the channel for more uniform and efficient cooling.
摘要翻译：冷却通道（36,36B）冷却外表面（40或42）或两个相对的外表面（40和42）。通道具有宽度（W1）的近壁内表面（48,50）。内侧表面（52,54）可以会聚到减小的通道宽度（W2）。近壁内表面（48,50）可以具有与冷却剂流（22）对准的翅片（44）。翅片在近壁内表面的中间宽度处可能最高。双面冷却通道（36）可以具有两个平行于两个相应的外表面（40,42）的近壁内表面（48,50），并且可以具有沙漏形横截面轮廓。锥形通道宽度（W1，W2）和翅片高度轮廓（56A，56B）将冷却流（22）增加到通道的拐角（C），以实现更均匀和有效的冷却。

3. 发明申请

US20150003973A1 AFT OUTER RIM SEAL ARRANGEMENT 有权
标题翻译： AFT外部RIM密封安排
公开(公告)号：US20150003973A1
公开(公告)日：2015-01-01
申请号：US13930482
申请日：2013-06-28
申请人： Ching-Pang Lee , Kok-Mun Tham , Eric Schroeder , Jamie Meeroff , Samuel R. Miller, Jr. , John J. Marra , Christian X. Campbell
发明人： Ching-Pang Lee , Kok-Mun Tham , Eric Schroeder , Jamie Meeroff , Samuel R. Miller, Jr. , John J. Marra , Christian X. Campbell
IPC分类号： F01D11/02 , F01D5/18
CPC分类号： F01D11/02 , F01D5/082 , F01D5/18 , F01D5/187 , F01D11/04 , F05D2260/14
摘要： An outer rim seal arrangement (10), including: an annular rim (70) centered about a longitudinal axis (30) of a rotor disc (31), extending fore and having a fore-end (72), an outward-facing surface (74), and an inward-facing surface (76); a lower angel wing (62) extending aft from a base of a turbine blade (22) and having an aft end (64) disposed radially inward of the rim inward-facing surface to define a lower angel wing seal gap (80); an upper angel wing (66) extending aft from the turbine blade base and having an aft end (68) disposed radially outward of the rim outward-facing surface to define a upper angel wing seal gap (80, 82); and guide vanes (100) disposed on the rim inward-facing surface in the lower angel wing seal gap. Pumping fins (102) may be disposed on the upper angel wing seal aft end in the upper angel wing seal gap.
摘要翻译：外缘密封装置（10），包括：以转子盘（31）的纵向轴线（30）为中心的环形边缘（70），其在前面延伸并具有前端（72），面向外的表面（74）和面向内的表面（76）; 从天线叶片（22）的底部向后延伸的下部天使翼（62），并且具有设置在所述边缘向内相对表面的径向内侧的后端（64），以限定下部天使翼密封间隙（80）; 从所述涡轮叶片基部向后延伸的上天使翼（66），并且具有设置在所述轮缘朝外的表面的径向外侧的后端（68），以限定上天使翼密封间隙（80,82）; 以及设置在下天使翼密封间隙中的边缘向内表面上的导向叶片（100）。抽吸翼（102）可以设置在上天使翼密封间隙中的上天使翼密封后端。

4. 发明申请

US20130156579A1 AMBIENT AIR COOLING ARRANGEMENT HAVING A PRE-SWIRLER FOR GAS TURBINE ENGINE BLADE COOLING 有权
标题翻译：具有用于气体涡轮发动机叶片冷却器的预吹扫器的环境空气冷却装置
公开(公告)号：US20130156579A1
公开(公告)日：2013-06-20
申请号：US13766909
申请日：2013-02-14
申请人： Ching-Pang Lee , Kok-Mun Tham , Eric Schroeder , Jamie Meeroff , Samuel R. Miller, JR. , John J. Marra
发明人： Ching-Pang Lee , Kok-Mun Tham , Eric Schroeder , Jamie Meeroff , Samuel R. Miller, JR. , John J. Marra
IPC分类号： F01D5/18 , F01D25/12
CPC分类号： F01D5/187 , F01D5/082 , F01D5/143 , F01D9/065 , F01D11/001 , F01D25/12 , F02C7/12 , F05D2240/127
摘要： A gas turbine engine including: an ambient-air cooling circuit (10) having a cooling channel (26) disposed in a turbine blade (22) and in fluid communication with a source (12) of ambient air: and an pre-swirler (18), the pre-swirler having: an inner shroud (38); an outer shroud (56); and a plurality of guide vanes (42), each spanning from the inner shroud to the outer shroud. Circumferentially adjacent guide vanes (46, 48) define respective nozzles (44) there between. Forces created by a rotation of the turbine blade motivate ambient air through the cooling circuit. The pre-swirler is configured to impart swirl to ambient air drawn through the nozzles and to direct the swirled ambient air toward a base of the turbine blade. The end walls (50, 54) of the pre-swirler may be contoured.
摘要翻译：一种燃气涡轮发动机，包括：环境空气冷却回路（10），其具有设置在涡轮机叶片（22）中并与环境空气源（12）流体连通的冷却通道（26）;以及预旋流器 18），所述预旋转器具有：内罩（38）; 外护罩（56）; 以及多个导向叶片（42），每个导向叶片从内护罩跨越到外护罩。周向相邻的导向叶片（46,48）在其间限定相应的喷嘴（44）。通过涡轮叶片的旋转产生的力通过冷却回路激励环境空气。预旋流器被配置为对通过喷嘴抽吸的环境空气赋予涡流，并且将旋转的环境空气引导到涡轮叶片的基部。预旋转器的端壁（50,54）可以是轮廓。

5. 发明申请

US20120269647A1 COOLED AIRFOIL IN A TURBINE ENGINE 有权
标题翻译：涡轮发动机冷却空气
公开(公告)号：US20120269647A1
公开(公告)日：2012-10-25
申请号：US13090294
申请日：2011-04-20
申请人： Paul H. Vitt , David A. Kemp , Ching-Pang Lee , John J. Marra
发明人： Paul H. Vitt , David A. Kemp , Ching-Pang Lee , John J. Marra
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D5/188 , F05D2250/30 , F05D2260/221 , F05D2260/941
摘要： An airfoil in a gas turbine engine includes an outer wall and an inner wall. The outer wall includes a leading edge, a trailing edge opposed from the leading edge in a chordal direction, a pressure side, and a suction side. The inner wall is coupled to the outer wall at a single chordal location and includes portions spaced from the pressure and suction sides of the outer wall so as to form first and second gaps between the inner wall and the respective pressure and suction sides. The inner wall defines a chamber therein and includes openings that provide fluid communication between the respective gaps and the chamber. The gaps receive cooling fluid that provides cooling to the outer wall as it flows through the gaps. The cooling fluid, after traversing at least substantial portions of the gaps, passes into the chamber through the openings in the inner wall.
摘要翻译：燃气涡轮发动机中的翼型件包括外壁和内壁。外壁包括前缘，从前缘朝向方向相对的后缘，压力侧和吸力侧。内壁在单个弦位置处联接到外壁，并且包括与外壁的压力和吸力侧隔开的部分，以便在内壁和相应的压力和吸力侧之间形成第一和第二间隙。内壁在其中限定一个室，并且包括在相应间隙和室之间提供流体连通的开口。间隙接收冷却流体，当其流过间隙时，向外壁提供冷却。冷却流体在穿过至少大部分间隙之后通过内壁中的开口进入腔室。

6. 发明授权

US09017014B2 Aft outer rim seal arrangement 有权
标题翻译：后外缘密封布置
公开(公告)号：US09017014B2
公开(公告)日：2015-04-28
申请号：US13930482
申请日：2013-06-28
申请人： Ching-Pang Lee , Kok-Mun Tham , Eric Schroeder , Jamie Meeroff , Samuel R. Miller, Jr. , John J. Marra , Christian X. Campbell
发明人： Ching-Pang Lee , Kok-Mun Tham , Eric Schroeder , Jamie Meeroff , Samuel R. Miller, Jr. , John J. Marra , Christian X. Campbell
IPC分类号： F01D11/08 , F01D25/12 , F01D11/02 , F01D5/18
CPC分类号： F01D11/02 , F01D5/082 , F01D5/18 , F01D5/187 , F01D11/04 , F05D2260/14
摘要： An outer rim seal arrangement (10), including: an annular rim (70) centered about a longitudinal axis (30) of a rotor disc (31), extending fore and having a fore-end (72), an outward-facing surface (74), and an inward-facing surface (76); a lower angel wing (62) extending aft from a base of a turbine blade (22) and having an aft end (64) disposed radially inward of the rim inward-facing surface to define a lower angel wing seal gap (80); an upper angel wing (66) extending aft from the turbine blade base and having an aft end (68) disposed radially outward of the rim outward-facing surface to define a upper angel wing seal gap (80, 82); and guide vanes (100) disposed on the rim inward-facing surface in the lower angel wing seal gap. Pumping fins (102) may be disposed on the upper angel wing seal aft end in the upper angel wing seal gap.
摘要翻译：外缘密封装置（10），包括：以转子盘（31）的纵向轴线（30）为中心的环形边缘（70），其在前面延伸并具有前端（72），面向外的表面（74）和面向内的表面（76）; 从天线叶片（22）的底部向后延伸的下部天使翼（62），并且具有设置在所述边缘向内相对表面的径向内侧的后端（64），以限定下部天使翼密封间隙（80）; 从所述涡轮叶片基部向后延伸的上天使翼（66），并且具有设置在所述轮缘朝外的表面的径向外侧的后端（68），以限定上天使翼密封间隙（80,82）; 以及设置在下天使翼密封间隙中的边缘向内表面上的导向叶片（100）。抽吸翼（102）可以设置在上天使翼密封间隙中的上天使翼密封后端。

7. 发明授权

US08894367B2 Compound cooling flow turbulator for turbine component 有权
标题翻译：用于涡轮机部件的复合式冷却流动紊流器
公开(公告)号：US08894367B2
公开(公告)日：2014-11-25
申请号：US12884464
申请日：2010-09-17
申请人： Ching-Pang Lee , Nan Jiang , John J. Marra , Ronald J. Rudolph
发明人： Ching-Pang Lee , Nan Jiang , John J. Marra , Ronald J. Rudolph
IPC分类号： F01D5/18
CPC分类号： F01D5/18 , F01D5/187 , F05D2250/181 , F05D2250/60 , F05D2250/611 , F05D2250/70 , F05D2250/711 , F05D2250/712 , F05D2260/2212 , F05D2260/22141
摘要： Multi-scale turbulation features, including first turbulators (46, 48) on a cooling surface (44), and smaller turbulators (52, 54, 58, 62) on the first turbulators. The first turbulators may be formed between larger turbulators (50). The first turbulators may be alternating ridges (46) and valleys (48). The smaller turbulators may be concave surface features such as dimples (62) and grooves (54), and/or convex surface features such as bumps (58) and smaller ridges (52). An embodiment with convex turbulators (52, 58) in the valleys (48) and concave turbulators (54, 62) on the ridges (46) increases the cooling surface area, reduces boundary layer separation, avoids coolant shadowing and stagnation, and reduces component mass.
摘要翻译：多尺度紊流特征，包括在冷却表面（44）上的第一湍流器（46,48）和在第一湍流器上的较小湍流器（52,54,58,62）。可以在较大的湍流器（50）之间形成第一湍流器。第一个紊流器可以是交替的脊（46）和谷（48）。较小的湍流器可以是诸如凹坑（62）和凹槽（54）的凹表面特征，和/或诸如凸块（58）和较小脊（52）的凸表面特征。在脊（46）上的谷（48）和凹形湍流器（54,62）中具有凸起的湍流器（52,58）的实施例增加了冷却表面面积，减少了边界层分离，避免了冷却剂遮蔽和停滞，并且减少了部件质量

8. 发明申请

US20110171023A1 AIRFOIL INCORPORATING TAPERED COOLING STRUCTURES DEFINING COOLING PASSAGEWAYS 有权
标题翻译：定义冷却通道的飞轮冷却结构
公开(公告)号：US20110171023A1
公开(公告)日：2011-07-14
申请号：US12908029
申请日：2010-10-20
申请人： Ching-Pang Lee , John J. Marra
发明人： Ching-Pang Lee , John J. Marra
IPC分类号： F01D5/18 , B28B7/28
CPC分类号： F01D5/187 , B22C9/103 , F05D2230/21 , F05D2240/122 , F05D2240/304 , F05D2250/18 , F05D2250/292
摘要： A gas turbine engine (10) and an airfoil (50) for use therein, the airfoil (50) having a structure (128) containing cooling passageways (110, 120) extending between a chamber (100) and a series of apertures (78) positioned along the trailing edge (72) through which cooling fluid (144) received from the chamber (100) exits the airfoil (50), wherein the structure (128) is characterized by a variable thickness (t) between the pressure and suction sidewalls (74, 76) of the airfoil as a function of position along the cooling passageways (110, 120) such that each in a plurality of cooling passageways are characterized by a cross sectional flow area (170, 174) which decreases as a function of distance from the chamber (100).
摘要翻译：一种用于其中的燃气涡轮发动机（10）和翼型件（50），所述翼型件（50）具有包括在室（100）和一系列孔（78）之间延伸的冷却通道（110,120）的结构），其沿着所述后缘（72）定位，冷却流体（144）从所述腔室（100）接收的所述后缘离开所述翼型件（50），其中所述结构（128）的特征在于所述压力和抽吸作为沿着冷却通道（110,120）的位置的函数的翼型件的侧壁（74,76），使得在多个冷却通道中的每一个的特征在于作为功能而减小的横截面流动面积（170,174）距离室（100）的距离。

9. 发明授权

US09022736B2 Integrated axial and tangential serpentine cooling circuit in a turbine airfoil 有权
标题翻译：涡轮机翼中集成的轴向和切向蛇形冷却回路
公开(公告)号：US09022736B2
公开(公告)日：2015-05-05
申请号：US13027333
申请日：2011-02-15
申请人： Ching-Pang Lee , Nan Jiang , John J. Marra , Ronald J. Rudolph , John P. Dalton
发明人： Ching-Pang Lee , Nan Jiang , John J. Marra , Ronald J. Rudolph , John P. Dalton
IPC分类号： F01D5/18
CPC分类号： F01D5/188 , F01D5/186 , F01D5/187 , F05D2250/185 , F05D2260/2212
摘要： A continuous serpentine cooling circuit forming a progression of radial passages (44, 45, 46, 47A, 48A) between pressure and suction side walls (52, 54) in a MID region of a turbine airfoil (24). The circuit progresses first axially, then tangentially, ending in a last radial passage (48A) adjacent to the suction side (54) and not adjacent to the pressure side (52). The passages of the axial progression (44, 45, 46) may be adjacent to both the pressure and suction side walls of the airfoil. The next to last radial passage (47A) may be adjacent to the pressure side wall and not adjacent to the suction side wall. The last two radial passages (47A, 48A) may be longer along the pressure and suction side walls respectively than they are in a width direction, providing increased direct cooling surface area on the interiors of these hot walls.
摘要翻译：连续的蛇形冷却回路，形成在涡轮机翼型件（24）的MID区域中的压力和吸力侧壁（52,54）之间的径向通道（44,45,46,47A，48A）的进展。电路首先轴向前进，然后切向地结束于邻近吸力侧（54）并且不与压力侧（52）相邻的最后一个径向通道（48A）。轴向行进（44,45,46）的通道可以与翼型件的压力和吸力侧壁相邻。最后一个径向通道（47A）的下一个可以与压力侧壁相邻并且不与吸力侧壁相邻。最后两个径向通道（47A，48A）可以沿着压力和吸力侧壁分别比在宽度方向上更长，从而在这些热壁的内部提供增加的直接冷却表面积。

10. 发明授权

US09011077B2 Cooled airfoil in a turbine engine 有权
标题翻译：涡轮发动机冷却翼型
公开(公告)号：US09011077B2
公开(公告)日：2015-04-21
申请号：US13090294
申请日：2011-04-20
申请人： Paul H. Vitt , David A. Kemp , Ching-Pang Lee , John J. Marra
发明人： Paul H. Vitt , David A. Kemp , Ching-Pang Lee , John J. Marra
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D5/188 , F05D2250/30 , F05D2260/221 , F05D2260/941
摘要： An airfoil in a gas turbine engine includes an outer wall and an inner wall. The outer wall includes a leading edge, a trailing edge opposed from the leading edge in a chordal direction, a pressure side, and a suction side. The inner wall is coupled to the outer wall at a single chordal location and includes portions spaced from the pressure and suction sides of the outer wall so as to form first and second gaps between the inner wall and the respective pressure and suction sides. The inner wall defines a chamber therein and includes openings that provide fluid communication between the respective gaps and the chamber. The gaps receive cooling fluid that provides cooling to the outer wall as it flows through the gaps. The cooling fluid, after traversing at least substantial portions of the gaps, passes into the chamber through the openings in the inner wall.
摘要翻译：燃气涡轮发动机中的翼型件包括外壁和内壁。外壁包括前缘，从前缘朝向方向相对的后缘，压力侧和吸力侧。内壁在单个弦位置处联接到外壁，并且包括与外壁的压力和吸力侧隔开的部分，以便在内壁和相应的压力和吸力侧之间形成第一和第二间隙。内壁在其中限定一个室，并且包括在相应间隙和室之间提供流体连通的开口。间隙接收冷却流体，当其流过间隙时，向外壁提供冷却。冷却流体在穿过至少大部分间隙之后通过内壁中的开口进入腔室。

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