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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：US10422226B2
公开(公告)日：2019-09-24
申请号：US15113607
申请日：2014-08-22
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Edward J. Gallagher , Byron R. Monzon , Ling Liu , Linda S. Li , Darryl Whitlow , Barry M. Ford
Abstract: An airfoil for a turbine engine includes pressure and suction sides 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. The airfoil has a relationship between an axial leading edge location and a span position that is at least a third order polynomial with a generally U-shaped curve having an initial negative slope followed by a positive slope. The positive slope leans aftward and the negative slope leans forward. The curve has a critical point in the range of 30-50% span position at which the curve changes from the negative slope to the positive slope. The curve is generally linear from 55% span to 75% span and has a positive slope that increases at a rate of about 0.0875 inch (2.22 mm) per 1% span, +/−0.04 inch (1.01 mm) per 1% span.
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公开(公告)号：US10385866B2
公开(公告)日：2019-08-20
申请号：US15113470
申请日：2014-08-25
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Edward J. Gallagher , Byron R. Monzon , Ling Liu , Linda S. Li , Darryl Whitlow , Barry M. Ford
Abstract: In one exemplary embodiment, an airfoil for a turbine engine includes pressure and suction sides 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. The airfoil geometry corresponds to tangential leading and trailing edge curves and a tangential stacking offset curve. The airfoil extends from a root. A zero tangential reference point corresponds to tangential center of the root. YLE corresponds to a tangential distance from a leading edge to the reference point at a given span position. YTE corresponds to a tangential distance from a trailing edge to the reference point at a given span position. Yd corresponds to a tangential stacking offset at a given span position. (YLE−Yd)/(Yd−YTE) at 40% span position is about 1.5 and (YLE−Yd)/(Yd−YTE) at 20% span position is about 2.
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公开(公告)号：US10370974B2
公开(公告)日：2019-08-06
申请号：US14836577
申请日：2015-08-26
Applicant: United Technologies Corporation
Inventor： Edward J. Gallagher , Byron R. Monzon , Ling Liu , Linda S. Li , Darryl Whitlow , Barry M. Ford
Abstract: An airfoil of a turbine engine includes pressure and suction sides that extend 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 relationship between a tangential stacking offset and a span position that is at least a third order polynomial curve that includes at least one positive and negative slope. The positive slope leans toward the suction side and the negative slope leans toward the pressure side. An initial slope starts at the 0% span position is either zero or positive. The first critical point is less than 15% span.
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Patent Agency Ranking
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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公开(公告)号：US10309414B2
公开(公告)日：2019-06-04
申请号：US15470462
申请日：2017-03-27
Applicant: United Technologies Corporation
Inventor： Edward J. Gallagher , Byron R. Monzon , Ling Liu , Linda S. Li , Darryl Whitlow , Barry M. Ford
Abstract: An airfoil for a turbine engine includes an airfoil that has pressure and suction sides that extend 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 trailing edge sweep angle and a span position. The trailing edge sweep angle is in a range of 10° to 20° in a range of 40-70% span position. The trailing edge sweep angle is positive from 0% span to at least 95% span. The airfoil has a relationship between a leading edge dihedral and a span position. The leading edge dihedral is negative from the 0% span position to the 100% span position. A positive dihedral corresponds to suction side-leaning. A negative dihedral corresponds to pressure side-leaning. The trailing edge sweep angle is positive from 0%-95% span. A positive-most trailing edge sweep angle is within the range of 10° to 20° in the range of 40-70% span position. The airfoil is a fan blade for the turbine engine.
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公开(公告)号：US10184483B2
公开(公告)日：2019-01-22
申请号：US15063594
申请日：2016-03-08
Applicant: United Technologies Corporation
Inventor： Edward J. Gallagher , Byron R. Monzon , Ling Liu , Linda S. Li , Darryl Whitlow , Barry M. Ford
Abstract: An airfoil for a turbine engine includes pressure and suction sides that extend 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 relationship between a total chord length and a span position and corresponds to a curve that has an increasing total chord length from the 0% span position to a first peak. The first peak occurs in the range of 45-65% span position, and the curve either remains constant or has a decreasing total chord length from the first peak toward the 100% span position. The total chord length is at the 0% span position in the range of 8.2-10.5 inches (20.8-26.7 cm). The curve is at least a third order polynomial and has an initial positive slope.
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公开(公告)号：US09926885B2
公开(公告)日：2018-03-27
申请号：US15709540
申请日：2017-09-20
Applicant: United Technologies Corporation
Inventor： Edward J. Gallagher , Byron R. Monzon
CPC classification number: F02K3/06 , F01D17/14 , F02K1/06 , F05D2220/327 , F05D2260/4031
Abstract: A gas turbine engine includes a bypass flow passage that has an inlet and defines a bypass ratio in a range of approximately 8.5 to 13.5. A fan is arranged within the bypass flow passage. A first turbine is a 5-stage turbine and is coupled with a first shaft, which is coupled with the fan. A first compressor is coupled with the first shaft and is a 3-stage compressor. A second turbine is coupled with a second shaft and is a 2-stage turbine. The fan includes a row of fan blades that extend from a hub. The row includes a number (N) of the fan blades, a solidity value (R) at tips of the fab blades, and a ratio of N/R that is from 14 to 16.
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公开(公告)号：US20170191494A1
公开(公告)日：2017-07-06
申请号：US15470462
申请日：2017-03-27
Applicant: United Technologies Corporation
Inventor： Edward J. Gallagher , Byron R. Monzon , Ling Liu , Linda S. Li , Darryl Whitlow , Barry M. Ford
CPC classification number: F04D29/325 , F01D5/141 , F02K3/06 , F04D19/002 , F04D29/324 , F04D29/384 , F05D2220/32 , F05D2220/36 , F05D2240/30 , Y02T50/672 , Y02T50/673
Abstract: An airfoil for a turbine engine includes an airfoil that has pressure and suction sides that extend 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 trailing edge sweep angle and a span position. The trailing edge sweep angle is in a range of 10° to 20° in a range of 40-70% span position. The trailing edge sweep angle is positive from 0% span to at least 95% span. The airfoil has a relationship between a leading edge dihedral and a span position. The leading edge dihedral is negative from the 0% span position to the 100% span position. A positive dihedral corresponds to suction side-leaning. A negative dihedral corresponds to pressure side-leaning. The trailing edge sweep angle is positive from 0%-95% span. A positive-most trailing edge sweep angle is within the range of 10° to 20° in the range of 40-70% span position. The airfoil is a fan blade for the turbine engine.
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