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公开(公告)号：US20160076446A1
公开(公告)日：2016-03-17
申请号：US14856834
申请日：2015-09-17
Applicant: Airbus Operations S.L.
Inventor： Nicolas Bailey Noval , Raul Llamas Sandin
CPC classification number: F02C6/14 , F02C6/20 , F02C6/206 , F02K3/06 , F02K5/00 , F05D2220/323 , F05D2220/64 , F05D2220/76
Abstract: A propulsion engine comprising at least a first propulsion unit including a first fan encased by a geared ring and a gas turbine engine driving a first shaft connected to the first fan, at least a second propulsion unit including a second fan encased by a geared ring connected to a second shaft operatively coupled to an electric machine and at least an electric storage device connected to the electric machine. The geared rings are configured to transmit torque between the fans so that they can rotate in conjunction (directly or through an intermediate gear) when they are driven by at least one of said first and second shafts. The propulsion engine is arranged for controlling the torque to be supplied to the assembly of the first and second fans by the gas turbine engine and/or by the electric machine acting as a motor or as a generator.
Abstract translation: 一种推进发动机，包括至少第一推进单元，其包括由齿轮环包围的第一风扇和驱动连接到第一风扇的第一轴的燃气涡轮发动机，至少第二推进单元，包括由齿轮环连接的第二风扇， 到可操作地耦合到电机的第二轴和连接到电机的至少一个蓄电装置。 齿轮环被配置为在风扇之间传递扭矩，使得它们可以在它们被所述第一和第二轴中的至少一个驱动时结合（直接地或通过中间齿轮）旋转。 推进发动机被布置成用于控制由燃气涡轮发动机和/或用作电动机或发电机的电机供应到第一和第二风扇的组件的扭矩。
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公开(公告)号：US10371049B2
公开(公告)日：2019-08-06
申请号：US14856834
申请日：2015-09-17
Applicant: Airbus Operations S.L.
Inventor： Nicolas Bailey Noval , Raul Llamas Sandin
Abstract: A propulsion engine comprising at least a first propulsion unit including a first fan encased by a geared ring and a gas turbine engine driving a first shaft connected to the first fan, at least a second propulsion unit including a second fan encased by a geared ring connected to a second shaft operatively coupled to an electric machine and at least an electric storage device connected to the electric machine. The geared rings are configured to transmit torque between the fans so that they can rotate in conjunction (directly or through an intermediate gear) when they are driven by at least one of said first and second shafts. The propulsion engine is arranged for controlling the torque to be supplied to the assembly of the first and second fans by the gas turbine engine and/or by the electric machine acting as a motor or as a generator.
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公开(公告)号：US10006361B2
公开(公告)日：2018-06-26
申请号：US14857103
申请日：2015-09-17
Applicant: Airbus Operations S.L.
Inventor： Nicolas Bailey Noval , Raul Llamas Sandin
CPC classification number: F02C3/107 , F02C7/36 , F02K3/06 , F02K3/077 , F05D2220/32 , F05D2260/4031 , F16H1/20
Abstract: A multi-fan engine including a gas turbine engine, a casing and fans encased by geared rings, which connect with the geared rings of an adjacent fan(s) such that the rotation of one fan rotates the other fans. Intermediate gears may prove the connection between adjacent geared rings, wherein the intermediate gears are retracted by linear actuators to disengage the intermediate gears from the geared rings and thereby disengage the fans from each other. The multi-fan engine may be mounted flush to the fuselage of an aircraft invention to capture into the fans boundary layer airflow moving over the skin of the fuselage.
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