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公开(公告)号：US11118470B2
公开(公告)日：2021-09-14
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
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.
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公开(公告)号：US11111791B2
公开(公告)日：2021-09-07
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
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.
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公开(公告)号：US10539021B2
公开(公告)日：2020-01-21
申请号：US15399457
申请日：2017-01-05
Applicant: ROLLS-ROYCE PLC
Inventor： David A Edwards , Stewart T Thornton
IPC: F01D3/04 , F04D29/041 , F16C17/04 , F01D25/16 , F16C17/08
Abstract: A thrust balancing mechanism for balancing axial loads on a rotor thrust bearing 3 is described. The mechanism comprises a piston arrangement 6 axially mounted on a stationary structure 2, about a center axis arranged, in use, in coaxial alignment with a rotating shaft 1 carrying the rotor thrust bearing 3. A hydrodynamic thrust bearing 8 is mounted, in use, between the piston 6 and the rotor thrust bearing 3. The piston 6 is pressurized so as to impart to the rotor thrust bearing 3, via the hydrodynamic thrust bearing 8, an axial load which counters an axial load imparted to the rotor thrust bearing 3 by the rotating shaft 1.
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公开(公告)号：US11333021B2
公开(公告)日：2022-05-17
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
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.
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Patent Agency Ranking
公开(公告)号：US10598022B1
公开(公告)日：2020-03-24
申请号：US16451467
申请日：2019-06-25
Applicant: ROLLS-ROYCE plc
Inventor： Chathura K Kannangara , Jillian C Gaskell , Stewart T Thornton , Timothy Philp
Abstract: A gas turbine engine (10) for an aircraft comprises an engine core (11) comprising: a compressor system comprising a first, lower pressure, compressor (14), and a second, higher pressure, compressor (15); and an outer core casing (70) surrounding the compressor system. The gas turbine engine further comprises a fan (23) located upstream of the engine core (11), the fan comprising a plurality of fan blades. The outer core casing comprises: a first flange connection (60) arranged to allow separation of the outer core casing (70) at an axial position of the first flange connection (60), the first flange connection (60) having a first flange radius (104), wherein the first flange connection (60) 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 (14) and the mid-span axial location on the leading edge of the most upstream aerofoil of the second compressor (15). A fan blade mass ratio of: first flange radius ( 104 ) mass of each fan blade is equal to or less than 19.0 mm/lb.
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公开(公告)号：US10393068B2
公开(公告)日：2019-08-27
申请号：US15262612
申请日：2016-09-12
Applicant: ROLLS-ROYCE plc
Inventor： Andrew Swift , Stewart T Thornton , Paul Simms , Glenn A Knight
Abstract: A gas turbine engine, including: a low pressure spool having a low pressure compressor and a low pressure turbine connected by a low pressure shaft; a reduction gear train having a sun gear, a carrier having a plurality of planet gears attached thereto, and a ring gear, wherein one of 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 which is connected to the output drive of the gear train and a fan support shaft which passes through center of the gear train along the axis of rotation of the gearbox and fan, wherein the fan shafting arrangement is rotatably supported by at least two axially separated bearings.
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公开(公告)号：US11008870B2
公开(公告)日：2021-05-18
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
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.
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公开(公告)号：US10858942B2
公开(公告)日：2020-12-08
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
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.
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公开(公告)号：US10584632B1
公开(公告)日：2020-03-10
申请号：US16505765
申请日：2019-07-09
Applicant: ROLLS-ROYCE plc
Inventor： Chathura K Kannangara , Jillian C Gaskell , Stewart T Thornton , Timothy Philp
Abstract: A gas turbine engine includes an engine core; a fan located upstream of engine core and having a fan diameter; a nacelle surrounding engine core and defining a bypass duct between engine core and nacelle; and a fan OGV extending radially across bypass duct, fan OGV having a radially inner and outer edge, wherein the radially inner edge's axial midpoint is the fan OGV root centrepoint. The engine core includes a compressor system encompassing a 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 outer core casing at an axial position of first flange connection, the first flange connection having a first flange radius, wherein the first flange connection is downstream of an axial position. A fan OGV root position ratio of: axial distance between the first flange connection and the fan OGV root centrepoint first flange radius is equal to or less than 2.6.
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