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公开(公告)号：US20140165591A1
公开(公告)日：2014-06-19
申请号：US13717913
申请日：2012-12-18
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Seth J. Thomen , Wieslaw A. Chlus
IPC: F01D5/30
CPC classification number: F01D11/006 , F01D5/3007 , F01D5/3092 , F05D2300/173
Abstract: A gas turbine engine stage includes a rotor having a slot. A blade has a root received in the slot, and a shank that extends radially outward from the root to a platform that supports an airfoil. A seal is supported on the shank and in engagement circumferentially between and with the shank and the rotor within the slot. A gas turbine engine includes compressor and turbine sections. The turbine section has a rotor with a slot. A combustor is provided axially between the compressor and turbine sections. A turbine blade in the turbine section includes a root received in the slot and a shank that extends radially outward from the root to a platform that supports an airfoil.
Abstract translation: 燃气涡轮发动机级包括具有槽的转子。 叶片具有容纳在槽中的根部，以及从根部径向向外延伸到支撑翼型的平台的柄部。 密封件支撑在柄上并且在柄内和槽内的转子之间周向地接合。 燃气涡轮发动机包括压缩机和涡轮部分。 涡轮部分具有带槽的转子。 在压缩机和涡轮机部分之间轴向地设置有燃烧器。 涡轮部分中的涡轮叶片包括容纳在槽中的根部和从根部径向向外延伸到支撑翼型件的平台的柄部。
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公开(公告)号：US09995173B2
公开(公告)日：2018-06-12
申请号：US14924369
申请日：2015-10-27
Applicant: United Technologies Corporation
Inventor： Pedro L. Castaneda , Edward F. Pietraszkiewicz , Rafael A. Perez , Nestor A. Alvarez , Seth J. Thomen
CPC classification number: F01D25/12 , F01D9/041 , F01D9/065 , F05D2220/30 , F05D2240/81 , F05D2260/20 , F05D2260/202 , F05D2260/205 , F05D2260/22141 , Y02T50/676
Abstract: The present disclosure relates to cooling systems for turbine stators. A stator may include a vane platform. A ducting plate may be coupled to the vane platform. The ducting plate and the vane platform may form a cooling chamber between the ducting plate and the vane platform. The ducting plate may include an inlet adjacent to a leading edge of the vane platform. The vane platform may include an outlet adjacent to a trailing edge of the vane platform. The ducting plate may be configured to channel cooling air through the cooling chamber from the leading edge to the trailing edge.
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公开(公告)号：US20160032730A1
公开(公告)日：2016-02-04
申请号：US14774157
申请日：2014-03-13
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Seth J. Thomen , Edward F. Pietraszkiewicz , Dominic J. Mongillo, JR. , Wieslaw A. Chlus , Erik R. Granstrand
Abstract: An airfoil includes a cooling air passage for receiving a cooling air flow. A chevron including a first rib and a second rib extends from a common tip is disposed within the cooling passage for generating a turbulent flow to improve heat transfer. The chevron includes an angle between the first rib and the second rib that is greater than 90 degrees.
Abstract translation: 翼型件包括用于接收冷却空气流的冷却空气通道。 包括第一肋和第二肋的人字形从共同的尖端延伸设置在冷却通道内，用于产生湍流以改善热传递。 人字形包括大于90度的第一肋和第二肋之间的角度。
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公开(公告)号：US20160003074A1
公开(公告)日：2016-01-07
申请号：US14769208
申请日：2014-03-10
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Wieslaw A. Chlus , Seth J. Thomen
CPC classification number: F01D9/042 , F01D9/023 , F01D9/041 , F05D2240/81 , Y02T50/672 , Y02T50/676 , Y02T50/6765
Abstract: An airfoil component for a gas turbine engine includes a platform joined to an airfoil. The platform includes a flow path surface that extends between spaced apart lateral surfaces. The airfoil extends from the flow path surface. A contoured surface adjoins the flow path surface and one of the lateral surfaces.
Abstract translation: 用于燃气涡轮发动机的翼型件包括连接到翼型件的平台。 平台包括在间隔开的侧表面之间延伸的流动路径表面。 机翼从流路表面延伸。 轮廓表面毗邻流动路径表面和一个侧面。
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公开(公告)号：US20150369055A1
公开(公告)日：2015-12-24
申请号：US14762582
申请日：2014-01-24
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Seth J. Thomen , Wieslaw A. Chlus
CPC classification number: F01D5/186 , F01D5/02 , F01D5/081 , F02C3/04 , F02C7/18 , F05D2220/32 , F05D2230/10 , F05D2250/23 , F05D2250/232 , F05D2250/27 , F05D2250/711 , F05D2260/202 , Y02T50/676 , Y10T29/49343
Abstract: An airfoil assembly for a gas turbine engine is disclosed and includes a platform portion defining a portion of a gas flow path and a root portion for attachment of the turbine airfoil, the root portion including a bottom surface including a bottom area and a plurality of inlets that define a total inlet area as a ratio of the inlet area to the bottom area. An airfoil extends from the platform and including a plurality of cooling air passages in communication with the plurality of inlets.
Abstract translation: 公开了一种用于燃气涡轮发动机的翼型组件，并且包括限定气体流动路径的一部分的平台部分和用于附接涡轮机翼面的根部，该根部包括底表面和多个入口 其将总入口面积定义为入口面积与底部面积的比率。 机翼从平台延伸并且包括与多个入口连通的多个冷却空气通道。
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Patent Agency Ranking
公开(公告)号：US20140112792A1
公开(公告)日：2014-04-24
申请号：US14143828
申请日：2013-12-30
Applicant: United Technologies Corporation
Inventor： Seth J. Thomen , Christopher Corcoran
CPC classification number: F01D5/22 , F01D11/006 , F01D11/008 , F05D2250/25 , Y10S416/50
Abstract: A damper pin for coupling platforms of adjacent turbine blades includes a first flat longitudinal end region, a second flat longitudinal end region and a reduced cross sectional area. The reduced cross sectional area is separated from the first flat longitudinal end region by a first main body region and the reduced cross sectional area is separated from the second flat longitudinal end region by a second main body region. The cross sectional area of the reduced cross sectional area is less than the cross sectional area of each of the first and second main body regions.
Abstract translation: 用于联接相邻涡轮机叶片的平台的减震器销包括第一平坦纵向端部区域，第二平坦纵向端部区域和减小的横截面面积。 减小的横截面积由第一主体区域与第一平坦纵向端部区域分离，并且减小的横截面面积与第二平坦纵向端部区域通过第二主体区域分离。 横截面积减小的截面积小于第一和第二主体区域的横截面面积。
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公开(公告)号：US10215051B2
公开(公告)日：2019-02-26
申请号：US14911285
申请日：2014-08-13
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Seth J. Thomen , Edward Pietraszkiewicz
IPC: F01D25/12 , F04D29/54 , F04D29/58 , F01D11/24 , F02C7/12 , F01D9/04 , F01D11/08 , F04D29/16 , F01D9/06
Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform having a non-gas path surface and a gas path surface, a cover plate positioned relative to the non-gas path surface and a cooling passage that extends between the cover plate and the non-gas path surface. At least one cooling entrance is formed through the cover plate and configured to bias the flow of a cooling fluid toward a prioritized location of the non-gas path surface.
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公开(公告)号：US09982549B2
公开(公告)日：2018-05-29
申请号：US13717913
申请日：2012-12-18
Applicant: United Technologies Corporation
Inventor： Seth J. Thomen , Wieslaw A. Chlus
CPC classification number: F01D11/006 , F01D5/3007 , F01D5/3092 , F05D2300/173
Abstract: A gas turbine engine stage includes a rotor having a slot. A blade has a root received in the slot, and a shank that extends radially outward from the root to a platform that supports an airfoil. A seal is supported on the shank and in engagement circumferentially between and with the shank and the rotor within the slot. A gas turbine engine includes compressor and turbine sections. The turbine section has a rotor with a slot. A combustor is provided axially between the compressor and turbine sections. A turbine blade in the turbine section includes a root received in the slot and a shank that extends radially outward from the root to a platform that supports an airfoil.
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公开(公告)号：US20160047271A1
公开(公告)日：2016-02-18
申请号：US14924369
申请日：2015-10-27
Applicant: United Technologies Corporation
Inventor： Pedro L. Castaneda , Edward F. Pietraszkiewicz , Rafael A. Perez , Nestor A. Alvarez , Seth J. Thomen
CPC classification number: F01D25/12 , F01D9/041 , F01D9/065 , F05D2220/30 , F05D2240/81 , F05D2260/20 , F05D2260/202 , F05D2260/205 , F05D2260/22141 , Y02T50/676
Abstract: The present disclosure relates to cooling systems for turbine stators. A stator may include a vane platform. A ducting plate may be coupled to the vane platform. The ducting plate and the vane platform may form a cooling chamber between the ducting plate and the vane platform. The ducting plate may include an inlet adjacent to a leading edge of the vane platform. The vane platform may include an outlet adjacent to a trailing edge of the vane platform. The ducting plate may be configured to channel cooling air through the cooling chamber from the leading edge to the trailing edge.
Abstract translation: 本公开涉及涡轮定子的冷却系统。 定子可以包括叶片平台。 管道板可以联接到叶片平台。 导管板和叶片平台可以在管道板和叶片平台之间形成冷却室。 导管板可以包括与叶片平台的前缘相邻的入口。 叶片平台可以包括与叶片平台的后缘相邻的出口。 导管板可以被配置成将冷却空气从前缘引导到后缘。
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公开(公告)号：US09243504B2
公开(公告)日：2016-01-26
申请号：US14143828
申请日：2013-12-30
Applicant: United Technologies Corporation
Inventor： Seth J. Thomen , Christopher Corcoran
CPC classification number: F01D5/22 , F01D11/006 , F01D11/008 , F05D2250/25 , Y10S416/50
Abstract: A damper pin for coupling platforms of adjacent turbine blades includes a first flat longitudinal end region, a second flat longitudinal end region and a reduced cross sectional area. The reduced cross sectional area is separated from the first flat longitudinal end region by a first main body region and the reduced cross sectional area is separated from the second flat longitudinal end region by a second main body region. The cross sectional area of the reduced cross sectional area is less than the cross sectional area of each of the first and second main body regions.
Abstract translation: 用于联接相邻涡轮机叶片的平台的减震器销包括第一平坦纵向端部区域，第二平坦纵向端部区域和减小的横截面面积。 减小的横截面积由第一主体区域与第一平坦纵向端部区域分离，并且减小的横截面面积与第二平坦纵向端部区域通过第二主体区域分离。 横截面积减小的截面积小于第一和第二主体区域的横截面面积。
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