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    Compound cycle engine
    32.
    发明公开
    Compound cycle engine 有权
    复合循环引擎

    公开(公告)号：EP2687675A2

    公开(公告)日：2014-01-22

    申请号：EP13177313.7

    申请日：2013-07-19

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Thomassin, Jean

    IPC: F01C1/22

    CPC classification number: F02B53/14 ,  F01C1/22 ,  F01C11/002 ,  F01C11/008 ,  F02B53/10 ,  F02B2053/005 ,  F02C6/12 ,  F02C6/20

    Abstract: A compound cycle engine (10) has at least one rotary unit (12) defining an internal combustion engine, a velocity turbine (26) in proximity of each unit (12), and a turbocharger (18). The exhaust port of each rotary unit (12) is in fluid communication with the flowpath of the velocity turbine (26) upstream of its rotor. The rotors of the velocity turbine (26) and of each rotary unit (12) drive a common load (16). The outlet of the compressor (20) of the turbocharger (18) is in fluid communication with the inlet port of each rotary unit (12), and the inlet of the pressure turbine (22) of the turbocharger (18) is in fluid communication with the flowpath of the velocity turbine (26) downstream of its rotor.

    Abstract translation: 复合循环发动机（10）具有限定内燃机的至少一个旋转单元（12），每个单元（12）附近的速度涡轮（26）以及涡轮增压器（18）。 每个旋转单元（12）的排气口与其转子上游的速度涡轮机（26）的流路流体连通。 速度涡轮机（26）的转子和每个旋转单元（12）的转子驱动共同的负载（16）。 涡轮增压器18的压缩机20的出口与每个旋转单元12的入口端口流体连通，并且涡轮增压器18的压力涡轮机22的入口流体连通 与其转子下游的速度涡轮机（26）的流动路径相连。

    Perfected helicopter drive
    35.
    发明公开
    Perfected helicopter drive 有权
    巫婆哈伯斯

    公开(公告)号：EP1728975A1

    公开(公告)日：2006-12-06

    申请号：EP05425390.1

    申请日：2005-05-30

    Applicant: Agusta S.p.A.

    Inventor： Regonini Roberto

    IPC: F01D25/18 ,  F04C29/02 ,  B01D45/14

    CPC classification number: F01D25/18 ,  B01D45/14 ,  B64C27/14 ,  F02C6/20 ,  F05D2220/329 ,  F05D2260/4031 ,  F16H37/065

    Abstract: There is described a drive (6) for a helicopter, the drive (6) having at least one rotary member (10, 11); a casing (8) housing the rotary member (10, 11) and defining a compartment (9) containing a lubricating fluid and air; and separating means (23) for separating the lubricating fluid from the air and retaining the lubricating fluid inside the casing (8) in the presence of airflow outwards of the casing (8) and produced by pressure gradients between the compartment (9) and the outside; the separating means (23) are angularly integral with the rotary member (10, 11) to centrifugally separate the lubricating fluid from the air radially with respect to the axis (A).

    Abstract translation: 描述了用于直升机的驱动器（6），驱动器（6）具有至少一个旋转构件（10,11）; 壳体（8），其容纳所述旋转构件（10,11）并限定包含润滑流体和空气的隔室（9）; 以及分离装置（23），用于从空气中分离润滑流体，并且在壳体（8）向外存在的气流的存在下将润滑流体保持在壳体（8）内部，并且通过隔室（9）和 外; 分离装置（23）与旋转构件（10,11）成角度地一体地将润滑流体相对于轴线（A）沿径向离心地从空气中分离。

    GAS TURBINE GENERATOR SET
    38.
    发明公开
    GAS TURBINE GENERATOR SET 失效
    GASTURBINENGENERATORSET

    公开(公告)号：EP0746680A1

    公开(公告)日：1996-12-11

    申请号：EP95909213.0

    申请日：1995-01-05

    Applicant: CAPSTONE TURBINE CORPORATION

    Inventor： NOE, James, C. ,  MCKEIRNAN, Robert, D., Jr.

    IPC: F02B63 ,  F02C6 ,  F02C7

    CPC classification number: F02C6/20 ,  B60L1/003 ,  B60L3/0061 ,  B60L11/126 ,  B60L2240/34 ,  B60L2240/36 ,  F02C7/08 ,  F05D2220/50 ,  F28D9/0012 ,  F28D9/0075 ,  F28F3/044 ,  H02K1/185 ,  H02K5/20 ,  H02K7/083 ,  H02K7/1823 ,  H02K9/14 ,  Y02T10/6217 ,  Y02T10/641 ,  Y02T10/7077

    Abstract: A small gas turbine generator set (100) comprising a rotating group and combustor contained within a circumferential recuperator (110). The rotating group comprises an alternator rotor (222) on a common shaft with a turbine wheel (400) and compressor impeller (312), supported by double acting compliant foil thrust bearings and a radial compliant foil bearing. The circumferential recuperator consists of a plurality of apertured boundary foils (122) having embossments for structurally spacing the foils apart, arranged to provide the flow channels, manifolds, and structure to permit the existence of differential pressure between each surface of the foil. The circumferential recuperator (110) is unitarily constructed surrounding the rotating group and combustor (700) wherein the inflowing air is heated by the recuperator (110) before entering the combustor. Due to the intercompatibility and modularity of the components, the air flow path associated with the compressor discharge and the turbine inlet is formed upon installation of the rotating group and the recuperator and by final assembly of the combustor unit (700) which forms a final enclosure for the turbine inlet air.

    KLEINGASTURBINE
    39.
    发明公开
    KLEINGASTURBINE 失效
    小型燃气轮机。

    公开(公告)号：EP0641235A1

    公开(公告)日：1995-03-08

    申请号：EP93906578.0

    申请日：1993-03-22

    Applicant: SCHNEIDER-SANCHEZ Ges.m.b.H.

    Inventor： SCHRECKLING, Kurt

    IPC: A63H27 ,  F01B17 ,  F02C3 ,  F02C6 ,  F23R3

    CPC classification number: F23R3/32 ,  A63H27/06 ,  F01B17/02 ,  F02C3/08 ,  F02C6/20 ,  F23R3/06 ,  F23R3/50 ,  F23R3/60 ,  Y02T50/675

    Abstract: A small gas turbine, especially for powering model aircraft, with a casing (3), a compressor impeller (1, 2), a combustion chamber (15-17) and a turbine wheel (5), in which the turbine wheel (5) drives the compressor impeller (1, 2) via a shaft running in a shaft tunnel (8) passing through the combustion chamber (15-17) which is surrounded by a helical fuel supply and evaporator pipe (22, 23), in which the combustion chamber (15-17) is bounded by a cylindrical outer wall (15) and a truncated conical inner wall (16) having combustion air inlets (19-21). The outlet end of the combustion chamber inner wall (16) enters, forming an annular gap, a cylindrical flow body (6, 7) which in turn, also forming an annular gap, lies in the central aperture of the vane ring (4) on the turbine side and is supported by the end (9) of the shaft tunnel (8). The other end of the shaft tunnel (8) is secured to the casing (3) between the compressor impeller (1, 2) and the front wall (17) of the combustion chamber.

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