公开(公告)号：US11879357B2

公开(公告)日：2024-01-23

申请号：US18067961

申请日：2022-12-19

Applicant: ROLLS-ROYCE plc

Inventor： Peter T. Ireland ,  John Coull ,  João António Coelho Vieira

IPC: F01D5/18 ,  F01D25/12

CPC classification number: F01D5/186 ,  F01D25/12 ,  F05D2220/32 ,  F05D2240/30 ,  F05D2240/304 ,  F05D2240/307 ,  F05D2260/202

Abstract: A turbine blade includes an aerofoil including a leading edge, a trailing edge, a first sidewall, a second sidewall, and an internal cooling circuit disposed within the aerofoil and configured to direct a cooling fluid within the aerofoil. The turbine blade includes at least one first recessed portion formed on the first sidewall proximal to a tip of the turbine blade. The first recessed portion is disposed proximal to and spaced apart from the trailing edge of the aerofoil. The first recessed portion includes a base surface, a first surface, and a second surface. The first recessed portion further includes at least one slot extending from the first surface to the internal cooling circuit. The slot is configured to allow a flow of the cooling fluid from the internal cooling circuit to the first recessed portion.

公开(公告)号：US10968749B2

公开(公告)日：2021-04-06

申请号：US16393137

申请日：2019-04-24

Applicant: ROLLS-ROYCE plc

Inventor： Shahrokh Shahpar ,  John Coull ,  Matthew Symes

IPC: F01D5/00 ,  F01D5/14 ,  F01D9/04

Abstract: A combustion chamber arrangement includes an annular combustion chamber, a plurality of lean burn fuel injectors and a stage of turbine nozzle guide vanes. The stage of turbine nozzle guide vanes is arranged at the downstream end of the annular combustion chamber and includes a plurality of circumferentially spaced vanes extending between and being secured to an annular inner wall and an annular outer wall. The annular inner wall has an outer surface which has a plurality of outer surface portions and each portion is positioned between a pair of circumferentially adjacent vanes and the annular outer wall has an inner surface which has a plurality of inner surface portions and each portion is positioned between a pair of circumferentially adjacent vanes.

公开(公告)号：US12252266B2

公开(公告)日：2025-03-18

申请号：US18483106

申请日：2023-10-09

Applicant: ROLLS-ROYCE plc

Inventor： Marko Bacic ,  John Coull

IPC: B64D37/30 ,  B64D37/34 ,  F02C3/22 ,  F02C7/14 ,  F02C7/22 ,  F02C7/224 ,  F02C9/40

Abstract: An aircraft propulsion system fuel system comprises a fuel line configured to receive liquid hydrogen fuel from a fuel tank, a vaporizer configured to vaporize liquid hydrogen fuel from the fuel line to generate a supercritical or gaseous fuel, a main fuel pump configured to receive and to pump the gaseous or supercritical fuel from the vaporizer during operation of the propulsion system, and a heater provided downstream in fuel flow to the main fuel pump, and configured to raise the temperature of the gaseous or supercritical fuel to a propulsion system delivery temperature.