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    HYBRID ELECTRIC AIRCRAFT PROPULSION INCORPORATING A RECUPERATED PRIME MOVER
    63.
    发明公开
    HYBRID ELECTRIC AIRCRAFT PROPULSION INCORPORATING A RECUPERATED PRIME MOVER 审中-公开
    混合式电动飞机推进装备了一种再生式发动机

    公开(公告)号：EP3228544A1

    公开(公告)日：2017-10-11

    申请号：EP17165254.8

    申请日：2017-04-06

    Applicant: Hamilton Sundstrand Corporation

    Inventor： HIMMELMANN, Richard A. ,  TONGUE, Stephen E.

    IPC: B64D27/02 ,  F02C3/04 ,  B64D27/10

    CPC classification number: B64D27/24 ,  B60Y2400/112 ,  B60Y2400/431 ,  B60Y2400/602 ,  B64D27/02 ,  B64D27/10 ,  B64D2027/026 ,  F01D15/10 ,  F02C3/04 ,  F02C3/34 ,  F02C6/00 ,  F02C7/10 ,  F02K3/00 ,  F02K5/00 ,  F05D2220/323 ,  F05D2220/76 ,  Y02T50/64 ,  Y10S903/903

    Abstract: A hybrid-electric propulsion system (10) includes a gas turbine engine (12), an electric machine (14) coupled to and rotatably driven by the gas turbine engine to produce AC electric power, an energy storage system (18), and a propulsion unit (16). The gas turbine engine includes a combustor (26) and a recuperator (20) that places an exhaust air flow that is downstream from the combustor in a heat exchange relationship with a compressed air flow that is upstream from the combustor to transfer thermal energy from the exhaust flow to the compressed flow. The propulsion unit includes a fan (44) and an electric motor (42) rotably coupled to the fan, the electric motor being driven by electric power from one of the electric machine or the energy storage system.

    Abstract translation: 一种混合动力电动推进系统（10），包括燃气涡轮发动机（12），联接到燃气涡轮发动机并由燃气涡轮发动机可旋转地驱动以产生AC电力的电机（14），储能系统（18）和 推进单元（16）。 该燃气涡轮发动机包括燃烧器（26）和换热器（20），该换热器（20）将与燃烧器上游的压缩空气流成换热关系的位于燃烧器下游的排气流放置成从燃烧器 排气流向压缩流。 推进单元包括风扇（44）和可旋转地联接到风扇的电动机（42），电动机由来自电机或能量存储系统之一的电力驱动。

    HYBRID PROPULSION SYSTEM
    64.
    发明公开
    HYBRID PROPULSION SYSTEM 有权
    混合推进系统

    公开(公告)号：EP3184789A1

    公开(公告)日：2017-06-28

    申请号：EP16203096.9

    申请日：2016-12-09

    Applicant: General Electric Company

    Inventor： SENNOUN, Mohammed El Hacin

    IPC: F02K3/06 ,  F02K5/00 ,  F02C6/10 ,  F02C6/14

    CPC classification number: F01D15/10 ,  F02C6/10 ,  F02C6/14 ,  F02K3/06 ,  F02K5/00 ,  F05D2220/36 ,  F05D2260/4031 ,  F05D2260/42

    Abstract: An aeronautical propulsion system includes a fan 38 having a plurality of fan 38 blades and an electric motor 82 drivingly connected to the fan 38 for rotating the plurality of fan 38 blades. A chemically rechargeable ultra-capacitor 86 is included for providing the electric motor 82 with a substantially continuous flow of electric energy during operation of the chemically rechargeable ultra-capacitor 86, resulting in a more efficient aeronautical propulsion system.

    Abstract translation: 航空推进系统包括具有多个风扇38叶片的风扇38和驱动地连接到风扇38以便旋转多个风扇叶片38的电动机82。 包括化学可再充电的超电容器86，用于在化学可再充电的超电容器86的操作期间为电动机82提供基本上连续的电能流，从而导致更有效的航空推进系统。

    AUXILIARY POWER UNIT WITH COMBINED COOLING OF GENERATOR
    65.
    发明公开
    AUXILIARY POWER UNIT WITH COMBINED COOLING OF GENERATOR 审中-公开
    HILFSTRIEBWERK MIT KOMBINIERTERKÜHLUNGEINES发电机

    公开(公告)号：EP3133266A1

    公开(公告)日：2017-02-22

    申请号：EP16183260.5

    申请日：2016-08-08

    Applicant: Pratt & Whitney Canada Corp.

    Inventor： JONES, Anthony ,  JULIEN, Andre ,  MENHEERE, David ,  THOMASSIN, Jean ,  ULLYOTT, Richard

    IPC: F02C7/14 ,  F02C7/18 ,  B64D33/08 ,  B64D41/00 ,  F02C5/00 ,  F02K5/00 ,  F01C1/22

    CPC classification number: F02B63/04 ,  B64D33/08 ,  B64D41/00 ,  F01C1/22 ,  F01C21/18 ,  F01P1/06 ,  F01P5/04 ,  F01P5/06 ,  F02B37/00 ,  F02B53/02 ,  F02B53/14 ,  F02B63/06 ,  F02B67/04 ,  F02B2053/005 ,  F02C5/00 ,  F02C7/14 ,  F02C7/18 ,  F02K5/00 ,  F05D2220/50 ,  F05D2260/213 ,  Y02T10/144 ,  Y02T10/17 ,  Y02T50/53 ,  Y02T50/672 ,  Y02T50/676

    Abstract: An auxiliary power unit (10) for an aircraft, including an internal combustion engine (12) having a liquid coolant system, a generator (64) drivingly engaged to the internal combustion engine (12) and having a liquid coolant system distinct from the liquid coolant system of the internal combustion engine (12), a first heat exchanger (66) in fluid communication with the liquid coolant system of the internal combustion engine (12), a second heat exchanger (68) in fluid communication with the liquid coolant system of the generator (64), an exhaust duct (70) in fluid communication with air passages (66b, 68b) of the heat exchangers (66, 68), and a fan (78) received in the exhaust duct (70) and rotatable by the internal combustion engine (12) for driving a cooling air flow through the air passages (66b, 68b). The liquid coolant system of the engine (12) may be distinct from fuel and lubricating systems of the auxiliary power unit (10).

    Abstract translation: 一种用于飞行器的辅助动力单元（10），包括具有液体冷却剂系统的内燃机（12），与所述内燃机（12）驱动接合并具有不同于所述液体的液体冷却剂系统的发电机（64） 内燃机（12）的冷却剂系统，与内燃机（12）的液体冷却剂系统流体连通的第一热交换器（66），与液体冷却剂系统流体连通的第二热交换器 ，与所述热交换器（66,68）的空气通道（66b，68b）流体连通的排气管道（70）和容纳在所述排气管道（70）中的可旋转的风扇（78） 通过用于驱动通过空气通道（66b，68b）的冷却空气流的内燃机（12）。 发动机（12）的液体冷却剂系统可以不同于辅助动力单元（10）的燃料和润滑系统。

    An aircraft having a lift/propulsion unit
    66.
    发明公开
    An aircraft having a lift/propulsion unit 有权
    Flugzeug mit einer Auftriebs- / Antriebs-Einheit

    公开(公告)号：EP2256036A2

    公开(公告)日：2010-12-01

    申请号：EP10159995.9

    申请日：2010-04-15

    Applicant: Rolls-Royce plc

    Inventor： Harris, Paul Jeremy Hugh ,  Hewitt, Frank Anthony ,  Johnson, Martin Christopher ,  Wright, Christopher

    IPC: B64C29/00

    CPC classification number: B64C29/0016 ,  B64C15/14 ,  B64C29/0075 ,  B64D2027/026 ,  F02C3/10 ,  F02K1/004 ,  F02K5/00 ,  F05D2220/328 ,  F05D2220/76 ,  Y02T50/671

    Abstract: An aircraft comprises a lift/propulsion unit 8 which comprises a power unit such as a turboshaft engine 14 which drives a fan 10 through a transmission mechanism 16. The fan 10 discharges to vectoring nozzles 24 which can be independently swivelled to provide lift or propulsion thrust. An output shaft 20 of the transmission mechanism 16 serves as the main shaft of a motor/generator 26 of modular form. The motor/generator 26 can act as a generator to charge an electrical storage device such as a battery 32, or as a motor to drive the fan 10, either alone or to supplement the output of the engine 14. Reaction control nozzles 38 are provided at extremities of the aircraft to provide stabilising thrust.
    The aircraft is capable of vertical take off and hovering, with the vectoring nozzles 24 swivelled to a lift position, and forward thrust with the vectoring nozzles 24 swivelled to a propulsion position.

    Abstract translation: 飞行器包括升降机/推进单元8，其包括诸如涡轮轴发动机14的动力单元，涡轮轴发动机14通过传动机构16驱动风扇10.风扇10排放到矢量喷嘴24，其可独立地旋转以提供升力或推进推力 。 传动机构16的输出轴20用作模块化形式的马达/发电机26的主轴。 马达/发电机26可以用作发电机，以对诸如电池32的电存储装置或作为电动机来单独驱动风扇10或补充发动机14的输出。提供反应控制喷嘴38 在飞机的四肢提供稳定推力。 飞机能够垂直起飞和悬停，矢量喷嘴24旋转到提升位置，并且向量推力与向量喷嘴24旋转到推进位置。

    Axial flow progressive cavity type gas generator
    67.
    发明公开
    Axial flow progressive cavity type gas generator 有权
    轴流式螺杆式气体发生器

    公开(公告)号：EP1816315A1

    公开(公告)日：2007-08-08

    申请号：EP06125360.5

    申请日：2006-12-04

    Applicant: General Electric Company

    Inventor： MURROW, Kurt David ,  GRIFFIN, Rollin George ,  FAKUNLE, Oladapo

    IPC: F01C1/107 ,  F01C11/00 ,  F03C2/08 ,  F02B53/00 ,  F02C5/06 ,  F01C1/08

    CPC classification number: F01C1/084 ,  F01C1/107 ,  F01C11/008 ,  F02B53/00 ,  F02C5/06 ,  F02K5/00 ,  F03C2/08 ,  Y02T50/671

    Abstract: An axial flow positive displacement compressor (8) has an inlet (20) axially spaced apart and upstream from an outlet (22). Inner and outer bodies (12, 14) have offset inner and outer axes (16, 18) extend from the inlet (20) to the outlet (22) through first and second sections (24, 26) of a compressor assembly (15) in serial downstream flow relationship. At least one of the bodies is rotatable about its axis. The inner and outer bodies have intermeshed inner and outer helical blades (17, 27) wound about the inner and outer axes respectively (16, 18). The inner and outer helical blades (17, 27) extend radially outwardly and inwardly respectively. The helical blades have first and second twist slopes (34, 36) in the first and second sections (24, 26) respectively. The first twist slopes (34) are less than the second twist slopes (36). An engine (100) including the compressor has in downstream serial flow relationship from the compressor (8), a combustor (7), and a high pressure turbine (9) drivingly connected to the compressor by a high pressure shaft (5).

    Abstract translation: 轴向流正压容积式压缩机（8）具有轴向间隔开且位于出口（22）上游的入口（20）。 通过压缩机组件（15）的第一和第二部分（24,26），内部和外部主体（12,14）具有从入口（20）延伸到出口（22）的偏移的内轴线和外轴线（16,18） 串联下游流量关系。 至少有一个主体可以绕其轴线转动。 内体和外体具有分别围绕内轴和外轴（16,18）缠绕的内螺旋叶片和外螺旋叶片（17,27）。 内部和外部螺旋叶片（17,27）分别径向向外和向内延伸。 螺旋叶片分别在第一和第二部分（24,26）中具有第一和第二扭曲斜坡（34,36）。 第一扭曲坡度（34）小于第二扭曲坡度（36）。 包括压缩机的发动机（100）具有与压缩机（8），燃烧室（7）和通过高压轴（5）驱动地连接到压缩机的高压涡轮机（9）的下游串联流动关系。

    AIR-JET PROPELLER
    68.
    发明公开
    AIR-JET PROPELLER 审中-公开
    AIR-JET螺旋桨

    公开(公告)号：EP1806286A1

    公开(公告)日：2007-07-11

    申请号：EP04791373.6

    申请日：2004-10-29

    Applicant: Sanchez Sanchez, Felix

    Inventor： Sanchez Sanchez, Felix

    IPC: B64C15/00 ,  F02K5/02 ,  F02K1/00

    CPC classification number: F03H99/00 ,  B64C11/001 ,  B64D27/16 ,  F02K5/00

    Abstract: SUMMARY
    Air jet propeller with three basic bodies, the first body or head has a half ellipse of revolution and a grille on its upper part while the lower part is being closed down by a pipe and a shutting hoop.
    The second body or central part with a cylindrical tubular shape has the helical round honeycomb rotor incorporated and fitted to an explosion engine.
    The third body or back with a conical base shape has a series of windows, hatches and butterflies balancing, stabilizing and orientating the aircraft with a considerable reduction in petrol consumption and therefore ensuring a decrease in pollution levels, this is possible as aircrafts can fly quite slowly (few kms/h.) facilitating landing and taking off processes with a minimum length of landing strips. The risks involved in landing and taking off at high speed are also being reduced.

    Abstract translation: 发明内容具有三个基体的空气喷射螺旋桨，第一主体或头部具有半旋转椭圆形并且在其上部具有格栅，而下部由管和关闭箍关闭。 具有圆柱形管状的第二本体或中心部分具有并入并安装在爆炸引擎上的螺旋形圆形蜂窝转子。 第三个身体或背部呈圆锥形底座形状，有一系列窗户，舱口和蝴蝶，平衡，稳定和定向飞机，大大减少了汽油消耗，从而确保污染水平的降低，这是可能的，因为飞机可以飞行 慢慢地（几公里/小时）促进着陆和起飞过程中起落条的最小长度。 降落和高速起飞所涉及的风险也在减少。

    ENGINE
    70.
    发明公开
    ENGINE 审中-公开

    公开(公告)号：EP4428359A2

    公开(公告)日：2024-09-11

    申请号：EP24190717.9

    申请日：2020-05-28

    Applicant: Reaction Engines Limited

    Inventor： BOND, Alan ,  EVANS, Kathryn ,  JOHNSON, Martin ,  PAYNE, Russell

    IPC: F02K9/78

    CPC classification number: F02C7/04 ,  F02C7/143 ,  F02K9/78 ,  F02K5/00 ,  F05D2220/8020130101 ,  B64D2033/02620130101 ,  F02C7/224 ,  B64D33/08 ,  B64D33/02

    Abstract: An engine comprises an air intake arrangement configured to receive air; a heat exchanger arrangement arranged downstream of the air intake arrangement, configured to cool the air, and comprising a plurality of heat exchanger modules; and one or more turbomachinery components configured to receive cooled air from the heat exchanger arrangement. The plurality of heat exchanger modules are arranged to be generally centred on and to be arranged along a longitudinal axis of the engine. At least one of the plurality of heat exchanger modules is arranged to at least partially overlap with at least one other one of the plurality of heat exchanger modules relative to the longitudinal axis of the engine.

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