发明名称 ROTOR DEVICE OF AN AIRCRAFT ENGINE WITH A DAMPING DEVICE BETWEEN TURBINES BLADES
摘要 A rotor of an aircraft engine includes a disk wheel and at least two turbine blades. A damping device is arranged below a blade platform and inside a cavity between the blades in the radial direction. The cavity is formed by a respective recess at adjoining blades, with respective recesses having an outer guide surface in the radial direction, acting together with the damping device during operation of the rotor. The guide surface extends radially, from the lateral edge area of the blade to the central area of the blade. The respective recess extends circumferentially from a boundary plane defined by the lateral edge area of the blade to a side surface that delimitates the guide surface towards the blade center. The recess of at least one of the adjacent blades completely receives the damping device.
申请公布号 US2017022819(A1) 申请公布日期 2017.01.26
申请号 US201615216935 申请日期 2016.07.22
申请人 Rolls-Royce Deutschland Ltd & Co KG 发明人 WEINERT Markus;LEYMANN Tobias
分类号 F01D5/10;F01D5/30;F01D5/12 主分类号 F01D5/10
代理机构 代理人
主权项 1. A rotor device of an aircraft engine with a disk wheel and at least two turbine blades arranged thereat and adjoining each other, and with at least one damping device that in operation is arranged below a blade platform of the turbine blades and inside a cavity between the turbine blades in the radial direction and at least in certain areas in the circumferential direction of the rotor device, wherein the respective cavity is formed by a recess at the adjoining turbine blades, wherein each of the recesses has an outer guide surface with respect to the radial direction of the rotor device, acting together with the damping device during operation of the rotor device, wherein the respective guide surface extends radially in the direction of the disk wheel from a lateral edge area of the turbine blade as viewed in the circumferential direction of the rotor device to a central area of the turbine blade, and wherein the respective recess extends in the circumferential direction of the rotor device from a boundary plane defined by the lateral edge area of the turbine blade to a side surface that delimits the guide surface towards the turbine blade center, characterized in that the recess of at least one of the adjoining turbine blades which is delimitated by the guide surface, the boundary plane and the side surface is configured for completely receiving the damping device.
地址 Blankenfelde-Mahlow DE