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    • 9. 发明授权
    • Core reflex nozzle for turbofan engine
    • 涡扇发动机的核心反射喷嘴
    • US08002520B2
    • 2011-08-23
    • US12159517
    • 2007-01-17
    • Stacie M. DawsonRichard Wiley
    • Stacie M. DawsonRichard Wiley
    • F01D25/00F04D31/00F04D29/00
    • F02K1/386F02K3/06
    • A turbofan engine is provided that includes a core nacelle at least partially surrounded by a fan nacelle. The core nacelle includes a reflex nozzle providing a core exit. The core nacelle includes a contour on its exterior surface upstream from the reflex nozzle. The contour is generally conical and tapers toward the core exit at a first slope. The reflex nozzle tapers toward the exit at a second slope that is less steep than the first slope. The reflex nozzle includes a generally linear portion. In one example, the reflex nozzle is provided by a generally cylindrical extension that sufficiently turns the bypass flow away from the core exit so that the core flow does not become choked.
    • 提供了一种涡轮风扇发动机,其包括至少部分地被风扇机舱包围的核心机舱。 核心机舱包括提供核心出口的反射喷嘴。 核心机舱在其反射喷嘴上游的外表面上包括轮廓。 轮廓通常是圆锥形的,并且在第一斜坡处朝向芯出口逐渐变细。 反射喷嘴在比第一斜坡不太陡的第二斜坡处朝向出口逐渐变细。 反射喷嘴包括大致线性的部分。 在一个示例中,反射喷嘴由大致圆柱形的延伸部提供,其充分地将旁路流动离开核心出口,使得芯流不被阻塞。
    • 10. 发明申请
    • CORE REFLEX NOZZLE FOR TURBOFAN ENGINE
    • 用于涡轮发动机的核心反射喷嘴
    • US20100221102A1
    • 2010-09-02
    • US12159517
    • 2007-01-17
    • Stacie M. DawsonRichard Wiley
    • Stacie M. DawsonRichard Wiley
    • F01B25/00
    • F02K1/386F02K3/06
    • A turbofan engine is provided that includes a core nacelle at least partially surrounded by a fan nacelle. The core nacelle includes a reflex nozzle providing a core exit. The core nacelle includes a contour on its exterior surface upstream from the reflex nozzle. The contour is generally conical and tapers toward the core exit at a first slope. The reflex nozzle tapers toward the exit at a second slope that is less steep than the first slope. The reflex nozzle includes a generally linear portion. In one example, the reflex nozzle is provided by a generally cylindrical extension that sufficiently turns the bypass flow away from the core exit so that the core flow does not become choked.
    • 提供了一种涡轮风扇发动机,其包括至少部分地被风扇机舱包围的核心机舱。 核心机舱包括提供核心出口的反射喷嘴。 核心机舱在其反射喷嘴上游的外表面上包括轮廓。 轮廓通常是圆锥形的,并且在第一斜坡处朝向芯出口逐渐变细。 反射喷嘴在比第一斜坡不太陡的第二斜坡处朝向出口逐渐变细。 反射喷嘴包括大致线性的部分。 在一个示例中,反射喷嘴由大致圆柱形的延伸部提供,其充分地将旁路流动离开核心出口,使得芯流不被阻塞。