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公开(公告)号：US20150033746A1
公开(公告)日：2015-02-05
申请号：US13957735
申请日：2013-08-02
Applicant: SOLAR TURBINES INCORPORATED
IPC: F02C7/24
CPC classification number: F02C7/24 , F23R3/002 , F23R3/10 , F23R2900/03044
Abstract: A heat shield for a combustion chamber of a gas turbine engine is disclosed. The heat shield includes a plate portion, an inner ring, and a plurality of standoffs. The plate portion includes an annular sector shape. The inner ring extends from an inner part of the plate portion. The inner ring includes a hollow cylinder shape. The plurality of standoffs extends from the plate portion, proximate outer edges of the plate portion and in the same direction as the inner ring. The plurality of standoffs forms a plurality of scallops. Each scallop is located between adjacent standoffs.
Abstract translation: 公开了一种用于燃气涡轮发动机的燃烧室的隔热罩。 隔热罩包括板部，内圈和多个支座。 板部分包括环形扇形。 内环从板部的内部延伸。 内圈包括中空圆筒形状。 多个支座从板部分延伸，邻近板部分的外边缘并且沿与内圈相同的方向延伸。 多个间隔形成多个扇贝。 每个扇贝位于相邻的支架之间。
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公开(公告)号：US20160334102A1
公开(公告)日：2016-11-17
申请号：US14711628
申请日：2015-05-13
Applicant: Solar Turbines Incorporated
Inventor： Crosby Hayhurst Johnson , Yong Weon Kim , Ted Edwin Groocock
CPC classification number: F23R3/002 , F23R3/045 , F23R3/06 , F23R3/50 , F23R2900/00012 , F23R2900/00014
Abstract: A grommet for a combustor of a gas turbine engine is disclosed. The grommet includes a lower platform and a raised platform. The lower platform includes a plurality of top slots located in the top surface and a plurality of bottom slots located in the bottom surface. Each top slot and bottom slot may extend radially along the lower platform. The plurality of top slots may be spaced equidistantly from one another along the circumference of the lower platform. The plurality of bottom slots may be spaced equidistantly from one another along the circumference of the lower platform.
Abstract translation: 公开了一种用于燃气涡轮发动机的燃烧器的垫圈。 索环包括一个较低的平台和一个凸起的平台。 下平台包括位于顶表面中的多个顶槽和位于底表面中的多个底槽。 每个顶槽和底槽可以沿下平台径向延伸。 多个顶部槽可以沿着下部平台的圆周彼此间隔开等距离地间隔开。 多个底槽可以沿着下平台的圆周彼此间隔开等间距。
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公开(公告)号：US20160281517A1
公开(公告)日：2016-09-29
申请号：US14669902
申请日：2015-03-26
Applicant: Solar Turbines Incorporated
Inventor： Yong Weon Kim , Garrett P. Prins
CPC classification number: F01D9/065 , F01D5/189 , F05D2230/21 , F05D2240/121
Abstract: A nozzle segment for a turbine nozzle of a gas turbine engine is disclosed. The nozzle segment includes an upper endwall, a lower endwall spaced apart from the upper endwall, a pressure portion, and a suction portion. The pressure portion extends between the upper endwall and the lower endwall adjacent a first side of the nozzle segment. The suction portion is spaced apart from the pressure portion and extends between the upper endwall and the lower endwall adjacent a second side of the nozzle segment. The second side is opposite the first side.
Abstract translation: 公开了一种用于燃气涡轮发动机的涡轮喷嘴的喷嘴段。 喷嘴段包括上端壁，与上端壁间隔开的下端壁，压力部分和抽吸部分。 压力部分在上端壁和下端壁之间相邻于喷嘴段的第一侧延伸。 抽吸部分与压力部分间隔开并且在上端壁和下端壁之间延伸，邻近喷嘴段的第二侧。 第二面与第一面相对。
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公开(公告)号：US20160201489A1
公开(公告)日：2016-07-14
申请号：US14593998
申请日：2015-01-09
Applicant: SOLAR TURBINES INCORPORATED
Inventor： Yong Weon Kim , Tsuhon Lin , Jeffrey Stephen Carullo
IPC: F01D9/04
Abstract: An insert tube of a turbine vane is disclosed. The insert tube includes a pressure side wall, a suction side wall opposite and spaced apart from the pressure side wall, a leading edge, and a trailing edge opposite the leading edge. The insert tube includes a plurality of cooling channels spaced along the pressure side wall. The insert tube includes an indented portion located between the trailing edge and the pressure side wall.
Abstract translation: 公开了一种涡轮叶片的插入管。 插入管包括压力侧壁，与压力侧壁相对且间隔开的吸力侧壁，前缘和与前缘相对的后缘。 插入管包括沿着压力侧壁间隔开的多个冷却通道。 插入管包括位于后缘和压力侧壁之间的凹入部分。
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Patent Agency Ranking
公开(公告)号：US20150198053A1
公开(公告)日：2015-07-16
申请号：US14152897
申请日：2014-01-10
Applicant: SOLAR TURBINES INCORPORATED
Inventor： Yong Weon Kim , Kidon Lee
IPC: F01D9/02
CPC classification number: F01D11/02 , F01D11/001
Abstract: A turbine stage for a gas turbine engine is disclosed. The turbine stage includes a turbine disk and a turbine diaphragm, forming a cavity there between. The turbine stage also includes an exit flow discourager comprised of at least two teeth. The teeth may be located radially apart from each other, each tooth including a length extending in the axial direction and a width extending in the radial direction. A channel is formed between the teeth and an axially adjacent surface. A recirculation region may be formed in between each pair of teeth.
Abstract translation: 公开了一种用于燃气涡轮发动机的涡轮级。 涡轮级包括涡轮盘和涡轮隔膜，在其间形成腔室。 涡轮级还包括由至少两个齿组成的出口流动盘。 齿可以彼此径向地分开，每个齿包括在轴向方向上延伸的长度和沿径向方向延伸的宽度。 在齿与轴向相邻的表面之间形成通道。 再循环区域可形成在每对齿之间。
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公开(公告)号：US20210277782A1
公开(公告)日：2021-09-09
申请号：US16696480
申请日：2019-11-26
Applicant: Solar Turbines Incorporated
Inventor： Yong Weon Kim , Jeffrey E. Tarczy
IPC: F01D5/14
Abstract: A pressure capture canister is disclosed. The pressure capture canister includes a body, a cap, and a seal. The cap and the seal are positioned within the body and are arranged to allow fluid communication from outside of the pressure capture canister to within the body. The seal can be selected to melt or soften at a temperature threshold.
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公开(公告)号：US09879554B2
公开(公告)日：2018-01-30
申请号：US14593998
申请日：2015-01-09
Applicant: SOLAR TURBINES INCORPORATED
Inventor： Yong Weon Kim , Tsuhon Lin , Jeffrey Stephen Carullo
Abstract: An insert tube of a turbine vane is disclosed. The insert tube includes a pressure side wall, a suction side wall opposite and spaced apart from the pressure side wall, a leading edge, and a trailing edge opposite the leading edge. The insert tube includes a plurality of cooling channels spaced along the pressure side wall. The insert tube includes an indented portion located between the trailing edge and the pressure side wall.
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公开(公告)号：US09803863B2
公开(公告)日：2017-10-31
申请号：US14711628
申请日：2015-05-13
Applicant: Solar Turbines Incorporated
Inventor： Crosby Hayhurst Johnson , Yong Weon Kim , Ted Edwin Groocock
CPC classification number: F23R3/002 , F23R3/045 , F23R3/06 , F23R3/50 , F23R2900/00012 , F23R2900/00014
Abstract: A grommet for a combustor of a gas turbine engine is disclosed. The grommet includes a lower platform and a raised platform. The lower platform includes a plurality of top slots located in the top surface and a plurality of bottom slots located in the bottom surface. Each top slot and bottom slot may extend radially along the lower platform. The plurality of top slots may be spaced equidistantly from one another along the circumference of the lower platform. The plurality of bottom slots may be spaced equidistantly from one another along the circumference of the lower platform.
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公开(公告)号：US09765639B2
公开(公告)日：2017-09-19
申请号：US14152897
申请日：2014-01-10
Applicant: SOLAR TURBINES INCORPORATED
Inventor： Yong Weon Kim , Kidon Lee
CPC classification number: F01D11/02 , F01D11/001
Abstract: A turbine stage for a gas turbine engine is disclosed. The turbine stage includes a turbine disk and a turbine diaphragm, forming a cavity there between. The turbine stage also includes an exit flow discourager comprised of at least two teeth. The teeth may be located radially apart from each other, each tooth including a length extending in the axial direction and a width extending in the radial direction. A channel is formed between the teeth and an axially adjacent surface. A recirculation region may be formed in between each pair of teeth.
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