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公开(公告)号：US20210087934A1
公开(公告)日：2021-03-25
申请号：US16575935
申请日：2019-09-19
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Thomas VEITCH , Richard IVAKITCH , Bernard CHOW
Abstract: A balancing weight is disclosed. The balancing weight is engageable in a hole defined in a rotor, the hole having a predetermined cross-sectional dimension. The balancing weight comprises: a head having a predetermined weight, and a shank extending axially from the head. The shank includes at least two portions expandable in a direction transverse to a hole engagement direction between a first position in which a cross-sectional dimension of the shank is less than the predetermined cross-sectional dimension of the hole and a second position in which the cross-sectional dimension of the shank is greater than the predetermined cross-sectional dimension of the hole in the rotor. A method for installing a balancing weight to an engine rotor is also disclosed.
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公开(公告)号：US20200018176A1
公开(公告)日：2020-01-16
申请号：US16562701
申请日：2019-09-06
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Thomas VEITCH , Farid ABRARI , Ernest ADIQUE , Paul AITCHISON , Daniel FUDGE , Kari HEIKURINEN , Paul STONE , Tibor URAC
Abstract: A compressor rotor for a gas turbine engine has blades circumferentially distributed around and extending a span length from a central hub. The blades include alternating first and second blades having airfoils with corresponding geometric profiles. The airfoil of the first blade has a coating varying in thickness relative to the second blade to provide natural vibration frequencies different between the first and the second blades.
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公开(公告)号：US20190085704A1
公开(公告)日：2019-03-21
申请号：US15706247
申请日：2017-09-15
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Thomas VEITCH , Farid ABRARI , Ernest ADIQUE , Daniel FUDGE , Kari HEIKURINEN , Paul STONE , Ignatius THERATIL , Peter TOWNSEND , Tibor URAC
Abstract: A rotor for a gas turbine engine. The rotor includes blades circumferentially distributed around a hub. The blades have airfoils with a span defined between a root and tip, a chord defined between a leading edge and a trailing edge, and a thickness defined between a pressure side surface and suction side surface. The blades include first blades and second blades. The airfoil of the first blades has a first thickness distribution defining a first natural vibration frequency of the airfoils of the first blades. The airfoil of the second blades has a second thickness distribution defining a second natural vibration frequency different than the first natural vibration frequency. The first thickness distribution is different than the second thickness distribution along a radially-inner half of the span, and the first thickness distribution matches the second thickness distribution along a radially-outer half of the span.
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公开(公告)号：US20140255179A1
公开(公告)日：2014-09-11
申请号：US13789756
申请日：2013-03-08
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Bruce FIELDING , Nathan TOMES , Thomas VEITCH
CPC classification number: F01D9/041 , F01D9/042 , F01D25/246 , F05D2260/12 , Y10T29/4995
Abstract: A gas turbine having an annular casing with a series of circumferentially spaced openings defined therethrough; a plurality of vanes extending radially inwardly though respective casing openings, an outer end of the vanes projecting radially outwardly from the casing through the respective openings and located within the respective openings by grommets, and an inner end of the vanes being mounted to an inner portion of the casing; a flexible, segmented strap extending around the annular casing, surrounding the projecting outer ends of the vanes; and a spring radially loading the flexible strap configured to apply a tension force to the flexible strap.
Abstract translation: 一种燃气轮机，其具有环形壳体，其具有通过其限定的一系列周向间隔开的开口; 多个叶片径向向内延伸穿过相应的壳体开口，叶片的外端通过相应的开口从壳体径向向外突出并且通过索环位于相应的开口内，并且叶片的内端安装到内部 的套管 围绕所述环形壳体延伸的柔性分段带，围绕所述叶片的突出的外端; 并且弹簧径向地加载被配置为向柔性带施加张力的柔性带。
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公开(公告)号：US20200165924A1
公开(公告)日：2020-05-28
申请号：US16201255
申请日：2018-11-27
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Jason NICHOLS , Thomas VEITCH , Peter TOWNSEND , Hien DUONG , Guiherme WATSON
Abstract: An inter-compressor case for a gas turbine engine is disclosed. The inter-compressor case comprises: an outer casing and an inner casing radially spaced apart relative to a longitudinal axis; a gas path extending from a plurality of radial inlets arranged in a circumferentially spaced apart array around the outer casing to an annular outlet defined by an axially extending downstream portion of the outer casing and an axially extending downstream portion of the inner casing; a plurality of struts having a gas path surface extending across the gas path between the outer casing and the inner casing; and a plurality of flow separators extending from the adjacent radial inlets. The flow separators have trailing edges disposed upstream of the annular outlet and include a plurality of full length flow separators and a plurality of truncated flow separators.
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Patent Agency Ranking
公开(公告)号：US20190128282A1
公开(公告)日：2019-05-02
申请号：US16226694
申请日：2018-12-20
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Thomas VEITCH , Tibor URAC , Tyler RICHARDSON
Abstract: A gas turbine engine casing apparatus includes annular first and second annular cases connected by a spigot joint. The spigot joint includes an annular projection of the first annular case fitted into an annular recess of the second annular case. A plurality of circumferentially spaced apart scallops are formed on one of surfaces of the annular projection or of the annular recess, and are located in selective circumferential locations adjacent respective enhanced stiff areas of the first and second annular cases.
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公开(公告)号：US20190078589A1
公开(公告)日：2019-03-14
申请号：US15703472
申请日：2017-09-13
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Thomas VEITCH , Farid ABRARI , Ernest ADIQUE , Daniel FUDGE , Kari HEIKURINEN , Paul STONE , Ignatius THERATIL , Peter TOWNSEND , Tibor URAC
CPC classification number: F04D29/666 , F01D5/16 , F04D29/324 , F04D29/327 , F04D29/668 , F05D2220/36 , F05D2240/307 , F05D2260/961
Abstract: A rotor for a gas turbine engine comprises a rotor having a hub and blades around the hub, and extending from the hub to tips. The tips include first and second tip portions between their respective tip leading edge and tip trailing edge. Tips are spaced from a rotational axis of the rotor by spans. A mean span of a first tip portion of a first blade is greater than a mean span of a corresponding first tip portion of a second blade. A mean span of a second tip portion the first blade is less than a mean span of a corresponding second tip portion of the second blade.
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公开(公告)号：US20180066522A1
公开(公告)日：2018-03-08
申请号：US15808060
申请日：2017-11-09
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Raman WARIKOO , Krishna Prasad BALIKE , Keegan LOBO , Hien DUONG , Thomas VEITCH
CPC classification number: F01D5/141 , F01D9/041 , F04D29/324 , F05D2220/32 , F05D2240/12 , F05D2240/30 , F05D2240/301 , F05D2250/292
Abstract: An airfoil for a gas turbine engine comprises at least three successive sections defined between a root and a tip. A first decrease of maximum thickness-to-chord ratios defined by a difference between a maximum thickness-to-chord ratio at the root and a maximum thickness-to-chord ratio at a first spanwise position, a second decrease of the maximum thickness-to-chord ratios defined by a difference between the maximum thickness-to-chord ratio at the first spanwise position and a maximum thickness-to-chord ratio at a second spanwise position, a third decrease of the maximum thickness-to-chord ratios defined by a difference between the maximum thickness-to-chord ratio at the second spanwise position and a maximum thickness-to-chord ratio at the tip, the second decrease being greater than the corresponding first and third decreases.
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公开(公告)号：US20160146012A1
公开(公告)日：2016-05-26
申请号：US14553119
申请日：2014-11-25
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Raman WARIKOO , Krishna Prasad BALIKE , Keegan LOBO , Hien DUONG , Thomas VEITCH
CPC classification number: F01D5/141 , F01D9/041 , F04D29/324 , F05D2220/32 , F05D2240/12 , F05D2240/30 , F05D2240/301 , F05D2250/292
Abstract: An airfoil in a gas turbine engine includes opposed pressure and suction sides joined together at chordally opposite leading and trailing edges. The pressure and suction sides extend spanwise from a root to a tip of the airfoil. The airfoil has a spanwise distribution of maximum thicknesses of chordwise cross-sections of the airfoil. The spanwise distribution of maximum thicknesses decreases from the root to the tip. In one aspect, the spanwise distribution is stepped between a first portion extending from the root and a second portion extending to the tip.
Abstract translation: 燃气涡轮发动机中的翼型件包括在弦向相对的前缘和后缘处连接在一起的相对的压力和吸力侧。 压力和吸力侧从翼面的根部延伸到尖端。 翼型件具有翼型的弦横截面的最大厚度的翼展方向分布。 最大厚度的翼展方向分布从根部向尖端减小。 在一个方面，翼展方向分布在从根部延伸的第一部分和延伸到尖端的第二部分之间是阶梯状的。
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公开(公告)号：US20160061216A1
公开(公告)日：2016-03-03
申请号：US14469938
申请日：2014-08-27
Applicant: Pratt & Whitney Canada Corp.
Inventor： Hien DUONG , Krishna Prasad BALIKE , Thomas VEITCH , Raman WARIKOO , Keegan LOBO
CPC classification number: F04D29/384 , F01D5/141 , F01D5/145 , F04D19/00 , F04D19/02 , F04D29/324 , F05D2240/303 , F05D2270/17
Abstract: A compressor rotor airfoil in a gas turbine engine is presented. Opposed pressure and suction sides are joined together at chordally opposite leading and trailing edges. The pressure and suction sides extend in a span direction from a root to a tip. A leading edge dihedral angle is defined at a point on the leading edge between a tangent to the airfoil and a vertical. The leading edge dihedral angle has a span-wise distribution. The distribution has at least one inflection point. A method of reducing a rub angle between a compressor rotor blade and a casing surrounding the blade is also presented.
Abstract translation: 提出了一种燃气涡轮发动机中的压缩机转子翼型件。 相反的压力和吸力侧在弦向相反的前缘和后缘连接在一起。 压力和吸力侧在从根部到尖端的跨度方向上延伸。 前缘二面角定义在翼型的切线与垂直线之间的前缘上的一点上。 前缘二面角具有跨度分布。 分布至少有一个拐点。 还提出了一种降低压缩机转子叶片和围绕叶片的壳体之间的摩擦角的方法。
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