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    • 3. 发明申请
    • Multi-component two-phase power cycle
    • 多组分两相电源循环
    • US20120006024A1
    • 2012-01-12
    • US12803911
    • 2010-07-09
    • Lance G. HaysPhillip R. Welch
    • Lance G. HaysPhillip R. Welch
    • F01K25/08F22D11/02
    • F01K25/065F01D1/06F05D2210/13
    • A multi-component apparatus characterized as performing a two-phase thermodynamic cycle, for conversion of heat energy to useful power comprises: fluid means consisting to two or more chemical components to absorb heat energy, the fluid means providing an increasing temperature and increasing fraction of gas phase as increasing amounts of heat are absorbed, expander means operating to convert the enthalpy in a received mixture of gas and liquid, formed in said fluid means, as a result of the said heat energy absorbed by the fluid means, to mechanical, shaft power, heat exchanger means operating to transfer the heat energy to be absorbed by the fluid means, condenser means operating to reject the unconverted enthalpy, by the expander means, in the fluid means, thereby condensing any gas to convert the fluid means to liquid, and pump means operating to pressurize liquid fluid means leaving the condenser means, in order to return the fluid means to the heat exchanger means, closing the thermodynamic cycle.
    • 特征在于执行用于将热能转换为有用功率的两相热力学循环的多组分装置包括:由两个或更多个化学组分组成以吸收热能的流体装置,所述流体装置提供增加的温度和增加的分数 吸收增加热量的气相,膨胀器意味着将由所述流体装置吸收的所述热能形成在所述流体装置中的所接收的气体和液体混合物中的焓转换成机械轴 动力,热交换器装置,其操作以传递被流体装置吸收的热能,冷凝器装置通过膨胀器装置在流体装置中操作以排除未转换的焓,从而冷凝任何气体以将流体装置转换成液体, 以及泵装置,用于对离开冷凝器装置的液体流体装置进行加压,以便将流体装置返回到热交换器装置,关闭第 erm动周期。
    • 6. 发明授权
    • Jet diffuser usable as a propeller shroud
    • US3230702A
    • 1966-01-25
    • US38537264
    • 1964-07-27
    • BERTIN & CIE
    • MARIE SOULEZ-LARIVIERE JEAN PAHENRI BERTIN JEAN
    • B22D33/00B64C11/00B64C23/00B64C29/00F02K1/28F02K1/36F16C17/10F16F9/06F16F9/32F16F9/34F16F9/348F22D11/02
    • F22D11/02B22D33/00B64C11/001B64C23/005B64C29/0016F02K1/28F02K1/36F16F9/06F16F9/3214F16F9/3415F16F9/3482Y02T50/672
    • 948,067. Propelling and lifting aircraft; wind tunnels; screw propellers. SOC. BERTIN & CIE. Oct. 14, 1960 [Oct. 16, 1959], No. 35343/60. Headings B7G, B7V and B7W. [Also in Divisions F1, F2 and F4] A diffuser, which may be incorporated in an aircraft lifting jet system, a ducted screw propeller, or a wind tunnel, comprises a portion of progressively increasing divergence bounded by a solid wall, the longitudinal section of which is of progressively increasing curvature going downstream, the downstream end of the portion having boundary layer control means whereby the marginal layers of the flow are maintained in contact with the wall while being accelerated by the increasing divergence, these layers being then slowed down and recompressed. In Fig. 1, the exhaust from a gas turbine engine nozzle 3 induces air flow through a vertical duct comprising a convergent portion 4 and divergent portion 5, to produce a lifting force on an aircraft. The radially outer parts of the flow are stated to have a higher velocity and lower pressure than the inner part, as a result of the divergence of portion 5, and to correct this, the end portion 6 of portion 5 has a high curvature, and a fluid screen shown by arrows f is ejected from a slot nozzle 9 leading from a manifold 7 fed from the gas turbine compressor 1, and thus prevents flow breakaway. Further annular guide vanes 10, 11 are provided, the former being solid, and the latter hollow, and receiving air from manifold 7 and discharging through a slot nozzle 12. In Fig. 2, a propeller 14 is situated at the throat of a convergent-divergent duct. Again, the outlet end of the divergent section has a high curvature, and boundary layer suction is applied at a slot 22 to prevent detachment of the airflow from the duct wall and to ensure diffusion of the radially outer part of the flow. Annular guide vanes 18, 19, 20, 21 define diverging annular channels, and may be extended upstream as shown for vanes 19 and 21. The outermost part of each propeller blade may have an increased angle of incidence. Further, the different parts of the blades which deliver air to the respective channels between vanes 18 ... 21 may have different angles of incidence. In a modification, Fig. 2a (not shown), boundary layer suction is replaced by boundary layer blowing over the inner wall of the duct and over the propeller hub. In this embodiment, the propeller blades extend radially outwardly and upstream from the hub. Struts supporting and upstream of the propeller hub impart a rotation to the flow, which is cancelled by the propeller blades. In Fig. 3, a propeller 25 is located within an annular wing of which the lower part 27 has a cross-section larger than that of the upper part 28, the whole forming a convergent-divergent duct. The rear part 27a is rounded, and a slot 29 extends round the lower half of the outer surface of the wing. The slot has a rounded leading edge 30, and a thin trailing edge 31, and air is blown through the slot to prevent separation of the airflow through the duct, and to increase the vertical component of the flow out of the duct to increase the lift. The wing and propeller are tiltable on the aircraft to vary the lifting and propulsive thrust components. Specifications 847,500 and 877,766 are referred to.