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公开(公告)号：US10683761B1
公开(公告)日：2020-06-16
申请号：US15871392
申请日：2018-01-15
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： William R. Edwards , Stephen W. Milks , Steven J. Feigleson , Mark A. Stephens , Joseph C. Straccia
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 2.13-2.43 inch (54.2-61.8 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 3.56-3.86 inch (90.3-97.9 mm). The airfoil element includes at least one of a first mode with a frequency of 1049±10% Hz and a second mode with a frequency of 1271±10% Hz.
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公开(公告)号：US20200149544A1
公开(公告)日：2020-05-14
申请号：US16740817
申请日：2020-01-13
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Edward J. Gallagher , Lisa I. Brilliant , Joseph C. Straccia , Stanley J. Balamucki , Mark A. Stephens , Kate Hudon
Abstract: A gas turbine engine includes a combustor section arranged between a compressor section and a turbine section. The compressor section includes at least a low pressure compressor and a high pressure compressor. The high pressure compressor is arranged upstream of the combustor section. A fan section has an array of twenty-six or fewer fan blades. The low pressure compressor is downstream from the fan section. An airfoil is arranged in the low pressure compressor and includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a camber angle and span position that defines a curve with a decreasing camber angle within the range of 80% span to 100% span. The camber angle is less than 20° within the entire range of 40% span to 100% span.
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公开(公告)号：US10557477B2
公开(公告)日：2020-02-11
申请号：US15113870
申请日：2015-02-16
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Edward J. Gallagher , Lisa I. Brilliant , Joseph C. Straccia , Stanley J. Balamucki , Mark A. Stephens , Kate Hudon
Abstract: A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a tangential stacking offset and span position that defines a curve that is non-linear.
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公开(公告)号：US20170175759A1
公开(公告)日：2017-06-22
申请号：US15116000
申请日：2015-02-17
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Edward J. Gallagher , Lisa I. Brilliant , Joseph C. Straccia , Stanley J. Balamucki , Mark A. Stephens , Kate Hudon
Abstract: A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a tangential trailing edge position and span position that defines a curve with a non-positive slope from 90% span to 100% span. The non-positive slope corresponds to a pressure side-leaning trailing edge.
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公开(公告)号：US20160131151A1
公开(公告)日：2016-05-12
申请号：US14996351
申请日：2016-01-15
Applicant: United Technologies Corporation
Inventor： Edward J. Gallagher , Lisa I. Brilliant , Joseph C. Straccia , Stanley J. Balamucki , Mark A. Stephens , Kate Hudon
CPC classification number: F01D5/141 , F04D29/324 , F05D2220/32 , F05D2260/40311 , Y02T50/672 , Y02T50/673
Abstract: An airfoil arrangement of a turbine engine according to an example of the present disclosure includes adjacent airfoils including pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position. The airfoils have a relationship between a gap/chord ratio and span position that defines a curve with a gap/chord ratio having a portion with a negative slope.
Abstract translation: 根据本公开的示例的涡轮发动机的翼型布置包括相邻的翼型件，其包括在从0％跨度位置到100％跨度位置的径向方向上延伸的压力和吸力侧。 翼型件具有间隙/弦比和跨度位置之间的关系，其限定具有具有负斜率的部分的间隙/弦比的曲线。
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Patent Agency Ranking
公开(公告)号：US10767488B1
公开(公告)日：2020-09-08
申请号：US15871197
申请日：2018-01-15
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： William R. Edwards , Stephen W. Milks , Steven J. Feigleson , Mark A. Stephens , Joseph C. Straccia
Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and is joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 3.18-3.48 inch (80.7-88.4 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 1.17-1.47 inch (29.6-37.3 mm). The airfoil element includes at least two of a first mode with a frequency of 333±10% Hz, a second mode with a frequency of 1554±10% Hz, a third mode with a frequency of 2356±10% Hz, a fourth mode with a frequency of 2830±10% Hz, a fifth mode with a frequency of 4075±10% Hz and a sixth mode with a frequency of 5239±10% 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：US10570916B2
公开(公告)日：2020-02-25
申请号：US15115360
申请日：2015-02-16
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Edward J. Gallagher , Lisa I. Brilliant , Joseph C. Straccia , Stanley J. Balamucki , Mark A. Stephens , Kate Hudon
Abstract: A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between an axial stacking offset and span position that includes a curve with a negative slope from 90% span to 100% span. The negative slope leans forward relative to an engine axis.
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公开(公告)号：US10465702B2
公开(公告)日：2019-11-05
申请号：US15114745
申请日：2015-02-17
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Edward J. Gallagher , Lisa I. Brilliant , Joseph C. Straccia , Stanley J. Balamucki , Mark A. Stephens , Kate Hudon
Abstract: A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between leading edge sweep angle and span position defined by a curve in which the leading edge sweep angle is positive at 0% span and crosses to a negative leading edge sweep angle at a span position less than 80% span. A negative sweep angle is in the forward direction, and a positive sweep angle is in the rearward direction.
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公开(公告)号：US10352331B2
公开(公告)日：2019-07-16
申请号：US15115779
申请日：2015-02-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Edward J. Gallagher , Lisa I. Brilliant , Joseph C. Straccia , Stanley J. Balamucki , Mark A. Stephens , Kate Hudon
Abstract: An airfoil of a turbine engine includes pressure and suction sides and extends in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a camber angle and span position that defines a curve with the camber angle having a positive slope from 0% span to 100% span.
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