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1. 发明公开

EP4306423A3 AIRCRAFT PROPULSION SYSTEM WITH INTERMITTENT COMBUSTION ENGINE(S) 审中-实审
公开(公告)号：EP4306423A3
公开(公告)日：2024-04-17
申请号：EP23185418.3
申请日：2023-07-13
申请人： PRATT & WHITNEY CANADA CORP.
发明人： FREER, Richard
IPC分类号： B64D27/04 , B64D35/02 , F01D15/12 , F02C5/00 , F02C7/36
CPC分类号： B64D27/04 , B64D35/02 , F02K5/00 , B64D35/04
摘要： An aircraft system (20) includes a first propulsor (36A), a second propulsor (36B), a drivetrain and an intermittent combustion engine (66). The first propulsor (36A) includes a first propulsor rotor (42A) and a first vane array (44A). The second propulsor (36B) includes a second propulsor rotor (42B) and a second vane array (44). The drivetrain includes a drive structure (100) and a transmission (106). An output (118) of the transmission (106) is coupled to the first propulsor rotor (42A) and the second propulsor rotor (42B) through the drive structure (100). The intermittent combustion engine (66) is configured to drive rotation of the first propulsor rotor (42A) and the second propulsor rotor (42B) through the drivetrain.

2. 发明授权

EP3922815B1 SYSTÈME DE LUBRIFICATION POUR FOURNIR UN FLUIDE AUX CANNELURES D'UN ARBRE D'ENTRAINEMENT 有权
公开(公告)号：EP3922815B1
公开(公告)日：2024-02-14
申请号：EP21305765.6
申请日：2021-06-07
发明人： LEWIS, Nathan
IPC分类号： F01D5/02 , F01D15/12 , F01D25/18 , F02C7/32 , F16N9/02

3. 发明公开

EP4159998A1 GEARED ARCHITECTURE TURBOFAN ENGINE THERMAL MANAGEMENT SYSTEM AND METHOD 审中-实审转让
公开(公告)号：EP4159998A1
公开(公告)日：2023-04-05
申请号：EP22210337.6
申请日：2014-03-13
申请人： Raytheon Technologies Corporation
发明人： SCHWARTZ, Frederick M. , PICKFORD, Simon
IPC分类号： F02K3/02 , F02K3/06 , F02C7/32 , F02K3/115 , F02C7/14 , F01D5/02 , F01D15/12 , F01D17/10 , F01D25/12
摘要： A method of sizing a heat exchanger (64) for a geared architecture gas turbine engine (20) includes sizing a minimum frontal area (65) of at least one heat exchanger (64) located in communication with a fan bypass airflow (W) such that a ratio of waste heat area to horsepower generation characteristic area is between 1.6 to 8.75.

4. 发明授权

EP3792514B1 BEARING PRELOAD USING EXTERNAL GEARBOX REACTION 有权
公开(公告)号：EP3792514B1
公开(公告)日：2022-07-20
申请号：EP20195954.1
申请日：2020-09-14
发明人： BRILLON, Louis , CARRIERES, Alain
IPC分类号： F16D3/26 , F16C19/16 , F16C27/06 , F16C27/08 , B64C27/12 , B64D27/10 , B64D35/08 , F01D13/00 , F01D25/16 , F01D25/18 , F02C7/06 , F02C7/36 , F01D5/02 , F01D15/12 , F16C37/00 , F16C33/66

5. 发明公开

EP3990748A1 STRUKTURBAUGRUPPE FÜR EIN GASTURBINENTRIEBWERK 有权
公开(公告)号：EP3990748A1
公开(公告)日：2022-05-04
申请号：EP20735294.9
申请日：2020-06-23
申请人： Rolls-Royce Deutschland Ltd & Co KG
发明人： BUCHHOLZ, Carsten
IPC分类号： F01D5/02 , F01D15/12 , F01D21/04

6. 发明授权

EP2898205B1 GEARED GAS TURBINE ENGINE ACCESSORY GEARBOX 有权转让
公开(公告)号：EP2898205B1
公开(公告)日：2021-11-24
申请号：EP13838121.5
申请日：2013-01-21
发明人： CLOFT, Thomas G. , GUKEISEN, Robert L.
IPC分类号： F02C7/32 , B64D41/00 , F01D15/10 , F01D15/12

7. 发明授权

EP2834501B1 SEAL WITH NON-METALLIC INTERFACE 有权转让
公开(公告)号：EP2834501B1
公开(公告)日：2020-09-02
申请号：EP13813501.7
申请日：2013-03-28
申请人： United Technologies Corporation
发明人： BURD, Steven W. , BURSEY, Roger W. , MARTINEZ, Gonzalo F. , HARRIS-MILLER, Meggan H.
IPC分类号： F02K3/072 , F02C3/067 , F01D15/12 , F02C7/36 , F16J15/08

8. 发明公开

EP3690201A1 FLEXIBLE SUPPORT STRUCTURE FOR A GEARED ARCHITECTURE GAS TURBINE ENGINE 审中-实审转让
公开(公告)号：EP3690201A1
公开(公告)日：2020-08-05
申请号：EP20160214.1
申请日：2012-06-01
申请人： United Technologies Corporation
发明人： MCCUNE, Michael E. , HUSBAND, Jason
IPC分类号： F01D25/16 , F02C7/20 , F02C7/36 , F01D15/12 , F16H1/28
摘要： A geared architecture (48) with a flex mount for a Fan Drive Gear System defined by a transverse stiffness relatonship.

9. 发明授权

EP3045684B1 FLEXIBLE SUPPORT STRUCTURE FOR A GEARED ARCHITECTURE GAS TURBINE ENGINE 有权转让
公开(公告)号：EP3045684B1
公开(公告)日：2020-03-04
申请号：EP16159312.4
申请日：2012-06-01
申请人： United Technologies Corporation
发明人： MCCUNE, Michael E. , HUSBAND, Jason
IPC分类号： F01D25/16 , F02C7/20 , F02C7/36 , F01D15/12 , F16H1/28

10. 发明公开

EP3608511A1 GAS TURBINE ENGINE WITH CERAMIC MATRIX COMPOSITE TURBINE COMPONENTS 有权转让
公开(公告)号：EP3608511A1
公开(公告)日：2020-02-12
申请号：EP19189309.8
申请日：2019-07-31
申请人： Rolls-Royce plc
发明人： Townes, Roderick , Dunning, Pascal , Whittle, Michael
IPC分类号： F01D5/28 , F01D15/12 , F01D25/12 , F02C3/107 , F02K3/06
摘要： A gas turbine engine (10) for an aircraft with an engine core (11) comprising a first turbine (19), a first compressor (14), and a first core shaft (26) connecting the first turbine to the first compressor, a second turbine (17), a combustor, a second compressor (15), and a second core shaft (27) connecting the second turbine to the second compressor, the second turbine, second compressor, and second core shaft being arranged to rotate at a higher rotational speed than the first core shaft, the gas turbine engine further comprising a fan (23) comprising a plurality of fan blades and a gearbox (30) that receives an input from the first core shaft (26) and outputs drive to the fan so as to drive the fan at a lower rotational speed than the first core shaft, wherein part (C) of the flow (A) that enters the engine core bypasses the combustor and is used as turbine cooling flow to cool the turbine, a cooling flow requirement is defined as the ratio of the mass flow rate of the turbine cooling flow (C) to the mass flow rate of the flow entering the engine core (A) at cruise conditions,a turbine entry temperature is defined as the temperature (K) at the inlet to the most axially upstream turbine rotor in the gas turbine engine at a maximum power condition of the gas turbine engine and the cooling efficiency ratio, defined as the ratio between the turbine entry temperature and the cooling flow requirement, is in the range of from 8000 to 20000 K.

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