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：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。

公开(公告)号：US09228437B1

公开(公告)日：2016-01-05

申请号：US13427250

申请日：2012-03-22

Applicant: George Liang

Inventor： George Liang

IPC: F01D5/18 ,  F01D5/08 ,  B23P15/04

CPC classification number: F01D5/087 ,  B23P15/02 ,  B23P15/04 ,  F01D5/187 ,  F05D2230/21 ,  F05D2230/61 ,  F05D2240/304

Abstract: An air cooled turbine blade with a trailing edge cooling circuit that is formed by casting the airfoil with a pressure side trailing edge lip being oversized, and then machining away material from the pressure side wall to leave a pressure side bleed slot with a smaller (t/s) ratio than can be formed by casting alone. In another embodiment, the airfoil is cast with a trailing edge exit hole, and then the material on the pressure side wall in the trailing edge region is machined away to leave a pressure side bleed slot instead of an exit hole.

Abstract translation: 具有后缘冷却回路的空气冷却涡轮机叶片，该后缘冷却回路通过将压力侧后缘加上翼型而形成，然后从压力侧壁加工材料以留下具有较小的（t）的压力侧排放槽 / s）比可以通过铸造单独形成。 在另一个实施例中，翼型件具有后缘出口孔，然后在后缘区域中的压力侧壁上的材料被加工而离开压力侧泄放槽而不是出口孔。

公开(公告)号：US08827647B1

公开(公告)日：2014-09-09

申请号：US12822226

申请日：2010-06-24

Applicant: George Liang

Inventor： George Liang

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F05D2240/81 ,  F05D2260/201

Abstract: A turbine rotor blade with a four-pass aft flowing serpentine flow cooling circuit with a first leg located along the leading edge and the fourth leg located along the trailing edge region, and with two exit slots connected to the fourth leg with one exit slot opening on the trailing edge just above the platform and the second exit slot opening just below the platform.

Abstract translation: 一种涡轮转子叶片，具有四通后流动的蛇形流冷却回路，其第一支腿沿前缘定位，第四腿沿着后缘区域定位，并且两个出口槽连接到第四腿部，一个出口槽口 在平台的正上方的后缘，并且位于平台正下方的第二出口槽开口。

公开(公告)号：US08777571B1

公开(公告)日：2014-07-15

申请号：US13316485

申请日：2011-12-10

Applicant: George Liang

Inventor： George Liang

IPC: F01D5/20

CPC classification number: F01D5/187 ,  F05D2240/303 ,  F05D2260/202 ,  F05D2260/205

Abstract: An air cooled turbine airfoil with a leading edge region having rows of diffusion slots opening onto the airfoil surface. Each diffusion slot is connected to a plurality of metering and diffusion holes that meter the cooling air flow and provide for a first diffusion of the cooling air. The metering holes and diffusion holes are angled in order to improve the cooling effectiveness of the passages. The metering and diffusion holes and diffusion slots are formed from a metal printing process that can produce features that cannot be formed from an investment casting process that uses a ceramic core.

Abstract translation: 一种具有前缘区域的空气冷却涡轮机翼型件，其具有在翼型件表面上开口的一排扩散槽。 每个扩散槽连接到多个计量和扩散孔，其计量冷却空气流并提供冷却空气的第一扩散。 计量孔和扩散孔成角度，以提高通道的冷却效果。 计量和扩散孔和扩散槽由金属印刷工艺形成，该工艺可产生不能使用陶瓷芯的熔模铸造工艺形成的特征。

公开(公告)号：US08777570B1

公开(公告)日：2014-07-15

申请号：US12757226

申请日：2010-04-09

Applicant: George Liang

Inventor： George Liang

IPC: F01D5/08

CPC classification number: F01D5/187 ,  F01D5/186 ,  F05D2240/12 ,  F05D2240/81 ,  F05D2250/185

Abstract: A stator vane with endwalls having film cooling diffusion slots that open onto the hot gas surface. Each diffusion slot is formed as a row of one or more separated diffusion slots each having a serpentine flow channel and one or more metering inlet holes to supply spent cooling air from an impingement chamber to the diffusion slots. The metering inlet holes meter the flow of cooling air into the serpentine channels, the serpentine channels provide convection cooling for the endwalls, and the diffusion slots diffuse the cooling air into a layer of film cooling air onto the hot gas surface of the endwalls.

Abstract translation: 具有端壁的定子叶片具有通向热气体表面上的薄膜冷却扩散槽。 每个扩散槽形成为一排一个或多个分离的扩散槽，每个扩散狭槽具有蛇形流动通道和一个或多个计量入口孔，以将消耗的冷却空气从冲击室提供到扩散槽。 计量入口孔测量冷却空气进入蛇形通道的流量，蛇形通道为端壁提供对流冷却，扩散槽将冷却空气扩散到一层薄膜冷却空气到端壁的热气表面上。

公开(公告)号：US08721285B2

公开(公告)日：2014-05-13

申请号：US12397766

申请日：2009-03-04

Applicant: George Liang

Inventor： George Liang

IPC: F01D5/18

CPC classification number: F01D5/188 ,  F01D5/187 ,  F05D2250/185 ,  F05D2260/22141

Abstract: A turbine blade having an internal cooling system with incremental serpentine cooling channels in near walls forming an outer surface of the turbine blade is disclosed. The turbine blade may be formed from an internal structural spar that is covered with a thermal skin. The incremental serpentine cooling channels may be cut into the outer surface of the spar to which the thermal skin may be attached. The incremental serpentine cooling channels may be formed from two or more serpentine cooling channels aligned along an axis that extends generally spanwise throughout the turbine blade. A row of incremental serpentine cooling channels may extend from a root to a tip of the blade, but a single incremental cooling channel does not.

Abstract translation: 公开了一种具有内部冷却系统的涡轮机叶片，该内部冷却系统在形成涡轮机叶片的外表面的近壁处具有增量的蛇形冷却通道。 涡轮机叶片可以由内部结构的翼梁形成，内部的结构翼梁被热的皮肤覆盖。 增量蛇形冷却通道可以被切割到可以附着热皮肤的翼梁的外表面。 增量蛇形冷却通道可以由两个或更多个沿着轴线对齐的蛇形冷却通道形成，该轴线大致跨越涡轮机叶片。 一排增量蛇形冷却通道可以从根部延伸到刀片的尖端，但是单个增量冷却通道不会。

公开(公告)号：US08668437B1

公开(公告)日：2014-03-11

申请号：US12691529

申请日：2010-01-21

Applicant: George Liang

Inventor： George Liang

IPC: F01D5/14

CPC classification number: F01D5/14 ,  F01D5/082

Abstract: A cooling fluid feed system for a turbine engine for directing cooling fluids from a compressor, through one or more impellers, and into row one turbine vanes and one or more rows of turbine blades for increasing the cooling capacity of the turbine vanes and blades. Such a configuration increases cooling capacity, which in turn increases the capacity for growth within the turbine engine, creates a larger cooling fluid to gas side pressure differential and reduces amount of bleed off of cooling fluids from the compressor, thereby increasing efficiency of the turbine engine.

Abstract translation: 一种用于涡轮发动机的冷却流体进料系统，用于将来自压缩机的冷却流体引导通过一个或多个叶轮，以及一排涡轮叶片和一排或多排涡轮机叶片，用于增加涡轮叶片和叶片的冷却能力。 这种配置增加了冷却能力，这又增加了涡轮发动机内的增长能力，产生了更大的冷却流体到气体侧压力差并且减少了来自压缩机的冷却流体的泄漏量，从而提高了涡轮发动机的效率 。