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公开(公告)号：US10801330B1
公开(公告)日：2020-10-13
申请号：US15869148
申请日：2018-01-12
Applicant: United Technologies Corporation
Inventor： Charles H. Warner , Carl S. Richardson , Brian J. Schuler , Sue-Li Chuang
Abstract: A turbomachine airfoil element includes an airfoil that that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 0.46-0.58 inch (11.6-14.7 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span is in a range of 0.66-0.79 inch (16.7-20.0 mm. A first mode has a frequency of 35681±15% Hz and a second mode has a frequency of 39218±15% Hz.
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公开(公告)号：US20200232330A1
公开(公告)日：2020-07-23
申请号：US16251219
申请日：2019-01-18
Applicant: United Technologies Corporation
Inventor： Sue-Li Chuang , John Logan Whelan , Mark A. Stephens , Kenneth P. Clark , Liselle A. Joseph , James A. Eley
Abstract: A component system of a gas turbine engine including: a first component having an outer surface; a second component having an outer surface, the second component and the first component being in a facing spaced relationship defining an air passageway therebetween; and a first recess located in at least one of the outer surface of the first component proximate the air passage and the outer surface of the first component proximate the air passage, wherein the first recess is located proximate a throat within the air passageway stretching between the first component and the second component.
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公开(公告)号：US08997494B2
公开(公告)日：2015-04-07
申请号：US13664647
申请日：2012-10-31
Applicant: United Technologies Corporation
Inventor： Sue-Li Chuang , Yuan Dong , Sanjay S. Hingorani , Dilip Prasad
CPC classification number: F04D29/384 , F01D5/141 , F05D2220/36 , F05D2250/74 , Y02T50/672 , Y02T50/673 , Y10T137/0536 , Y10T137/0645
Abstract: A fan blade for a gas turbine engine includes an airfoil that includes leading and trailing edges joined by pressure and suction sides to provide an exterior airfoil surface that extends in a radial direction to a tip. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil described by a set of Cartesian coordinates set forth in Table 1. The Cartesian coordinates are provided by an axial coordinate scaled by a local axial chord. A circumferential coordinate is scaled by the local axial chord, and a span location. The local axial chord corresponds to a width of the airfoil between the leading and trailing edges at the span location.
Abstract translation: 用于燃气涡轮发动机的风扇叶片包括翼型件，其包括通过压力和吸力侧连接的前缘和后缘，以提供沿径向方向延伸到尖端的外部翼面。 外部翼面表面基本上符合由表1中所示的一组笛卡尔坐标所描述的翼型的多个横截面轮廓。笛卡尔坐标由通过局部轴向弦缩放的轴向坐标提供。 圆周坐标由局部轴向弦和跨度位置缩放。 局部轴向弦对应于跨距处的前缘和后缘之间的翼型的宽度。
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公开(公告)号：US11118459B2
公开(公告)日：2021-09-14
申请号：US16519475
申请日：2019-07-23
Applicant: United Technologies Corporation
Inventor： Edward J. Gallagher , Sue-Li Chuang
Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan section having a fan including a rotor hub rotatable about an engine longitudinal axis and an array of fan blades, a geared architecture, a compressor section including a low pressure compressor and a high pressure compressor, a turbine section including a low pressure turbine and a high pressure turbine. The low pressure turbine drives the fan through the geared architecture. Each fan blade of the array of fan blades includes pressure and suction sides and extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip, and facing pressure and suction sides of adjacent fan blades define a channel in a chordwise direction having a width between the facing pressure and suction sides at a given span position of the adjacent fan blades. The width at each pressure side location along the channel is defined as a minimum distance to a location along the suction side, and the width converges along the channel for at least some span positions.
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公开(公告)号：US10815787B1
公开(公告)日：2020-10-27
申请号：US15869206
申请日：2018-01-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： David Mikol , Kimberly Pash Boyington , Brian J. Schuler , Zhen Wu , Joseph Wieser , Xuedong Zhou , Sue-Li Chuang , John Joseph Papalia , Han J. Yu
Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 0.46-0.59 inch (11.8-14.9 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 0.73-0.86 inch (18.6-21.9 mm). The airfoil element includes at least two of a first mode with a frequency of 5133±15% Hz, a second mode with a frequency of 8542±15% Hz, a third mode with a frequency of 15487±15% Hz, a fourth mode with a frequency of 18774±15% Hz, a fifth mode with a frequency of 24295±15% Hz and a sixth mode with a frequency of 27084±15% Hz.
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Patent Agency Ranking
公开(公告)号：US10330111B2
公开(公告)日：2019-06-25
申请号：US15126371
申请日：2015-03-30
Applicant: United Technologies Corporation
Inventor： Scott C. Billings , Michael K. Gottschalk , William D. Owen , Edward J. Gallagher , Darryl Whitlow , Sue-Li Chuang , Mani Sadeghi
Abstract: In one exemplary embodiment, an airfoil for a turbine engine includes an airfoil that has pressure and suction sides and extends in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a curve that corresponds to a relationship between a leading edge dihedral and a span position. The leading edge dihedral has a portion of the curve with a change in dihedral in the range of 90% to 100% span position of greater than 10°. A positive dihedral corresponds to suction side-leaning. A negative dihedral corresponds to pressure side-leaning.
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公开(公告)号：US20160273361A1
公开(公告)日：2016-09-22
申请号：US14699322
申请日：2015-04-29
Applicant: United Technologies Corporation
Inventor： Edward J. Gallagher , Sue-Li Chuang
CPC classification number: F01D5/14 , F01D5/141 , F02C3/10 , F04D29/32 , F04D29/324 , F04D29/325 , F04D29/384 , F05D2220/36 , Y02T50/672 , Y02T50/673
Abstract: A fan section for a gas turbine engine according to an example of the present disclosure includes, among other things, a rotor hub defining an axis, and an array of airfoils circumferentially spaced about the rotor hub. Each of the airfoils include pressure and suction sides between a leading edge and a trailing edge and extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. Facing pressure and suction sides of adjacent airfoils define a channel in a chordwise direction having a width between the facing pressure and suction sides at a given span position of the adjacent airfoils. The width at each pressure side location along the channel is defined as a minimum distance to a location along the suction side. The width diverges without converging along the channel for at least some of the span positions.
Abstract translation: 根据本公开的示例的用于燃气涡轮发动机的风扇部分包括限定轴线的转子轮毂和围绕转子轮毂周向间隔开的翼型阵列。 每个翼型件包括在前缘和后缘之间的压力和吸力侧面，并且在径向方向上从内部流动路径位置处的0％跨度位置延伸到翼型端部处的100％跨度位置。 相邻翼型件的面对压力和吸力侧在相邻翼型件的给定跨度位置处限定具有在面向的压力和吸力侧之间的宽度的弦向方向的通道。 沿着通道的每个压力侧位置处的宽度被定义为到沿吸力侧的位置的最小距离。 宽度发散，而不会沿着通道聚集至少一些跨度位置。
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公开(公告)号：US20140311149A1
公开(公告)日：2014-10-23
申请号：US13664647
申请日：2012-10-31
Applicant: United Technologies Corporation
Inventor： Sue-Li Chuang , Yuan Dong , Sanjay S. Hingorani , Dilip Prasad
IPC: F04D29/38
CPC classification number: F04D29/384 , F01D5/141 , F05D2220/36 , F05D2250/74 , Y02T50/672 , Y02T50/673 , Y10T137/0536 , Y10T137/0645
Abstract: A fan blade for a gas turbine engine includes an airfoil that includes leading and trailing edges joined by pressure and suction sides to provide an exterior airfoil surface that extends in a radial direction to a tip. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil described by a set of Cartesian coordinates set forth in Table 1. The Cartesian coordinates are provided by an axial coordinate scaled by a local axial chord. A circumferential coordinate is scaled by the local axial chord, and a span location. The local axial chord corresponds to a width of the airfoil between the leading and trailing edges at the span location.
Abstract translation: 用于燃气涡轮发动机的风扇叶片包括翼型件，其包括通过压力和吸力侧连接的前缘和后缘，以提供沿径向方向延伸到尖端的外部翼面。 外部翼面表面基本上符合由表1中所示的一组笛卡尔坐标所描述的翼型的多个横截面轮廓。笛卡尔坐标由通过局部轴向弦缩放的轴向坐标提供。 圆周坐标由局部轴向弦和跨度位置缩放。 局部轴向弦对应于跨距处的前缘和后缘之间的翼型的宽度。
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公开(公告)号：US10358924B2
公开(公告)日：2019-07-23
申请号：US15045343
申请日：2016-02-17
Applicant: United Technologies Corporation
Inventor： Edward J. Gallagher , Sue-Li Chuang
Abstract: A fan section for a gas turbine engine according to an example of the present disclosure includes, among other things, a rotor hub defining an axis, and an array of airfoils circumferentially spaced about the rotor hub. Each of the airfoils include pressure and suction sides between a leading edge and a trailing edge and extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip, facing pressure and suction sides of adjacent airfoils defining a channel in a chordwise direction having a width between the facing pressure and suction sides at a given span position of the adjacent airfoils. The width at each pressure side location along the channel is defined as a minimum distance to a location along the suction side, the width converging and diverging along the channel for at least some span positions.
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公开(公告)号：US20170122336A1
公开(公告)日：2017-05-04
申请号：US15126371
申请日：2015-03-30
Applicant: United Technologies Corporation
Inventor： Scott C. Billings , Michael K. Gottschalk , William D. Owen , Edward J. Gallagher , Darryl Whitlow , Sue-Li Chuang , Mani Sadeghi
CPC classification number: F04D29/384 , F01D5/141 , F02C3/04 , F02C7/36 , F02K3/06 , F05D2220/36 , F05D2240/35 , F05D2250/70 , Y02T50/672 , Y02T50/673
Abstract: In one exemplary embodiment, an airfoil for a turbine engine includes an airfoil that has pressure and suction sides and extends in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a curve that corresponds to a relationship between a leading edge dihedral and a span position. The leading edge dihedral has a portion of the curve with a change in dihedral in the range of 90% to 100% span position of greater than 10°. A positive dihedral corresponds to suction side-leaning. A negative dihedral corresponds to pressure side-leaning.
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