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    SYSTEMS AND METHODS FOR AERODYNAMIC ANALYSIS FOR INSPECTED BLADED ROTORS
    1.
    发明公开
    SYSTEMS AND METHODS FOR AERODYNAMIC ANALYSIS FOR INSPECTED BLADED ROTORS 审中-公开

    公开(公告)号：EP4258074A1

    公开(公告)日：2023-10-11

    申请号：EP23166849.2

    申请日：2023-04-05

    申请人： Raytheon Technologies Corporation

    发明人： PRASAD, Anil ,  ROSE, Becky E. ,  ROBERTS, Lawrence P. ,  PHAN, Uyen

    IPC分类号： G05B23/02 ,  F01D5/00 ,  F01D5/34

    摘要： A method is providing comprising receiving, via a processor, a digital representation of a potentially repaired blade from an inspection system, the digital representation including a repair blend profile, the digital representation based on an inspected blade of an inspected bladed rotor; generating, via the processor, an airfoil definition file corresponding to the digital representation, inputting, via the processor, the airfoil definition file into an aerodynamic simulator, receiving, via the processor, simulation results from the aerodynamic simulator of the potentially repaired blade; analyzing, via the processor, an overall engine impact of the potentially repaired blade based on the simulation results, inputting, via the processor, a plurality of simulation results into an aerodynamic effect translator, and receiving, via the processor, a translated impact for local effect of a repaired bladed rotor with the potentially repaired blade.

    FAN STAGGER ANGLE FOR DIRT REJECTION
    3.
    发明公开
    FAN STAGGER ANGLE FOR DIRT REJECTION 审中-公开

    公开(公告)号：EP4144962A1

    公开(公告)日：2023-03-08

    申请号：EP22203597.4

    申请日：2012-06-29

    申请人： Raytheon Technologies Corporation

    发明人： GALLAGHER, Edward J. ,  ROSE, Becky E. ,  BRILLIANT, Lisa I

    IPC分类号： F01D25/34 ,  F02K3/06 ,  F01D15/12 ,  F02C7/05 ,  F01D21/04 ,  F01D5/14 ,  F02C7/36

    摘要： A gas turbine engine (20) includes a spool (30), a turbine (46) coupled to drive the spool (30), a propulsor (42) coupled to be rotated about an axis by the turbine (46) through the spool (30), and a gear assembly (48) coupled between the propulsor (74) and the spool (30) such that rotation of the turbine (46) drives the propulsor (42) at a different speed than the spool (30). The propulsor (42) includes a hub (76) and a row of propulsor blades (74) that extend from the hub (76). Each of the propulsor blades (74) has a span between a root (68) at the hub (76) and a tip (80), and a chord (30) between a leading edge (82) and a trailing edge (84). The chord forms a stagger angle α with the axis (A), and the stagger angle α is less than 15° at a position along the propulsor blade (74) that is within an inboard 20% of the span.

    STACK BASED REPAIR SYSTEMS AND METHODS
    5.
    发明公开
    STACK BASED REPAIR SYSTEMS AND METHODS 审中-公开

    公开(公告)号：EP4257798A1

    公开(公告)日：2023-10-11

    申请号：EP23164481.6

    申请日：2023-03-27

    申请人： Raytheon Technologies Corporation

    发明人： MICHAELS, Derek J. ,  PRIHAR, Ron I. ,  ROSE, Becky E.

    IPC分类号： F01D5/00 ,  B23P6/00 ,  F01D5/34 ,  G06F30/23

    摘要： A method can comprise: determining a plurality of potential repair processes for the stack of IBRs (110), each repair process associated with a defect (140) on an inspected IBR (100); generating (806) a finite element model of the stack of IBRs with a potential repaired defect of each inspected IBR being modeled, a plurality of vane stages (105) disposed between adjacent inspected IBRs, and an engine case (120); performing (808;810) a structural analysis and an aerodynamic analysis; determining (812) whether the stack of IBRs with the potential repaired defect of each inspected IBR meets a structural criteria and an aerodynamic criteria; and repairing (714) each IBR in the stack of IBRs with the repair process for the potential repaired defect for each inspected IBR in the stack of IBRs in response to determining the stack of IBRs meets the structural criteria and the aerodynamic criteria.