公开(公告)号：US20200347748A1

公开(公告)日：2020-11-05

申请号：US16451537

申请日：2019-06-25

Applicant: ROLLS-ROYCE plc

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

IPC: F01D25/24 ,  F01D15/12

Abstract: A gas turbine engine for an aircraft and an engine core including: a compressor system, a first lower pressure compressor, a second, higher pressure compressor; an outer core casing surrounding the compressor system. 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, wherein the first flange connection is the 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, and a front mount arranged to be connected to a pylon. A front mount position ratio of: axial   distance   between   the   first   flange   connection and   the   front   mount first   flange   radius is equal to or less than 1.18.

公开(公告)号：US20200347731A1

公开(公告)日：2020-11-05

申请号：US16778795

申请日：2020-01-31

Applicant: ROLLS-ROYCE plc

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

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

Abstract: A gas turbine engine includes an engine core including: a compressor system including first, lower pressure compressor, and second, higher pressure compressor; and an outer core casing. The engine includes a front mount arranged for connection to a pylon; and a fan located upstream of the engine core. The outer core casing includes a first flange connection that: is arranged to allow separation of the outer core casing at an axial position thereof, and is the first flange connection downstream of an axial position defined by the axial midpoint between the mid-span axial location on trailing edge of the most downstream aerofoil of first compressor and mid-span axial location on leading edge of the most upstream aerofoil of the second compressor. A front mount position ratio of: axial   distance   between   the   first   flange   connection and   the   front   mount first   flange   radius is equal to or less than 1.18.

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：US20200347730A1

公开(公告)日：2020-11-05

申请号：US16778617

申请日：2020-01-31

Applicant: ROLLS-ROYCE plc

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

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

Abstract: A gas turbine engine includes an engine core including: a compressor system including first, lower pressure compressor, and second, higher pressure compressor; and inner and outer core casings that define a core working gas flow path (A) therebetween, which has an outer radius that defines a gas path radius. The outer core casing includes a first flange connection that: has a first flange radius, is arranged to allow separation of the outer core casing at an axial position thereof, and is the first flange connection that is downstream of an axial position defined by the axial midpoint between the mid-span axial location on trailing edge of the most downstream aerofoil of first compressor and mid-span axial location on leading edge of the most upstream aerofoil of the second compressor. A gas path ratio of: first   flange   radius gas   path   radius is equal to or greater than 1.10.

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：US20200347742A1

公开(公告)日：2020-11-05

申请号：US16520740

申请日：2019-07-24

Applicant: ROLLS-ROYCE plc

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

IPC: F01D13/00 ,  F01D5/12 ,  F01D5/30

Abstract: A gas turbine engine includes an engine core including: a compressor system including first, lower pressure, compressor, and a 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, wherein 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 nacelle surrounding the engine core and defining a bypass duct between the engine core and the nacelle; wherein an axial midpoint of the radially outer edge is defined as the fan OGV tip centrepoint.

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.