公开(公告)号：US09004866B2

公开(公告)日：2015-04-14

申请号：US13311630

申请日：2011-12-06

Applicant: Ching-Pang Lee ,  Glenn E. Brown ,  Benjamin E. Heneveld

Inventor： Ching-Pang Lee ,  Glenn E. Brown ,  Benjamin E. Heneveld

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F01D5/186 ,  F05D2240/122 ,  F05D2240/304

Abstract: A turbine blade (10) including an airfoil (12) having multiple interior wall portions (70) each separating at least one chamber from another one of multiple chambers (46, 48, 50, 58, 60). In one embodiment a first wall portion (70-2) between first and second chambers (60, 52) includes first and second pluralities of flow paths (86P, 86S) extending through the first wall portion. The first wall portion includes a first region R1 having a first thickness, t, measurable as a distance between the chambers. One of the paths extends a first path distance, d, as measured from an associated path opening (78) in the first chamber (60), through the first region and to an exit opening (82) in the second chamber (52) which path distance is greater than the first thickness.

Abstract translation: 一种涡轮机叶片（10），包括具有多个内壁部分（70）的翼型件（12），每个内壁部分（70）将至少一个腔室与多个腔室（46,48,50,58,60）中的另一个分隔开。 在一个实施例中，第一和第二腔室（60,52）之间的第一壁部分（70-2）包括延伸穿过第一壁部分的第一和第二多个流动路径（86P，86S）。 第一壁部分包括具有第一厚度t的第一区域R1，其可测量为腔室之间的距离。 路径中的一个沿着第一腔室（60）中的相关联的路径开口（78）测量的第一路径距离（d）延伸穿过第一区域并延伸到第二腔室（52）中的出口开口（82） 路径距离大于第一厚度。

公开(公告)号：US20150118034A1

公开(公告)日：2015-04-30

申请号：US14068070

申请日：2013-10-31

Applicant: Ching-Pang Lee ,  Benjamin E. Heneveld ,  Glenn E. Brown ,  Jill Klinger

Inventor： Ching-Pang Lee ,  Benjamin E. Heneveld ,  Glenn E. Brown ,  Jill Klinger

IPC: F01D5/18 ,  F01D9/02

CPC classification number: F01D5/187 ,  F01D9/02 ,  F05D2240/122 ,  F05D2240/304 ,  F05D2260/201 ,  F05D2260/2212

Abstract: A gas turbine engine component, including: a pressure side (12) having an interior surface (34); a suction side (14) having an interior surface (36); a trailing edge portion (30); and a plurality of suction side and pressure side impingement orifices (24) disposed in the trailing edge portion (30). Each suction side impingement orifice is configured to direct an impingement jet (48) at an acute angle (52) onto a target area (60) that encompasses a tip (140) of a chevron (122) within a chevron arrangement (120) formed in the suction side interior surface. Each pressure side impingement orifice is configured to direct an impingement jet at an acute angle onto an elongated target area that encompasses a tip of a chevron within a chevron arrangement formed in the pressure side interior surface.

Abstract translation: 一种燃气涡轮发动机部件，包括：具有内表面（34）的压力侧（12）; 吸入侧（14），其具有内表面（36）; 后缘部分（30）; 以及设置在后缘部分（30）中的多个吸力侧和压力侧冲击孔（24）。 每个吸入侧冲击孔构造成将锐角（52）的冲击射流（48）引导到目标区域（60）上，所述目标区域包围形成的人字形布置（120）内的人字形（122）的尖端（140） 在吸力侧内表面。 每个压力侧冲击孔构造成将冲击射流以锐角引导到细长的目标区域上，所述细长目标区域包含形成在压力侧内表面中的人字形布置中的人字形尖端。

公开(公告)号：US20130142666A1

公开(公告)日：2013-06-06

申请号：US13311630

申请日：2011-12-06

Applicant: Ching-Pang Lee ,  Glenn E. Brown ,  Benjamin E. Heneveld

Inventor： Ching-Pang Lee ,  Glenn E. Brown ,  Benjamin E. Heneveld

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F01D5/186 ,  F05D2240/122 ,  F05D2240/304

Abstract: A turbine blade (10) including an airfoil (12) having multiple interior wall portions (70) each separating at least one chamber from another one of multiple chambers (46, 48, 50, 58, 60). In one embodiment a first wall portion (70-2) between first and second chambers (60, 52) includes first and second pluralities of flow paths (86P, 86S) extending through the first wall portion. The first wall portion includes a first region R1 having a first thickness, t, measurable as a distance between the chambers. One of the paths extends a first path distance, d, as measured from an associated path opening (78) in the first chamber (60), through the first region and to an exit opening (82) in the second chamber (52) which path distance is greater than the first thickness.

Abstract translation: 一种涡轮机叶片（10），包括具有多个内壁部分（70）的翼型件（12），每个内壁部分（70）将至少一个腔室与多个腔室（46,48,50,58,60）中的另一个分隔开。 在一个实施例中，第一和第二腔室（60,52）之间的第一壁部分（70-2）包括延伸穿过第一壁部分的第一和第二多个流动路径（86P，86S）。 第一壁部分包括具有第一厚度t的第一区域R1，其可测量为腔室之间的距离。 路径中的一个沿着第一腔室（60）中的相关联的路径开口（78）测量的第一路径距离（d）延伸穿过第一区域并延伸到第二腔室（52）中的出口开口（82） 路径距离大于第一厚度。

公开(公告)号：US09039371B2

公开(公告)日：2015-05-26

申请号：US14068070

申请日：2013-10-31

Applicant: Ching-Pang Lee ,  Benjamin E. Heneveld ,  Glenn E. Brown ,  Jill Klinger

Inventor： Ching-Pang Lee ,  Benjamin E. Heneveld ,  Glenn E. Brown ,  Jill Klinger

IPC: F01D5/18 ,  F01D9/02

CPC classification number: F01D5/187 ,  F01D9/02 ,  F05D2240/122 ,  F05D2240/304 ,  F05D2260/201 ,  F05D2260/2212

Abstract: A gas turbine engine component, including: a pressure side (12) having an interior surface (34); a suction side (14) having an interior surface (36); a trailing edge portion (30); and a plurality of suction side and pressure side impingement orifices (24) disposed in the trailing edge portion (30). Each suction side impingement orifice is configured to direct an impingement jet (48) at an acute angle (52) onto a target area (60) that encompasses a tip (140) of a chevron (122) within a chevron arrangement (120) formed in the suction side interior surface. Each pressure side impingement orifice is configured to direct an impingement jet at an acute angle onto an elongated target area that encompasses a tip of a chevron within a chevron arrangement formed in the pressure side interior surface.

Abstract translation: 一种燃气涡轮发动机部件，包括：具有内表面（34）的压力侧（12）; 吸入侧（14），其具有内表面（36）; 后缘部分（30）; 以及设置在后缘部分（30）中的多个吸力侧和压力侧冲击孔（24）。 每个吸入侧冲击孔构造成将锐角（52）的冲击射流（48）引导到目标区域（60）上，所述目标区域包围形成的人字形布置（120）内的人字形（122）的尖端（140） 在吸力侧内表面。 每个压力侧冲击孔构造成将冲击射流以锐角引导到细长的目标区域上，所述细长目标区域包含形成在压力侧内表面中的人字形布置中的人字形尖端。

公开(公告)号：US20120282108A1

公开(公告)日：2012-11-08

申请号：US13099521

申请日：2011-05-03

Applicant: Ching-Pang Lee ,  Shantanu P. Mhetras ,  Glenn E. Brown

Inventor： Ching-Pang Lee ,  Shantanu P. Mhetras ,  Glenn E. Brown

IPC: F01D5/18

CPC classification number: F01D5/20

Abstract: A squealer tip formed from a pressure side rib and a suction side rib extending radially outward from a tip of the turbine blade is disclosed. The pressure and suction side ribs may be positioned along the pressure side and the suction side of the turbine blade, respectively. The pressure and suction side ribs may include chamfered leading edges with film cooling holes having exhaust outlets positioned therein. The film cooling holes may be configured to be diffusion cooling holes with one or more tapered sections for reducing the velocity of cooling fluids and increasing the size of the convective surfaces.

Abstract translation: 公开了一种从压力侧肋和从涡轮叶片的尖端径向向外延伸的吸力侧肋形成的尖叫尖端。 压力和吸力侧肋可以分别沿涡轮叶片的压力侧和吸力侧定位。 压力和吸力侧肋可以包括倒角的前缘，其中膜冷却孔具有位于其中的排气口。 膜冷却孔可以被配置为具有一个或多个锥形部分的扩散冷却孔，用于降低冷却流体的速度并增加对流表面的尺寸。

公开(公告)号：US08684691B2

公开(公告)日：2014-04-01

申请号：US13099521

申请日：2011-05-03

Applicant: Ching-Pang Lee ,  Shantanu P. Mhetras ,  Glenn E. Brown

Inventor： Ching-Pang Lee ,  Shantanu P. Mhetras ,  Glenn E. Brown

IPC: F01D5/20

CPC classification number: F01D5/20

Abstract: A squealer tip formed from a pressure side rib and a suction side rib extending radially outward from a tip of the turbine blade is disclosed. The pressure and suction side ribs may be positioned along the pressure side and the suction side of the turbine blade, respectively. The pressure and suction side ribs may include chamfered leading edges with film cooling holes having exhaust outlets positioned therein. The film cooling holes may be configured to be diffusion cooling holes with one or more tapered sections for reducing the velocity of cooling fluids and increasing the size of the convective surfaces.

Abstract translation: 公开了一种从压力侧肋和从涡轮叶片的尖端径向向外延伸的吸力侧肋形成的尖叫尖端。 压力和吸力侧肋可以分别沿涡轮叶片的压力侧和吸力侧定位。 压力和吸力侧肋可以包括倒角的前缘，其中膜冷却孔具有位于其中的排气口。 膜冷却孔可以被配置为具有一个或多个锥形部分的扩散冷却孔，用于降低冷却流体的速度并增加对流表面的尺寸。

公开(公告)号：US08690536B2

公开(公告)日：2014-04-08

申请号：US12892515

申请日：2010-09-28

Applicant: Alexander R. Beeck ,  Glenn E. Brown

Inventor： Alexander R. Beeck ,  Glenn E. Brown

IPC: F01D5/20 ,  F01D5/08

CPC classification number: F01D5/20 ,  F01D5/187 ,  F05D2210/33 ,  F05D2240/127 ,  F05D2250/21 ,  F05D2260/2212

Abstract: A turbine blade for a turbine engine having a tip with one or more vortex generators for reducing tip leakage during operation of the turbine engine. The vortex generators may extend radially outward from the radially outer surface of the tip wall. The vortex generator may be positioned between a rib extending radially outward from the radially outer surface of the tip wall and an intersection between the outer surface of the tip wall and an outer surface on the pressure side. The vortex generators may include a base and three sides forming a triangular point with a first side having a larger surface are than second and third sides. One or more film cooling holes may be formed in the tip wall to provide cooling air to the tip. In one embodiment, film cooling holes may be positioned in one or more vortex generators.

Abstract translation: 一种用于涡轮发动机的涡轮叶片，其具有具有一个或多个涡流发生器的尖端，用于在涡轮发动机的运行期间减少尖端泄漏。 涡流发生器可以从尖端壁的径向外表面径向向外延伸。 涡流发生器可以位于从尖端壁的径向外表面径向向外延伸的肋与尖端壁的外表面与压力侧的外表面之间的交叉点之间。 涡流发生器可以包括基部，并且形成具有比第二和第三侧更大表面的第一侧的三角形点的三个边。 可以在尖端壁中形成一个或多个薄膜冷却孔，以向尖端提供冷却空气。 在一个实施例中，膜冷却孔可以定位在一个或多个涡流发生器中。

公开(公告)号：US4416761A

公开(公告)日：1983-11-22

申请号：US402353

申请日：1982-07-27

Applicant: Glenn E. Brown ,  Timothy P. Karpetsky ,  Phillip Jewett

Inventor： Glenn E. Brown ,  Timothy P. Karpetsky ,  Phillip Jewett

IPC: G01N27/447 ,  G01N27/26

CPC classification number: G01N27/44721 ,  G01N27/44773 ,  G01N27/44782

Abstract: An electrophoresis system which provides enhanced resolution and ability to identify nucleases through use of a two-dimensional technique involving isoelectric focussing of tube gels followed by the electrophoresis of second-dimension slab gels formed by the use of a holder allowing slab gels to be cast directly on the sides of the tube gels. DNA is employed as the enzyme substrate within the slab gels. The slab gels are electrophoresed for the second dimension in a chamber wherein the rack containing a stack of slab gels forms the partition between the anolyte and catholyte compartments. After the second-dimension electrophoresis, the slab gels are incubated in incubation buffer and placed in Pyronin Y to stain the unhydrolized DNA. After staining, they are destained in acetic acid. The DNAses are then visible as colorless spots in a reddish-colored gel.

Abstract translation: 一种电泳系统，其通过使用管凝胶的等电聚焦的二维技术提供增强的分辨率和识别核酸酶的能力，然后通过使用允许直接铸造凝胶的保持器形成的第二维平板凝胶电泳 在管凝胶的两侧。 DNA用作板状凝胶内的酶底物。 板坯凝胶在腔室中进行电泳，用于第二尺寸，其中，包含一叠板状凝胶的支架在阳极电解液和阴极电解液室之间形成隔板。 在二维电泳之后，将板状凝胶在温育缓冲液中温育并置于Pyronin Y中以染色未水解的DNA。 染色后，它们在乙酸中脱色。 然后DNAses可见为浅色凝胶中的无色斑点。

公开(公告)号：US4185899A

公开(公告)日：1980-01-29

申请号：US691385

申请日：1976-06-01

Applicant: Hugh P. Sherlock ,  Edwin E. Ewry ,  Werner E. Sandvoss ,  Werner W. Ciupke ,  Glenn E. Brown ,  William T. Link

Inventor： Hugh P. Sherlock ,  Edwin E. Ewry ,  Werner E. Sandvoss ,  Werner W. Ciupke ,  Glenn E. Brown ,  William T. Link

IPC: G03B21/10 ,  G03B21/16

CPC classification number: G03B21/10

Abstract: A combination viewer and projector having a housing with a rear-lighted viewing screen mounted therein. The housing is adapted to receive a magazine having a length of film therein which can be advanced past an aperture in the magazine. A source of light is provided in the housing and is then directed into the magazine to form an image from the film in the aperture. Means is provided in the housing for receiving the image and for directing it onto a rear-lighted screen or alternatively through a projection opening in the housing.

Abstract translation: 具有安装在其中的后照明观察屏幕的壳体的组合观察器和投影仪。 壳体适于容纳其中具有一定长度的胶片的盒，其可以超过盒中的孔。 光源提供在壳体中，然后被引导到盒中以从孔中的膜形成图像。 在壳体中设置用于接收图像并将其引导到后照明屏幕上或者替代地通过壳体中的突出开口的装置。

公开(公告)号：US4015598A

公开(公告)日：1977-04-05

申请号：US610682

申请日：1975-09-05

Applicant: Glenn E. Brown

Inventor： Glenn E. Brown

IPC: A61M16/00 ,  A61M16/01 ,  A61M16/06

CPC classification number: A61M16/06 ,  A61M16/009 ,  A61M16/01 ,  A61M2210/0618

Abstract: A system for administering anaesthesia or analgesia to a patient in a safe and effective way while limiting the escape of the anaesthetic gases into the environment of the patient and the person administering the process.

Abstract translation: 一种用于以安全和有效的方式向患者施用麻醉或止痛的系统，同时限制麻醉气体逃逸到患者的环境和施用该过程的人员。