公开(公告)号：US10119425B2

公开(公告)日：2018-11-06

申请号：US14827870

申请日：2015-08-17

Applicant: ROLLS-ROYCE PLC

Inventor： Colin Young ,  Guy D Snowsill

IPC: F01D5/30 ,  F01D25/32 ,  F01D5/08

Abstract: A gas turbine engine rotor arrangement comprising at least one blade and a disc is disclosed. The blade extends radially outwards from the disc and is secured thereto by cooperating shank of the blade and recess of the disc. The shank comprises a bottom surface facing a base surface of the recess, the bottom surface having axially extending peripheral edges. The bottom surface is shaped so that when the engine rotor arrangement is in use, liquid in a cavity between the bottom surface and base surface, acted upon by an unbalanced force in the radially outward direction, is guided by the bottom surface to flow between and away from the axial edges.

公开(公告)号：US11970975B2

公开(公告)日：2024-04-30

申请号：US17476129

申请日：2021-09-15

Applicant: ROLLS-ROYCE PLC

Inventor： Chloe J Palmer ,  Guy D Snowsill ,  Jonathan E Holt

IPC: F02C7/224 ,  F02C3/20 ,  F02C3/22 ,  F02C7/04 ,  F02C7/14 ,  F02C7/143 ,  F02C7/18 ,  F02C7/22 ,  F23R3/04 ,  F23R3/28 ,  F02C9/40

CPC classification number: F02C7/224 ,  F02C3/20 ,  F02C3/22 ,  F02C7/04 ,  F02C7/14 ,  F02C7/143 ,  F02C7/18 ,  F02C7/22 ,  F02C7/222 ,  F23R3/04 ,  F23R3/286 ,  F02C9/40 ,  F05D2220/32 ,  F05D2240/35

Abstract: A fuel delivery system (201) is shown for delivering the hydrogen fuel from a cryogenic storage system to a fuel injection system in a gas turbine engine. The fuel delivery system includes a pump (301), a metering device (302), and a fuel heating system (303,304) for heating the hydrogen fuel to an injection temperature for the fuel injection system.

公开(公告)号：US11814980B2

公开(公告)日：2023-11-14

申请号：US17966285

申请日：2022-10-14

Applicant: ROLLS-ROYCE plc

Inventor： Sean A Walters ,  John Irving ,  Nomesh P Kandaswamy ,  Jessica Kennedy ,  Benjamin Littley ,  Kali Charan Nayak ,  Guy D Snowsill

IPC: F01D5/06 ,  F01D5/30

CPC classification number: F01D5/06 ,  F01D5/30 ,  F05D2220/323 ,  F05D2250/71

Abstract: A bladed disc system for a turbine engine having a disk portion and a plurality of blade portions which are associated with a stator section and an intercavity sealing portion, disc portion shaped such that blade portions are able to fit within firtree slot in disc portion, blade portion having aerofoil section and root section, aerofoil section having portion shaped such that they extend proximate to intercavity sealing portion, disc portion extending from portion that connects with drum to outer edge at which blade portions are connected with disc portion having width transition region in which thickness of disc increases from point at which disc connects to drum to outer edge at which it holds blade portions, and wherein width transition region has curved width transition region with radius r, and an overhanging portion which extends into the intercavity spacing between the width transition region and the intercavity sealing portion.