公开(公告)号：US20110058939A1

公开(公告)日：2011-03-10

申请号：US12944177

申请日：2010-11-11

申请人： John Orosa ,  Matthew Montgomery

发明人： John Orosa ,  Matthew Montgomery

IPC分类号： F01D9/00

CPC分类号： F01D25/305

摘要： An exhaust diffuser system and method for a turbine engine includes an inner boundary and an outer boundary with a flow path defined therebetween. The inner boundary is defined at least in part by a hub structure that has an upstream end and a downstream end. The outer boundary may include a region in which the outer boundary extends radially inward toward the hub structure and may direct at least a portion of an exhaust flow in the diffuser toward the hub structure. The hub structure includes at least one jet exit located on the hub structure adjacent to the upstream end of the tail cone. The jet exit discharges a flow of gas substantially tangential to an outer surface of the tail cone to produce a Coanda effect and direct a portion of the exhaust flow in the diffuser toward the inner boundary.

摘要翻译： 用于涡轮发动机的排气扩散器系统和方法包括内边界和外边界，其间限定有流动路径。 内边界至少部分地由具有上游端和下游端的毂结构限定。 外部边界可以包括其中外部边界朝向轮毂结构径向向内延伸的区域，并且可以将扩散器中的排气流的至少一部分引向轮毂结构。 轮毂结构包括位于轮毂结构上的至少一个喷射出口，其邻近尾锥的上游端。 喷射出口排出基本上与尾锥的外表面相切的气体流，以产生柯恩达效应并将扩散器中的排气流的一部分引向内边界。

公开(公告)号：US08668449B2

公开(公告)日：2014-03-11

申请号：US12944210

申请日：2010-11-11

申请人： John Orosa

发明人： John Orosa

IPC分类号： F01D17/14

CPC分类号： F01D25/30 ,  F01D25/305

摘要： An exhaust diffuser system and method for a turbine engine. The outer boundary may include a region in which the outer boundary extends radially inwardly toward the hub structure and may direct at least a portion of an exhaust flow in the diffuser toward the hub structure. At least one gas jet is provided including a jet exit located on the outer boundary. The jet exit may discharge a flow of gas downstream substantially parallel to an inner surface of the outer boundary to direct a portion of the exhaust flow in the diffuser toward the outer boundary to effect a radially outward flow of at least a portion of the exhaust gas flow toward the outer boundary to balance an aerodynamic load between the outer and inner boundaries.

摘要翻译： 一种用于涡轮发动机的排气扩散器系统和方法。 外边界可以包括其中外边界朝向轮毂结构径向向内延伸的区域，并且可以将扩散器中的排气流的至少一部分引向轮毂结构。 提供至少一个气体喷射器，其包括位于外部边界上的喷射出口。 喷射出口可以排出大致平行于外边界内表面的气流，以将扩散器中的排气流的一部分引向外边界，以实现排气的至少一部分的径向向外流动 流向外边界以平衡外边界和内边界之间的空气动力学负载。

公开(公告)号：US20110056179A1

公开(公告)日：2011-03-10

申请号：US12944210

申请日：2010-11-11

申请人： John Orosa

发明人： John Orosa

IPC分类号： F02C7/08

CPC分类号： F01D25/30 ,  F01D25/305

摘要： An exhaust diffuser system and method for a turbine engine. The outer boundary may include a region in which the outer boundary extends radially inwardly toward the hub structure and may direct at least a portion of an exhaust flow in the diffuser toward the hub structure. At least one gas jet is provided including a jet exit located on the outer boundary. The jet exit may discharge a flow of gas downstream substantially parallel to an inner surface of the outer boundary to direct a portion of the exhaust flow in the diffuser toward the outer boundary to effect a radially outward flow of at least a portion of the exhaust gas flow toward the outer boundary to balance an aerodynamic load between the outer and inner boundaries.

摘要翻译： 一种用于涡轮发动机的排气扩散器系统和方法。 外边界可以包括其中外边界朝向轮毂结构径向向内延伸的区域，并且可以将扩散器中的排气流的至少一部分引向轮毂结构。 提供至少一个气体喷射器，其包括位于外部边界上的喷射出口。 喷射出口可以排出大致平行于外边界内表面的气流，以将扩散器中的排气流的一部分引向外边界，以实现排气的至少一部分的径向向外流动 流向外边界以平衡外边界和内边界之间的空气动力学负载。

公开(公告)号：US20100054946A1

公开(公告)日：2010-03-04

申请号：US12204034

申请日：2008-09-04

申请人： John Orosa ,  Matthew Montgomery

发明人： John Orosa ,  Matthew Montgomery

IPC分类号： F01D5/14

CPC分类号： F04D29/324 ,  F05D2220/3216 ,  F05D2250/74 ,  Y02T50/673

摘要： An airfoil for use as rotor blades in compressors for turbomachines, such as gas turbine engines. The airfoil includes increased forward sweep and forward dihedral effective to reduce losses generated by interaction of tip clearance flow, secondary flows and passage shocks.

摘要翻译： 用于涡轮机例如燃气轮机的压缩机中的转子叶片的翼型件。 翼型包括增加的向前扫掠和向前的二面体，以有效地减少由顶端间隙流动，次级流动和通道冲击的相互作用产生的损失。

公开(公告)号：US08727703B2

公开(公告)日：2014-05-20

申请号：US12876375

申请日：2010-09-07

申请人： Vincent P. Laurello ,  Keith D. Kimmel ,  John Orosa

发明人： Vincent P. Laurello ,  Keith D. Kimmel ,  John Orosa

IPC分类号： F01D25/08

CPC分类号： F01D5/081

摘要： A gas turbine engine includes a diffuser section supplying cooling fluid, a rotatable shaft, shaft cover structure disposed about the rotatable shaft, support structure, and a cooling fluid channel between the shaft cover structure and the support structure. The support structure provides structural support for the shaft cover structure and receives cooling fluid from the diffuser section. One of the diffuser section and the support structure comprises a plurality of apertures through which at least a portion of the cooling fluid passes. The cooling fluid channel is in fluid communication with the apertures in the one of the diffuser section and the support structure for supplying cooling fluid to a blade disc structure located in a turbine section of the engine.

摘要翻译： 燃气涡轮发动机包括供应冷却流体的扩散器部分，可旋转轴，围绕可旋转轴设置的轴盖结构，支撑结构以及轴盖结构和支撑结构之间的冷却流体通道。 支撑结构为轴盖结构提供结构支撑，并从扩散器部分接收冷却流体。 扩散器部分和支撑结构中的一个包括多个孔，冷却流体的至少一部分通过该孔。 冷却流体通道与扩散器部分和支撑结构之一中的孔口流体连通，用于将冷却流体供应到位于发动机涡轮机部分中的叶片结构。

公开(公告)号：US08647057B2

公开(公告)日：2014-02-11

申请号：US12944177

申请日：2010-11-11

申请人： John Orosa ,  Matthew Montgomery

发明人： John Orosa ,  Matthew Montgomery

IPC分类号： F01D25/24

CPC分类号： F01D25/305

摘要： An exhaust diffuser system and method for a turbine engine includes an inner boundary and an outer boundary with a flow path defined therebetween. The inner boundary is defined at least in part by a hub structure that has an upstream end and a downstream end. The outer boundary may include a region in which the outer boundary extends radially inward toward the hub structure and may direct at least a portion of an exhaust flow in the diffuser toward the hub structure. The hub structure includes at least one jet exit located on the hub structure adjacent to the upstream end of the tail cone. The jet exit discharges a flow of gas substantially tangential to an outer surface of the tail cone to produce a Coanda effect and direct a portion of the exhaust flow in the diffuser toward the inner boundary.

摘要翻译： 用于涡轮发动机的排气扩散器系统和方法包括内边界和外边界，其间限定有流动路径。 内边界至少部分地由具有上游端和下游端的毂结构限定。 外部边界可以包括其中外部边界朝向轮毂结构径向向内延伸的区域，并且可以将扩散器中的排气流的至少一部分引向轮毂结构。 轮毂结构包括位于轮毂结构上的至少一个喷射出口，其邻近尾锥的上游端。 喷射出口排出基本上与尾锥的外表面相切的气体流，以产生柯恩达效应并将扩散器中的排气流的一部分引向内边界。

公开(公告)号：US08147207B2

公开(公告)日：2012-04-03

申请号：US12204034

申请日：2008-09-04

申请人： John Orosa ,  Matthew Montgomery

发明人： John Orosa ,  Matthew Montgomery

IPC分类号： F01D5/14

CPC分类号： F04D29/324 ,  F05D2220/3216 ,  F05D2250/74 ,  Y02T50/673

摘要： An airfoil for use as rotor blades in compressors for turbomachines, such as gas turbine engines. The airfoil includes increased forward sweep and forward dihedral effective to reduce losses generated by interaction of tip clearance flow, secondary flows and passage shocks.

摘要翻译： 用于涡轮机例如燃气轮机的压缩机中的转子叶片的翼型件。 翼型包括增加的向前扫掠和向前的二面体，以有效地减少由顶端间隙流动，次级流动和通道冲击的相互作用产生的损失。

公开(公告)号：US20120057967A1

公开(公告)日：2012-03-08

申请号：US12876375

申请日：2010-09-07

申请人： Vincent P. Laurello ,  Keith D. Kimmel ,  John Orosa

发明人： Vincent P. Laurello ,  Keith D. Kimmel ,  John Orosa

IPC分类号： F01D25/08

CPC分类号： F01D5/081

摘要： A gas turbine engine includes a diffuser section supplying cooling fluid, a rotatable shaft, shaft cover structure disposed about the rotatable shaft, support structure, and a cooling fluid channel between the shaft cover structure and the support structure. The support structure provides structural support for the shaft cover structure and receives cooling fluid from the diffuser section. One of the diffuser section and the support structure comprises a plurality of apertures through which at least a portion of the cooling fluid passes. The cooling fluid channel is in fluid communication with the apertures in the one of the diffuser section and the support structure for supplying cooling fluid to a blade disc structure located in a turbine section of the engine.

摘要翻译： 燃气涡轮发动机包括供应冷却流体的扩散器部分，可旋转轴，围绕可旋转轴设置的轴盖结构，支撑结构以及轴盖结构和支撑结构之间的冷却流体通道。 支撑结构为轴盖结构提供结构支撑，并从扩散器部分接收冷却流体。 扩散器部分和支撑结构中的一个包括多个孔，冷却流体的至少一部分通过该孔。 冷却流体通道与扩散器部分和支撑结构之一中的孔口流体连通，用于将冷却流体供应到位于发动机涡轮机部分中的叶片结构。