公开(公告)号：US08556578B1

公开(公告)日：2013-10-15

申请号：US13585891

申请日：2012-08-15

Applicant: Robert L Memmen ,  John A Fedock ,  James P Downs

Inventor： Robert L Memmen ,  John A Fedock ,  James P Downs

IPC: F01D5/18

CPC classification number: F01D5/189

Abstract: A flexible seal having an X-shaped cross section that forms four contact points on four contact surfaces of two opposed seal slots. The flexible seal is used for a component in which the two seal slots undergo a large deflection such that the opposed slots are not aligned and a rigid seal will not form an adequate seal. The flexible seal can be used in a component of a combustor or a turbine in a gas turbine engine where opposed seal slots undergo the large deflection during operation.

Abstract translation: 具有X形横截面的柔性密封件，其在两个相对的密封槽的四个接触表面上形成四个接触点。 柔性密封件用于其中两个密封槽经历大的偏转的部件，使得相对的狭槽不对齐，并且刚性密封件将不形成适当的密封。 柔性密封件可以用在燃气涡轮发动机的燃烧器或涡轮机的部件中，其中在操作期间相对的密封槽经历大的偏转。

公开(公告)号：US08444389B1

公开(公告)日：2013-05-21

申请号：US12749580

申请日：2010-03-30

Applicant: Russell B Jones ,  John A Fedock

Inventor： Russell B Jones ,  John A Fedock

IPC: F01D5/14

CPC classification number: F01D5/14

Abstract: A multiple piece turbine rotor blade with a shell having an airfoil shape and secured between a spar and a platform with the spar including a tip end piece. a snap ring fits around the spar and abuts against the spar tip end piece on a top side and abuts against a shell on the bottom side so that the centrifugal loads from the shell is passed through the snap ring and into the spar and not through a tip cap dovetail slot and projection structure.

Abstract translation: 具有壳体的多片式涡轮转子叶片，其具有翼型并且固定在翼梁和平台之间，翼梁包括尖端部件。 卡环围绕翼梁并且抵靠在顶侧上的翼梁末端部件上并抵靠底侧的壳体，使得来自壳体的离心载荷通过卡环并进入翼梁，而不是通过 顶盖燕尾槽和投影结构。

公开(公告)号：US08167537B1

公开(公告)日：2012-05-01

申请号：US13298379

申请日：2011-11-17

Applicant: William L. Plank ,  James P. Downs ,  John A. Fedock

Inventor： William L. Plank ,  James P. Downs ,  John A. Fedock

IPC: F03B11/00 ,  F01D5/14 ,  F01D5/08 ,  F01D5/20 ,  F03D11/00 ,  F04D29/38

CPC classification number: F01D5/147 ,  F01D5/186 ,  F01D5/187 ,  F01D5/188 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/221 ,  Y02T50/671 ,  Y02T50/676

Abstract: An air cooled turbine airfoil such as a stator vane in which the airfoil is hollowed out and an insert is secured within the hollowed out section that produces sequential impingement cooling of the airfoil. The insert is formed from a plurality of plates bonded together outside of or inside of the airfoil to form a single piece insert with the cooling circuit. The plates are bonded together using TLP bonding process with sheets of boron placed between adjacent plates so that no excess material seeps out and into the cooling features formed with the plates. The cooling features of the plates are formed by photo-etching.

Abstract translation: 一种空气冷却的涡轮机翼片，例如定子叶片，其中翼型件被挖空，并且插入件固定在镂空部分内，以产生翼型件的顺序冲击冷却。 插入件由多个板结合在翼型外部或内部形成，以形成具有冷却回路的单件式插入件。 使用TLP粘合工艺将板粘合在一起，将硼放置在相邻板之间，使得没有多余的材料渗出并进入由板形成的冷却特征。 通过光蚀刻形成板的冷却特征。

公开(公告)号：US08322988B1

公开(公告)日：2012-12-04

申请号：US13241850

申请日：2011-09-23

Applicant: James P Downs ,  John A Fedock

Inventor： James P Downs ,  John A Fedock

IPC: F01D5/08 ,  F01D5/20

CPC classification number: F01D5/186 ,  B33Y80/00 ,  F01D5/147 ,  F01D5/187 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/221 ,  Y02T50/67 ,  Y02T50/676

Abstract: An air cooled turbine airfoil, such as a rotor blade, with a sequential impingement cooling circuit that provides a high level of cooling with a low amount of cooling air. The airfoil is formed of a spar and shell construction in which the spar is formed from a series of alternating layers that form the cooling circuit with the shell forming the gap for the impingement cooling channels. Two different layers form the impingement cooling channels with a third layer being a separation layer. The impingement cooling circuit includes a first impingement channel to cooling a forward half of the pressure side wall, a second impingement cooling channel to cool the aft half of the pressure side wall, a third impingement cooling channel to cool a forward section of the suction side wall, and a fourth impingement cooling channel to cool the aft section of the suction side wall.

Abstract translation: 具有顺序冲击冷却回路的风冷涡轮机翼片，例如转子叶片，其提供具有少量冷却空气的高水平冷却。 翼型件由翼梁和壳体结构形成，其中翼梁由形成冷却回路的一系列交替层形成，壳体形成用于冲击冷却通道的间隙。 两个不同的层形成冲击冷却通道，第三层是分离层。 冲击冷却回路包括：第一冲击通道，用于冷却压力侧壁的前半部;第二冲击冷却通道，用于冷却压力侧壁的后半部;第三冲击冷却通道，用于冷却吸入侧的前部; 壁和第四冲击冷却通道，以冷却吸入侧壁的后部。