公开(公告)号：US5141393A

公开(公告)日：1992-08-25

申请号：US753542

申请日：1991-09-03

申请人： John J. Marra

发明人： John J. Marra

IPC分类号： F01D11/00 ,  F01D11/16 ,  F01D25/24

CPC分类号： F01D11/005 ,  F01D11/16 ,  F01D25/246 ,  F05D2230/642 ,  F05D2240/11 ,  Y10T403/21 ,  Y10T403/32951

摘要： A casing around a turbine and a casing around discharge nozzles have a concentrically arranged shell portion. The seal contains internal pressure while accommodating eccentric, expansion and axial travel. Arcuate seal segments have one leg sealing against a radial surface extending from the inner shell and the other leg against the outer shell. A linkage guides travel of the segments.

摘要翻译： 围绕涡轮机的壳体和围绕排出喷嘴的壳体具有同心布置的壳部分。 密封件包含内部压力，同时容纳偏心，膨胀和轴向移动。 弧形密封段具有一个脚部，其抵靠从内壳和另一个腿部抵靠外壳延伸的径向表面。 A连杆引导段的行程。

公开(公告)号：US4835827A

公开(公告)日：1989-06-06

申请号：US228898

申请日：1988-08-05

申请人： John J. Marra

发明人： John J. Marra

IPC分类号： F01D5/02 ,  F16F15/34

CPC分类号： F16F15/34 ,  F01D5/027 ,  Y10T29/4932 ,  Y10T29/49764 ,  Y10T464/50

摘要： A balance ring (18) which is shrunk fit within each disk (12) of a rotor is selectively ground for detail balance. A plurality of openings (20) through the outer edge of the balance ring receive weights during the assembly balance of the rotor. A snap ring (44) retains the weights within the openings. An eccentric inwardly extending raised area 26 throughout a substantial minority of the circumference provides for initial gross unbalance correction upon installation.

摘要翻译： 在转子的每个盘（12）内收缩的平衡环（18）被选择性地研磨以便细节平衡。 通过平衡环的外缘的多个开口（20）在转子的组装平衡期间容纳重物。 卡环（44）将重物保持在开口内。 穿过整个圆周的大部分的偏心的向内延伸的凸起部分26提供安装时的初始总不平衡校正。

公开(公告)号：US4784012A

公开(公告)日：1988-11-15

申请号：US94214

申请日：1987-09-08

申请人： John J. Marra

发明人： John J. Marra

IPC分类号： F01D5/02 ,  F16F15/34 ,  F16F15/22 ,  F01D5/10

CPC分类号： F16F15/34 ,  F01D5/027

摘要： A balance ring (18) which is shrunk fit within each disk (12) of a rotor is selectively ground for detail balance. A plurality of openings (20) through the outer edge of the balance ring receive weights during the assembly balance of the rotor. A snap ring (44) retains the weights within the openings. An eccentric inwardly extending raised area (26) throughout a substantial minority of the circumference provides for initial gross unbalance correction upon installation.

摘要翻译： 在转子的每个盘（12）内收缩的平衡环（18）被选择性地研磨以便细节平衡。 通过平衡环的外缘的多个开口（20）在转子的组装平衡期间容纳重物。 卡环（44）将重物保持在开口内。 整个圆周的大部分的偏心向内延伸的凸起区域（26）提供安装时的初始总不平衡校正。

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。

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。

公开(公告)号：US08920111B2

公开(公告)日：2014-12-30

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 ,  B22C9/10

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减小的横截面流动面积（170,174） 距离室（100）的距离。

公开(公告)号：US08714920B2

公开(公告)日：2014-05-06

申请号：US12752460

申请日：2010-04-01

申请人： Christian X. Campbell ,  Jay A. Morrison ,  Allister W. James ,  Raymond G. Snider ,  Daniel M. Eshak ,  John J. Marra ,  Brian J. Wessell

发明人： Christian X. Campbell ,  Jay A. Morrison ,  Allister W. James ,  Raymond G. Snider ,  Daniel M. Eshak ,  John J. Marra ,  Brian J. Wessell

IPC分类号： F01D1/02 ,  F04D29/54

CPC分类号： F01D11/005 ,  B22D19/00 ,  B22D19/0081 ,  F01D9/044 ,  F05D2230/21 ,  F05D2240/80

摘要： A turbine airfoil (31) with an end portion (42) that tapers (44) toward the end (43) of the airfoil. A ridge (46) extends around the end portion. It has proximal (66) and distal (67) sides. A shroud platform (50) is bi-cast onto the end portion around the ridge without bonding. Cooling shrinks the platform into compression (62) on the end portion (42) of the airfoil. Gaps between the airfoil and platform are formed using a fugitive material (56) in the bi-casting stage. These gaps are designed in combination with the taper angle (44) to accommodate differential thermal expansion while maintaining a gas seal along the contact surfaces. The taper angle (44) may vary from lesser on the pressure side (36) to greater on the suction side (38) of the airfoil. A collar portion (52) of the platform provides sufficient contact area for connection stability.

摘要翻译： 具有朝向翼型的端部（43）逐渐变细（44）的端部（42）的涡轮机翼（31）。 脊（46）围绕端部延伸。 它具有近端（66）和远端（67）侧面。 护罩平台（50）在没有粘合的情况下双向铸造在脊的端部上。 冷却将平台收缩在翼型件的端部（42）上的压缩（62）中。 翼型和平台之间的间隙是在双浇铸阶段使用一种短暂的材料（56）形成的。 这些间隙与锥角（44）结合设计，以适应不同的热膨胀，同时沿着接触表面保持气体密封。 锥形角（44）可以在翼型的吸力侧（38）上的压力侧（36）上较小地变化到更大。 平台的凸缘部分（52）为连接稳定性提供了足够的接触面积。

公开(公告)号：US08684692B2

公开(公告)日：2014-04-01

申请号：US13023651

申请日：2011-02-09

申请人： Clinton A. Mayer ,  Christian X. Campbell ,  Andrew Whalley ,  John J. Marra

发明人： Clinton A. Mayer ,  Christian X. Campbell ,  Andrew Whalley ,  John J. Marra

IPC分类号： F01D5/18 ,  F01D5/22

CPC分类号： F01D5/187 ,  F01D5/22 ,  F05D2260/221

摘要： A turbine blade assembly in a turbine engine. The turbine blade assembly includes a turbine blade and a first snubber structure. The turbine blade includes an internal cooling passage containing cooling air. The first snubber structure extends outwardly from a sidewall of the turbine blade and includes a hollow interior portion that receives cooling air from the internal cooling passage of the turbine blade.

摘要翻译： 涡轮发动机中的涡轮叶片组件。 涡轮叶片组件包括涡轮叶片和第一缓冲结构。 涡轮机叶片包括内部冷却通道，其包含冷却空气。 第一缓冲结构从涡轮机叶片的侧壁向外延伸并且包括从涡轮叶片的内部冷却通道接收冷却空气的中空内部部分。

公开(公告)号：US20130064667A1

公开(公告)日：2013-03-14

申请号：US13227603

申请日：2011-09-08

申请人： Christian X. Campbell ,  Darryl Eng ,  John J. Marra

发明人： Christian X. Campbell ,  Darryl Eng ,  John J. Marra

IPC分类号： F01D5/30

CPC分类号： F01D11/008 ,  F01D5/3007

摘要： Platforms (36, 38) span between turbine blades (23, 24, 25) on a disk (32). Each platform may be individually mounted to the disk by a pin attachment (42). Each platform (36) may have a rotationally rearward edge portion (50) that underlies a forward portion (45) of the adjacent platform (38). This limits centrifugal bending of the rearward portion of the platform, and provides coolant sealing. The rotationally forward edge (44A, 44B) of the platform overlies a seal element (51) on the pressure side (28) of the forwardly adjacent blade, and does not underlie a shelf on that blade. The pin attachment allows radial mounting of each platform onto the disk via tilting (60) of the platform during mounting to provide mounting clearance for the rotationally rearward edge portion (50). This facilitates quick platform replacement without blade removal.

公开(公告)号：US20120263575A1

公开(公告)日：2012-10-18

申请号：US13084618

申请日：2011-04-12

申请人： John J. Marra

发明人： John J. Marra

IPC分类号： F01D5/08

CPC分类号： F01D11/001 ,  F01D5/082 ,  F01D11/04

摘要： A low pressure cooling system for a turbine engine for directing cooling fluids at low pressure, such as at ambient pressure, through at least one cooling fluid supply channel and into a cooling fluid mixing chamber positioned immediately downstream from a row of turbine blades extending radially outward from a rotor assembly to prevent ingestion of hot gases into internal aspects of the rotor assembly. The low pressure cooling system may also include at least one bleed channel that may extend through the rotor assembly and exhaust cooling fluids into the cooling fluid mixing chamber to seal a gap between rotational turbine blades and a downstream, stationary turbine component. Use of ambient pressure cooling fluids by the low pressure cooling system results in tremendous efficiencies by eliminating the need for pressurized cooling fluids for sealing this gap.

摘要翻译： 一种用于涡轮发动机的低压冷却系统，用于将低温（例如环境压力）的冷却流体引导通过至少一个冷却流体供应通道并且进入冷却流体混合室，所述冷却流体混合室位于从一排径向向外延伸的涡轮叶片的下游 来自转子组件以防止将热气体摄入到转子组件的内部方面。 低压冷却系统还可以包括至少一个排放通道，其可以延伸穿过转子组件并将冷却流体排出到冷却流体混合室中，以密封旋转涡轮叶片与下游固定涡轮机部件之间的间隙。 通过低压冷却系统使用环境压力的冷却流体，通过消除对用于密封该间隙的加压冷却流体的需要而产生巨大的效率。