公开(公告)号：US06554571B1

公开(公告)日：2003-04-29

申请号：US09683189

申请日：2001-11-29

Applicant: Ching-Pang Lee ,  Bin Wei ,  Robert Alan Johnson ,  Hsin-Pang Wang

Inventor： Ching-Pang Lee ,  Bin Wei ,  Robert Alan Johnson ,  Hsin-Pang Wang

IPC: F04D2938

CPC classification number: F01D5/187 ,  F05D2240/127 ,  F05D2260/2212 ,  F05D2260/22141

Abstract: A curved turbulator configuration is in a radial cooling passage of an airfoil, where the radial cooling passage is defined by at least a leading wall and a trailing wall, and the airfoil includes a tip and a root. The curved turbulator configuration includes a number of spaced curved turbulator pairs positioned along a center-line on an inner surface of the leading wall and a number of spaced complementary curved turbulator pairs positioned along a center-line on an inner surface of the trailing wall. An electrode for forming the curved turbulator configuration in the radial cooling passage includes a leading face having a curved turbulator pattern, a trailing face having a complementary curved turbulator pattern, a conductive core, and an insulating coating disposed thereon that is partly removed.

Abstract translation: 弯曲的湍流器构造在翼型件的径向冷却通道中，其中径向冷却通道由至少前导壁和后壁限定，并且翼型件包括尖端和根部。 弯曲的湍流器构造包括沿着前壁的内表面上的中心线定位的多个间隔开的弯曲的湍流器对，以及沿着后壁的内表面上的中心线定位的多个间隔开的互补弯曲湍流器对。 用于在径向冷却通道中形成弯曲的湍流器构造的电极包括具有弯曲的湍流器图案的前表面，具有互补弯曲湍流器图案的后表面，导电芯和位于其上的部分去除的绝缘涂层。

公开(公告)号：US06537619B2

公开(公告)日：2003-03-25

申请号：US09833796

申请日：2001-04-13

Applicant: Robert Alan Johnson ,  Jon Conrad Schaeffer ,  Ching-Pang Lee ,  Nesim Abuaf

Inventor： Robert Alan Johnson ,  Jon Conrad Schaeffer ,  Ching-Pang Lee ,  Nesim Abuaf

IPC: C23C408

CPC classification number: C23C4/00 ,  C23C4/073 ,  C23C4/131

Abstract: Castings for gas turbine parts exposed on one side to a high-temperature fluid medium have cast-in bumps on an opposite cooling surface side to enhance heat transfer. Areas on the cooling surface having defectively cast bumps, i.e., missing or partially formed bumps during casting, are thermally sprayed to provide a metallic cooling enhancement surface layer to salvage the part.

公开(公告)号：US06502622B2

公开(公告)日：2003-01-07

申请号：US10073590

申请日：2002-02-12

Applicant: Ching Pang Lee ,  Wayne Charles Hasz ,  Nesim Abuaf ,  Robert Alan Johnson

Inventor： Ching Pang Lee ,  Wayne Charles Hasz ,  Nesim Abuaf ,  Robert Alan Johnson

IPC: B22C702

CPC classification number: B22C9/02 ,  B22C7/02 ,  B22C9/04

Abstract: A casting includes a heat tranfer surface having a pluality of cavities. The plurality of cavities includes a density of at least about 25 cavities per square centimeter to about 1,100 cavities per square centimeter resulting in increased surface area and therefore enhanced heat transfer capability. Also disclosed is a mold for forming a pattern for molding the casting. The mold includes a surface defining a portion of a chamber to which are attached a plurality of particles having an average particle size in a range of about 300 microns to about 2,000 microns.

Abstract translation: 铸件包括具有空腔抽吸性的热传递表面。 多个空腔包括每平方厘米至少约25个腔体至每平方厘米约1,100个空腔的密度，导致增加的表面积，从而增强了传热能力。 还公开了一种用于形成用于模制铸件的图案的模具。 模具包括限定室的一部分的表面，其中连接有平均粒度在约300微米至约2,000微米范围内的多个颗粒。

公开(公告)号：US06382300B2

公开(公告)日：2002-05-07

申请号：US09863185

申请日：2001-05-24

Applicant: Ching Pang Lee ,  Wayne Charles Hasz ,  Nesim Abuaf ,  Robert Alan Johnson

Inventor： Ching Pang Lee ,  Wayne Charles Hasz ,  Nesim Abuaf ,  Robert Alan Johnson

IPC: B22C700

CPC classification number: B22C9/04 ,  B22C7/02 ,  B22C9/02 ,  B22D25/06

Abstract: A casting includes a heat transfer surface having a plurality of cavities. The plurality of cavities include a density of at least about 25 cavities per square centimeter to about 1,100 cavities per square centimeter resulting in increased surface area and therefore enhanced heat transfer capability. Also disclosed is a mold for forming a pattern for molding the casting. The mold includes a surface defining a portion of a chamber to which are attached a plurality of particles having an average particle size in a range of about 300 microns to about 2,000 microns.

Abstract translation: 铸件包括具有多个空腔的传热表面。 多个空腔包括每平方厘米至少约25个腔体至每平方厘米约1,100个空腔的密度，导致增加的表面积并因此提高传热能力。 还公开了一种用于形成用于模制铸件的图案的模具。 模具包括限定室的一部分的表面，其中连接有平均粒度在约300微米至约2,000微米范围内的多个颗粒。

公开(公告)号：US06234753B1

公开(公告)日：2001-05-22

申请号：US09317241

申请日：1999-05-24

Applicant: Ching-Pang Lee

Inventor： Ching-Pang Lee

IPC: F01D518

CPC classification number: F01D5/187 ,  F05D2240/127 ,  F05D2240/128 ,  Y02T50/676

Abstract: The flow of cooling fluid through core tie holes formed between the internal cooling passageways of turbine airfoils is reduced by disposing flow deflectors on the wall adjacent to the holes. The deflectors alter the local static pressure near the holes, thereby minimizing the pressure differential across the holes so as to reduce the flow of cooling fluid.

Abstract translation: 通过在涡轮翼型的内部冷却通道之间形成的通过芯连接孔的冷却流体的流动通过在与孔相邻的壁上设置偏流器而减少。 偏转器改变孔附近的局部静压力，从而最小化穿过孔的压差，从而减少冷却流体的流动。

公开(公告)号：US6050079A

公开(公告)日：2000-04-18

申请号：US997980

申请日：1997-12-24

Applicant: George A. Durgin ,  Randall C. Bauer ,  Ching-Pang Lee

Inventor： George A. Durgin ,  Randall C. Bauer ,  Ching-Pang Lee

IPC: F01D5/08 ,  F02C7/12 ,  F01D1/00

CPC classification number: F01D5/082 ,  F02C7/125

Abstract: A modulated flow transfer apparatus for transferring a fluid flow from a static element to a rotor of a gas turbine engine has an annular static inducer for accelerating the fluid flow in a substantially circumferential direction. The inducer has an annular row of identical first and second flow passages with first and second inlets respectively and outlets. First and second flow means direct first and second portions of the flow to the first and second flow passages, respectively. A valve is used for selectively modulating the second portion of the flow which together with a controller may be used for selectively preventing the second portion of flow from flowing through the second flow passages during a first cruise of engine operation and allowing substantially unrestricted flow therethrough during a takeoff mode of engine operation. The second flow means preferably includes an inducer manifold disposed between the valve and the second inlets. Exhaust ducts connect corresponding ones of the second inlets to the inducer manifold. The inducer manifold is preferably disposed inside a plenum used to feed cooling air to the first passages.

Abstract translation: 用于将流体流从静态元件传递到燃气涡轮发动机的转子的调制流传递装置具有用于在大致圆周方向上加速流体流动的环形静态诱导器。 导流器具有一排相同的第一和第二流动通道，分别具有第一和第二入口以及出口。 第一和第二流动装置分别将流体的第一和第二部分直接引导到第一和第二流动通道。 阀用于选择性地调节流量的第二部分，其与控制器一起可以用于在发动机操作的第一次巡航期间选择性地防止第二部分流动流过第二流动通道，并且允许基本上不受限制的流过其中 发动机运转的起飞模式。 第二流动装置优选地包括设置在阀和第二入口之间的导流器歧管。 排气管将相应的第二入口连接到导流器歧管。 导流器歧管优选地设置在用于将冷却空气供给到第一通道的增压室内部。

公开(公告)号：US5738491A

公开(公告)日：1998-04-14

申请号：US778529

申请日：1997-01-03

Applicant: Ching-Pang Lee ,  Brent A. Gregory ,  Ariel C. P. Jacala

Inventor： Ching-Pang Lee ,  Brent A. Gregory ,  Ariel C. P. Jacala

IPC: F01D5/14 ,  F01D5/18 ,  F01D5/20 ,  F01D5/28 ,  F01D11/18 ,  F01D25/14

CPC classification number: F01D11/18 ,  F01D5/147 ,  F01D5/187 ,  F01D5/20 ,  F01D5/28 ,  F05D2260/205 ,  F05D2260/221 ,  F05D2260/2322 ,  F05D2300/5024 ,  Y02T50/673 ,  Y02T50/676

Abstract: A turbine blade includes an airfoil having a root, tip cap, and laterally opposite pressure and suction sides extending between leading and trailing edges. A cooling circuit is disposed inside the airfoil and extends from the tip cap to the root for circulating a coolant. The airfoil also includes a pair of squealer tips extending radially upwardly from the tip cap along the pressure and suction sides which are spaced apart from the leading to trailing edges to define an upwardly open tip cavity. A thermal conductor is fixedly joined to the squealer tips and extends radially inwardly to the tip cap for conducting heat thereto for removal by the coolant. The conductor preferably surrounds the tip cavity inboard of the squealer tips and is coextensive therewith for being protected thereby.

Abstract translation: 涡轮机叶片包括具有根部，顶端盖和在前缘和后缘之间延伸的横向相对的压力和吸力侧的翼型件。 冷却回路设置在翼型件的内部，并且从顶盖延伸到根部以使冷却剂循环。 翼型件还包括一对从尖端沿径向向上延伸的尖叫尖端，其沿着压力和吸力侧分开，该侧面与前至后缘间隔开以限定向上开口的尖端腔。 热导体固定地连接到尖叫尖端，并且径向向内延伸到尖端盖，用于传导热量以便被冷却剂除去。 导体优选地围绕尖叫尖端的尖端空腔，并且与其共同延伸以便被保护。

公开(公告)号：US5690472A

公开(公告)日：1997-11-25

申请号：US830145

申请日：1992-02-03

Applicant: Ching-Pang Lee

Inventor： Ching-Pang Lee

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F05D2260/201 ,  Y02T50/676

Abstract: A turbine airfoil has a mesh cooling hole arrangement which includes first and second pluralities of cooling holes formed within the interior structure of the side walls of the airfoil so as to extend between and along but not intersect spaced internal and external surfaces of the side walls extending between leading and trailing edge portions of the airfoil. The cooling holes of each plurality extend generally parallel to one another. The cooling holes of the first and second pluralities intersect so as to define a plurality of spaced apart internal solid nodes in the side walls having pairs of opposite sides interconnected by pairs of opposite corners. The spaced nodes define a multiplicity of hole portions of the cooling holes extending between and along opposite sides of adjacent nodes and a plurality of flow intersections interconnecting the hole portions of the cooling holes and being disposed between the corners of adjacent nodes. The sides of the nodes have lengths which are greater than the widths of the hole portions between adjacent nodes such that when cooling fluid is passed through the cooling holes jet flow actions are created through the hole portions which in turn generate jet interactions at the flow intersections. The jet interactions restrict air flow and produce a pressure drop which creates turbulences in the air flow that enhance convective heat transfer between the airfoil side walls and the cooling air.

Abstract translation: 涡轮机翼型具有网格冷却孔布置，其包括形成在翼型件的侧壁的内部结构内的第一和第二多个冷却孔，以便在侧壁的延伸的侧壁之间延伸并且沿着但不相交的侧壁和外侧表面延伸 在翼型的前缘部分和后缘部分之间。 每个多个冷却孔通常彼此平行地延伸。 第一和第二多个的冷却孔相交，以在侧壁中限定多个间隔开的内部实心节点，其具有通过成对的相对角相互连接的成对的相对侧。 间隔开的节点限定了在相邻节点的相对侧和之间延伸的冷却孔的多个孔部分，以及互连冷却孔的孔部分并且设置在相邻节点的角部之间的多个流动交叉点。 节点的侧面具有大于相邻节点之间的孔部分的宽度的长度，使得当冷却流体通过冷却孔时，通过孔部分产生喷射流动作用，这些孔部分在流动相交处产生射流相互作用 。 射流相互作用限制空气流动并产生压力降，其在空气流中产生湍流，从而增强翼型件侧壁和冷却空气之间的对流传热。

公开(公告)号：US5660525A

公开(公告)日：1997-08-26

申请号：US94998

申请日：1993-07-23

Applicant: Ching-Pang Lee ,  Ronald Scott Bunker ,  Nesim Abuaf ,  Steven Joseph Brzozowski

Inventor： Ching-Pang Lee ,  Ronald Scott Bunker ,  Nesim Abuaf ,  Steven Joseph Brzozowski

IPC: F01D5/18

CPC classification number: F01D5/186 ,  F05D2250/12 ,  F05D2250/121 ,  F05D2260/202

Abstract: A wall adapted for use in a gas turbine engine between a first and a hotter second fluid includes a first side over which is flowable the first fluid, and an opposite second side over which is flowable the second fluid. An elongate slot extends inwardly from the second side and is disposed in flow communication with a plurality of longitudinally spaced apart holes extending inwardly from the first side. The holes are disposed at a compound angle relative to the second side for discharging the first fluid obliquely into the slot and at a shallow discharge angle from the slot along the second side. The holes are also disposed in converging pairs to impinge together in the slot the first fluid channeled therethrough. In a preferred embodiment, the slot has an aft surface including a plurality of longitudinally spaced apart grooves extending from the holes to the wall second side.

Abstract translation: 适于在第一和第二热液体之间的燃气涡轮发动机中使用的壁包括可流过第一流体的第一侧和可流动第二流体的相对的第二侧。 细长狭槽从第二侧向内延伸，并且设置成与从第一侧向内延伸的多个纵向间隔开的孔流动连通。 孔以相对于第二侧的复合角度设置，用于将第一流体倾斜地排放到槽中，并且沿着沿着第二侧的槽沿浅放电角排放。 这些孔也以会聚对设置，以将槽中的第一流体冲入其中。 在优选实施例中，槽具有包括从孔延伸到壁第二侧的多个纵向间隔开的槽的后表面。

公开(公告)号：US5660523A

公开(公告)日：1997-08-26

申请号：US829641

申请日：1992-02-03

Applicant: Ching-Pang Lee

Inventor： Ching-Pang Lee

IPC: F01D5/20 ,  F01D5/18

CPC classification number: F01D5/20 ,  F05D2260/20 ,  Y02T50/673 ,  Y02T50/676

Abstract: A turbine blade squealer tip has a cooling passage arrangement which includes a peripheral end wall surrounding a central portion of an end cap of the squealer tip, an outer peripheral groove defined in an outer surface of the peripheral end wall being spaced outwardly from the central portion of the end cap, and a multiplicity of holes extending through the end wall from the outer groove to an internal source of cooling air flow within the turbine blade, bypassing the central portion of the end cap of the squealer tip. The outer groove which receives the flow of cooling air from outlets of the holes tends to trap the air therein so as to form an annular air seal about the outer surface of the squealer tip end wall which impedes leakage of hot gas flow past the squealer tip.

Abstract translation: 涡轮叶片尖叫尖端具有冷却通道装置，该冷却通道装置包括围绕所述鸣响器尖端的端盖的中心部分的外周端壁，限定在所述外周端壁的外表面中的外周壁与所述中心部分 的端盖，以及多个孔，其跨过所述端壁从所述外槽延伸到所述涡轮机叶片内的冷却空气流的内部源，绕过所述尖叫尖端的所述端盖的中心部分。 接收从孔的出口流出的冷却空气的外槽倾向于将空气捕获在其中，以便围绕鸣叫器末端壁的外表面形成环形空气密封，阻止热气流经过鸣叫器尖端的泄漏 。