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公开(公告)号：US10190655B2
公开(公告)日：2019-01-29
申请号：US15738091
申请日：2016-06-21
Applicant: Safran Aircraft Engines
Inventor： Alain Roland Luinaud , Alain Decocq , Francois Viviande
Abstract: Tooling for balancing a turbine engine module (10) in a balancing machine, the turbine engine module having at least one stator housing (14) and a rotor (16) having a shaft (18) with a longitudinal axis A and at least one blade stage (20) surrounded by the stator housing (14). The tooling has at least a balancing frame (14), having rotor (16) guide bearings, first and second annular plates (30, 32) designed to be attached to the stator housing (14), third and fourth attachment lugs (34, 36) provided on the balancing frame (24), to attach the first and second annular plates (30, 32) to the frame. A trolley is for transporting the frame (24), and a support (84, 94) for supporting the frame, provided on the balancing frame (24) and cooperating equally well with the balancing machine and with the trolley.
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公开(公告)号：US11143031B2
公开(公告)日：2021-10-12
申请号：US16668972
申请日：2019-10-30
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Alain Roland Luinaud , Alain Decocq
Abstract: A tool for balancing a turbine engine module in a balancer, the module including a stator, a rotor and a shaft, the balancer including at least one power drive unit and a table equipped with two support of the shaft of the module. The tool includes at least: one stator support, fixed on the table of the balancer behind the supports, a tubular false bearing, configured to support a bearing for guiding the rotor in the stator and protruding outside of the stator, a guiding sleeve of the shaft, confining a support of the false bearing, and received on the supports of the balancer, a rear support plate of the stator, fixed to the support of the stator, and immobilising the rotor with respect to the stator, a front support plate of the stator, fixed to the stator support, and immobilising and centring the false bearing.
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公开(公告)号：US10197467B2
公开(公告)日：2019-02-05
申请号：US15578204
申请日：2016-06-29
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Alain Roland Luinaud , Alain Decocq , Christophe Guengant
Abstract: A calibration rotor for a horizontal balancer, configured to be driven by a driver. The calibration rotor includes a main barrel that has a longitudinal axis and the periphery of which includes points for attaching balance weights that are evenly distributed in an axial and angular manner about the axis. A rotation guide is arranged at each end of the main barrel. The rotor is modular, and the rotation guide includes adapters (40, 42) which are capable of being configured to be attached to the ends of the barrel. The guide is of a first type, suitable for rotatably guiding the barrel on rollers, or of a second type, suitable for rotatably guiding the half-shell barrel. Each type of adapter has the same predetermined moment of inertia and is interchangeable on the barrel.
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公开(公告)号：US20180149544A1
公开(公告)日：2018-05-31
申请号：US15578204
申请日：2016-06-29
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Alain Roland Luinaud , Alain Decocq , Christophe Guengant
Abstract: A calibration rotor for a horizontal balancer, configured to be driven by a driver. The calibration rotor includes a main barrel that has a longitudinal axis and the periphery of which includes points for attaching balance weights that are evenly distributed in an axial and angular manner about the axis. A rotation guide is arranged at each end of the main barrel. The rotor is modular, and the rotation guide includes adapters (40, 42) which are capable of being configured to be attached to the ends of the barrel. The guide is of a first type, suitable for rotatably guiding the barrel on rollers, or of a second type, suitable for rotatably guiding the half-shell barrel. Each type of adapter has the same predetermined moment of inertia and is interchangeable on the barrel.
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