公开(公告)号：US20220098984A1

公开(公告)日：2022-03-31

申请号：US17381767

申请日：2021-07-21

Applicant: ROLLS-ROYCE plc

Inventor： Chathura K KANNANGARA ,  Jillian C GASKELL ,  Stewart T THORNTON ,  Timothy PHILP

IPC: F01D5/14 ,  F01D25/24 ,  F01D25/28 ,  F02C7/36 ,  F16H1/28 ,  F02K3/06 ,  F02C7/20

Abstract: A gas turbine engine includes an engine core, a fan located upstream of the engine core, a nacelle surrounding the engine core and defining a bypass duct, and a fan outlet guide vane (OGV) extending radially across the bypass duct between an outer surface of the engine core and an inner surface of the nacelle. The engine core includes a compressor system, and an outer core casing surrounding the compressor system and including a first flange connection arranged to allow separation of the outer core casing at an axial position of the first flange connection. An axial midpoint of a radially inner edge of the fan OGV is defined as the fan OGV root centrepoint. A fan OGV root position to fan diameter ratio of: an ⁢ ⁢ axial ⁢ ⁢ distance ⁢ ⁢ between ⁢ ⁢ the ⁢ ⁢ first ⁢ ⁢ flange ⁢ ⁢ connection ⁢ ⁢ and the ⁢ ⁢ fan ⁢ ⁢ OGV ⁢ ⁢ root ⁢ ⁢ centrepoint the ⁢ ⁢ fan ⁢ ⁢ diameter is equal to or less than 0.33.

公开(公告)号：US20170081973A1

公开(公告)日：2017-03-23

申请号：US15262993

申请日：2016-09-12

Applicant: ROLLS-ROYCE PLC

Inventor： Andrew SWIFT ,  Stewart T THORNTON ,  Paul SIMMS ,  Glenn A. KNIGHT

IPC: F01D15/12 ,  F02K3/06 ,  F04D29/32 ,  F01D5/02

CPC classification number: F01D15/12 ,  F01D5/02 ,  F01D25/162 ,  F02C3/107 ,  F02C7/06 ,  F02C7/36 ,  F02K3/06 ,  F04D29/321 ,  F04D29/325 ,  F05D2220/32 ,  F05D2220/326 ,  F05D2220/327 ,  F05D2240/62 ,  F05D2250/232 ,  F05D2250/311 ,  F05D2260/40311 ,  F05D2260/941 ,  F05D2260/96 ,  F16H1/28 ,  Y02T50/671

Abstract: A gas turbine engine, including: low pressure spool having low pressure compressor and low pressure turbine connected by low pressure shaft; reduction gear train having sun gear, a carrier having a plurality of planet gears attached thereto, and a ring gear, wherein the sun gear, carrier or ring gear is connected to the low pressure shaft, and another of the sun gear, carrier and ring gear provides an output drive; a propulsive fan mounted fore of the gear train; a fan shafting arrangement comprising a fan shaft connected to the output drive of the gear train via a coupling, wherein the coupling includes a connection point to the fan shaft at a first end, and a connection point to the gear train at a second end wherein the first and second end are axial separated and radially separated and the axial separation is greater than the radial separation.

公开(公告)号：US20210115797A1

公开(公告)日：2021-04-22

申请号：US17082886

申请日：2020-10-28

Applicant: ROLLS-ROYCE plc

Inventor： Chathura K KANNANGARA ,  Jillian C GASKELL ,  Stewart T THORNTON ,  Timothy PHILP

IPC: F01D5/14 ,  F01D25/24 ,  F01D25/28 ,  F02C7/36 ,  F16H1/28 ,  F02K3/06 ,  F02C7/20

Abstract: A gas turbine engine includes an engine core and a fan located upstream of the engine core. The engine core includes: a compressor system including first, lower pressure compressor, and second, higher pressure compressor; and an outer core casing surrounding the compressor system and including a first flange connection arranged to allow separation of the outer core casing at an axial position of the first flange connection. The first flange connection is the first flange connection that is downstream of an axial position defined by the axial midpoint between the mid-span axial location on the trailing edge of the most downstream aerofoil of the first compressor and the mid-span axial location on the leading edge of the most upstream aerofoil of the second compressor. A fan diameter ratio of: first   flange   radius fan   diameter is equal to or greater than 0.125.

公开(公告)号：US20200347749A1

公开(公告)日：2020-11-05

申请号：US16505816

申请日：2019-07-09

Applicant: ROLLS-ROYCE PLC

Inventor： Chathura K KANNANGARA ,  Jillian C GASKELL ,  Stewart T THORNTON ,  Timothy PHILP

IPC: F01D25/24 ,  F01D5/04

Abstract: A gas turbine engine for an aircraft includes: an engine core with: a compressor system including a first, lower pressure, compressor, and a second, higher pressure, compressor; and an outer core casing surrounding the compressor system. The gas turbine engine further includes a fan located upstream of the engine core with a plurality of fan blades and having a fan diameter. The outer core casing includes a first flange connection arranged to allow separation of the outer core casing at an axial position of the first flange connection which has a first flange radius, wherein the first flange connection is downstream of an axial position defined by the axial midpoint between the mid-span axial location on the trailing edge of the most downstream aerofoil of the first compressor and the mid-span axial location on the leading edge of the most upstream aerofoil of the second compressor.

公开(公告)号：US20200347732A1

公开(公告)日：2020-11-05

申请号：US16520516

申请日：2019-07-24

Applicant: ROLLS-ROYCE PLC

Inventor： Chathura K KANNANGARA ,  Jillian C. GASKELL ,  Stewart T THORNTON ,  Timothy PHILP

IPC: F01D5/14 ,  F02C3/06 ,  F01D25/24

Abstract: A gas turbine engine for an aircraft includes: an engine core with a compressor system including a first, lower pressure, compressor, and a second, higher pressure, compressor; an inner core casing provided radially inwardly of the compressor blades of the compressor system; and an outer core casing surrounding the compressor system, the inner core casing and the outer core casing defining a core working gas flow path therebetween. The outer core casing includes: a first flange connection arranged to allow separation of the outer core casing at an axial position of the first flange connection, the first flange connection having a first flange radius, A gas path radius is defined as the outer radius of the core gas flow path at the axial position of the first flange connection, and a gas path ratio of: first   flange   radius gas   path   radius is equal to or greater than 1.10.