公开(公告)号：US20030146344A1

公开(公告)日：2003-08-07

申请号：US10341386

申请日：2003-01-14

Applicant: NATIONAL AEROSPACE LABORATORY OF JAPAN

Inventor： Yoshio Saito ,  Masanori Endo ,  Yukio Matsuda ,  Nanahisa Sugiyama ,  Takeshi Tagashira

IPC: B64D027/00

CPC classification number: F02K3/12 ,  F02C3/10 ,  F02C3/13 ,  F02C6/08 ,  F02K3/00 ,  F02K3/075 ,  F02K3/077

Abstract: This invention provides a multi-fan system separated core engine type turbofan engine in which high pressure air is used as the working fluid for a turbine which drives a fan, thereby reducing the manufacturing costs of the turbofan engine and simplifying the constitution thereof. A turbine for driving a fan 11 which is provided in a propulsion device 3 of the multi-fan system separated core engine type turbofan engine 1 is an air turbine 13 which is driven by the supply through a duct 9 of a part of high pressure air compressed in a compressor 5 of a core engine 2. Since the working fluid of the air turbine 13 for driving the fan 11 is not high temperature combustion gas, there is no need to use expensive heat-resistant material for the turbine, and thus the propulsion device 3 can be manufactured at low cost, the constitution thereof can be simplified, and operational control can be ameliorated.

Abstract translation: 本发明提供了一种多风扇系统分离式核心发动机型涡扇发动机，其中使用高压空气作为驱动风扇的涡轮机的工作流体，从而降低涡轮风扇发动机的制造成本并简化其结构。 用于驱动设置在多风扇系统分离的核心发动机型涡扇发动机1的推进装置3中的风扇11的涡轮机是由供应通过高压空气的一部分的管道9驱动的空气涡轮机13 在核心发动机2的压缩机5中被压缩。由于用于驱动风扇11的空气涡轮13的工作流体不是高温燃烧气体，因此不需要使用昂贵的用于涡轮机的耐热材料，因此， 推进装置3能够以低成本制造，其结构可以简化，并且可以改善操作控制。

公开(公告)号：US20030185680A1

公开(公告)日：2003-10-02

申请号：US10401669

申请日：2003-03-31

Applicant: NATIONAL AEROSPACE LABORATORY OF JAPAN

Inventor： Yoshio Saito

IPC: F03B001/00

CPC classification number: F02K3/068 ,  F01D1/12 ,  F01D5/022 ,  F01D15/08 ,  F02C3/045

Abstract: This invention provides a single cascade multistage turbine that has a compact turbine structure having only a single cascade, and enables power to be extracted efficiently in the same way as a multistage turbine having multistage rotor vanes. The working fluid supplied through the supply duct 3 flows on one side of the single cascade of rotor vanes 2 to one part of the circumference direction of the rotor vanes 2, and after passing through the rotor vanes 2 it passes through the circulation ducts 4a and 4b and returns to the former side of the rotor vanes 2. The circulation ducts 4a and 4b consist of exhaust duct members 6a and 6b, return duct members 7a and 7b, and inflow duct members 8a and 8b. Using the circulation ducts 4a and 4b this circulation process is repeated at least once whereby the working fluid is again passed through the rotor vanes 2 at a slightly different position in the circumferential direction of the rotor vanes 2. Each time the working fluid is passed through the rotor vanes 2, the energy contained in the fluid can be efficiently extracted as torque of the rotor vanes 2.

Abstract translation: 本发明提供了具有仅具有单个级联的紧凑型涡轮机结构的单级联多级涡轮机，并且能够以与具有多级转子叶片的多级涡轮机相同的方式有效地提取功率。 通过供给管道3供给的工作流体在转子叶片2的一个级联的一侧流动到转子叶片2的圆周方向的一部分，并且在通过转子叶片2之后，它通过循环管道4a和 4b并返回到转子叶片2的前一侧。循环管道4a和4b由排气管道构件6a和6b，返回管道构件7a和7b以及流入管道构件8a和8b组成。 使用循环管道4a和4b，该循环过程重复至少一次，从而工作流体在转子叶片2的圆周方向上稍微不同的位置再次通过转子叶片2.每次工作流体通过 转子叶片2能够有效地提取包含在流体中的能量作为转子叶片2的转矩。

公开(公告)号：US20030131585A1

公开(公告)日：2003-07-17

申请号：US10341390

申请日：2003-01-14

Applicant: NATIONAL AEROSPACE LABORATORY OF JAPAN

Inventor： Yoshio Saito ,  Masanori Endo ,  Yukio Matsuda ,  Nanahisa Sugiyama ,  Takeshi Tagashira

IPC: F02K003/02

CPC classification number: F02K3/077 ,  F02C1/02 ,  F02C3/10 ,  F02C3/13 ,  F02C3/14 ,  F02C6/08 ,  F02K3/075 ,  F02K3/11 ,  F02K3/12

Abstract: A low-noise separated core engine type turbofan engine is provided in which noise generated by a control propulsion device is reduced by using high pressure air as the working fluid of a turbine for driving a control fan used in the attitude control of the airframe. A control fan 17 of a separated core engine type turbofan engine 1, which is comprised in a control propulsion device 4 provided for attitude control of the aircraft, is driven by an air turbine 19 which uses as working fluid high pressure air compressed by a compressor 6 of the core engine 2 and supplied through a duct 10. The speed of the working fluid which is discharged from the control fan 17 and air turbine 19 is sufficiently low for attitude control and not as high as the speed of the working fluid which is discharged from a propulsion device 3 which is provided for thrust, and thus noise generated by the control propulsion device 4 can be reduced.

Abstract translation: 提供了一种低噪声分离式核心发动机型涡扇发动机，其中通过使用高压空气作为用于驾驶用于机身姿态控制的控制风扇的涡轮机的工作流体来减少由控制推进装置产生的噪声。 分离的核心发动机型涡扇发动机1的控制风扇17包括在用于飞行器的姿态控制的控制推进装置4中，由空气涡轮机19驱动，空气涡轮机19使用作为工作流体的压缩空气，压缩机 并且通过管道10供给。从控制风扇17和空气涡轮19排出的工作流体的速度对于姿态控制而言足够低，而不是工作流体的速度高 从用于推力的推进装置3排出，从而可以减少由控制推进装置4产生的噪音。