公开(公告)号：US06616406B2

公开(公告)日：2003-09-09

申请号：US09877042

申请日：2001-06-11

Applicant: George Liang

Inventor： George Liang

IPC: F01D518

CPC classification number: F01D5/187 ,  F01D5/186 ,  F05D2250/141 ,  F05D2250/241 ,  F05D2250/70 ,  F05D2260/202 ,  Y02T50/673 ,  Y02T50/676

Abstract: An airfoil in a gas turbine comprises an improved cooling construction at its trailing edge providing impingement as well as enhanced film cooling. The airfoil comprises cavities arranged between the suction and pressure side wall for a cooling fluid and exit passages leading from the cavities to exit ports positioned on the pressure side wall. According to the invention the suction side wall is shaped such that the tip portion of the trailing edge has a cross-section comprising a part of a circle that is equal or greater than a semi-circle extending from the suction side around the tip to the pressure side and beyond into the exit passage. The exit passages comprise a bend in the region of the tip where they form an exit plenum for the cooling fluid to diffuse further.

公开(公告)号：US06609894B2

公开(公告)日：2003-08-26

申请号：US09681915

申请日：2001-06-26

Applicant: Melvin Robert Jackson ,  Charles Gitahi Mukira

Inventor： Melvin Robert Jackson ,  Charles Gitahi Mukira

IPC: F01D518

CPC classification number: B23P6/005 ,  B23P15/02 ,  F01D5/14 ,  F01D5/28 ,  F01D5/288 ,  F05D2260/202 ,  F05D2300/13 ,  F05D2300/143 ,  Y02T50/67 ,  Y02T50/676 ,  Y10T29/49318 ,  Y10T29/49336

Abstract: A gas turbine airfoil and methods for manufacturing and repair of an airfoil, the airfoil comprising a wall, the wall defining the perimeter of the airfoil and comprising a leading edge section and a trailing edge section, wherein a majority of the surface area of the wall comprises a first material, the first material having an oxidation resistance and a melting temperature, and at least one portion of the wall comprises a second material, the second material having an oxidation resistance that is greater than the oxidation resistance of the first material and a melting temperature that is at least about 83 degrees Celsius (about 150 degrees Fahrenheit) greater than the melting temperature of the first material, the at least one portion of the wall located in at least one section of the wall selected from the group consisting of the leading edge section and the trailing edge section.

公开(公告)号：US06609891B2

公开(公告)日：2003-08-26

申请号：US09943527

申请日：2001-08-30

Applicant: Leslie Eugene Leeke ,  Sean Robert Keith ,  Ronald Eugene Mc Rae, Jr. ,  Lawrence Paul Timko ,  David Alan Frey

Inventor： Leslie Eugene Leeke ,  Sean Robert Keith ,  Ronald Eugene Mc Rae, Jr. ,  Lawrence Paul Timko ,  David Alan Frey

IPC: F01D518

CPC classification number: F01D5/186 ,  F05D2260/202 ,  F05D2260/94 ,  F05D2260/941 ,  Y02T50/673 ,  Y02T50/676

Abstract: A hollow cooled turbine airfoil is provided having pressure and suction side walls and a plurality of trailing edge cooling passages that feed cooling air bleed slots at the trailing edge. The airfoil trailing edge is selectively thickened in the root portion so as to allow shortened trailing edge slots, thereby improving trailing edge cooling and reducing mechanical and thermal stresses.

Abstract translation: 中空的冷却涡轮机翼片设置有压力和吸力侧壁以及多个后缘冷却通道，其在后缘进给冷却空气排放槽。 叶片后缘在根部部分中选择性地加厚，以便允许缩短的后缘槽，从而改善后缘冷却并降低机械和热应力。

公开(公告)号：US06607355B2

公开(公告)日：2003-08-19

申请号：US09973222

申请日：2001-10-09

Applicant: Frank J. Cunha ,  Young H. Chon ,  Bryan P. Dube

Inventor： Frank J. Cunha ,  Young H. Chon ,  Bryan P. Dube

IPC: F01D518

CPC classification number: F01D5/189 ,  F01D5/18 ,  F05D2260/2212 ,  F05D2260/22141 ,  Y02T50/67 ,  Y02T50/676

Abstract: A turbine airfoil section having an internal cavity and a plurality of indentations on the inner surface of the internal cavity is described. The indentations provide enhanced heat transfer for cooling the internal cavity of an airfoil thereby improving the life of the airfoil and optimizing the efficiency of the engine by minimizing the amount of compressor bleed air required. Advantageously, this cooling scheme also does not restrict the cooling flow within the internal cavity. The indentations may have varying patterns and alternative geometric configurations.

公开(公告)号：US06602052B2

公开(公告)日：2003-08-05

申请号：US09884018

申请日：2001-06-20

Applicant: George Liang

Inventor： George Liang

IPC: F01D518

CPC classification number: F01D5/20 ,  F01D5/18

Abstract: An airfoil for a gas turbine includes a pressure sidewall and a suction sidewall, a tip cap, and a tip squealer. Cooling fluid flows from a hollow space within the airfoil through exit passages extending to the pressure side of the airfoil and to the tip cavity defined by the tip cap and the tip squealer. The tip squealer includes a smooth contour with curved and straight portions, allowing an even flow of the cooling fluid about the tip squealer and within the tip cavity. Furthermore, the exit passages are partially diffused and oriented at angles with respect to the radial direction. The smooth contour and shape of the exit passages avoids the formation of vortices and enhances film cooling of the tip squealer.

Abstract translation: 用于燃气轮机的翼型件包括压力侧壁和吸力侧壁，尖端帽和尖端尖叫器。 冷却流体从机翼内的中空空间通过延伸到翼型的压力侧的出口通道和由顶端盖和尖端尖叫器限定的尖端腔流动。 尖端尖叫器包括具有弯曲和直线部分的平滑轮廓，允许冷却流体围绕尖端推进器并在尖端腔内均匀流动。 此外，出口通道部分地扩散并相对于径向方向定向。 出口通道的平滑轮廓和形状避免了涡流的形成，并增强了尖端尖叫机的薄膜冷却。

公开(公告)号：US06595741B2

公开(公告)日：2003-07-22

申请号：US09946337

申请日：2001-09-06

Applicant: Jan Briesenick ,  Winfried-Hagen Friedl

Inventor： Jan Briesenick ,  Winfried-Hagen Friedl

IPC: F01D518

CPC classification number: F01D5/081 ,  F01D5/08 ,  F01D11/001 ,  F01D11/025 ,  Y02T50/671 ,  Y02T50/676

Abstract: A pre-swirl nozzle carrier for an aircraft gas turbine with a body (1) is provided with a fitted seat (2) for the location of the pre-swirl nozzle carrier on a main carrier (3) and which features several pre-swirl nozzles (4), characterized in that the body (1) is extended radially inward, that it has several secondary pre-swirl nozzles (6) on its radial inward area (5) and that it is provided with an inner seal area (7) on its inner radial side.

Abstract translation: 用于具有主体（1）的飞机燃气轮机的预旋转喷嘴载体设置有用于在主载体（3）上预旋喷嘴载体的位置的配合的座（2），并且具有几个预旋 喷嘴（4），其特征在于，主体（1）径向向内延伸，在其径向内部区域（5）上具有多个二次预旋喷嘴（6），并且其设有内密封区域（7） ）在其内径向侧。

公开(公告)号：US06551062B2

公开(公告)日：2003-04-22

申请号：US09943526

申请日：2001-08-30

Applicant: Leslie Eugene Leeke ,  Sean Robert Keith ,  Ronald Eugene McRae, Jr. ,  Richard William Albrecht, Jr. ,  David Alan Frey

Inventor： Leslie Eugene Leeke ,  Sean Robert Keith ,  Ronald Eugene McRae, Jr. ,  Richard William Albrecht, Jr. ,  David Alan Frey

IPC: F01D518

CPC classification number: F01D5/186 ,  F05D2250/71 ,  F05D2260/202 ,  F05D2260/94 ,  F05D2260/941 ,  Y02T50/67 ,  Y02T50/671 ,  Y02T50/673 ,  Y02T50/676

Abstract: A hollow cooled turbine airfoil is provided having pressure and suction side walls and a plurality of trailing edge cooling passages that feed cooling air bleed slots at the trailing edge. The suction side wall has a selectively reduced thickness, which allows shortened trailing edge slots, improving trailing edge cooling.

Abstract translation: 中空的冷却涡轮机翼片设置有压力和吸力侧壁以及多个后缘冷却通道，其在后缘进给冷却空气排放槽。 吸力侧壁具有选择性地减小的厚度，这允许缩短的后缘槽，改善后缘冷却。

公开(公告)号：US06544001B2

公开(公告)日：2003-04-08

申请号：US09944366

申请日：2001-09-04

Applicant: Geoffrey M Dailey

Inventor： Geoffrey M Dailey

IPC: F01D518

CPC classification number: F01D5/186 ,  B22C9/10 ,  F01D5/187

Abstract: A turbine blade for a gas turbine engine comprises an aerofoil having a suction and pressure side. The pressure side is provided with a reflex curvature at the aerofoil trailing edge region so as to reduce the thickness of the aerofoil in that region.

公开(公告)号：US06514038B2

公开(公告)日：2003-02-04

申请号：US09988167

申请日：2001-11-19

Applicant: Ryo Akiyama ,  Shinya Marushima ,  Manabu Matsumoto

Inventor： Ryo Akiyama ,  Shinya Marushima ,  Manabu Matsumoto

IPC: F01D518

CPC classification number: F01D11/005 ,  F01D5/084 ,  F01D5/085 ,  F01D5/187 ,  F02C7/12 ,  F05D2260/205

Abstract: A turbine rotor comprises first and second wheels each having turbine blades fixed to a peripheral portion thereof, and a spacer arranged so as to be sandwiched between the first and second wheels, and is characterized in that in a partitioning member is provided between the spacer and at least one of the first and second wheels, coolant paths in which coolant for cooling the turbine blades flows are provided inside the turbine blades, and a cavity formed by the partitioning member and the spacer is provided in a recovery course through which the coolant passed through the coolant paths is exhausted from the turbine blades. A gas turbine comprising the turbine rotor as mentioned above and a cooling method of the turbine rotor are disclosed.

公开(公告)号：US06511293B2

公开(公告)日：2003-01-28

申请号：US09867166

申请日：2001-05-29

Applicant: Scott M. Widrig ,  Ronald J. Rudolph ,  Gregg P. Wagner

Inventor： Scott M. Widrig ,  Ronald J. Rudolph ,  Gregg P. Wagner

IPC: F01D518

CPC classification number: F01D5/187 ,  F05D2260/2214

Abstract: An airfoil, a method of manufacturing an airfoil, and a system for cooling an airfoil is provided. The cooling system can be used with an airfoil located in the first stages of a combustion turbine within a combined cycle power generation plant and involves flowing closed loop steam through a pin array set within an airfoil. The airfoil can comprise a cavity having a cooling chamber bounded by an interior wall and an exterior wall so that steam can enter the cavity, pass through the pin array, and then return to the cavity to thereby cool the airfoil. The method of manufacturing an airfoil can include a type of lost wax investment casting process in which a pin array is cast into an airfoil to form a cooling chamber.

Abstract translation: 提供一种翼型件，制造翼型的方法以及用于冷却翼型的系统。 冷却系统可以与位于组合循环发电厂内的燃气轮机的第一级中的翼型一起使用，并且涉及使闭环蒸汽流过设置在翼型内的销阵列。 翼型件可以包括具有由内壁和外壁限定的冷却室的空腔，使得蒸汽可以进入空腔，穿过销阵列，然后返回到空腔，从而冷却翼型件。 制造翼型的方法可以包括一种失蜡投资铸造工艺，其中销阵列被铸造成翼型以形成冷却室。