公开(公告)号：US20180016920A1

公开(公告)日：2018-01-18

申请号：US15625226

申请日：2017-06-16

Applicant: ROLLS-ROYCE PLC

Inventor： Jae-Hoon CHUNG

IPC: F01D5/30 ,  F01D5/12

CPC classification number: F01D5/3007 ,  F01D5/12 ,  F01D5/16 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2260/30 ,  F05D2260/961 ,  Y02T50/673

Abstract: A rotor assembly for a turbomachine includes a hub, a plurality of first blades, and a plurality of second blades. The hub includes an axis of rotation, a first face and an opposite second face, with each of the first face and the second face being normal to the axis of rotation. Each of the first blades includes a first blade root portion, and each of the second blades includes a second blade root portion.

公开(公告)号：US20200017225A1

公开(公告)日：2020-01-16

申请号：US16437387

申请日：2019-06-11

Applicant: ROLLS-ROYCE plc

Inventor： Jae-Hoon CHUNG ,  Lorenzo RAFFAELLI

IPC: B64D27/02 ,  B64D27/10 ,  B64D27/24 ,  H02K11/00 ,  H02K7/20 ,  H02K7/18

Abstract: An aircraft propulsion system. The system comprises an internal combustion engine configured to drive a first propulsor and an electric generator. The system further comprises an electric motor or motors each configured to be powered by electric power provided by the generator, and configured to drive the first propulsor and/or a second propulsor. An electrical energy storage unit is provided, and is configured to store electrical energy supplied from the generator and supply electrical power to the electric motor. At maximum take-off power, the electric motor provides between 5% and 20% of total maximum aircraft propulsive take-off power.

公开(公告)号：US20190106997A1

公开(公告)日：2019-04-11

申请号：US16112940

申请日：2018-08-27

Applicant: ROLLS-ROYCE plc

Inventor： Jae-Hoon CHUNG ,  Malcolm L. HILLEL

IPC: F01D5/34 ,  B23P15/02 ,  F01D5/28

Abstract: A bladed disk may be arranged to rotate about an axis of rotation and including a rotor disk having an axial length extending from a first end to a second end, along the axis of rotation and a radial thickness extending between a first radius from the axis of rotation and a second radius from the axis of rotation, less than the first radius. The bladed disk may include a plurality of blades formed integrally with the rotor disk and arranged circumferentially around the rotor disk, and a first set of divides and a second set of divides, each divide comprising a partial break in the rotor disk extending axially from the first end of the rotor disk to the second end of the rotor disk and radially from the first radius to a third radius, less than the first radius and greater than the second radius.