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    Complementary cooled turbine nozzle
    1.
    发明授权
    Complementary cooled turbine nozzle 有权
    互补冷却涡轮喷嘴

    公开(公告)号：US06884036B2

    公开(公告)日：2005-04-26

    申请号：US10413922

    申请日：2003-04-15

    申请人： Baolan Shi ,  Robert Francis Manning ,  Randall Brent Rydbeck ,  Nigel Brian Thomas Langley

    发明人： Baolan Shi ,  Robert Francis Manning ,  Randall Brent Rydbeck ,  Nigel Brian Thomas Langley

    IPC分类号： F01D9/02 ,  F01D5/08 ,  F01D5/18 ,  F01D9/04 ,  F01D25/12 ,  F02C7/18

    CPC分类号： F01D5/187 ,  F01D9/041 ,  F05D2220/3213 ,  F05D2230/21 ,  F05D2240/121 ,  F05D2240/303 ,  F05D2250/185 ,  F05D2260/22141 ,  Y02T50/676

    摘要： A turbine nozzle includes outer and inner bands integrally joined to a vane having a three-pass serpentine flow circuit between opposite pressure and suction sidewalls. The outer band includes an inlet for channeling cooling air into a first channel of the circuit located behind a leading edge of the vane. A first outlet is disposed in the inner band at the bottom of the first channel where it joins the second channel of the circuit. A second outlet is also disposed in the inner band at the bottom of a third channel of the circuit which is disposed in flow communication with the second channel. The first channel behind the leading edge is smooth except for corresponding rows of first and second turbulators spaced laterally apart. The first turbulators bridge the pressure and suction sidewalls directly behind the leading edge, and the second turbulators are disposed behind the suction sidewall.

    摘要翻译： 涡轮喷嘴包括与相对的压力侧壁和吸力侧壁之间具有三通蛇形流动回路的叶片整体接合的外部和内部带。 外带包括用于将冷却空气引导到位于叶片的前缘后面的电路的第一通道中的入口。 第一出口设置在第一通道的底部的内带中，其中它连接电路的第二通道。 第二出口还设置在与第二通道流动连通的电路的第三通道的底部的内带中。 前缘后面的第一个通道是平滑的，除了横向分开的第一和第二个紊流器的相应排。 第一个紊流器将压力和吸力侧壁直接连接在前缘的后面，第二个紊流器设置在吸力侧壁的后面。

    Stepped outlet turbine airfoil
    7.
    发明授权
    Stepped outlet turbine airfoil 有权
    阶梯式出口涡轮机翼型

    公开(公告)号：US07246999B2

    公开(公告)日：2007-07-24

    申请号：US10959615

    申请日：2004-10-06

    申请人： Robert Francis Manning ,  Thomas Edward Demarche ,  David Allen Flodman

    发明人： Robert Francis Manning ,  Thomas Edward Demarche ,  David Allen Flodman

    IPC分类号： B63H1/14

    CPC分类号： F01D5/187 ,  F01D5/186 ,  F05D2260/202 ,  Y02T50/671 ,  Y02T50/673 ,  Y02T50/676

    摘要： A turbine airfoil includes an internal cooling circuit between opposite pressure and suction sidewalls. The pressure sidewall includes a row of outlet slots for the circuit separated by converging partitions. Each slot includes an inlet, throat, and diverging outlet. Each of the partitions includes a step in a converging sidewall thereof for increasing divergence of the slots to diffuse coolant discharged therethrough.

    摘要翻译： 涡轮机翼片包括在相对的压力和抽吸侧壁之间的内部冷却回路。 压力侧壁包括一排用于通过会聚隔板分开的电路的出口槽。 每个槽包括一个入口，喉部和发散出口。 每个分隔件包括在其会聚的侧壁中的台阶，用于增加槽的扩散，以扩散从其中排出的冷却剂。

    Crossover cooled airfoil trailing edge
    8.
    发明授权
    Crossover cooled airfoil trailing edge 有权
    交叉冷却翼型后缘

    公开(公告)号：US06607356B2

    公开(公告)日：2003-08-19

    申请号：US10044249

    申请日：2002-01-11

    申请人： Robert Francis Manning ,  Mohammad Esmail Taslim

    发明人： Robert Francis Manning ,  Mohammad Esmail Taslim

    IPC分类号： F01D518

    CPC分类号： F01D5/187 ,  F05D2260/201 ,  F05D2260/22141 ,  Y02T50/676

    摘要： A turbine airfoil includes pressure and suction sidewalls having first and second flow channels disposed therebetween and separated by a longitudinally extending bridge. The bridge includes a row of inlet holes, and a row of outlet holes extends from the second channel toward the trailing edge of the airfoil. A row of turbulator ribs is disposed inside the second channel along the pressure sidewall and are longitudinally elongate and substantially colinear. The ribs face the inlet holes for crossover impingement cooling from the air channeled therefrom.

    摘要翻译： 涡轮机翼片包括压力和抽吸侧壁，其具有设置在其间并由纵向延伸的桥隔开的第一和第二流动通道。 桥梁包括一排入口孔，一排出口孔从第二通道延伸到翼型的后缘。 一排湍流肋沿着压力侧壁设置在第二通道的内部，并且纵向伸长并且基本上是共线的。 这些肋面朝向入口孔，用于从其引导的空气中进行交叉冲击冷却。

    Hybrid impingement cooled airfoil
    9.
    发明授权
    Hybrid impingement cooled airfoil 有权
    混合冲击冷却翼型

    公开(公告)号：US08172504B2

    公开(公告)日：2012-05-08

    申请号：US12055101

    申请日：2008-03-25

    申请人： David Allen Flodman ,  Jason David Shapiro ,  Robert Francis Manning ,  Mark Douglas Gledhill ,  Tyler Frederick Hooper

    发明人： David Allen Flodman ,  Jason David Shapiro ,  Robert Francis Manning ,  Mark Douglas Gledhill ,  Tyler Frederick Hooper

    IPC分类号： F01D5/18

    CPC分类号： F01D5/189 ,  F05D2260/201 ,  F05D2260/202 ,  Y02T50/676

    摘要： A turbine nozzle for a gas turbine engine includes: (a) spaced-apart arcuate inner and outer bands; (b) a hollow, airfoil-shaped turbine vane extending between the inner and outer bands, the interior of the vane defining at least a forward cavity and a mid-cavity positioned aft of the forward cavity; (c) a hollow impingement insert received inside the mid-cavity, the impingement insert having walls which are pierced with at least one impingement cooling hole; (d) a passage in the turbine vane at a radially outer end of the forward cavity adapted to be coupled to a source of cooling air; and (e) a passage in the inner band in fluid communication with a radially inner end of the forward cavity and a radially inner end of the impingement insert.

    摘要翻译： 用于燃气涡轮发动机的涡轮喷嘴包括：（a）间隔开的弓形内部和外部带; （b）在所述内部和外部带之间延伸的中空翼型涡轮机叶片，所述叶片的内部至少限定前腔和位于所述前腔后面的中空腔; （c）容纳在中空腔内的中空冲击插入件，冲击插入件具有用至少一个冲击冷却孔刺穿的壁; （d）在所述前腔的径向外端处的涡轮叶片中的通道，其适于联接到冷却空气源; 和（e）内带中的与前腔的径向内端流体连通的通道和冲击插入件的径向内端。

    Turbine blades and turbine blade cooling systems and methods
    10.
    发明授权
    Turbine blades and turbine blade cooling systems and methods 有权
    涡轮叶片和涡轮叶片冷却系统及方法

    公开(公告)号：US07857587B2

    公开(公告)日：2010-12-28

    申请号：US11606731

    申请日：2006-11-30

    申请人： Victor Hugo Silva Correia ,  Robert Francis Manning ,  Bhanu Mahasamudram Reddy

    发明人： Victor Hugo Silva Correia ,  Robert Francis Manning ,  Bhanu Mahasamudram Reddy

    IPC分类号： F01D5/18 ,  B64C11/24

    CPC分类号： F01D5/187 ,  F01D5/20 ,  F05D2260/202 ,  Y02T50/673 ,  Y02T50/676

    摘要： A turbine blade with improved tip cooling includes an airfoil having a tip cap and a tip wall extending outwardly from the tip cap. A recessed portion of the tip wall forms a tip shelf. At least one tip shelf hole extends through the tip shelf in flow communication with an internal airfoil cooling circuit. At least one tip wall opening extends through the recessed portion of the tip wall radially outward of the tip shelf in flow communication with the internal cooling circuit. The recessed tip wall portion may be tapered from a wider base to a minimum thickness. In a cooling method, cooling air channeled through the tip wall openings joins and mixes with a stream of hot combustion gases downstream of where cooling air channeled through the tip shelf openings joins and mixes with the stream of hot gasses to enhance convection cooling of the blade tip. A system for cooling a blade includes at least one tip shelf hole and at least one tip wall opening for channeling cooling air from an internal cooling circuit toward a stream of hot combustion gases for improved cooling of at least the blade tip.

    摘要翻译： 具有改进的尖端冷却的涡轮机叶片包括具有尖端帽和从顶盖向外延伸的顶端壁的翼型件。 尖端壁的凹陷部分形成尖端架。 至少一个尖端搁架孔延伸穿过末端架，与内部翼型件冷却回路流通。 至少一个尖端壁开口延伸穿过顶端壁的位于尖端架的径向外侧的凹部，与内部冷却回路流通。 凹入的顶壁部分可以从更宽的基部到最小厚度成锥形。 在冷却方法中，通过尖端壁开口引导的冷却空气与下游的热燃烧气体流接合并混合，其中通过尖端搁架开口引导的冷却空气与热气流混合并增强了叶片的对流冷却 小费。 用于冷却叶片的系统包括至少一个尖端搁架孔和至少一个尖端壁开口，用于将冷却空气从内部冷却回路引向热燃烧气体流，以改善至少叶片尖端的冷却。