HYBRID AMPLIFICATION OF HIGH SPOOL MOTORING VIA LOW SPOOL POWER EXTRACTION AND MOTORING OF A DIFFERENTIAL GEARED GENERATOR

    公开(公告)号:EP3904657A1

    公开(公告)日:2021-11-03

    申请号:EP21175641.6

    申请日:2019-05-29

    IPC分类号: F02C3/113 F02C7/32

    摘要: A power extraction and amplification system (200; 400; 500; 600; 700) for a gas turbine engine (20) is disclosed. In various embodiments, the power extraction and amplification system (200; 400; 500; 600; 700) includes a low spool tower shaft (204; 404; 504; 604) configured for engagement with a low speed spool (30), a high spool tower shaft (202; 402; 502; 602) configured for engagement with a high speed spool (32), a first motor (242; 442; 542; 642), a generator (266; 466; 566; 666), a differential gear box operably coupled to the low spool tower shaft (204; 404; 504; 604), to the first motor (242; 442; 542; 642) and to the generator (266; 466; 566; 666), and a second motor (270; 470; 570; 670) operably coupled to the generator (266; 466; 566; 666) and the high spool tower shaft (202; 402; 502; 602).

    SPLITTER AND GUIDE VANE ARRANGEMENT FOR GAS TURBINE ENGINES

    公开(公告)号:EP3919733A1

    公开(公告)日:2021-12-08

    申请号:EP21177641.4

    申请日:2021-06-03

    IPC分类号: F02K3/068 F02K3/075 F02K3/077

    摘要: A section for a gas turbine engine (120) according to an example of the present disclosure includes, among other things, a rotor including a row of blades (162) extending in a radial direction outwardly from a hub (164). The row of blades (162) deliver flow to a bypass flow path (B), an intermediate flow path (I), and a core flow path (C). A first case surrounds the row of blades (162) to establish the bypass flow path (B). A first flow splitter (170) divides flow between the bypass flow path (B) and a second duct (21). A row of guide vanes (168) extends in the radial direction across the bypass flow path (B). A second flow splitter (172) radially inboard of the first flow splitter (170) divides flow from the second duct (121) between the intermediate flow path (I) and the core flow path (C). A bypass port (174) interconnects the intermediate and bypass flow paths. A method of operation for a gas turbine engine (120) is also disclosed.

    INTEGRATED ELECTRO-AERO-THERMAL ENGINE
    5.
    发明公开

    公开(公告)号:EP4151843A1

    公开(公告)日:2023-03-22

    申请号:EP22206507.0

    申请日:2020-06-15

    IPC分类号: F02C3/113 F02C7/36 F02K5/00

    摘要: A turbine engine (20) includes integrated electric machines in the compressor section (24) and the turbine section (28) to supplement power produced from fuel with electric power. The example compressor section (24) includes a compressor electric motor (74) that is coupled to a compressor generator (76). The example turbine section (28) includes a turbine electric motor (94) that is coupled to a geared architecture (48) to supplement power driving a fan section (22). A turbine generator (96) provides electric power to the turbine electric motor (94).

    TURBOSHAFT ENGINE WITH AXIAL COMPRESSOR
    6.
    发明公开

    公开(公告)号:EP4086447A1

    公开(公告)日:2022-11-09

    申请号:EP22172178.0

    申请日:2022-05-06

    IPC分类号: F02K3/077 F02C3/10

    摘要: A turboshaft engine (10) includes a core section (100) extending between an inlet (12) and an outlet (14) of the turboshaft engine (10). The core section (100) includes a compressor (18, 26), a main combustor (44), and a main turbine (20, 28), such that combustion products from the main combustor (44) drives rotation of the turbine (20, 28) and the compressor (18, 26). A power turbine (46) is fluidly connected to the main turbine (20, 28) and driven by exhaust (42) from the main turbine (20, 28). A primary bypass (40) is fluidly connected to the inlet (12) and the outlet (14). The primary bypass (40) directs a portion (38) of an airflow (40) entering the inlet (12) around the core section (100) to the outlet (14). A secondary bypass (56) is located in the core section (100) and is configured to divert a portion (68) of a core airflow (42) of the core section (100) around the main combustor (44) and the main turbine (20, 28) to the power turbine (46).

    ASSISTED ENGINE START BLEED SYSTEM
    9.
    发明公开

    公开(公告)号:EP3736424A1

    公开(公告)日:2020-11-11

    申请号:EP20172625.4

    申请日:2020-05-01

    IPC分类号: F02C6/08 F02C9/18

    摘要: A system for bleeding air from a core flow path of a gas turbine engine includes a bleed valve (102) in a bleed air duct (104) configured to receive bleed air from a first entrance point (112) to the core flow path (C) into the bleed air duct (104); a pressurized air valve (106) in a pressurized air duct (108) configured to receive pressurized air from a second entrance point (114) to the core flow path (C), the pressurized air at a pressure greater than that received into the first entrance point (112); an eductor outlet (126) from the pressurized air duct (108) located in the bleed air duct (104); and a control system (110) operable to control operation of the bleed valve (102) and the pressurized air valve (106).

    GEARED TURBOFAN WITH THREE TURBINES WITH FIRST TWO CO-ROTATING AND THIRD ROTATING IN AN OPPOSED DIRECTION

    公开(公告)号:EP4242428A2

    公开(公告)日:2023-09-13

    申请号:EP23184871.4

    申请日:2013-03-29

    IPC分类号: F01D15/12

    摘要: A gas turbine engine has a fan rotor, a first compressor rotor and a second compressor rotor. The second compressor rotor compresses air to a higher pressure than the first compressor rotor. A first turbine rotor drives the second compressor rotor and a second turbine rotor. The second turbine drives the compressor rotor. A fan drive turbine is positioned downstream of the second turbine rotor. The fan drive turbine drives the fan through a gear reduction. The first compressor rotor and second turbine rotor rotate as an intermediate speed spool. The second compressor rotor and first turbine rotor together as a high speed spool. The high speed spool rotating in the same direction as the intermediate speed spool. The fan drive turbine rotates in an opposed direction as the intermediate speed spool.