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公开(公告)号：US09803559B2
公开(公告)日：2017-10-31
申请号：US14615665
申请日：2015-02-06
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Andrew D. Burdick , Thomas J. Praisner , Andrew S. Aggarwala , Eric A. Hudson , Michael G. McCaffrey
CPC classification number: F02C9/20 , F01D5/148 , F01D9/02 , F01D11/025 , F01D17/162 , F02C3/04 , F05D2240/122 , Y02T50/672 , Y02T50/673 , Y10T137/0536
Abstract: One exemplary embodiment of this disclosure relates to a system including an airfoil having a static portion, a moveable portion, and a seal between the static portion and the moveable portion. The seal is moveable separate from the static portion and the moveable portion.
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公开(公告)号：US20150240712A1
公开(公告)日：2015-08-27
申请号：US14608304
申请日：2015-01-29
Applicant: United Technologies Corporation
Inventor： Renee J. Jurek , Thomas J. Praisner
CPC classification number: F01D5/143 , F01D9/041 , F05D2220/3213 , Y02T50/673
Abstract: A mid-turbine vaned duct comprises a duct upstream end to abut a downstream end of an upstream turbine rotor. A duct downstream end abuts an upstream end of a downstream turbine rotor. The vaned duct includes a first gap extending between the upstream turbine rotor and an upstream end of a vane positioned within the duct, intermediate the vaned duct upstream and downstream ends. A second gap is defined between a downstream end of the vane and the downstream turbine rotor. The first gap extends for a first axial distance and the second gap extends for a second axial distance. A length ratio of the first axial distance to the second axial distance is less than or equal to 2.0.
Abstract translation: 中涡轮叶片管道包括用于邻接上游涡轮转子的下游端的管道上游端。 管道下游端邻接下游涡轮转子的上游端。 所述带式管道包括在所述上游涡轮机转子和位于所述管道内的叶片的上游端之间延伸的第一间隙，所述第一间隙位于所述带通管道上游和下游端部的中间。 第二间隙限定在叶片的下游端和下游涡轮转子之间。 第一间隙延伸第一轴向距离，第二间隙延伸第二轴向距离。 第一轴向距离与第二轴向距离的长度比小于或等于2.0。
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公开(公告)号：US08915090B2
公开(公告)日：2014-12-23
申请号：US14221450
申请日：2014-03-21
Applicant: United Technologies Corporation
Inventor： Thomas J. Praisner , Shankar S. Magge , Matthew B. Estes
CPC classification number: F01D9/041 , F01D5/141 , F01D9/04 , F01D9/065 , F01D25/28 , F02K3/06 , F05D2240/12 , Y02T50/673
Abstract: A gas turbine engine includes first and second stages having a rotational axis. A circumferential array of airfoils is arranged axially between the first stage and the second stage. At least one of the airfoils have a curvature provided equidistantly between pressure and suction sides. The airfoils extend from a leading edge to a trailing edge at a midspan plane along the airfoil. An angle is defined between first and second lines respectively tangent to the intersection of the midspan plane and the curvature at airfoil leading and trailing edges. The angle is equal to or greater than about 10°.
Abstract translation: 燃气涡轮发动机包括具有旋转轴线的第一和第二级。 在第一阶段和第二阶段之间轴向布置有圆周阵列的翼型件。 至少一个翼型件具有在压力侧和吸力侧之间等距离设置的曲率。 翼型件从翼缘沿着翼型在中跨平面处从前缘延伸到后缘。 第一和第二线之间的角度分别与翼型前缘和后缘的中跨平面和曲率的交点相切。 该角度等于或大于约10°。
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公开(公告)号：US20140202133A1
公开(公告)日：2014-07-24
申请号：US14221450
申请日：2014-03-21
Applicant: United Technologies Corporation
Inventor： Thomas J. Praisner , Shankar S. Magge , Matthew B. Estes
CPC classification number: F01D9/041 , F01D5/141 , F01D9/04 , F01D9/065 , F01D25/28 , F02K3/06 , F05D2240/12 , Y02T50/673
Abstract: A gas turbine engine includes first and second stages having a rotational axis. A circumferential array of airfoils is arranged axially between the first stage and the second stage. At least one of the airfoils have a curvature provided equidistantly between pressure and suction sides. The airfoils extend from a leading edge to a trailing edge at a midspan plane along the airfoil. An angle is defined between first and second lines respectively tangent to the intersection of the midspan plane and the curvature at airfoil leading and trailing edges. The angle is equal to or greater than about 10°.
Abstract translation: 燃气涡轮发动机包括具有旋转轴线的第一和第二级。 在第一阶段和第二阶段之间轴向布置有圆周阵列的翼型件。 至少一个翼型件具有在压力侧和吸力侧之间等距离设置的曲率。 翼型件从翼缘沿着翼型在中跨平面处从前缘延伸到后缘。 第一和第二线之间的角度分别与翼型前缘和后缘的中跨平面和曲率的交点相切。 该角度等于或大于约10°。
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公开(公告)号：US10774650B2
公开(公告)日：2020-09-15
申请号：US15782547
申请日：2017-10-12
Applicant: United Technologies Corporation
Inventor： Timothy Charles Nash , Thomas J. Praisner
Abstract: A component for a gas turbine engine includes a platform that has a radially inner side and a radially outer side. A root portion extends from the radially inner side of the platform. An airfoil extends from the radially outer side of the platform. The airfoil includes a pressure side that extends between a leading edge and a trailing edge. A suction side extends between the leading edge and the trailing edge. A curvature inflection point is located between 30% and 70% of an axial chord length of the airfoil.
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Patent Agency Ranking
公开(公告)号：US10508549B2
公开(公告)日：2019-12-17
申请号：US14728514
申请日：2015-06-02
Applicant: United Technologies Corporation
Inventor： Wolfgang Balzer , Thomas J. Praisner , Atul Kohil , Mark F. Zelesky , Dominic J. Mongillo, Jr.
Abstract: An airfoil for a gas turbine engine includes an airfoil with pressure and suction sides that are joined at leading and trailing edges. The airfoil extends a span from a support to an end in a radial direction. 0% span and 100% span positions respectively correspond to the airfoil at the support and at the end. The leading and trailing edges are spaced apart from one another an axial chord in an axial direction. A cross-section of the airfoil at a span location has a diameter tangent to the pressure and suction sides. The diameter corresponds to the largest circle fitting within the cross-section. A ratio of the diameter to the axial chord is at least 0.4 between 50% and 95% span location.
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公开(公告)号：US10364690B2
公开(公告)日：2019-07-30
申请号：US14766178
申请日：2014-01-28
Applicant: United Technologies Corporation
Inventor： Jorge I. Farah , Jonathan P. Burt , Thomas J. Praisner
Abstract: A stator vane assembly includes a plurality of distinct vane segments that each respectively include a first platform, a second platform and at least one vane airfoil connected at opposed ends thereof to the first platform and the second platform. The first platforms meet at distinct first joints with each other, and the second platforms meet at distinct second joints with each other such that the plurality of vane segments forms an annular structure.
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公开(公告)号：US20190112930A1
公开(公告)日：2019-04-18
申请号：US15782547
申请日：2017-10-12
Applicant: United Technologies Corporation
Inventor： Timothy Charles Nash , Thomas J. Praisner
Abstract: A component for a gas turbine engine includes a platform that has a radially inner side and a radially outer side. A root portion extends from the radially inner side of the platform. An airfoil extends from the radially outer side of the platform. The airfoil includes a pressure side that extends between a leading edge and a trailing edge. A suction side extends between the leading edge and the trailing edge. A curvature inflection point is located between 30% and 70% of an axial chord length of the airfoil.
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公开(公告)号：US20160312654A1
公开(公告)日：2016-10-27
申请号：US15105443
申请日：2014-12-19
Applicant: UNITED TECHNOLOGIES CORPORATION
CPC classification number: F01D25/12 , F01D5/12 , F01D5/145 , F01D9/02 , F02C3/04 , F05D2220/323 , F05D2240/35 , F05D2240/81 , F05D2260/20 , Y02T50/673 , Y02T50/676
Abstract: An airfoil assembly has at least one cooling hole in an aft edge of at least one platform for cooling at least one of an axially downstream airfoil root and/or tip region. The airfoil assembly may be a high pressure turbine first stage vane coupled with a combustor operating at a low Pattern Factor.
Abstract translation: 翼型组件在至少一个平台的后边缘中具有至少一个冷却孔，用于冷却轴向下游的翼型根部和/或尖端区域中的至少一个。 翼型组件可以是与以低模式因数运行的燃烧器相连的高压涡轮机第一级叶片。
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公开(公告)号：US20150377048A1
公开(公告)日：2015-12-31
申请号：US14766178
申请日：2014-01-28
Applicant: United Technologies Corporation
Inventor： Jorge I. Farah , Jonathan P. Burt , Thomas J. Praisner
CPC classification number: F01D9/047 , F01D25/162 , F02C7/20 , F05D2230/23 , F05D2240/12 , F05D2240/80
Abstract: A stator vane assembly includes a plurality of distinct vane segments that each respectively include a first platform, a second platform and at least one vane airfoil connected at opposed ends thereof to the first platform and the second platform. The first platforms meet at distinct first joints with each other, and the second platforms meet at distinct second joints with each other such that the plurality of vane segments forms an annular structure.
Abstract translation: 定子叶片组件包括多个不同的叶片段，每个叶片段分别包括第一平台，第二平台和在其相对端连接到第一平台和第二平台的至少一个叶片翼型件。 第一平台在不同的第一接头彼此相交，并且第二平台在彼此不同的第二接头处相交，使得多个叶片段形成环形结构。
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