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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：US20170107830A1
公开(公告)日：2017-04-20
申请号：US14886201
申请日：2015-10-19
Applicant: United Technologies Corporation
Inventor： Joseph F. Englehart , Edward F. Pietraszkiewicz , Wieslaw A. Chlus , David M. Konopka , Luke A. Hmiel , Kenneth Boucher
Abstract: A blade assembly includes a blade and a blade platform secured to the blade. The blade extends radially from the blade platform. The blade platform includes at least one platform airflow passage located therein. A gusset extends from the blade to the blade platform. The gusset includes a gusset airflow passage fluidly connected to the platform airflow passage to convey an airflow to the platform airflow passage. a gas turbine engine includes a combustor and a plurality of gas turbine engine components located in fluid communication with the combustor. The gas turbine engine component includes an airfoil portion and a platform secured to the airfoil portion. The platform includes at least one platform airflow passage positioned therein. A gusset extends from the airfoil portion to the platform. The gusset includes a gusset airflow passage fluidly connected to the platform airflow passage to convey an airflow to the platform airflow passage.
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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：US20150354369A1
公开(公告)日：2015-12-10
申请号：US14728568
申请日：2015-06-02
Applicant: United Technologies Corporation
Inventor： Wieslaw A. Chlus , Seth J. Thomen
IPC: F01D5/18
CPC classification number: F01D5/186 , F01D5/143 , F01D5/187 , F05D2250/292 , F05D2250/312 , F05D2250/314 , F05D2250/322 , F05D2260/202 , Y02T50/672 , Y02T50/673 , Y02T50/676
Abstract: An airfoil for a gas turbine engine includes an airfoil that extends from a platform that has first and second circumferential sides that respectively extend to first and second circumferential edges. The first circumferential side has a tapered surface at a first angle relative to a flow path surface. The second circumferential surface has a cooling hole that extends toward the second lateral edge at a second angle relative to the flow path surface. The tapered surface and the cooling hole are axially aligned with one another.
Abstract translation: 用于燃气涡轮发动机的翼型件包括从具有分别延伸到第一和第二圆周边缘的第一和第二圆周侧的平台延伸的翼型件。 第一圆周侧相对于流路表面具有第一角度的锥形表面。 第二圆周表面具有相对于流路表面以第二角度朝向第二侧边缘延伸的冷却孔。 锥形表面和冷却孔彼此轴向对准。
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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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Patent Agency Ranking
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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公开(公告)号：US10677070B2
公开(公告)日：2020-06-09
申请号：US14886201
申请日：2015-10-19
Applicant: United Technologies Corporation
Inventor： Joseph F. Englehart , Edward F. Pietraszkiewicz , Wieslaw A. Chlus , David M. Konopka , Luke A. Hmiel , Kenneth Boucher
Abstract: A blade assembly includes a blade and a blade platform secured to the blade. The blade extends radially from the blade platform. The blade platform includes at least one platform airflow passage located therein. A gusset extends from the blade to the blade platform. The gusset includes a gusset airflow passage fluidly connected to the platform airflow passage to convey an airflow to the platform airflow passage. a gas turbine engine includes a combustor and a plurality of gas turbine engine components located in fluid communication with the combustor. The gas turbine engine component includes an airfoil portion and a platform secured to the airfoil portion. The platform includes at least one platform airflow passage positioned therein. A gusset extends from the airfoil portion to the platform. The gusset includes a gusset airflow passage fluidly connected to the platform airflow passage to convey an airflow to the platform airflow passage.
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公开(公告)号：US10156150B2
公开(公告)日：2018-12-18
申请号：US14769208
申请日：2014-03-10
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Wieslaw A. Chlus , Seth J. Thomen
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.
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公开(公告)号：US09850761B2
公开(公告)日：2017-12-26
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.
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