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公开(公告)号：US10774650B2
公开(公告)日：2020-09-15
申请号：US15782547
申请日：2017-10-12
Applicant: United Technologies Corporation
Inventor： Timothy Charles Nash , Thomas J. Praisner
Abstract: A component for a gas turbine engine includes a platform that has a radially inner side and a radially outer side. A root portion extends from the radially inner side of the platform. An airfoil extends from the radially outer side of the platform. The airfoil includes a pressure side that extends between a leading edge and a trailing edge. A suction side extends between the leading edge and the trailing edge. A curvature inflection point is located between 30% and 70% of an axial chord length of the airfoil.
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公开(公告)号：US20190112930A1
公开(公告)日：2019-04-18
申请号：US15782547
申请日：2017-10-12
Applicant: United Technologies Corporation
Inventor： Timothy Charles Nash , Thomas J. Praisner
Abstract: A component for a gas turbine engine includes a platform that has a radially inner side and a radially outer side. A root portion extends from the radially inner side of the platform. An airfoil extends from the radially outer side of the platform. The airfoil includes a pressure side that extends between a leading edge and a trailing edge. A suction side extends between the leading edge and the trailing edge. A curvature inflection point is located between 30% and 70% of an axial chord length of the airfoil.
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公开(公告)号：US20150361826A1
公开(公告)日：2015-12-17
申请号：US14712067
申请日：2015-05-14
Applicant: United Technologies Corporation
Inventor： Alex J. Simpson , Timothy Charles Nash
CPC classification number: F01D25/06 , F01D1/02 , F01D5/02 , F01D5/10 , F01D5/141 , F01D5/143 , F01D5/145 , F01D5/16 , F01D5/22 , F01D5/26 , F01D9/04 , F01D9/041 , F01D9/047 , F05D2220/32 , F05D2260/96 , Y02T50/673
Abstract: A gas turbine engine includes an array of airfoils. Each airfoil includes a first circumferentially extreme position. The first circumferentially extreme positions of the airfoils are circumferentially spaced apart from one another a pitch. Each airfoil includes a second circumferentially extreme position circumferentially spaced from the first circumferentially extreme position in an angular spacing that is at least one half the pitch.
Abstract translation: 燃气涡轮发动机包括翼型阵列。 每个翼型件包括第一周向极限位置。 翼型件的第一周向极限位置彼此沿间隔开间距。 每个翼型件包括第二周向极限位置，该第二周向极限位置与第一周向极限位置圆周地间隔开，其间距至少为间距的一半。
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公开(公告)号：US11473434B2
公开(公告)日：2022-10-18
申请号：US16654380
申请日：2019-10-16
Applicant: United Technologies Corporation
Inventor： Timothy Charles Nash , Gary A. Zess , Eric A. Grover , Jin Hu
Abstract: An airfoil includes pressure and suction sides that extend between a leading edge and a trailing edge. The airfoil has a camber line along an airfoil section that is equidistant between the exterior surface of the pressure and suction sides. The camber line extends from a 0% camber position at the leading edge to a 100% camber position at the trailing edge. A ratio of a maximum thickness to an axial chord length is between 0.2 and 0.5. The maximum thickness is located along the camber line between about 13% and 38% camber position.
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公开(公告)号：US10280756B2
公开(公告)日：2019-05-07
申请号：US15722566
申请日：2017-10-02
Applicant: United Technologies Corporation
Inventor： Timothy Charles Nash , Wolfgang Balzer
Abstract: A component for a gas turbine engine includes a platform that has a radially inner side and a radially outer side. A root portion extends from the radially inner side of the platform. An airfoil extends from a radially outer side of the platform. The airfoil includes a pressure side that extends between a leading edge and a trailing edge. A suction side extends between the leading edge and the trailing edge. A ratio of maximum thickness to axial chord length is between 0.40 (Tmax/bx) and 0.65 (Tmax/bx).
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Patent Agency Ranking
公开(公告)号：US20190101001A1
公开(公告)日：2019-04-04
申请号：US15722566
申请日：2017-10-02
Applicant: United Technologies Corporation
Inventor： Timothy Charles Nash , Wolfgang Balzer
Abstract: A component for a gas turbine engine includes a platform that has a radially inner side and a radially outer side. A root portion extends from the radially inner side of the platform. An airfoil extends from a radially outer side of the platform. The airfoil includes a pressure side that extends between a leading edge and a trailing edge. A suction side extends between the leading edge and the trailing edge. A ratio of maximum thickness to axial chord length is between 0.40 (Tmax/bx) and 0.65 (Tmax/bx).
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公开(公告)号：US11261737B1
公开(公告)日：2022-03-01
申请号：US15871260
申请日：2018-01-15
Applicant: United Technologies Corporation
Inventor： Daniel A. Snyder , Edwin Otero , Di Wu , Timothy Charles Nash , Brandon W. Spangler
Abstract: A turbomachine airfoil element comprises an airfoil having: an inboard end; an outboard end; a leading edge; a trailing edge; a pressure side; and a suction side. A span between the inboard end and the outboard end is 1.35-1.65 inches. A chord length at 50% span is 1.20-1.60 inches. At least two of: a first mode resonance frequency is 2858±10% Hz; a second mode resonance frequency is 4916±10% Hz; a third mode resonance frequency is 7160±10% Hz; a fourth mode resonance frequency is 10268±10% Hz; a fifth mode resonance frequency is 14235±10% Hz; and a sixth mode resonance frequency is 15088±10% Hz.
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公开(公告)号：US20210115803A1
公开(公告)日：2021-04-22
申请号：US16654380
申请日：2019-10-16
Applicant: United Technologies Corporation
Inventor： Timothy Charles Nash , Gary A. Zess , Eric A. Grover , Jin Hu
IPC: F01D9/02
Abstract: An airfoil includes pressure and suction sides that extend between a leading edge and a trailing edge. The airfoil has a camber line along an airfoil section that is equidistant between the exterior surface of the pressure and suction sides. The camber line extends from a 0% camber position at the leading edge to a 100% camber position at the trailing edge. A ratio of a maximum thickness to an axial chord length is between 0.2 and 0.5. The maximum thickness is located along the camber line between about 13% and 38% camber position.
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公开(公告)号：US20190120059A1
公开(公告)日：2019-04-25
申请号：US15793454
申请日：2017-10-25
Applicant: United Technologies Corporation
Inventor： Timothy Charles Nash , Loubriel Ramirez
IPC: F01D5/14
CPC classification number: F01D5/145 , F01D5/143 , F01D9/041 , F04D29/522 , F04D29/68 , F05D2240/12
Abstract: An airfoil array includes an endwall. A first airfoil and a second airfoil each extend radially from the endwall and have a first side and an opposite second side that extends along an axially chord between a leading edge and a trailing edge. A first profiled region is recessed into the endwall along the first side of the first airfoil. A second profiled region protrudes from the endwall approximately equidistant from the first side of the first airfoil and the second side of the second airfoil. A third profiled region is recessed into the endwall along adjacent the leading edge of the second side of the second airfoil. The third profiled region is at least partially axially aligned with the second profiled region.
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公开(公告)号：US20140154068A1
公开(公告)日：2014-06-05
申请号：US13664031
申请日：2012-10-30
Applicant: United Technologies Corporation
Inventor： Andrew S. Aggarwala , Timothy Charles Nash , Eunice Allen-Bradley , Eric A. Grover
CPC classification number: F01D9/02 , F01D5/143 , F01D5/145 , F04D29/324 , F04D29/542 , F04D29/681 , Y02T50/673
Abstract: An airfoil array is disclosed. The airfoil array may include an endwall, and a plurality of airfoils radially projecting from the endwall. Each airfoil may have a first side and an opposite second side extending axially in chord between a leading edge and a trailing edge. The airfoils may be circumferentially spaced apart on the endwall thereby defining a plurality of flow passages between adjacent airfoils. The airfoil array may further include a convex profiled region extending from the endwall adjacent to the first side of at least one of said plurality of airfoils near the leading edge of the at least one of said plurality of airfoils, and a concave profiled region in the endwall and extending across said at least one of said plurality of flow passages.
Abstract translation: 公开了一种翼型阵列。 翼型阵列可以包括端壁和从端壁径向突出的多个翼型件。 每个翼型件可以具有在前缘和后缘之间以弦状轴向延伸的第一侧和相对的第二侧。 翼型件可以在端壁上周向间隔开，从而在相邻翼型之间限定多个流动通道。 翼型阵列还可以包括凸出的轮廓区域，该凸形轮廓区域从靠近所述多个翼型件中的至少一个的前缘的所述多个翼型件中的至少一个的第一侧面的端壁延伸，并且在所述多个翼型件中的凹形轮廓区域 并且延伸穿过所述多个流动通道中的所述至少一个。
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