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公开(公告)号：US20180238268A1
公开(公告)日：2018-08-23
申请号：US15910827
申请日：2018-03-02
发明人： Donald W. Peters , Emma J. Place
CPC分类号： F02K1/80 , F01D25/168 , F02K1/1223 , F05D2220/32 , F05D2240/128 , F05D2260/231 , F05D2300/434 , F05D2300/44 , F05D2300/603 , F05D2300/614 , F16C29/001 , F16C29/02 , F16C33/201 , Y02T50/672
摘要： A composite wear pad for being coupled to a slider block of a convergent nozzle of a gas turbine engine includes a high heat capacity composite having a resin and a plurality of carbon fibers bonded together by the resin. The composite wear pad also includes a first rod coupled to the high heat capacity composite at a first axial end of the composite wear pad such that a first end thickness. The composite wear pad also includes a second rod coupled to the high heat capacity composite at a second axial end of the composite wear pad such that the first axial end and the second axial end of the composite wear pad each have an end thickness that is greater than a middle thickness of the composite wear pad.
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公开(公告)号：US20160333725A1
公开(公告)日：2016-11-17
申请号：US14709072
申请日：2015-05-11
发明人： DONALD W. PETERS , Emma J. Place
CPC分类号： F02K1/80 , F01D25/168 , F02K1/1223 , F05D2220/32 , F05D2240/128 , F05D2260/231 , F05D2300/434 , F05D2300/44 , F05D2300/603 , F05D2300/614 , F16C29/001 , F16C29/02 , F16C33/201 , Y02T50/672
摘要： A composite wear pad for being coupled to a slider block of a convergent nozzle of a gas turbine engine includes a high heat capacity composite having a resin and a plurality of carbon fibers bonded together by the resin. The composite wear pad also includes a first rod coupled to the high heat capacity composite at a first axial end of the composite wear pad such that a first end thickness. The composite wear pad also includes a second rod coupled to the high heat capacity composite at a second axial end of the composite wear pad such that the first axial end and the second axial end of the composite wear pad each have an end thickness that is greater than a middle thickness of the composite wear pad.
摘要翻译： 用于连接到燃气涡轮发动机的会聚喷嘴的滑块的复合耐磨垫包括具有通过树脂粘合在一起的树脂和多个碳纤维的高热容复合材料。 复合耐磨垫还包括在复合耐磨垫的第一轴向端处耦合到高热容复合材料的第一杆，使得第一端厚度。 复合耐磨垫还包括在复合耐磨垫的第二轴向端处耦合到高热容复合材料的第二杆，使得复合耐磨垫的第一轴向端和第二轴向端各自具有更大的端部厚度 比中厚度的复合耐磨垫。
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公开(公告)号：US20210115799A1
公开(公告)日：2021-04-22
申请号：US16654674
申请日：2019-10-16
发明人： Emma J. Place , Carlos Calixtro
IPC分类号： F01D5/14
摘要： A core is provided for fabricating a blade to include an airfoil. The airfoil includes pressure and suction surfaces, leading and trailing edges extending along the pressure and suction surfaces and a tip shelf with a first sweep configuration and a wall. The core includes channel sections configured to form internal channels within the airfoil by casting processes and tip rods extending from respective portions of the channel sections proximate to a tip shelf location. The respective portions of the channel sections have a second sweep configuration corresponding to the first sweep configuration. The tip rods are configured to extend through the wall at an angle of about 5-12 degrees inclusive relative to a normal angle of the wall during the casting processes to form through-holes angled at about 5-12 degrees inclusive in the wall.
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公开(公告)号：US20210062658A1
公开(公告)日：2021-03-04
申请号：US16593076
申请日：2019-10-04
IPC分类号： F01D5/18
摘要： Methods for forming airfoil, cores for forming airfoil, and airfoils for gas turbine engines are described. The methods include forming an airfoil body about a core assembly, the core assembly comprising at least one core structure having a radially extending purge slot protrusion extending from a portion of the at least one core structure, removing the core assembly from the airfoil body to form one or more internal cavities, wherein at least one internal cavity has a cavity extension define by the purge slot protrusion, and forming a squealer pocket in a tip of the formed airfoil body, wherein a cavity purge slot is formed at the cavity extension to fluidly connect the respect internal cavity with the squealer pocket. The radially extending protrusion has a radial height that is equal to or less than five times a width thereof.
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公开(公告)号：US11041395B2
公开(公告)日：2021-06-22
申请号：US16453101
申请日：2019-06-26
摘要： Methods for forming airfoils, core assemblies, and airfoils for gas turbine engines are described. The methods include forming an airfoil body about a core assembly configured to define one or more internal cavities of the airfoil body, the core assembly comprising at least core structure having a purge slot protrusion extending from a portion of the core structure, removing the core assembly from the airfoil body to form one or more internal cavities, wherein at least one internal cavity has a cavity extension define by the purge slot protrusion, and forming a squealer pocket in a tip of the formed airfoil body, wherein a cavity purge slot is formed at the cavity extension to fluidly connect the respect internal cavity with the squealer pocket.
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公开(公告)号：US11143035B2
公开(公告)日：2021-10-12
申请号：US16654674
申请日：2019-10-16
发明人： Emma J. Place , Carlos Calixtro
摘要： A core is provided for fabricating a blade to include an airfoil. The airfoil includes pressure and suction surfaces, leading and trailing edges extending along the pressure and suction surfaces and a tip shelf with a first sweep configuration and a wall. The core includes channel sections configured to form internal channels within the airfoil by casting processes and tip rods extending from respective portions of the channel sections proximate to a tip shelf location. The respective portions of the channel sections have a second sweep configuration corresponding to the first sweep configuration. The tip rods are configured to extend through the wall at an angle of about 5-12 degrees inclusive relative to a normal angle of the wall during the casting processes to form through-holes angled at about 5-12 degrees inclusive in the wall.
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公开(公告)号：US11015457B2
公开(公告)日：2021-05-25
申请号：US16202483
申请日：2018-11-28
发明人： Christopher J. Peters , Emma J. Place , Jeffrey J. DeGray , Dominic J. Mongillo , Timothy J. Jennings , Raymond Surace , Jeremy B. Fredette
摘要： A method of forming an airfoil, includes forming a hybrid skin core, a tip flag core, and a trailing edge core. The hybrid skin core, tip flag core, and trailing edge core are connected to form a first core portion. A leading edge core and a serpentine core are formed. The first core portion, the leading edge core, and the serpentine core are assembled together to form an airfoil core. An airfoil is formed around the airfoil core.
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公开(公告)号：US10760529B2
公开(公告)日：2020-09-01
申请号：US15910827
申请日：2018-03-02
发明人： Donald W. Peters , Emma J. Place
摘要： A composite wear pad for being coupled to a slider block of a convergent nozzle of a gas turbine engine includes a high heat capacity composite having a resin and a plurality of carbon fibers bonded together by the resin. The composite wear pad also includes a first rod coupled to the high heat capacity composite at a first axial end of the composite wear pad such that a first end thickness. The composite wear pad also includes a second rod coupled to the high heat capacity composite at a second axial end of the composite wear pad such that the first axial end and the second axial end of the composite wear pad each have an end thickness that is greater than a middle thickness of the composite wear pad.
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公开(公告)号：US09938930B2
公开(公告)日：2018-04-10
申请号：US14709072
申请日：2015-05-11
发明人： Donald W. Peters , Emma J. Place
CPC分类号： F02K1/80 , F01D25/168 , F02K1/1223 , F05D2220/32 , F05D2240/128 , F05D2260/231 , F05D2300/434 , F05D2300/44 , F05D2300/603 , F05D2300/614 , F16C29/001 , F16C29/02 , F16C33/201 , Y02T50/672
摘要： A composite wear pad for being coupled to a slider block of a convergent nozzle of a gas turbine engine includes a high heat capacity composite having a resin and a plurality of carbon fibers bonded together by the resin. The composite wear pad also includes a first rod coupled to the high heat capacity composite at a first axial end of the composite wear pad such that a first end thickness. The composite wear pad also includes a second rod coupled to the high heat capacity composite at a second axial end of the composite wear pad such that the first axial end and the second axial end of the composite wear pad each have an end thickness that is greater than a middle thickness of the composite wear pad.
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公开(公告)号：US11053803B2
公开(公告)日：2021-07-06
申请号：US16593076
申请日：2019-10-04
摘要： Methods for forming airfoil, cores for forming airfoil, and airfoils for gas turbine engines are described. The methods include forming an airfoil body about a core assembly, the core assembly comprising at least one core structure having a radially extending purge slot protrusion extending from a portion of the at least one core structure, removing the core assembly from the airfoil body to form one or more internal cavities, wherein at least one internal cavity has a cavity extension define by the purge slot protrusion, and forming a squealer pocket in a tip of the formed airfoil body, wherein a cavity purge slot is formed at the cavity extension to fluidly connect the respect internal cavity with the squealer pocket. The radially extending protrusion has a radial height that is equal to or less than five times a width thereof.
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