公开(公告)号：US20100180568A1

公开(公告)日：2010-07-22

申请号：US12357530

申请日：2009-01-22

申请人： Humberto W. Sachs

发明人： Humberto W. Sachs

IPC分类号： F02C7/10

CPC分类号： F02K3/06 ,  F02C5/02 ,  F02C7/10 ,  F23R3/28 ,  F23R3/42 ,  F23R3/50

摘要： The invention adds details and alternate design supplementing the concept established with my patent application Ser. No. 12/013,431, Aircraft Propulsion System (APS). The APS ultimate fuel economy objectives requires long term design development, and this invention compromises some fuel economy for the expediency of short term implementation of a heat regeneration for turbofans via the re-arrangement of existing components and a few unique items readily designed. While this Velarus Propulsion (VPx) attains only 42% fuel economy, it retains the original APS fundamental architecture implementing heat regeneration for a turbofan engine, as well as the additional benefits of noise and emission abatement. This invention consists of the three APS technologies as follows: a) A novel arrangement of the power generation core features the turbine exhaust entering directly into the thrust chamber, thus providing heat regeneration with an appropriate configuration of the thrust chamber. b) The design of a modified combustor introduces the concept of a supersonic nozzle driving the turbines which allows for greater combustor's chamber temperature while injecting the gases at temperatures acceptable to current turbine blade metallurgy. This feature increases the engine thermal efficiency. c) The hub design allows for two options, a simpler fixed fanblade design or an advanced controllable pitch fan blade, increasing the mission and performance flexibility of a given turbofan size. In addition, this invention adds functionality to the aft cone, such as debris purge, accessories installation, and thrust reversers free from hot gases.

摘要翻译： 本发明增加了与我的专利申请Ser。建立的概念的细节和替代设计。 飞机推进系统（APS）第12 / 013,431号。 APS的最终燃油经济性目标需要长期的设计开发，本发明通过重新安排现有组件和容易设计的几个独特项目，有利于短期实施涡轮风扇热再生的方便性。 虽然这种Velarus推进（VPx）的燃油经济性只有42％，但它保留了对涡轮风扇发动机实施热再生的原始APS基本架构，以及噪声和减排的附加益处。 本发明由以下三种APS技术组成：a）发电核心的新颖布置使得涡轮机排气直接进入推力室，从而提供具有推力室适当构型的热再生。 b）改进的燃烧器的设计引入驱动涡轮机的超音速喷嘴的概念，其允许在当前涡轮机叶片冶金的可接受温度下喷射气体时允许更大的燃烧器室温度。 该特征提高了发动机的热效率。 c）轮毂设计允许两个选项，一个更简单的固定风扇叶片设计或先进的可控俯仰风扇叶片，增加给定涡轮风扇尺寸的任务和性能灵活性。 另外，本发明增加了后锥的功能，例如碎屑吹扫，附件安装以及没有热气体的推力反向器。

公开(公告)号：US20090178386A1

公开(公告)日：2009-07-16

申请号：US12013431

申请日：2008-01-12

申请人： Humberto W. Sachs

发明人： Humberto W. Sachs

IPC分类号： F02K3/02

CPC分类号： F02K3/068 ,  F02C3/165 ,  F02K3/06 ,  F05D2250/25 ,  F05D2250/314 ,  F05D2250/51 ,  F05D2250/52 ,  Y02T50/671

摘要： The invention is a novel aircraft propulsion system architecture that delivers thrust at minimum fuel consumption rates with the side benefits of noise and pollution emission abatement. The invention implements three technologies: a. Unique turbine nozzle design allowing for a cooling cycle, thus increasing its thermal efficiency. b. Specific jet-drive design propelling the fan blades allowing for power amplification. At any given shaft velocity, the output torque of a machine is proportional to shaft power. Jet-driven torque is insensitive to velocity. For nozzle velocities greater than 550 fps, there is power amplification (et propulsion principle). c. Specific exhaust and waste heat regeneration design increasing the fanjet thrust with no additional fuel consumption. This aircraft propulsion system invention is henceforth called APS.

摘要翻译： 本发明是一种新颖的飞机推进系统架构，其以最小的燃料消耗率提供推力，具有噪声和污染物排放减少的副作用。 本发明实现三种技术：a。 独特的涡轮喷嘴设计允许冷却循环，从而提高其热效率。 b。 特定的喷射驱动设计推动了风扇叶片，从而实现功率放大。 在任何给定的轴速度下，机器的输出扭矩与轴功率成比例。 喷射驱动扭矩对速度不敏感。 对于大于550fps的喷嘴速度，存在功率放大（et推进原理）。 C。 具体的排气和废热再生设计增加了风扇喷气推力，无需额外的燃油消耗。 这种飞机推进系统的发明从此称为APS。