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1. 再颁专利

USRE43710E1 Swept turbomachinery blade 有权
标题翻译：扫涡轮机叶片
公开(公告)号：USRE43710E1
公开(公告)日：2012-10-02
申请号：US09874931
申请日：2001-06-05
申请人： David A. Spear , Dennis N. Kantor, legal representative , Bruce P. Biederman , John A. Orosa
发明人： David A. Spear , Bruce P. Biederman , John A. Orosa
IPC分类号： F01D5/14
CPC分类号： F01D5/16 , F01D5/141 , F04D21/00 , F04D29/324 , F04D29/384 , F04D29/386 , F05D2220/327 , F05D2240/302 , F05D2250/70 , F05D2250/711 , F05D2250/712 , F05D2250/713
摘要： A swept turbomachinery blade for use in a cascade of such blades is disclosed. The blade (12) has an airfoil (22) uniquely swept so that an endwall shock (64) of limited radial extent and a passage shock (66) are coincident and a working medium (48) flowing through interblade passages (50) is subjected to a single coincident shock rather than the individual shocks. In one embodiment of the invention the forwardmost extremity of the airfoil defines an inner transition point (40) located at an inner transition radius rt-inner. The sweep angle of the airfoil is nondecreasing with increasing radius from the inner transition radius to an outer transition radius rt-outer, radially inward of the airfoil tip (26), and is nonincreasing with increasing radius between the outer transition radius and the airfoil tip.
摘要翻译：公开了一种用于这种叶片级联的扫掠式涡轮机叶片。叶片（12）具有独特地扫过的翼型件（22），使得有限径向范围的端壁冲击（64）和通道冲击（66）重合，并且流经叶片间通道（50）的工作介质（48）以单一的同时震惊而不是个别的冲击。在本发明的一个实施例中，翼型件的最前端限定位于内部过渡半径rt-内部的内部转变点（40）。翼型的扫掠角度随着从内部过渡半径到外部过渡半径rt-半径的增加而减小，这在外部过渡半径（外部过渡半径）外部，在翼型端部（26）的径向内侧，并且随着外部过渡半径和翼型尖端之间的半径的增加而增加。

2. 再颁专利

USRE45689E1 Swept turbomachinery blade 有权
公开(公告)号：USRE45689E1
公开(公告)日：2015-09-29
申请号：US12785222
申请日：2010-05-21
申请人： David A. Spear , Dennis N. Kantor , Bruce P. Biederman , John A. Orosa
发明人： David A. Spear , Bruce P. Biederman , John A. Orosa
IPC分类号： F01D5/14 , F01D5/16 , F04D21/00 , F04D29/32 , F04D29/38
CPC分类号： F01D5/16 , F01D5/141 , F04D21/00 , F04D29/324 , F04D29/384 , F04D29/386 , F05D2220/327 , F05D2240/302 , F05D2250/70 , F05D2250/711 , F05D2250/712 , F05D2250/713
摘要： A swept turbomachinery blade for use in a cascade of such blades is disclosed. The blade (12) has an airfoil (22) uniquely swept so that an endwall shock (64) of limited radial extent and a passage shock (66) are coincident and a working medium (48) flowing through interblade passages (50) is subjected to a single coincident shock rather than the individual shocks. In one embodiment of the invention the forwardmost extremity of the airfoil defines an inner transition point (40) located at an inner transition radius rt-inner. The sweep angle of the airfoil is nondecreasing with increasing radius from the inner transition radius to an outer transition radius rt-outer, radially inward of the airfoil tip (26), and is nonincreasing with increasing radius between the outer transition radius and the airfoil tip.

3. 再颁专利

USRE38040E1 Swept turbomachinery blade 有权
标题翻译：扫涡轮机叶片
公开(公告)号：USRE38040E1
公开(公告)日：2003-03-18
申请号：US09343736
申请日：1999-06-30
申请人： David A. Spear , Bruce P. Biederman , John A. Orosa
发明人： David A. Spear , Bruce P. Biederman , John A. Orosa
IPC分类号： F01D514
CPC分类号： F01D5/16 , F01D5/141 , F04D21/00 , F04D29/324 , F04D29/384 , F04D29/386 , F05D2220/327 , F05D2240/302 , F05D2250/70 , F05D2250/711 , F05D2250/712 , F05D2250/713
摘要： A swept turbomachinery blade for use in a cascade of such blades is disclosed. The blade (12) has an airfoil (22) uniquely swept so that an endwall shock (64) of limited radial extent and a passage shock (66) are coincident and a working medium (48) flowing through interblade passages (50) is subjected to a single coincident shock rather than the individual shocks. In one embodiment of the invention the forwardmost extremity of the airfoil defines an inner transition point (40) located at an inner transition radius rt-inner. The sweep angle of the airfoil is nondecreasing with increasing radius from the inner transition radius to an outer transition radius rt-outer, radially inward of the airfoil tip (26), and is nonincreasing with increasing radius between the outer transition radius and the airfoil tip.
摘要翻译：公开了一种用于这种叶片级联的扫掠式涡轮机叶片。叶片（12）具有独特地扫过的翼型件（22），使得有限径向范围的端壁冲击（64）和通道冲击（66）重合，并且流经叶片间通道（50）的工作介质（48）以单一的同时震惊而不是个别的冲击。在本发明的一个实施例中，翼型件的最前端限定位于内部过渡半径rt-内部的内部转变点（40）。翼型的扫掠角度随着从内部过渡半径到外部过渡半径rt-半径的增加而减小，这在外部过渡半径（外部过渡半径）外部，在翼型端部（26）的径向内侧，并且随着外部过渡半径和翼型尖端之间的半径的增加而增加。

4. 发明授权

US5642985A Swept turbomachinery blade 失效
标题翻译：扫涡轮机叶片
公开(公告)号：US5642985A
公开(公告)日：1997-07-01
申请号：US559965
申请日：1995-11-17
申请人： David A. Spear , Bruce P. Biederman , John A. Orosa
发明人： David A. Spear , Bruce P. Biederman , John A. Orosa
IPC分类号： F01D5/14 , F01D5/16 , F02K3/06 , F04D21/00 , F04D29/32 , F04D29/38
CPC分类号： F01D5/16 , F01D5/141 , F04D21/00 , F04D29/324 , F04D29/384 , F04D29/386 , F05D2220/327 , F05D2240/302 , F05D2250/70 , F05D2250/711 , F05D2250/712 , F05D2250/713
摘要： A swept turbomachinery blade for use in a cascade of such blades is disclosed. The blade (12) has an airfoil (22) uniquely swept so that an endwall shock (64) of limited radial extent and a passage shock (66) are coincident and a working medium (48) flowing through interblade passages (50) is subjected to a single coincident shock rather than the individual shocks. In one embodiment of the invention the forwardmost extremity of the airfoil defines an inner transition point (40) located at an inner transition radius r.sub.t -inner. The sweep angle of the airfoil is nondecreasing with increasing radius from the inner transition radius to an outer transition radius r.sub.t-outer, radially inward of the airfoil tip (26), and is nonincreasing with increasing radius between the outer transition radius and the airfoil tip.
摘要翻译：公开了一种用于这种叶片级联的扫掠式涡轮机叶片。叶片（12）具有独特地扫过的翼型件（22），使得有限径向范围的端壁冲击（64）和通道冲击（66）重合，并且流经叶片间通道（50）的工作介质（48）以单一的同时震惊而不是个别的冲击。在本发明的一个实施例中，翼型件的最前端限定位于内部过渡半径rt-内部的内部转变点（40）。翼型的扫掠角度随着从内部过渡半径到外部过渡半径rt-半径的增加而减小，这在外部过渡半径（外部过渡半径）外部，在翼型端部（26）的径向内侧，并且随着外部过渡半径和翼型尖端之间的半径的增加而增加。

5. 发明授权

US09598981B2 Industrial gas turbine exhaust system diffuser inlet lip 有权
公开(公告)号：US09598981B2
公开(公告)日：2017-03-21
申请号：US14087042
申请日：2013-11-22
申请人： Anil L. Salunkhe , John A. Orosa , Yevgeniy Shteyman , Lijuan Han , Matthew J. Delisa, III , Daniel F. Riveros
发明人： Anil L. Salunkhe , John A. Orosa , Yevgeniy Shteyman , Lijuan Han , Matthew J. Delisa, III , Daniel F. Riveros
IPC分类号： F01D25/30 , F02K1/78 , F02K1/80 , F02K1/82 , F01D9/04 , F01D11/00 , F01D25/16 , F01D25/24 , F01D5/14
CPC分类号： F01D25/30 , F01D5/143 , F01D9/041 , F01D11/001 , F01D25/162 , F01D25/243 , F02K1/78 , F02K1/80 , F02K1/82 , F05D2250/15
摘要： An integrated single-piece exhaust system (SPEX) with modular construction that facilitates design changes for enhanced aerodynamics, structural integrity or serviceability. The SPEX defines splined or curved exhaust path surfaces, such as a series of cylindrical and frusto-conical sections that mimic curves. The constructed sections may include: (i) a tail cone assembly fabricated from conical sections that taper downstream to a reduced diameter; or (ii) an area-ruled cross section axially aligned with one or more rows of turbine struts; or both features. Modular inner and outer diameter inlet lips enhance transitional flow between the last row blades and the SPEX, as well as enhance structural integrity. Modular strut collars have large radius profiles between the SPEX annular inner diameter and outer diameter flow surfaces, for enhanced airflow and constant thickness walls for uniform heat transfer and thermal expansion. Scalloped mounting flanges enhance structural integrity and longevity.

6. 发明申请

US20140041357A1 EXHAUST DIFFUSER INCLUDING FLOW MIXING RAMP FOR A GAS TURBINE ENGINE 有权
标题翻译：排气发动机，包括用于燃气涡轮发动机的流量混合器
公开(公告)号：US20140041357A1
公开(公告)日：2014-02-13
申请号：US14053642
申请日：2013-10-15
申请人： Anthony J. Malandra , John A. Orosa
发明人： Anthony J. Malandra , John A. Orosa
IPC分类号： F01D25/30
CPC分类号： F01D25/30 , F05D2240/127
摘要： 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.
摘要翻译：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。

7. 发明申请

US20130098039A1 EXHAUST DIFFUSER ADJUSTMENT SYSTEM FOR A GAS TURBINE ENGINE 失效
标题翻译：用于气体涡轮发动机的排气歧管调节系统
公开(公告)号：US20130098039A1
公开(公告)日：2013-04-25
申请号：US13276346
申请日：2011-10-19
申请人： John A. Orosa , Jason A. Kopko
发明人： John A. Orosa , Jason A. Kopko
IPC分类号： F02C7/00
CPC分类号： F01D25/30 , F05D2240/127
摘要： A turbine exhaust diffuser adjustment system for a gas turbine engine capable of altering the flow of turbine exhaust gases is disclosed. The turbine exhaust diffuser adjustment system may be formed from one or more flow ramps positioned in a flowpath. The flow ramp may include 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. The flow ramp may be adjustable such that an angular position of a radially outer surface of the flow ramp may be adjusted relative to the ID flowpath boundary, thereby enabling the flowpath to be changed during turbine operation to enhance the efficiency of the turbine engine throughout its range of operation.
摘要翻译：公开了一种能够改变涡轮废气流量的燃气涡轮发动机的涡轮排气扩散器调节系统。涡轮排气扩散器调节系统可以由位于流路中的一个或多个流动斜面形成。流动斜坡可以包括从位于ID流路边界的径向向外延伸的下游的径向向外的点，该点与位于下游径向向外的点的上游的径向向外的上游点相比。流动斜坡可以是可调节的，使得流道的径向外表面的角位置可以相对于ID流路边界进行调整，从而使得在涡轮机运行期间可以改变流路，以提高涡轮发动机在整个涡轮发动机中的效率操作范围。

8. 发明授权

US09644497B2 Industrial gas turbine exhaust system with splined profile tail cone 有权
公开(公告)号：US09644497B2
公开(公告)日：2017-05-09
申请号：US14087040
申请日：2013-11-22
申请人： Anil L. Salunkhe , John A. Orosa , Yevgeniy Shteyman , Matthew R. Porter , Lijuan Han , Matthew J. Delisa, III
发明人： Anil L. Salunkhe , John A. Orosa , Yevgeniy Shteyman , Matthew R. Porter , Lijuan Han , Matthew J. Delisa, III
IPC分类号： F01D25/30 , F01D25/24 , F01D9/04 , F01D11/00 , F01D25/16 , F01D5/14
CPC分类号： F01D25/30 , F01D5/143 , F01D9/041 , F01D11/001 , F01D25/162 , F01D25/243 , F05D2250/15
摘要： An integrated single-piece exhaust system (SPEX) with modular construction that facilitates design changes for enhanced aerodynamics, structural integrity or serviceability. The SPEX defines splined or curved exhaust path surfaces, such as a series of cylindrical and frusto-conical sections that mimic curves. The constructed sections may include: (i) a tail cone assembly fabricated from conical sections that taper downstream to a reduced diameter; or (ii) an area-ruled cross section axially aligned with one or more rows of turbine struts; or both features. Modular inner and outer diameter inlet lips enhance transitional flow between the last row blades and the SPEX, as well as enhance structural integrity. Modular strut collars have large radius profiles between the SPEX annular inner diameter and outer diameter flow surfaces, for enhanced airflow and constant thickness walls for uniform heat transfer and thermal expansion. Scalloped mounting flanges enhance structural integrity and longevity.

9. 发明授权

US09512740B2 Industrial gas turbine exhaust system with area ruled exhaust path 有权
标题翻译：工业燃气轮机排气系统带有排气排气道
公开(公告)号：US09512740B2
公开(公告)日：2016-12-06
申请号：US14087050
申请日：2013-11-22
申请人： John A. Orosa , Angelina Hinklein
发明人： John A. Orosa , Angelina Hinklein
IPC分类号： F01D25/30 , F01D9/04 , F01D11/00 , F01D25/16 , F01D25/24 , F01D5/14
CPC分类号： F01D25/30 , F01D5/143 , F01D9/041 , F01D11/001 , F01D25/162 , F01D25/243 , F05D2250/15 , Y10T29/49234
摘要： An integrated single-piece exhaust system (SPEX) with modular construction that facilitates design changes for enhanced aerodynamics, structural integrity or serviceability. The SPEX defines splined or curved exhaust path surfaces, such as a series of cylindrical and frusto-conical sections that mimic curves. The constructed sections may include: (i) a tail cone assembly fabricated from conical sections that taper downstream to a reduced diameter; or (ii) an area-ruled cross section axially aligned with one or more rows of turbine struts; or both features. Modular inner and outer diameter inlet lips enhance transitional flow between the last row blades and the SPEX, as well as enhance structural integrity. Modular strut collars have large radius profiles between the SPEX annular inner diameter and outer diameter flow surfaces, for enhanced airflow and constant thickness walls for uniform heat transfer and thermal expansion. Scalloped mounting flanges enhance structural integrity and longevity.
摘要翻译：具有模块化结构的集成单件式排气系统（SPEX），有助于设计更改，以提高空气动力学，结构完整性或可维护性。 SPEX定义了花键或弯曲的排气路径表面，例如模拟曲线的一系列圆柱形和截头圆锥形截面。构造的部分可以包括：（i）由圆锥形部分制造的尾锥组件，其锥形下游到减小的直径; 或（ii）与一排或多排涡轮支架轴向对准的面积划线的横截面; 或两个功能。模块化的内径和外径入口唇缘增强了最后一排叶片和SPEX之间的过渡流，并增强了结构完整性。模块化支柱套环在SPEX环形内径和外径流动表面之间具有大的半径分布，用于增强气流和恒定厚度的壁，以实现均匀的热传递和热膨胀。扇形安装法兰增强了结构的完整性和使用寿命。

10. 发明申请

US20150086339A1 DIFFUSER WITH STRUT-INDUCED VORTEX MIXING 有权
标题翻译：具有诱导型VORTEX混合的扩散器
公开(公告)号：US20150086339A1
公开(公告)日：2015-03-26
申请号：US14033788
申请日：2013-09-23
申请人： John A. Orosa
发明人： John A. Orosa
IPC分类号： F01D25/30 , F01D17/16 , F01D17/14
CPC分类号： F01D25/30 , F01D17/143 , F01D17/16 , F05D2220/32 , F05D2240/122 , F05D2240/127 , F05D2250/70
摘要： A gas turbine engine includes inner and outer shrouds forming an annular gas path, and a plurality of struts connecting the inner shroud to the outer shroud. Airfoil shaped shields surround the struts, and each of the shields include a main body having an upstream leading edge defining a chordal axis extending in a downstream axial direction from the leading edge toward a downstream end of the shield. A trailing edge flap is located at the downstream end of each shield, the trailing edge flap including first and second span-wise portions. The first span-wise portion is oriented to direct flow at an angle relative to the chordal axis of the main body and the second span-wise portion is oriented to direct flow in a direction that is at a different angle than the angle of first span-wise portion.
摘要翻译：燃气涡轮发动机包括形成环形气体路径的内罩和外罩，以及将内护罩连接到外罩的多个支柱。翼型护罩围绕支柱，并且每个护罩包括主体，该主体具有限定从下游轴向方向延伸的弦线轴线的上游前缘，从前缘朝向盾构件的下游端延伸。后缘皮瓣位于每个护罩的下游端，后缘皮瓣包括第一和第二跨度部分。第一跨度部分被定向成相对于主体的弦线以一定角度引导流动，并且第二跨度部分被定向成在与第一跨度的角度不同的角度上引导流动方向。

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