公开(公告)号：US20140041357A1

公开(公告)日：2014-02-13

申请号：US14053642

申请日：2013-10-15

Applicant: Anthony J. Malandra ,  John A. Orosa

Inventor： Anthony J. Malandra ,  John A. Orosa

IPC: F01D25/30

CPC classification number: F01D25/30 ,  F05D2240/127

Abstract: A turbine exhaust diffuser for a gas turbine engine. The diffuser includes a flow ramp positioned on an ID flowpath boundary within a flowpath of the diffuser. The flow ramp extends circumferentially about the hub and includes a downstream, radially outward point that extends radially outward further from the ID flowpath boundary than an upstream, radially outward point that is positioned upstream from the downstream, radially outward point. A wavy portion is located at the downstream, radially outward point of the flow ramp. The wavy portion includes a circumferentially extending, undulating surface defined by alternating axially extending crests and troughs.

Abstract translation: 一种用于燃气涡轮发动机的涡轮机排气扩散器。 扩散器包括位于扩散器的流路内的ID流路边界上的流动斜坡。 所述流动斜坡围绕所述轮毂周向延伸，并且包括从位于所述ID流路边界的径向向外延伸的下游径向外部点，所述下游径向向外点位于比所述下游径向向外点的上游位置的上游径向向外点。 波纹部分位于流动斜坡的下游径向向外的点。 波浪形部分包括由交替的轴向延伸的波峰和波谷限定的周向延伸的起伏的表面。

公开(公告)号：US09115602B2

公开(公告)日：2015-08-25

申请号：US14053642

申请日：2013-10-15

Applicant: Anthony J. Malandra ,  John A. Orosa

Inventor： Anthony J. Malandra ,  John A. Orosa

IPC: F02K1/78 ,  B63H11/10 ,  F01D25/30

CPC classification number: F01D25/30 ,  F05D2240/127

Abstract: A turbine exhaust diffuser for a gas turbine engine. The diffuser includes a flow ramp positioned on an ID flowpath boundary within a flowpath of the diffuser. The flow ramp extends circumferentially about the hub and includes a downstream, radially outward point that extends radially outward further from the ID flowpath boundary than an upstream, radially outward point that is positioned upstream from the downstream, radially outward point. A wavy portion is located at the downstream, radially outward point of the flow ramp. The wavy portion includes a circumferentially extending, undulating surface defined by alternating axially extending crests and troughs.

Abstract translation: 一种用于燃气涡轮发动机的涡轮机排气扩散器。 扩散器包括位于扩散器的流路内的ID流路边界上的流动斜坡。 所述流动斜坡围绕所述轮毂周向延伸，并且包括从位于所述ID流路边界的径向向外延伸的下游径向外部点，所述下游径向向外点位于比所述下游径向向外点的上游位置的上游径向向外点。 波纹部分位于流动斜坡的下游径向向外的点。 波浪形部分包括由交替的轴向延伸的波峰和波谷限定的周向延伸的起伏的表面。

公开(公告)号：US20120269649A1

公开(公告)日：2012-10-25

申请号：US13092312

申请日：2011-04-22

Applicant: Christopher Rawlings ,  Robert M. Dysert ,  Billie E. Sealey ,  Jose Paulino ,  Anthony J. Malandra

Inventor： Christopher Rawlings ,  Robert M. Dysert ,  Billie E. Sealey ,  Jose Paulino ,  Anthony J. Malandra

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F05D2210/33 ,  F05D2240/127 ,  F05D2250/185 ,  F05D2260/2212

Abstract: A turbine blade (110) is provided, where an exterior surface of the turbine blade (110) is exposed to a hot combustion gas (125) above a flow path line (141). The turbine blade (110) includes a trailing edge pin bank cooling channel (118) in an airfoil section (112), a cooling air supply channel (120) in a root section (114), and a channel (122) shaped with a radius of curvature (126), to extend the channel (122) across the flow path line (141) and interconnect the cooling air supply channel (120) to the trailing edge pin bank cooling channel (118). A width of the trailing edge pin bank cooling channel (118) is adjusted, such that the width at an inner diameter region (128) and an outer diameter region (131) is less than the width at an intermediate region (130) between the inner and outer diameter regions (128,131).

Abstract translation: 提供了一种涡轮机叶片（110），其中涡轮机叶片（110）的外表面暴露于流动路线（141）上方的热燃烧气体（125）。 涡轮叶片（110）包括翼型部分（112）中的后缘销组冷却通道（118），根部部分（114）中的冷却空气供应通道（120）和形成有 曲率半径（126），以使通道（122）跨过流动路径（141）延伸，并将冷却空气供应通道（120）与后缘销钉组冷却通道（118）互连。 调节后缘销组排冷却通道（118）的宽度，使得内径区域（128）和外径区域（131）处的宽度小于中间区域（130）之间的宽度， 内外径区域（128,131）。

公开(公告)号：US20080273984A1

公开(公告)日：2008-11-06

申请号：US11707190

申请日：2007-02-15

Applicant: George Liang ,  Anthony J. Malandra

Inventor： George Liang ,  Anthony J. Malandra

IPC: F01D5/14

CPC classification number: F01D5/141 ,  F05D2220/3212 ,  F05D2250/74 ,  Y02T50/673 ,  Y10S416/02

Abstract: A turbine blade including an airfoil having a pressure sidewall and a suction sidewall joined together along an upstream leading edge and a downstream trailing edge. The leading edge and trailing edge are formed as substantially straight edges, and portions of the pressure sidewall and suction sidewall adjacent the trailing edge form substantially planar surfaces. The airfoil has an uncoated nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein Z represents a perpendicular distance from a plane normal to a radius of a turbine centerline and containing the X and Y values with the Z value commencing at zero in the X, Y plane at a radially innermost aerodynamic section of the airfoil, and X and Y represent coordinate values defining the airfoil profile at each distance Z which, when connected by smooth continuing arcs, define profile sections at each distance Z.

Abstract translation: 一种涡轮机叶片，包括具有沿着上游前缘和下游后缘连接在一起的压力侧壁和吸力侧壁的翼型件。 前缘和后缘形成为基本上直的边缘，并且邻近后缘的压力侧壁和抽吸侧壁的部分形成基本平坦的表面。 翼型件具有基本上根据表1中所示的X，Y和Z的笛卡尔坐标值的未涂覆的标称轮廓，其中Z表示垂直于平面于涡轮机中心线的半径的平面的垂直距离，并且包含X和Y值与 在翼型的径向最内侧的空气动力学部分的X，Y平面处的Z值从零开始，X和Y表示在每个距离Z处限定翼面轮廓的坐标值，当通过平滑连续的弧连接时， 每个距离Z

公开(公告)号：US07632075B2

公开(公告)日：2009-12-15

申请号：US11707190

申请日：2007-02-15

Applicant: George Liang ,  Anthony J. Malandra

Inventor： George Liang ,  Anthony J. Malandra

IPC: F01D5/14

CPC classification number: F01D5/141 ,  F05D2220/3212 ,  F05D2250/74 ,  Y02T50/673 ,  Y10S416/02

Abstract: A turbine blade including an airfoil having a pressure sidewall and a suction sidewall joined together along an upstream leading edge and a downstream trailing edge. The leading edge and trailing edge are formed as substantially straight edges, and portions of the pressure sidewall and suction sidewall adjacent the trailing edge form substantially planar surfaces. The airfoil has an uncoated nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein Z represents a perpendicular distance from a plane normal to a radius of a turbine centerline and containing the X and Y values with the Z value commencing at zero in the X, Y plane at a radially innermost aerodynamic section of the airfoil, and X and Y represent coordinate values defining the airfoil profile at each distance Z which, when connected by smooth continuing arcs, define profile sections at each distance Z.

Abstract translation: 一种涡轮机叶片，包括具有沿着上游前缘和下游后缘连接在一起的压力侧壁和吸力侧壁的翼型件。 前缘和后缘形成为基本上直的边缘，并且邻近后缘的压力侧壁和抽吸侧壁的部分形成基本平坦的表面。 翼型件具有基本上根据表1中所示的X，Y和Z的笛卡尔坐标值的未涂覆的标称轮廓，其中Z表示垂直于平面于涡轮机中心线的半径的平面的垂直距离，并且包含X和Y值与 在翼型的径向最内侧的空气动力学部分的X，Y平面处的Z值从零开始，X和Y表示在每个距离Z处限定翼面轮廓的坐标值，当通过平滑连续的弧连接时， 每个距离Z

公开(公告)号：US5482435A

公开(公告)日：1996-01-09

申请号：US329609

申请日：1994-10-26

Applicant: Robert A. Dorris ,  William E. North ,  Anthony J. Malandra

Inventor： Robert A. Dorris ,  William E. North ,  Anthony J. Malandra

IPC: F01D5/18 ,  F01D5/08 ,  F01D5/20 ,  F01D5/22

CPC classification number: F01D5/08 ,  F01D5/225 ,  F05D2240/81

Abstract: A gas turbine blade having a shroud extending outwardly from the tip of the airfoil portion of the blade. The shroud is cooled by cooling air passages formed within it. A radial cooling air supply hole directs cooling air directly from the blade root through the airfoil and to the shroud. A plurality of cooling air passages extend from the supply hole and are disposed adjacent bearing surfaces along which the shroud contacts the shroud of an adjacent blade. One of these cooling air holes is formed in the portion of the shroud that projects from the convex surface of the airfoil and another one of the cooling air holes is formed in the portion of the shroud that projects from the concave surface of the airfoil. The cooling air holes extend to the edge of the shroud and discharge the cooling through an opening in the edge.

Abstract translation: 一种燃气轮机叶片，其具有从叶片的翼型部分的尖端向外延伸的护罩。 护罩由其内形成的冷却空气通道冷却。 径向冷却空气供应孔将冷却空气直接从叶片根部通过翼型件引导至护罩。 多个冷却空气通道从供应孔延伸并且设置在相邻的支承表面附近，护罩沿着该表面与邻近的叶片的护罩接触。 这些冷却空气孔中的一个形成在从翼型件的凸形表面突出的护罩的部分中，另一个冷却空气孔形成在从翼型件的凹面突出的护罩的部分中。 冷却空气孔延伸到护罩的边缘并通过边缘中的开口排出冷却物。

公开(公告)号：US09920625B2

公开(公告)日：2018-03-20

申请号：US13005733

申请日：2011-01-13

Applicant: Christopher Rawlings ,  Robert M. Dysert ,  Billie E. Sealey ,  Jose Paulino ,  Anthony J. Malandra

Inventor： Christopher Rawlings ,  Robert M. Dysert ,  Billie E. Sealey ,  Jose Paulino ,  Anthony J. Malandra

IPC: F01D5/14 ,  F01D5/02

CPC classification number: F01D5/027 ,  F01D5/147 ,  F05D2260/15 ,  F05D2260/961

Abstract: A turbine blade airfoil (32) with a center of mass (ACM) that is laterally offset from the center of mass (PCM) of a platform (42) to which the airfoil is attached. Respective offsets (da, dp) balance these centers of mass (ACM, PCM) about an attachment plane (64) of the blade root (30), providing balanced centrifugal loading on opposite lobes (51, 52) or other attachment surfaces of the root. The attachment plane (64) may be a plane of bilateral symmetry of the root, and/or it may include an attachment axis (65) that passes through the root center of mass (RCM) along a radius of rotation of the airfoil. The airfoil and platform centers of mass (ACM, PCM) may be dynamically balanced about the attachment axis (65) and/or the attachment plane (64).

公开(公告)号：US08864457B2

公开(公告)日：2014-10-21

申请号：US13589264

申请日：2012-08-20

Applicant: Anthony J. Malandra ,  Ching-Pang Lee ,  Barry J. Brown ,  Eric Munoz

Inventor： Anthony J. Malandra ,  Ching-Pang Lee ,  Barry J. Brown ,  Eric Munoz

IPC: F01D25/30 ,  F01D9/04 ,  F01D5/14

CPC classification number: F01D5/141 ,  F01D9/041 ,  F05D2220/3213 ,  F05D2250/74

Abstract: A turbine airfoil assembly for installation in a gas turbine engine. The airfoil assembly includes an endwall and an airfoil extending radially outwardly from the endwall. The airfoil includes pressure and suction sidewalls defining chordally spaced apart leading and trailing edges of the airfoil. An airfoil mean line is defined located centrally between the pressure and suction sidewalls. An angle between the mean line and a line parallel to the engine axis at the leading and trailing edges defines gas flow entry angles, α, and exit angles, β. Airfoil inlet and exit angles are substantially in accordance with pairs of inlet angle values, α, and exit angle values, β, set forth in one of Tables 1, 3, 5 and 7.

Abstract translation: 一种用于安装在燃气涡轮发动机中的涡轮机翼型组件。 翼型组件包括端壁和从端壁径向向外延伸的翼型件。 翼型件包括压力和抽吸侧壁，其限定翼型的弦向间隔开的前缘和后缘。 机翼平均线被定义为位于压力和吸力侧壁之间的中心。 平均线与平行于前缘和后缘的发动机轴线的直线之间的角度限定了气流入口角α和出口角度＆bgr。 翼型件的入口角和出口角度基本上与表1,3,5和7中的一个中的入口角度值α和出口角度值bgr对成对。

公开(公告)号：US20130089415A1

公开(公告)日：2013-04-11

申请号：US13589264

申请日：2012-08-20

Applicant: Barry J. Brown ,  Ching-Pang Lee ,  Anthony J. Malandra ,  Eric Munoz

Inventor： Barry J. Brown ,  Ching-Pang Lee ,  Anthony J. Malandra ,  Eric Munoz

IPC: F01D9/04

CPC classification number: F01D5/141 ,  F01D9/041 ,  F05D2220/3213 ,  F05D2250/74

Abstract: A turbine airfoil assembly for installation in a gas turbine engine. The airfoil assembly includes an endwall and an airfoil extending radially outwardly from the endwall. The airfoil includes pressure and suction sidewalls defining chordally spaced apart leading and trailing edges of the airfoil. An airfoil mean line is defined located centrally between the pressure and suction sidewalls. An angle between the mean line and a line parallel to the engine axis at the leading and trailing edges defines gas flow entry angles, α, and exit angles, β. Airfoil inlet and exit angles are substantially in accordance with pairs of inlet angle values, α, and exit angle values, β, set forth in one of Tables 1, 3, 5 and 7.

Abstract translation: 一种用于安装在燃气涡轮发动机中的涡轮机翼型组件。 翼型组件包括端壁和从端壁径向向外延伸的翼型件。 翼型件包括压力和抽吸侧壁，其限定翼型的弦向间隔开的前缘和后缘。 机翼平均线被定义为位于压力和吸力侧壁之间的中心。 平均线与平行于前缘和后缘的发动机轴线的直线之间的角度限定了气流入口角α和出口角度＆bgr。 翼型件的入口角和出口角度基本上与表1,3,5和7中的一个中的入口角度值α和出口角度值bgr对成对。

公开(公告)号：US20120183405A1

公开(公告)日：2012-07-19

申请号：US13005733

申请日：2011-01-13

Applicant: Christopher Rawlings ,  Robert M. Dysert ,  Billie E. Sealey ,  Jose Paulino ,  Anthony J. Malandra

Inventor： Christopher Rawlings ,  Robert M. Dysert ,  Billie E. Sealey ,  Jose Paulino ,  Anthony J. Malandra

IPC: F01D5/14

CPC classification number: F01D5/027 ,  F01D5/147 ,  F05D2260/15 ,  F05D2260/961

Abstract: A turbine blade airfoil (32) with a center of mass (ACM) that is laterally offset from the center of mass (PCM) of a platform (42) to which the airfoil is attached. Respective offsets (da, dp) balance these centers of mass (ACM, PCM) about an attachment plane (64) of the blade root (30), providing balanced centrifugal loading on opposite lobes (51, 52) or other attachment surfaces of the root. The attachment plane (64) may be a plane of bilateral symmetry of the root, and/or it may include an attachment axis (65) that passes through the root center of mass (RCM) along a radius of rotation of the airfoil. The airfoil and platform centers of mass (ACM, PCM) may be dynamically balanced about the attachment axis (65) and/or the attachment plane (64).

Abstract translation: 具有中心质量（ACM）的涡轮叶片翼型件（32），其横向偏离所述翼型件附接到所述平台（42）的质心（PCM）。 相应的偏移量（da，dp）围绕叶片根部（30）的附接平面（64）平衡这些质心（ACM，PCM），从而在相对的叶片（51,52）或其他附接表面 根。 附接平面（64）可以是根部的双侧对称的平面，和/或其可以包括沿着翼型的旋转半径穿过根质心（RCM）的附接轴线（65）。 翼型和平台质心（ACM，PCM）可围绕附接轴线（65）和/或附接平面（64）动态平衡。