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    COMPRESSOR ABRADABLE MATERIAL SEAL WITH TAILORED WEAR RATIO AND DESIRABLE EROSION RESISTANCE
    41.
    发明申请
    COMPRESSOR ABRADABLE MATERIAL SEAL WITH TAILORED WEAR RATIO AND DESIRABLE EROSION RESISTANCE 审中-公开
    压缩机不可磨损的材料密封具有定制的磨损比和耐腐蚀性

    公开(公告)号：US20160186595A1

    公开(公告)日：2016-06-30

    申请号：US14862430

    申请日：2015-09-23

    Applicant: United Technologies Corporation

    Inventor： Christopher W. Strock ,  Changsheng Guo ,  Yan Chen

    IPC: F01D11/12 ,  F01D5/28 ,  C22C9/06 ,  C22C19/05 ,  C22C9/01 ,  C22C9/00 ,  F01D5/20 ,  F01D25/24

    CPC classification number: F01D11/122 ,  C22C9/00 ,  C22C9/01 ,  C22C9/06 ,  C22C19/055 ,  F05D2300/172 ,  Y02T50/672

    Abstract: What is described is a wear resistant seal system that is adapted for resisting wear of a rotating part in a gas turbine engine as it rotates against a stationary part in the engine. The system includes an axially rotable member including an abrasive tip having a first tensile strength. The system also includes a stationary structure radially exterior and adjacent to the rotable member and including an abradable material. The abradable material includes a matrix material having a second tensile strength that, at least in a first temperature range, is lower than the first tensile strength and a filler material interspersed with the matrix material.

    Abstract translation: 所描述的是一种耐磨密封系统，其适于抵抗燃气涡轮发动机中的旋转部件在其相对于发动机中的静止部件旋转时的磨损。 该系统包括轴向可旋转构件，其包括具有第一拉伸强度的研磨尖端。 该系统还包括径向外部并且与可旋转构件相邻并包括可磨损材料的固定结构。 可磨损材料包括具有至少在第一温度范围内低于第一拉伸强度的第二拉伸强度的矩阵材料和散布有基质材料的填充材料。

    ALUMINUM FAN BLADE TIP WITH THERMAL BARRIER
    42.
    发明申请
    ALUMINUM FAN BLADE TIP WITH THERMAL BARRIER 有权
    铝制风扇叶片带热障板

    公开(公告)号：US20160040538A1

    公开(公告)日：2016-02-11

    申请号：US14711237

    申请日：2015-05-13

    Applicant: United Technologies Corporation

    Inventor： Yan Chen ,  Changsheng Guo

    IPC: F01D5/28 ,  B05D7/14 ,  F01D5/14

    CPC classification number: F01D5/288 ,  B05D7/14 ,  F01D5/147 ,  F01D11/122 ,  F02K3/06 ,  F05D2230/90 ,  F05D2300/611

    Abstract: A fan blade for a gas turbine engine is described. The fan blade may comprise a body portion formed from a metallic material, and it may include a suction side, a pressure side, a leading edge, a trailing edge, and a tip. A coating may be applied to the tip, and the coating may have a thermal conductivity of no more than about 10 watt per meter kelvin. The coating may be a thermal barrier coating comprising yttria-stabilized zirconia.

    Abstract translation: 描述了用于燃气涡轮发动机的风扇叶片。 风扇叶片可以包括由金属材料形成的主体部分，并且其可以包括吸力侧，压力侧，前缘，后缘和尖端。 可以将涂层施加到尖端，并且涂层的热导率可以不超过约10瓦特/米尔开尔文。 涂层可以是包含氧化钇稳定的氧化锆的热障涂层。

    Fan blades with abrasive tips
    43.
    发明授权
    Fan blades with abrasive tips 有权

    公开(公告)号：US11333169B2

    公开(公告)日：2022-05-17

    申请号：US16565269

    申请日：2019-09-09

    Applicant: United Technologies Corporation

    Inventor： Christopher W. Strock ,  Changsheng Guo

    IPC: F01D5/28 ,  F04D29/38 ,  F04D19/00 ,  F01D11/12

    Abstract: A fan blade for a gas turbine engine is disclosed. The disclosed fan blade includes an airfoil having a leading edge, a trailing ling edge, a convex side, a concave side and a distal tip. The leading edge, trailing edge, convex side and concave side of the airfoil is at least partially coated with an erosion resistant coating. The distal tip of the airfoil is coated with a bonded abrasive coating. The bonded abrasive coating engages the abradable coating disposed on the fan liner and, because of its low thermal conductivity, reduces heat transfer to the distal tip of the fan blade. The reduction in heat transfer to the distal tip of the fan blade preserves the integrity of erosion resistant coatings that may be applied to the body or the airfoil of the fan blade.

    Closed-loop fluid control to obtain efficient machining
    44.
    发明授权
    Closed-loop fluid control to obtain efficient machining 有权

    公开(公告)号：US10807209B2

    公开(公告)日：2020-10-20

    申请号：US15916683

    申请日：2018-03-09

    Applicant: United Technologies Corporation

    Inventor： Zhigang Wang ,  Changsheng Guo ,  Daniel V. Viens

    IPC: B23Q11/10 ,  B23Q11/12 ,  B23Q17/00 ,  F16N29/02 ,  B23Q17/09

    Abstract: A system includes a machine tool that includes a cutting tool, a fluid subsystem that provides fluid to the cutting tool, and at least one processor that executes instructions that cause the at least one processor to: obtain a signal indicative of a load on the cutting tool, establish a first value of at least one parameter of the fluid based on the signal, obtain a second value of the at least one parameter that is based on a simulation, determine a difference between the first value and the second value, and adjust a state of a device of the fluid subsystem based on the determined difference.

    Fan blades with abrasive tips
    45.
    发明授权
    Fan blades with abrasive tips 有权

    公开(公告)号：US10408224B2

    公开(公告)日：2019-09-10

    申请号：US14509780

    申请日：2014-10-08

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Christopher W. Strock ,  Changsheng Guo

    IPC: F01D5/28 ,  F04D29/38 ,  F04D19/00 ,  F01D11/12

    Abstract: A fan blade for a gas turbine engine is disclosed. The disclosed fan blade includes an airfoil having a leading edge, a trailing edge, a convex side, a concave side and a distal tip. The leading edge, trailing edge, convex side and concave side of the airfoil is at least partially coated with an erosion resistant coating. The distal tip of the airfoil is coated with a bonded abrasive coating. The bonded abrasive coating engages the abradable coating disposed on the fan liner and, because of its low thermal conductivity, reduces heat transfer to the distal tip of the fan blade. The reduction in heat transfer to the distal tip of the fan blade preserves the integrity of erosion resistant coatings that may be applied to the body or the airfoil of the fan blade.

    Blade rub material
    46.
    发明授权
    Blade rub material 有权

    公开(公告)号：US10408078B2

    公开(公告)日：2019-09-10

    申请号：US14761496

    申请日：2013-01-29

    Applicant: United Technologies Corporation

    Inventor： Christopher W. Strock ,  Changsheng Guo

    IPC: F01D11/12 ,  F01D5/02 ,  F01D25/24 ,  B82Y30/00 ,  F01D5/28

    Abstract: One aspect of the disclosure involves a nib material comprising a polymeric matrix and carbon nanotubes in the matrix. In one or more embodiments of any of the foregoing embodiments, the matrix comprises a silicone. In one or more embodiments of any of the foregoing embodiments, the rub material is at least 1.0 mm thick. In one or more embodiments of any of the foregoing embodiments, the silicone is selected from the group consisting of dimethyl- and fluoro-silicone rubbers and their copolymers. In one or more embodiments of any of the foregoing embodiments, the carbon nanotubes at least locally have a concentration of 1-20% by weight.

    Curved blade retention slot for turbine blade in a turbine disk
    48.
    发明授权
    Curved blade retention slot for turbine blade in a turbine disk 有权

    公开(公告)号：US10273815B2

    公开(公告)日：2019-04-30

    申请号：US15498520

    申请日：2017-04-27

    Applicant: United Technologies Corporation

    Inventor： Changsheng Guo

    IPC: F03B3/12 ,  F01D5/30 ,  B23C3/34 ,  B24B19/02 ,  B23C5/10

    Abstract: A method of forming a curved slot in a turbine disk includes the steps of forming a pre-slot in the turbine disk and finishing the pre-slot to form a slot that receives a portion of a turbine blade. The turbine disk including a first face, an opposing second face, and an outer perimeter surface extending between the first face and the opposing second face. The pre-slot includes a first curved wall and a second curved wall that each extend between the first face and the opposing second face. An intersection between the outer perimeter surface and each of the first curved wall and the second curved wall is defined by a curved line.

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