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    • 1. 发明授权
    • Turbofan jet engine
    • Turbofan喷气发动机
    • US07887287B2
    • 2011-02-15
    • US11902564
    • 2007-09-24
    • Ryoji YanagiHisao FutamuraHitoshi Fujiwara
    • Ryoji YanagiHisao FutamuraHitoshi Fujiwara
    • F02K3/02
    • F02K3/065B64D27/18B64D33/02B64D33/04B64D2033/026F02K3/075F02K3/077Y02T50/44Y02T50/671
    • To provide a turbofan jet engine for a supersonic aircraft, which enables a supersonic cruise with small additional drag due to engine installation while minimizing the jet noise at takeoff. In the turbofan jet engine, two fans, i.e., a front fan and an aft fan, are disposed, and an air inlet and an air outlet are provided on each of the front and aft fans, whereby at takeoff, air is introduced to each of the air inlets of the front and aft fans to drive the front and aft fans in parallel, and the air is then ejected from each of the outlets. On the other hand, during a supersonic cruise, an inlet of an aft fan duct is coupled to an outlet of a front fan duct, where external air is introduced only to an air inlet of the front fan duct and the air compressed through the front fan is fed to the aft fan duct and further compressed through the aft fan, and ejected from a nozzle, so that the front and aft fans are driven in series.
    • 为超音速飞机提供涡轮风扇喷气发动机,由于发动机安装,能够实现超短距离巡航,同时使起飞时的喷气噪声最小化。 在涡轮风扇喷气发动机中,设置有两个风扇,即前风扇和后风扇,并且在前风扇和后风扇中的每一个上设置有空气入口和空气出口,由此在起飞时,空气被引入到每个 的前风扇和后风扇的进气口并联驱动前后风扇,然后从每个出口排出空气。 另一方面,在超音速巡航期间,后风扇通道的入口连接到前风扇通道的出口,其中外部空气仅被引入前风扇通道的空气入口,并且通过前部压缩的空气 风扇被送入后风扇风管,并通过后风扇进一步压缩,并从喷嘴喷出,使得前后风扇被串联驱动。
    • 2. 发明授权
    • High bypass-ratio turbofan jet engine
    • 高旁通比涡轮风扇喷气发动机
    • US07921637B2
    • 2011-04-12
    • US12392203
    • 2009-02-25
    • Ryoji YanagiHitoshi Fujiwara
    • Ryoji YanagiHitoshi Fujiwara
    • F02K3/02
    • F02K3/065B64C7/02B64D29/02F02C7/04F05D2250/14Y02T50/671
    • To provide a turbofan jet engine which is capable of increasing the bypass ratio without increasing the fan diameter, and of reducing air resistance acting on the engine, a front fan duct that discharges air compressed by a front fan to the atmosphere and an aft fan duct that introduces air into an aft fan are disposed such as to change cross-sectional shapes thereof by rotating around a core engine in a counterclockwise direction, so that the cross-sectional geometric relationship between the front fan duct and the aft fan duct at a position immediately posterior to the front fan and a cross-sectional geometric relationship between the front fan duct and the aft fan duct at a position immediately anterior to the aft fan are inverted.
    • 为了提供一种涡轮风扇喷气发动机,其能够在不增加风扇直径的同时增加旁路比,并且降低作用在发动机上的空气阻力,将由前风扇压缩的空气排出到大气的前风扇管道和向后排出的风扇导管 将空气引入后风扇的方式设置成通过围绕核心发动机沿逆时针方向旋转来改变其横截面形状,使得前风扇管道和后风扇管道在位置处的横截面几何关系 紧靠前风扇的后方,在风扇前方的前方风扇管道与后风扇管道之间的横截面几何关系被反转。
    • 3. 发明申请
    • Turbofan jet engine
    • Turbofan喷气发动机
    • US20080075580A1
    • 2008-03-27
    • US11902564
    • 2007-09-24
    • Ryoji YanagiHisao FutamuraHitoshi Fujiwara
    • Ryoji YanagiHisao FutamuraHitoshi Fujiwara
    • F01N1/00
    • F02K3/065B64D27/18B64D33/02B64D33/04B64D2033/026F02K3/075F02K3/077Y02T50/44Y02T50/671
    • To provide a turbofan jet engine for a supersonic aircraft, which enables a supersonic cruise with small additional drag due to engine installation while minimizing the jet noise at takeoff. In the turbofan jet engine, two fans, i.e., a front fan and an aft fan, are disposed, and an air inlet and an air outlet are provided on each of the front and aft fans, whereby at takeoff, air is introduced to each of the air inlets of the front and aft fans to drive the front and aft fans in parallel, and the air is then ejected from each of the outlets. On the other hand, during a supersonic cruise, an inlet of an aft fan duct is coupled to an outlet of a front fan duct, where external air is introduced only to an air inlet of the front fan duct and the air compressed through the front fan is fed to the aft fan duct and further compressed through the aft fan, and ejected from a nozzle, so that the front and aft fans are driven in series.
    • 为超音速飞机提供涡轮风扇喷气发动机,由于发动机安装,能够实现超短距离巡航,同时使起飞时的喷气噪声最小化。 在涡轮风扇喷气发动机中,设置有两个风扇,即前风扇和后风扇,并且在前风扇和后风扇中的每一个上设置有空气入口和空气出口,由此在起飞时,空气被引入到每个 的前风扇和后风扇的进气口并联驱动前后风扇,然后从每个出口排出空气。 另一方面,在超音速巡航期间,后风扇通道的入口连接到前风扇通道的出口,其中外部空气仅被引入前风扇通道的空气入口,并且通过前部压缩的空气 风扇被送入后风扇风管,并通过后风扇进一步压缩,并从喷嘴喷出,使得前后风扇被串联驱动。
    • 4. 发明申请
    • HIGH BYPASS-RATIO TURBOFAN JET ENGINE
    • 高比例涡轮喷气式发动机
    • US20090226297A1
    • 2009-09-10
    • US12392203
    • 2009-02-25
    • Ryoji YanagiHitoshi Fujiwara
    • Ryoji YanagiHitoshi Fujiwara
    • F01D25/24
    • F02K3/065B64C7/02B64D29/02F02C7/04F05D2250/14Y02T50/671
    • To provide a turbofan jet engine which is capable of increasing the bypass ratio without increasing the fan diameter, and of reducing air resistance acting on the engine, a front fan duct that discharges air compressed by a front fan to the atmosphere and an aft fan duct that introduces air into an aft fan are disposed such as to change cross-sectional shapes thereof by rotating around a core engine in a counterclockwise direction, so that the cross-sectional geometric relationship between the front fan duct and the aft fan duct at a position immediately posterior to the front fan and a cross-sectional geometric relationship between the front fan duct and the aft fan duct at a position immediately anterior to the aft fan are inverted.
    • 为了提供一种涡轮风扇喷气发动机,其能够在不增加风扇直径的同时增加旁路比,并且降低作用在发动机上的空气阻力,将由前风扇压缩的空气排出到大气的前风扇管道和向后排出的风扇导管 将空气引入后风扇的方式设置成通过围绕核心发动机沿逆时针方向旋转来改变其横截面形状,使得前风扇管道和后风扇管道在位置处的横截面几何关系 紧靠前风扇的后方,在风扇前方的前方风扇管道与后风扇管道之间的截面几何关系被反转。