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Patent Agency Ranking
公开(公告)号：US20140341749A1
公开(公告)日：2014-11-20
申请号：US14361594
申请日：2012-11-22
Applicant: SNECMA
Inventor： Vincent Paul Gabriel Perrot , Damien Cellier , Alicia Lise, Julia Dufresne , Philippe Pierre Marcel Marie Pelletrau , Jean-Francois Antoine Christian Rios , Laurent Christophe Francis Villaines
IPC: F01D5/14
CPC classification number: F01D5/141 , F01D5/34 , F04D29/324 , F05D2220/3216 , F05D2240/242 , F05D2240/303 , F05D2250/70 , F05D2250/71 , Y02T50/673
Abstract: A turbine engine blade comprising an airfoil extending axially between a leading edge and a trailing edge and extending radially between a root and a tip. The leading edge of the airfoil presents a sweep angle that is positive and that increases continuously from the root to a first radial height of the airfoil situated in the range 20% to 40% of the total radial height of the airfoil as measured from the root to the tip, and decreases continuously from this first radial height of the airfoil to the tip.
Abstract translation: 一种涡轮发动机叶片，包括在前缘和后缘之间轴向延伸并且在根部和尖端之间径向延伸的翼型件。 翼型的前缘呈现为正的扫掠角，并且从根部到第一径向高度连续增加，该翼型位于翼型的总径向高度的20％至40％的范围内，从根部测量 并且从翼型的第一径向高度到尖端连续地减小。
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公开(公告)号：US09556740B2
公开(公告)日：2017-01-31
申请号：US14361594
申请日：2012-11-22
Applicant: SNECMA
Inventor： Vincent Paul Gabriel Perrot , Damien Cellier , Alicia Lise Julia Dufresne , Philippe Pierre Marcel Marie Pelletrau , Jean-Francois Antoine Christian Rios , Laurent Christophe Francis Villaines
CPC classification number: F01D5/141 , F01D5/34 , F04D29/324 , F05D2220/3216 , F05D2240/242 , F05D2240/303 , F05D2250/70 , F05D2250/71 , Y02T50/673
Abstract: A turbine engine blade comprising an airfoil extending axially between a leading edge and a trailing edge and extending radially between a root and a tip. The leading edge of the airfoil presents a sweep angle that is positive and that increases continuously from the root to a first radial height of the airfoil situated in the range 20% to 40% of the total radial height of the airfoil as measured from the root to the tip, and decreases continuously from this first radial height of the airfoil to the tip.
Abstract translation: 一种涡轮发动机叶片，包括在前缘和后缘之间轴向延伸并且在根部和尖端之间径向延伸的翼型件。 翼型的前缘呈现为正的扫掠角，并且从根部到第一径向高度连续增加，该翼型位于翼型的总径向高度的20％至40％的范围内，从根部测量 并且从翼型的第一径向高度到尖端连续地减小。
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公开(公告)号：US10138897B2
公开(公告)日：2018-11-27
申请号：US14778317
申请日：2014-03-18
Applicant: Snecma
Inventor： Damien Cellier
Abstract: The invention relates to a compressor blade, defined at each one of the points of its surface by a sweep angle and a dihedral angle, comprising: a root, a tip, the distance between the root and the tip, measured along an axis referred to as the radial axis, perpendicular to an axis of rotation of the compressor, being referred to as radial height (h), a zone, between the root and the tip, of which a first portion has a strictly positive leading edge dihedral angle, and a second portion has a strictly negative leading edge dihedral angle, the zone of maximum dihedral angle being, along the radial axis, between r=0.25 h and r=0.7 h.
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公开(公告)号：US20160061218A1
公开(公告)日：2016-03-03
申请号：US14778317
申请日：2014-03-18
Applicant: Snecma
Inventor： Damien Cellier
CPC classification number: F04D29/384 , F01D5/141 , F04D29/324 , F04D29/544 , F04D29/563 , F05D2250/71 , Y02T50/673
Abstract: The invention relates to a compressor blade, defined at each one of the points of its surface by a sweep angle and a dihedral angle, comprising: a root, a tip, the distance between the root and the tip, measured along an axis referred to as the radial axis, perpendicular to an axis of rotation of the compressor, being referred to as radial height (h), a zone, between the root and the tip, of which a first portion has a strictly positive leading edge dihedral angle, and a second portion has a strictly negative leading edge dihedral angle, the zone of maximum dihedral angle being, along the radial axis, between r=0.25 h and r=0.7 h.
Abstract translation: 本发明涉及一种压缩机叶片，其在其表面的每个点处被限定为扫掠角和二面角，包括：根部，尖端，根部和尖端之间的距离，沿着所指的轴线 作为垂直于压缩机的旋转轴线的径向轴线被称为径向高度（h），根部和尖端之间的区域，第一部分具有严格正的前缘二面角，以及 第二部分具有严格负的前缘二面角，沿着径向轴的最大二面角的区域在r = 0.25h和r = 0.7h之间。
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公开(公告)号：US20140248144A1
公开(公告)日：2014-09-04
申请号：US14349000
申请日：2012-10-11
Applicant: SNECMA
Inventor： Damien Cellier , Alicia Lise, Julia Dufresne , Philippe Pierre Marcel, Marie Pelletrau , Vincent Paul, Gabriel Perrot , Jean-Francois Antoine, Christian Rios , Laurent Christophe, Francis Villaines
CPC classification number: F04D29/661 , F01D5/141 , F01D5/16 , F01D9/041 , F04D29/324 , F04D29/403 , F05D2260/96
Abstract: A turbomachine compressor blade of main radial orientation with respect to a main axis of the turbomachine. The blade includes a radially internal root portion, a radially external tip portion, a radially intermediate portion, a curved portion tangentially in a direction, and at least one straight portion on the root portion and/or on the tip portion.
Abstract translation: 相对于涡轮机的主轴线的主要径向取向的涡轮机压缩机叶片。 叶片包括径向内部根部部分，径向外部末端部分，径向中间部分，沿着方向切向的弯曲部分，以及根部部分和/或尖端部分上的至少一个直线部分。
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