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公开(公告)号：US20200217205A1
公开(公告)日：2020-07-09
申请号：US16827135
申请日：2020-03-23
Applicant: United Technologies Corporation
Inventor： Matthew P. Forcier , Brian J. Schuler
Abstract: A gas turbine engine includes a compressor section and a compressor case with a low pressure compressor (LPC) and a high pressure compressor (HPC). The HPC is aft of the LPC. The compressor case defines a centerline axis. The compressor section also includes a rotor disk defined between the compressor case and the centerline axis. A plurality of stages are defined radially inward relative to the compressor case. The plurality of stages include at least one tandem blade stage. The tandem blade stage includes a plurality of blade pairs. Each blade pair is circumferentially spaced apart from the other blade pairs, and is operatively connected to the rotor disk. Each blade pair includes a forward blade and an aft blade. The aft blade is configured to further condition air flow with respect to the forward blade without an intervening stator vane stage shrouded cavity therebetween.
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公开(公告)号：US10584598B2
公开(公告)日：2020-03-10
申请号：US14422368
申请日：2013-03-14
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Matthew E. Bintz , Peter T. Schutte , Brian J. Schuler , Anthony R. Bifulco
Abstract: A cantilevered airfoil includes, among other things, an airfoil having a body section and a tip, the body section extending in a first direction that is angled relative to a radial direction, the tip of the airfoil angled radially in a second direction relative to the body section.
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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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公开(公告)号：US10598024B2
公开(公告)日：2020-03-24
申请号：US14882722
申请日：2015-10-14
Applicant: United Technologies Corporation
Inventor： Matthew P. Forcier , Brian J. Schuler
Abstract: A gas turbine engine includes a compressor section and a compressor case with a low pressure compressor (LPC) and a high pressure compressor (HPC). The HPC is aft of the LPC. The compressor case defines a centerline axis. The compressor section also includes a rotor disk defined between the compressor case and the centerline axis. A plurality of stages are defined radially inward relative to the compressor case. The plurality of stages include at least one tandem blade stage. The tandem blade stage includes a plurality of blade pairs. Each blade pair is circumferentially spaced apart from the other blade pairs, and is operatively connected to the rotor disk. Each blade pair includes a forward blade and an aft blade. The aft blade is configured to further condition air flow with respect to the forward blade without an intervening stator vane stage shrouded cavity therebetween.
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公开(公告)号：US20160108735A1
公开(公告)日：2016-04-21
申请号：US14882722
申请日：2015-10-14
Applicant: United Technologies Corporation
Inventor： Matthew P. Forcier , Brian J. Schuler
Abstract: A gas turbine engine includes a compressor section and a compressor case with a low pressure compressor (LPC) and a high pressure compressor (HPC). The HPC is aft of the LPC. The compressor case defines a centerline axis. The compressor section also includes a rotor disk defined between the compressor case and the centerline axis. A plurality of stages defined radially inward relative to the compressor case. The plurality of stages includes at least one tandem blade stage. The tandem blade stage includes a plurality of blade pairs. Each blade pair is circumferentially spaced apart from the other blade pairs, and is operatively connected to the rotor disk. Each blade pair includes a forward blade and an aft blade. The aft blade is configured to further condition air flow with respect to the forward blade without an intervening stator vane stage shrouded cavity therebetween.
Abstract translation: 燃气涡轮发动机包括压缩机部分和具有低压压缩机（LPC）和高压压缩机（HPC）的压缩机壳体。 HPC是LPC的尾。 压缩机壳体定义一个中心线轴。 压缩机部分还包括限定在压缩机壳体和中心线轴线之间的转子盘。 相对于压缩机壳体径向向内限定的多个级。 多个级包括至少一个串联刀片级。 串联叶片台包括多个叶片对。 每个叶片对与其它叶片对周向间隔开，并且可操作地连接到转子盘。 每个刀片对包括前刀片和后刀片。 后叶片构造成进一步调节相对于前叶片的空气流动，而在它们之间没有中间的定子叶片级覆盖腔。
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Patent Agency Ranking
公开(公告)号：US10161250B2
公开(公告)日：2018-12-25
申请号：US14618041
申请日：2015-02-10
Applicant: United Technologies Corporation
Inventor： Matthew P. Forcier , Brian J. Schuler , Jordan T. Wall
Abstract: A rotor includes a rotor hub that is rotatable about an axis. The rotor hub includes a bore portion and a rim. An arm extends axially and radially inwardly from the rim. The arm has a radially inner side, a radially outer side, and a protruding ramp on the radially outer side.
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公开(公告)号：US20160230575A1
公开(公告)日：2016-08-11
申请号：US14618035
申请日：2015-02-10
Applicant: United Technologies Corporation
Inventor： Matthew P. Forcier , Brian J. Schuler , Jordan T. Wall
CPC classification number: F01D9/041 , F01D5/02 , F01D11/001 , F01D11/02 , F01D25/24 , F04D29/164 , F04D29/542 , F05D2220/32 , F05D2240/12 , F05D2240/80 , F05D2250/16 , F05D2250/712
Abstract: An airfoil includes a stator vane that has a platform with a first radial side and a second radial side, and a platform axial leading end and a platform axial trailing end. An airfoil portion extends radially outwardly from the first side. The platform axial trailing end includes a rear axial face that extends from the first radial side and a radially sloped face that extends from the rear axial face to the second radial side.
Abstract translation: 翼型件包括具有第一径向侧和第二径向侧的平台的定子叶片，以及平台轴向前端和平台轴向后端。 翼型部分从第一侧径向向外延伸。 平台轴向后端包括从第一径向侧延伸的后轴向面和从后轴向面延伸到第二径向侧的径向倾斜面。
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公开(公告)号：US20160230559A1
公开(公告)日：2016-08-11
申请号：US14618041
申请日：2015-02-10
Applicant: United Technologies Corporation
Inventor： Matthew P. Forcier , Brian J. Schuler , Jordan T. Wall
CPC classification number: F01D5/02 , F01D9/041 , F01D11/001 , F01D11/005 , F01D11/02 , F01D25/24 , F04D29/164 , F04D29/542 , F05D2240/12 , F05D2240/80
Abstract: A rotor includes a rotor hub that is rotatable about an axis. The rotor hub includes a bore portion and a rim. An arm extends axially and radially inwardly from the rim. The arm has a radially inner side, a radially outer side, and a protruding ramp on the radially outer side.
Abstract translation: 转子包括可围绕轴线旋转的转子轮毂。 转子毂包括孔部分和轮缘。 臂从轮缘轴向和径向向内延伸。 臂具有径向内侧，径向外侧和径向外侧上的突出斜面。
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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：US09938840B2
公开(公告)日：2018-04-10
申请号：US14618035
申请日：2015-02-10
Applicant: United Technologies Corporation
Inventor： Matthew P. Forcier , Brian J. Schuler , Jordan T. Wall
CPC classification number: F01D9/041 , F01D5/02 , F01D11/001 , F01D11/02 , F01D25/24 , F04D29/164 , F04D29/542 , F05D2220/32 , F05D2240/12 , F05D2240/80 , F05D2250/16 , F05D2250/712
Abstract: An airfoil includes a stator vane that has a platform with a first radial side and a second radial side, and a platform axial leading end and a platform axial trailing end. An airfoil portion extends radially outwardly from the first side. The platform axial trailing end includes a rear axial face that extends from the first radial side and a radially sloped face that extends from the rear axial face to the second radial side.
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