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公开(公告)号：US10781695B1
公开(公告)日：2020-09-22
申请号：US15869912
申请日：2018-01-12
Applicant: United Technologies Corporation
Inventor： Charles H. Warner , William R. Edwards , Matthew R. Willett , Sean Nolan , Ernest D. Casparie
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 0.55-0.65 inch (14.0-16.5 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 0.76-0.86 inch (19.3-21.8 mm). The airfoil element includes at least two of a first mode with a frequency of 3335±10% Hz, a second mode with a frequency of 5715±10% Hz and a third mode with a frequency of 41797±10% Hz.
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公开(公告)号：US20180066673A1
公开(公告)日：2018-03-08
申请号：US15255663
申请日：2016-09-02
Applicant: United Technologies Corporation
Inventor： Simon W. Evans , Yuan Dong , Sean Nolan
CPC classification number: F04D29/384 , F01D5/145 , F04D19/02 , F04D29/324 , F05D2210/30 , F05D2220/3216 , F05D2240/307 , F05D2260/821 , F05D2270/3013 , Y02T50/673
Abstract: A compressor section for a gas turbine engine includes a blade including a platform, a tip and an airfoil extending between the platform and tip. The airfoil includes a root portion adjacent to the platform, a midspan portion and a tip portion. Each of the root portion, midspan portion and tip portion define a meridional velocity at stage exit with the tip portion including a first meridional velocity greater than a second meridional velocity of the midspan portion. A blade for an axial compressor of a gas turbine engine and a method of operating a compressor section of a gas turbine engine are also disclosed.
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公开(公告)号：US11248622B2
公开(公告)日：2022-02-15
申请号：US15255663
申请日：2016-09-02
Applicant: United Technologies Corporation
Inventor： Simon W. Evans , Yuan Dong , Sean Nolan
Abstract: A compressor section for a gas turbine engine includes a blade including a platform, a tip and an airfoil extending between the platform and tip. The airfoil includes a root portion adjacent to the platform, a midspan portion and a tip portion. Each of the root portion, midspan portion and tip portion define a meridional velocity at stage exit with the tip portion including a first meridional velocity greater than a second meridional velocity of the midspan portion. A blade for an axial compressor of a gas turbine engine and a method of operating a compressor section of a gas turbine engine are also disclosed.
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公开(公告)号：US10677266B1
公开(公告)日：2020-06-09
申请号：US15869939
申请日：2018-01-12
Applicant: United Technologies Corporation
Inventor： Charles H. Warner , William R. Edwards , Mark David Ring , Sean Nolan , Ernest D. Casparie
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 0.63-0.73 inch (16.0-18.5 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 0.61-0.71 inch (15.5-18.0 mm). The airfoil element includes at least two of a first mode with a frequency of 4852±10% Hz, a second mode with a frequency of 11917±10% Hz, a third mode with a frequency of 30842±10% Hz and a fourth mode with a frequency of 35225±10% Hz.
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公开(公告)号：US10415591B2
公开(公告)日：2019-09-17
申请号：US15272310
申请日：2016-09-21
Applicant: United Technologies Corporation
Inventor： Robert W Fessenden , Abhir A Adhate , Yuan Dong , Sean Nolan , Li Xing Pan
Abstract: A compressor may include an airfoil configured to rotate about an axis. The airfoil may have a span measured radially from a root of the airfoil to a tip of the airfoil. A compressor case may be radially adjacent to the airfoil. The airfoil and the compressor case may define a clearance between the tip of the airfoil and a radially inner surface of the compressor case. A ratio of the clearance to the span may be between 1.5 to 2.5 percent.
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Patent Agency Ranking
公开(公告)号：US20180073517A1
公开(公告)日：2018-03-15
申请号：US15261011
申请日：2016-09-09
Applicant: United Technologies Corporation
Inventor： Li Xing Pan , Yuan Dong , Simon W. Evans , Robert W. Fessenden , Sue-Li Kingsley Chuang , Sean Nolan
Abstract: Rotor of a gas turbine engines having a rotor hub and a plurality of blades extending from the rotor hub, wherein each blade has a full-span forward sweep along a leading edge of the blade that starts at an airfoil root of the blade at the hub and extends to a blade tip, wherein a sweep of a blade is a percentage of a root axial chord length of the respective blade.
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公开(公告)号：US10718223B1
公开(公告)日：2020-07-21
申请号：US15867820
申请日：2018-01-11
Applicant: United Technologies Corporation
Inventor： Charles H. Warner , William R. Edwards , Mark David Ring , Sean Nolan , Ernest D. Casparie
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 1.13-1.23 inch (28.7-31.2 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 0.64-0.74 inch (16.3-18.8 mm). The airfoil element includes at least two of a first mode with a frequency of 1634±10% Hz, a second mode with a frequency of 5611±10% Hz, a third mode with a frequency of 19027±10% Hz, a fourth mode with a frequency of 29268±10% Hz, a fifth mode with a frequency of 33103±10% Hz, a sixth mode with a frequency of 34908±10% Hz and a seventh mode with a frequency of 41277±10% Hz.
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公开(公告)号：US20180080472A1
公开(公告)日：2018-03-22
申请号：US15272310
申请日：2016-09-21
Applicant: United Technologies Corporation
Inventor： Robert W. Fessenden , Abhir A. Adhate , Yuan Dong , Sean Nolan , Li Xing Pan
CPC classification number: F04D29/526 , F01D5/12 , F01D11/14 , F01D25/24 , F04D29/164 , F04D29/324 , F05D2220/32 , F05D2230/50
Abstract: A compressor may include an airfoil configured to rotate about an axis. The airfoil may have a span measured radially from a root of the airfoil to a tip of the airfoil. A compressor case may be radially adjacent to the airfoil. The airfoil and the compressor case may define a clearance between the tip of the airfoil and a radially inner surface of the compressor case. A ratio of the clearance to the span may be between 1.5 to 2.5 percent.
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公开(公告)号：US20140096536A1
公开(公告)日：2014-04-10
申请号：US13646822
申请日：2012-10-08
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Brittany Travis , Crystal Monteiro , Sean Nolan , Rishon Saftler , John P. Virtue, JR. , Stephen A. Sarcich
CPC classification number: F02C6/08 , F02C9/18 , F04D27/0207 , F04D27/0215 , F04D27/023 , F04D29/526 , F04D29/644 , Y10T29/49236
Abstract: A disclosed gas turbine engine includes a case for a case for a compressor section including a bleed air slot. The bleed air slot includes an inlet having a first area radially inward of an outlet having a second area with the second area being greater than the first area. The bleed air slot further includes a center portion disposed along a radial line extending from an axis of the engine and an elongated portion extending from the opening at an angle relative to a line normal to the radial line.
Abstract translation: 所公开的燃气涡轮发动机包括用于包括排气槽的压缩机部分的壳体的壳体。 放气空气狭槽包括入口，入口具有出口的径向向内的第一区域，其具有第二区域，第二区域大于第一区域。 排放空气狭槽还包括沿着从发动机的轴线延伸的径向线设置的中心部分和从开口以相对于径向线垂直的线成一定角度延伸的细长部分。
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公开(公告)号：US11231050B1
公开(公告)日：2022-01-25
申请号：US15869402
申请日：2018-01-12
Applicant: United Technologies Corporation
Inventor： Haiyun Li , Eliannah Hunderfund , Sean Nolan , Joseph Steele , Marian A. Iskandar
Abstract: A turbomachine airfoil element includes an airfoil having 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 0.60-0.70 inch (15.3-17.8 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 0.90-1.00 inch (22.9-25.5 mm). The airfoil element includes at least two of a first mode with a frequency of 5327±10% Hz, a second mode with a frequency of 8393±10% Hz, a third mode with a frequency of 16289±10% Hz, a fourth mode with a frequency of 25049±10% Hz and a fifth mode with a frequency of 27423±10% Hz.
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