公开(公告)号：US20060083620A1

公开(公告)日：2006-04-20

申请号：US10966471

申请日：2004-10-15

Applicant: Michael Scheurlen ,  Xubin Gu

Inventor： Michael Scheurlen ,  Xubin Gu

IPC: F01D11/00

CPC classification number: F01D11/008 ,  F05D2240/57 ,  Y10S277/93

Abstract: A seal for sealing a seal groove in a shroud of a turbine vane. The seal may include a cooling system configured to pass cooling fluids through a cooling fluid supply port in a shroud, through a cooling system in which the cooling fluids contact the shroud and the seal, and exhaust the fluids through a gap between adjacent turbine vanes. The seal may include an elongated cooling channel for channeling cooling fluids from a supply to an exhaust channel at a first end. The cooling system may remove heat from the turbine vane shroud, the seal, and other related components, thereby reducing the likelihood of premature failure.

Abstract translation: 用于密封涡轮叶片的护罩中的密封槽的密封件。 密封件可以包括冷却系统，该冷却系统构造成使冷却流体通过冷却流体通过护罩中的冷却流体供应口，通过其中冷却流体接触护罩和密封件的冷却系统，并且通过相邻的涡轮叶片之间的间隙排出流体。 密封件可以包括细长的冷却通道，用于在第一端处将冷却流体从供应件引导到排气通道。 冷却系统可以从涡轮叶片护罩，密封件和其他相关部件移除热量，从而降低过早失效的可能性。

公开(公告)号：US08016562B2

公开(公告)日：2011-09-13

申请号：US11942885

申请日：2007-11-20

Applicant: Xubin Gu

Inventor： Xubin Gu

IPC: F01D5/20

CPC classification number: F01D5/187 ,  F01D5/20 ,  F05D2240/122 ,  F05D2240/304

Abstract: A turbine blade for a turbine engine having a cooling system in the turbine blade including a camber-line rib extending radially outward from a tip of the blade and extending from a trailing edge of the blade toward a leading edge. The camber-line rib may form pressure and suction side cooling slots at the tip of the blade. The camber-line rib my include a cooling channel positioned in the camber-line rib and in fluid communication with the at least one cavity forming the cooling system in the blade for cooling aspects of the tip at the trailing edge.

Abstract translation: 一种用于涡轮发动机的涡轮叶片，其具有在涡轮机叶片中的冷却系统，包括从叶片的尖端径向向外延伸并从叶片的后缘朝向前缘延伸的外倾线肋。 拱形肋可以在叶片的尖端处形成压力和吸力侧冷却槽。 弧形肋条包括一个定位在弧形肋条中的冷却通道，并且与至少一个空腔流体连通，形成叶片中的冷却系统，用于冷却在后缘处的尖端部分。

公开(公告)号：US20130259704A1

公开(公告)日：2013-10-03

申请号：US13436009

申请日：2012-03-30

Applicant: Luzeng Zhang ,  Xubin Gu ,  Juan Yin ,  Hee Koo Moon

Inventor： Luzeng Zhang ,  Xubin Gu ,  Juan Yin ,  Hee Koo Moon

IPC: F01D5/18

CPC classification number: F01D5/081 ,  F01D5/082 ,  F01D5/186 ,  F01D5/188 ,  F01D5/189 ,  F01D25/08 ,  F01D25/12

Abstract: A turbine blade for a gas turbine engine is disclosed. The turbine blade can include at least one internal cooling path, and an internal vane disposed in the at least one internal cooling path. The internal vane can include a central portion, a first leg extending in a first direction from the central portion, and a second leg extending in a second direction from the central portion. The central portion can have a thickness greater than a thickness of the first leg or a thickness of the second leg.

Abstract translation: 公开了一种用于燃气涡轮发动机的涡轮叶片。 涡轮叶片可以包括至少一个内部冷却路径和设置在至少一个内部冷却路径中的内部叶片。 内部叶片可以包括中心部分，从中心部分沿第一方向延伸的第一腿部，以及沿第二方向从中心部分延伸的第二腿部。 中心部分可以具有大于第一腿部的厚度或第二腿部的厚度的厚度。

公开(公告)号：US07934906B2

公开(公告)日：2011-05-03

申请号：US11939592

申请日：2007-11-14

Applicant: Xubin Gu ,  George Liang

Inventor： Xubin Gu ,  George Liang

IPC: F01D5/18

CPC classification number: F01D5/20 ,  F01D5/187 ,  F05D2230/21 ,  F05D2240/127 ,  F05D2250/611 ,  F05D2250/71 ,  F05D2260/2212

Abstract: A turbine blade for a turbine engine having a cooling system in the turbine blade formed from at least one elongated tip cooling chamber forming a portion of the cooling system and at least partially defined by the tip wall proximate to the first end. An inner surface of the tip wall may include a plurality of curved bumper protrusions extending from the inner surface radially inward toward the root. The cooling system may include a plurality of ribs generally aligned with the trailing edge, and the curved bumper protrusions may be offset in a chordwise direction relative to the ribs. A throat section may extend between a first forwardmost curved bumper protrusion and a second immediately adjacent downstream curved bumper protrusion and may be offset radially outward from an inner tip surface, thereby creating a first recessed tip slot with a reduced tip wall thickness.

Abstract translation: 一种用于涡轮发动机的涡轮机叶片，其具有在涡轮机叶片中的冷却系统，该冷却系统由形成冷却系统的一部分的至少一个细长尖端冷却室形成，并且至少部分地由靠近第一端的顶端壁限定。 尖端壁的内表面可以包括从内表面径向向内朝向根延伸的多个弯曲的保险杠突起。 冷却系统可以包括大致与后缘对齐的多个肋，并且弯曲的保险杠突起可以相对于肋沿弦向偏移。 喉部可以在第一最前面的弯曲的保险杠突出部和第二直接相邻的下游弯曲保险杠突起之间延伸，并且可以从内部末端表面径向向外偏移，从而产生具有减小的顶端壁厚度的第一凹入尖端狭槽。

公开(公告)号：US20090129934A1

公开(公告)日：2009-05-21

申请号：US11942885

申请日：2007-11-20

Applicant: Xubin Gu

Inventor： Xubin Gu

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F01D5/20 ,  F05D2240/122 ,  F05D2240/304

Abstract: A turbine blade for a turbine engine having a cooling system in the turbine blade including a camber-line rib extending radially outward from a tip of the blade and extending from a trailing edge of the blade toward a leading edge. The camber-line rib may form pressure and suction side cooling slots at the tip of the blade. The camber-line rib my include a cooling channel positioned in the camber-line rib and in fluid communication with the at least one cavity forming the cooling system in the blade for cooling aspects of the tip at the trailing edge.

Abstract translation: 一种用于涡轮发动机的涡轮叶片，其具有在涡轮机叶片中的冷却系统，包括从叶片的尖端径向向外延伸并从叶片的后缘朝向前缘延伸的外倾线肋。 拱形肋可以在叶片的尖端处形成压力和吸力侧冷却槽。 弧形肋条包括一个定位在弧形肋条中的冷却通道，并且与至少一个空腔流体连通，形成叶片中的冷却系统，用于冷却在后缘处的尖端部分。

公开(公告)号：US08985940B2

公开(公告)日：2015-03-24

申请号：US13436009

申请日：2012-03-30

Applicant: Luzeng Zhang ,  Xubin Gu ,  Juan Yin ,  Hee Koo Moon

Inventor： Luzeng Zhang ,  Xubin Gu ,  Juan Yin ,  Hee Koo Moon

IPC: F01D5/18 ,  F01D5/08 ,  F01D25/08 ,  F01D25/12

CPC classification number: F01D5/081 ,  F01D5/082 ,  F01D5/186 ,  F01D5/188 ,  F01D5/189 ,  F01D25/08 ,  F01D25/12

Abstract: A turbine blade for a gas turbine engine is disclosed. The turbine blade can include at least one internal cooling path, and an internal vane disposed in the at least one internal cooling path. The internal vane can include a central portion, a first leg extending in a first direction from the central portion, and a second leg extending in a second direction from the central portion. The central portion can have a thickness greater than a thickness of the first leg or a thickness of the second leg.

Abstract translation: 公开了一种用于燃气涡轮发动机的涡轮叶片。 涡轮叶片可以包括至少一个内部冷却路径和设置在至少一个内部冷却路径中的内部叶片。 内部叶片可以包括中心部分，从中心部分沿第一方向延伸的第一腿部，以及沿第二方向从中心部分延伸的第二腿部。 中心部分可以具有大于第一腿部的厚度或第二腿部的厚度的厚度。

公开(公告)号：US20130223987A1

公开(公告)日：2013-08-29

申请号：US13409028

申请日：2012-02-29

Applicant: Scott Stafford ,  Xubin Gu

Inventor： Scott Stafford ,  Xubin Gu

IPC: F02C7/18 ,  B23P15/00 ,  F02C7/00

CPC classification number: F01D5/189 ,  F01D25/007 ,  F05D2240/12 ,  F05D2250/185 ,  F05D2250/71 ,  Y10T29/49236

Abstract: A turbine nozzle insert of a gas turbine engine is disclosed. The insert may comprise an elongated hollow body portion, a flange portion formed at a first end of the elongated body portion, and a contact portion formed at a second end of the elongated body portion opposite the first end.

Abstract translation: 公开了一种燃气涡轮发动机的涡轮喷嘴插件。 插入件可以包括细长的中空主体部分，形成在细长主体部分的第一端的凸缘部分和形成在细长主体部分的与第一端相对的第二端的接触部分。

公开(公告)号：US07806658B2

公开(公告)日：2010-10-05

申请号：US11586455

申请日：2006-10-25

Applicant: George Liang ,  Xubin Gu

Inventor： George Liang ,  Xubin Gu

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F05D2260/2212 ,  F05D2260/22141

Abstract: A cooling system for a turbine airfoil of a turbine engine having an inflow mid-chord feed channel and a trailing edge feed channel that are separated by an equalizer rib having a plurality of supply holes. The supply holes enable cooling fluids to be supplied to the trailing edge from the mid-chord feed channel to satisfy the cooling requirements of the entire trailing edge, which is greater than the mid-chord region. A crossover hole may be positioned in the equalizer rib at the tip section to enable the cooling fluids to pass between the mid-chord feed channel and a trailing edge feed channel. The crossover hole may enable cooling fluids to pass from the trailing edge feed channel into the mid-chord feed channel along the tip section to reduce stagnation in the outboard turn of the mid-chord serpentine channel.

Abstract translation: 一种用于涡轮发动机的涡轮机翼的冷却系统，其具有由具有多个供应孔的均衡肋分离的流入中和进给通道和后缘进料通道。 供应孔使得冷却流体能够从中弦馈送通道供应到后缘，以满足整个后缘的冷却要求，其大于中和弦区域。 交叉孔可以在尖端部分处的均衡器肋中定位，以使得冷却流体能够在中和弦馈送通道和后缘馈送通道之间通过。 交叉孔可以使得冷却流体可以沿着末端部分从后缘进料通道进入中和弦进料通道，以减少中和弦蛇形通道的外侧转动的停滞。

公开(公告)号：US20090123292A1

公开(公告)日：2009-05-14

申请号：US11939592

申请日：2007-11-14

Applicant: Xubin Gu ,  George Liang

Inventor： Xubin Gu ,  George Liang

IPC: F01D5/18 ,  F01D5/08

CPC classification number: F01D5/20 ,  F01D5/187 ,  F05D2230/21 ,  F05D2240/127 ,  F05D2250/611 ,  F05D2250/71 ,  F05D2260/2212

Abstract: A turbine blade for a turbine engine having a cooling system in the turbine blade formed from at least one elongated tip cooling chamber forming a portion of the cooling system and at least partially defined by the tip wall proximate to the first end. An inner surface of the tip wall may include a plurality of curved bumper protrusions extending from the inner surface radially inward toward the root. The cooling system may include a plurality of ribs generally aligned with the trailing edge, and the curved bumper protrusions may be offset in a chordwise direction relative to the ribs. A throat section may extend between a first forwardmost curved bumper protrusion and a second immediately adjacent downstream curved bumper protrusion and may be offset radially outward from an inner tip surface, thereby creating a first recessed tip slot with a reduced tip wall thickness.

Abstract translation: 一种用于涡轮发动机的涡轮机叶片，其具有在涡轮机叶片中的冷却系统，该冷却系统由形成冷却系统的一部分的至少一个细长尖端冷却室形成，并且至少部分地由靠近第一端的顶端壁限定。 尖端壁的内表面可以包括从内表面径向向内朝向根延伸的多个弯曲的保险杠突起。 冷却系统可以包括大致与后缘对齐的多个肋，并且弯曲的保险杠突起可以相对于肋沿弦向偏移。 喉部可以在第一最前面的弯曲的保险杠突出部和第二直接相邻的下游弯曲保险杠突起之间延伸，并且可以从内部末端表面径向向外偏移，从而产生具有减小的顶端壁厚度的第一凹入尖端狭槽。

公开(公告)号：US20080101961A1

公开(公告)日：2008-05-01

申请号：US11586455

申请日：2006-10-25

Applicant: George Liang ,  Xubin Gu

Inventor： George Liang ,  Xubin Gu

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F05D2260/2212 ,  F05D2260/22141

Abstract: A cooling system for a turbine airfoil of a turbine engine having an inflow mid-chord feed channel and a trailing edge feed channel that are separated by an equalizer rib having a plurality of supply holes. The supply holes enable cooling fluids to be supplied to the trailing edge from the mid-chord feed channel to satisfy the cooling requirements of the entire trailing edge, which is greater than the mid-chord region. A crossover hole may be positioned in the equalizer rib at the tip section to enable the cooling fluids to pass between the mid-chord feed channel and a trailing edge feed channel. The crossover hole may enable cooling fluids to pass from the trailing edge feed channel into the mid-chord feed channel along the tip section to reduce stagnation in the outboard turn of the mid-chord serpentine channel.

Abstract translation: 一种用于涡轮发动机的涡轮机翼的冷却系统，其具有由具有多个供应孔的均衡肋分离的流入中和进给通道和后缘进料通道。 供应孔使得冷却流体能够从中弦馈送通道供应到后缘，以满足整个后缘的冷却要求，其大于中和弦区域。 交叉孔可以在尖端部分处的均衡器肋中定位，以使得冷却流体能够在中和弦馈送通道和后缘馈送通道之间通过。 交叉孔可以使得冷却流体可以沿着末端部分从后缘进料通道进入中和弦进料通道，以减少中和弦蛇形通道的外侧转动的停滞。