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1. 发明公开

EP4310312A1 MULTI-DUCT EXHAUST SYSTEM FOR GAS TURBINE ENGINE 审中-公开
公开(公告)号：EP4310312A1
公开(公告)日：2024-01-24
申请号：EP23187106.2
申请日：2023-07-21
申请人： RTX Corporation
发明人： BURD, Steven W.
IPC分类号： F02K1/00 , F01D17/16 , F02K1/40 , F02K3/075
摘要： A system (20) is provided for an aircraft. This aircraft system (20) includes an exhaust duct (68), an exhaust flow regulator (108), a nozzle bypass duct (70) and a bypass flow regulator (98). The exhaust duct (68) extends longitudinally to an exhaust nozzle (80). The exhaust flow regulator (108) is configured to regulate fluid flow through the exhaust duct (68) to the exhaust nozzle (80). The nozzle bypass duct (70) projects out from a side of the exhaust duct (68). The bypass flow regulator (98) is configured to regulate fluid flow from the exhaust duct (68) into the nozzle bypass duct (70). The bypass flow regulator (98) is disposed upstream of the exhaust flow regulator (108).

3. 发明授权

EP3728797B1 ENSEMBLE PROPULSIF POUR AÉRONEF ET PROCÉDÉ DE VENTILATION D'UNE ENCEINTE MOTEUR 有权
公开(公告)号：EP3728797B1
公开(公告)日：2023-02-01
申请号：EP18839842.4
申请日：2018-12-20
发明人： BOILEAU, Patrick
IPC分类号： F01D21/00 , F01D25/12 , F02K3/06 , F02C7/18 , B64D29/00 , F02C7/14 , F02K3/075

7. 发明公开

EP3808963A1 GAS TURBINE ENGINE 有权
公开(公告)号：EP3808963A1
公开(公告)日：2021-04-21
申请号：EP20196568.8
申请日：2020-09-17
申请人： Rolls-Royce plc
发明人： Harvey, Giles
IPC分类号： F02K3/06 , F02K3/075 , F01D15/08 , F01D15/10
摘要： A gas turbine engine, which may be a turbofan gas turbine engine that may optionally be geared, and in particular arrangements of turbine blades around an exhaust nozzle of an engine core of such a turbine. Example embodiments include a gas turbine engine for an aircraft comprising: an engine core (11) comprising a turbine (19), a compressor (14), and a core shaft (26) connecting the turbine to the compressor, the engine core (11) comprising an inlet upstream of the compressor (14) and an exhaust nozzle at a downstream outlet of the turbine (19); a fan (23) located upstream of the engine core inlet; and a set of exhaust nozzle vanes spanning the exhaust nozzle, the turbine (19) comprising a first row of turbine blades upstream of the exhaust nozzle vanes and a second row of turbine blades downstream of the exhaust nozzle guide vanes, one or more of the exhaust nozzle guide vanes comprising a passage configured to direct airflow downstream from the first row of turbine blades towards the second row of turbine blades.

10. 发明授权

EP3524807B1 APPARATUS COMPRISING A GAS TURBINE AND AN EJECTOR 有权
公开(公告)号：EP3524807B1
公开(公告)日：2020-11-04
申请号：EP19157332.8
申请日：2009-12-23
申请人： Rolls-Royce Corporation
发明人： Khalid, Syed Jalaluddin
IPC分类号： F02K1/36 , F02K3/077 , B64C21/06 , F04D29/64 , F01D9/06 , F04D29/68 , F02K3/02 , F02K3/075

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