HOLLOW ROTATING SHAFT-FINISHING METHOD AND HOLLOW ROTATING SHAFT

    公开(公告)号:EP3156158A4

    公开(公告)日:2018-03-07

    申请号:EP15839664

    申请日:2015-07-21

    申请人: IHI CORP

    摘要: In the process of cutting the outer circumference 10o of a hollow rotating shaft 10 by using a finishing turning tool 36, the position of the finishing turning tool 36 is adjusted in the direction orthogonal to the virtual reference shaft center VS so that the center position CPo of the outer circumference 10o of the hollow rotating shaft 10 is deviated from the virtual reference shaft center VS in the same direction as the direction of the deviation vector ”Di by an amount corresponding to the magnitude |”Di| of the deviation vector ”Di. This can reduce the unbalance to zero also in the middle of the shaft and sufficiently reduce runout of the hollow rotating shaft 10 even if the rotation speed of the hollow rotating shaft 10 increases. Accordingly, it is possible to further improve the reliability of the hollow rotating shaft 10 at high rotation speed.

    OCEAN DATA MEASUREMENT SYSTEM
    7.
    发明公开

    公开(公告)号:EP3159255A4

    公开(公告)日:2018-02-28

    申请号:EP14894926

    申请日:2014-11-04

    申请人: IHI CORP

    发明人: ICHIKAWA MASAAKI

    IPC分类号: B63B22/00 B63B21/20 B63B22/04

    摘要: A system includes: an anchor 3 placed on a sea bottom 2; a submersible mooring cable 4 having a first end connected to the anchor 3; an intermediate buoy 5 connected to a second end of the submersible mooring cable 4 and floating in the sea; an intermediate mooring cable 6 having a first end connected to the intermediate buoy 5; an observation buoy 8 connected to a second end of the intermediate mooring cable 6, and measuring ocean data of an upper layer from a sea surface 7 to the intermediate buoy 5 while floating and sinking between the intermediate buoy 5 and the sea surface 7; and a lower layer-observation unit 9 placed along the submersible mooring cable 4, and measuring ocean data of a lower layer in a location deeper than the intermediate buoy 5. Ocean data of a wide area between the sea surface and the sea bottom can be acquired easily.

    CMC TURBINE STATOR VANE
    8.
    发明公开

    公开(公告)号:EP2412929A4

    公开(公告)日:2018-02-28

    申请号:EP10756123

    申请日:2010-03-24

    申请人: IHI CORP

    摘要: A CMC turbine stator blade 1 includes a blade 2 of a ceramic matrix composite material formed or a metallic material, and a band 5 formed of a ceramic matrix composite material and supporting the blade 2. The blade 2 includes a first fitting portion 3 to which the band 5 is fitted outside. The band 5 includes a second fitting portion 7 to which the first fitting portion 3 is fitted inside. A flexible wire 8 is disposed between the fitting portions 3, 7 to fix the blade 2 and the band 5. A first groove 3a in the outer peripheral surface of the first fitting portion 3 extends in the front-to-rear direction of the blade 2. A second groove 7a in the inner peripheral surface of the second fitting portion 7a extends along the first groove 3a. The wire 8 is disposed between the grooves 3a,7a.

    CONTROL DEVICE FOR ROCKET
    9.
    发明公开

    公开(公告)号:EP3150495A4

    公开(公告)日:2018-02-14

    申请号:EP15799554

    申请日:2015-05-20

    申请人: IHI CORP

    发明人: OTSUKA TAKENORI

    摘要: To drop a discarded object, such as a discarded n-th-stage rocket body or a single-staged rocket of which the engine has cut-off, to impact within a safe area while consuming as much carried fuel as possible to improve launch capability. The flight path of a two-staged rocket (1) is periodically predicted during flight, and the predicted impact point when a first-stage rocket body (11) or a fairing (15) is separated and discarded is periodically predicted from a second-stage rocket (13) at each passing scheduled point in the predicted flight path. As long as there is a passing scheduled point such that the predicted impact points of the first-stage rocket body (11) and the fairing (15) are both within the safe area, a process is periodically performed to designate the passing scheduled point furthest from the launch location of the two-staged rocket (1) as the separate-and-discard point of the first-stage rocket body (11), and when the two-staged rocket (1) reaches this separate-and-discard point, the first-stage rocket body (11) or the fairing (15) is separated and discarded.