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    FLADE fan with different inner and outer airfoil stagger angles at a shroud therebetween
    3.
    发明授权
    FLADE fan with different inner and outer airfoil stagger angles at a shroud therebetween 有权
    FLADE风扇在其间的护罩处具有不同的内部和外部翼型交错角度

    公开(公告)号：US07758303B1

    公开(公告)日：2010-07-20

    申请号：US11496676

    申请日：2006-07-31

    申请人： Aspi Rustom Wadia ,  Alan Glen Turner ,  Aaron Michael Dziech ,  Peter Nicholas Szucs ,  John Jared Decker

    发明人： Aspi Rustom Wadia ,  Alan Glen Turner ,  Aaron Michael Dziech ,  Peter Nicholas Szucs ,  John Jared Decker

    IPC分类号： F01D1/26

    CPC分类号： F01D5/022 ,  F02K3/072 ,  F02K3/077 ,  Y02T50/671 ,  Y02T50/673

    摘要： A FLADE fan assembly includes radially inner and outer airfoils extending radially inwardly and outwardly respectively from an annular shroud circumferentially disposed about a centerline. Inner and outer chords extend between inner and outer leading and trailing edges of inner and outer airfoil cross-sections of the radially inner and outer airfoils respectively. Inner and outer stagger angles between the inner and outer chords respectively at the shroud and the centerline are different. The radially outer airfoils may outnumber the radially inner airfoils and particularly by a ratio in a range of 1.5:1 to about 4:1. Load paths or radii may extend radially through the inner and outer airfoils and through the rotating shroud between the inner and outer airfoils and may pass near or through the inner and outer leading edges and through the inner and outer trailing edges.

    摘要翻译： FLADE风扇组件包括分别从围绕中心线周向设置的环形护罩径向向内和向外延伸的径向内部和外部翼型件。 内部和外部弦杆分别在径向内部和外部翼型的内部和外部翼型截面的内部和外部前缘和后缘之间延伸。 分别在护罩和中心线处的内外弦之间的内外交角是不同的。 径向外部翼型件可以超过径向内部翼型件，特别是在1.5:1至约4:1的范围内的比例。 载荷路径或半径可以径向延伸穿过内部和外部翼型件并且穿过内部和外部翼型之间的旋转护罩，并且可以通过内部和外部前缘附近或穿过内部和外部后缘。

    FLADE FAN WITH DIFFERENT INNER AND OUTER AIRFOIL STAGGER ANGLES AT A SHROUD THEREBETWEEN
    5.
    发明申请
    FLADE FAN WITH DIFFERENT INNER AND OUTER AIRFOIL STAGGER ANGLES AT A SHROUD THEREBETWEEN 有权
    风扇内有不同的内部风扇和外部空气压缩机

    公开(公告)号：US20100180572A1

    公开(公告)日：2010-07-22

    申请号：US11496676

    申请日：2006-07-31

    申请人： Aspi Rustom Wadia ,  Alan Glen Turner ,  Aaron Michael Dziech ,  Peter Nicholas Szucs ,  John Jared Decker

    发明人： Aspi Rustom Wadia ,  Alan Glen Turner ,  Aaron Michael Dziech ,  Peter Nicholas Szucs ,  John Jared Decker

    IPC分类号： F02K3/072 ,  F02C3/00

    CPC分类号： F01D5/022 ,  F02K3/072 ,  F02K3/077 ,  Y02T50/671 ,  Y02T50/673

    摘要： A FLADE fan assembly includes radially inner and outer airfoils extending radially inwardly and outwardly respectively from an annular shroud circumferentially disposed about a centerline. Inner and outer chords extend between inner and outer leading and trailing edges of inner and outer airfoil cross-sections of the radially inner and outer airfoils respectively. Inner and outer stagger angles between the inner and outer chords respectively at the shroud and the centerline are different. The radially outer airfoils may outnumber the radially inner airfoils and particularly by a ratio in a range of 1.5:1 to about 4:1. Load paths or radii may extend radially through the inner and outer airfoils and through the rotating shroud between the inner and outer airfoils and may pass near or through the inner and outer leading edges and through the inner and outer trailing edges.

    摘要翻译： FLADE风扇组件包括分别从围绕中心线周向设置的环形护罩径向向内和向外延伸的径向内部和外部翼型件。 内部和外部弦杆分别在径向内部和外部翼型的内部和外部翼型截面的内部和外部前缘和后缘之间延伸。 分别在护罩和中心线处的内外弦之间的内外交角是不同的。 径向外部翼型件可以超过径向内部翼型件，特别是在1.5:1至约4:1的范围内的比例。 载荷路径或半径可以径向延伸穿过内部和外部翼型件并且穿过内部和外部翼型之间的旋转护罩，并且可以通过内部和外部前缘附近或穿过内部和外部后缘。

    Low solidity turbofan
    6.
    发明授权
    Low solidity turbofan 有权
    低固体涡轮风扇

    公开(公告)号：US07374403B2

    公开(公告)日：2008-05-20

    申请号：US11100752

    申请日：2005-04-07

    申请人： John Jared Decker ,  Peter Nicholas Szucs ,  William Joseph Solomon ,  Virginia Louise Wilson

    发明人： John Jared Decker ,  Peter Nicholas Szucs ,  William Joseph Solomon ,  Virginia Louise Wilson

    IPC分类号： F01D25/24

    CPC分类号： F01D5/141 ,  F02K3/06 ,  F05D2240/30 ,  F05D2250/70 ,  Y02T50/672 ,  Y02T50/673 ,  Y10S416/05

    摘要： A turbofan includes a row of fan blades extending from a supporting disk inside an annular casing. Each blade includes an airfoil having opposite pressure and suction sides extending radially in span between a root and tip and axially in chord between leading and trailing edges. Adjacent airfoils define corresponding flow passages therebetween for pressurizing air. Each airfoil includes stagger increasing between the root and tip, and the flow passage has a mouth between the airfoil leading edge and the suction side of an adjacent airfoil and converges to a throat aft from the mouth. The row includes no more than twenty fan blades having low tip solidity for increasing the width of the passage throat.

    摘要翻译： 涡轮风扇包括一排风扇叶片，其从环形壳体内的支撑盘延伸。 每个叶片包括具有相反的压力和吸力侧的翼型，其在根部和尖端之间的跨度中径向延伸，并且在前缘和后缘之间在弦中轴向延伸。 相邻的翼型件在其间限定相应的流动通道，用于对空气加压。 每个翼型件包括在根部和尖端之间的交错的增加，并且流动通道在翼型件前缘和相邻翼型的吸力侧之间具有嘴部并且会聚到从嘴部后方的喉部。 该行包括不超过二十个具有低尖端固体的风扇叶片，用于增加通道喉部的宽度。

    Methods and apparatus for varying gas turbine engine inlet air flow
    7.
    发明授权
    Methods and apparatus for varying gas turbine engine inlet air flow 有权
    改变燃气涡轮发动机入口气流的方法和装置

    公开(公告)号：US06619916B1

    公开(公告)日：2003-09-16

    申请号：US10086018

    申请日：2002-02-28

    申请人： Joseph Capozzi ,  Ruby Lasandra Zenon ,  Alan Glen Turner ,  Carol Vaczy Wallis ,  Peter Nicholas Szucs

    发明人： Joseph Capozzi ,  Ruby Lasandra Zenon ,  Alan Glen Turner ,  Carol Vaczy Wallis ,  Peter Nicholas Szucs

    IPC分类号： F01D1716

    CPC分类号： F04D29/644 ,  F01D5/148 ,  F01D17/162 ,  F02C7/042 ,  F04D29/563 ,  Y10T29/49323

    摘要： A method for assembling an articulated fan front frame for a gas turbine engine facilitates improving engine performance. The method includes forming a strut including a pair of sidewalls connected at a leading edge and a trailing edge, forming a flap including a first sidewall and a second sidewall connected at a leading edge and a trailing edge, and extending in radial span between a root endwall and a tip endwall, wherein each endwall extends between the first and second sidewalls, and wherein at least one of the root endwall and the tip endwall is contoured in a radial direction extending between the flap leading and trailing edges, and pivotally coupling the flap downstream from the strut such that a gap is defined between the flap and the strut.

    摘要翻译： 用于组装用于燃气涡轮发动机的铰接式风扇前框架的方法有助于提高发动机性能。 该方法包括形成支柱，该支柱包括连接在前缘和后缘处的一对侧壁，形成包括第一侧壁和在前缘和后缘连接的第二侧壁的翼片，并且在径向跨度之间延伸 端壁和末端壁，其中每个端壁在第一和第二侧壁之间延伸，并且其中根端壁和尖端端壁中的至少一个沿着在翼片前缘和后缘之间延伸的径向方向成轮廓，并且枢转地联接翼片 在支柱的下游，使得在翼片和支柱之间限定间隙。

    Methods and apparatus for improving engine operation
    8.
    发明授权
    Methods and apparatus for improving engine operation 有权
    改善发动机运行的方法和装置

    公开(公告)号：US06568909B2

    公开(公告)日：2003-05-27

    申请号：US09964019

    申请日：2001-09-26

    申请人： Peter Nicholas Szucs ,  Gregory Scott McNulty ,  Syed Arif Khalid ,  David William Crall

    发明人： Peter Nicholas Szucs ,  Gregory Scott McNulty ,  Syed Arif Khalid ,  David William Crall

    IPC分类号： F01D520

    CPC分类号： F01D5/20 ,  Y10T29/49336

    摘要： An airfoil for a gas turbine engine includes a leading edge, a trailing edge, a tip plate, a first sidewall, and a second sidewall. The first sidewall extends in radial span between an airfoil root and the tip plate. Furthermore, the first sidewall defines a pressure side of the airfoil. The second sidewall is connected to the first sidewall at the leading and trailing edges, and extends in radial span between the airfoil root and the tip plate. The second sidewall defines a suction side of the airfoil. The tip plate includes at least one groove that extends substantially between the first and second sidewalls.

    摘要翻译： 用于燃气涡轮发动机的翼型件包括前缘，后缘，顶板，第一侧壁和第二侧壁。 第一侧壁在翼型根和尖端板之间沿径向间隔延伸。 此外，第一侧壁限定翼型的压力侧。 第二侧壁在前缘和后缘处连接到第一侧壁，并且在翼型根和尖端板之间以径向跨度延伸。 第二侧壁限定翼型的吸力侧。 顶板包括至少一个在第一和第二侧壁之间大致延伸的凹槽。

    Bifurcated splitter for variable bleed flow
    9.
    发明授权
    Bifurcated splitter for variable bleed flow 有权
    分流式分流器，用于可变流量

    公开(公告)号：US06438941B1

    公开(公告)日：2002-08-27

    申请号：US09843565

    申请日：2001-04-26

    申请人： Dale Bradley Elliott ,  Peter Nicholas Szucs ,  Nicholas Damlis ,  Kenneth Paul Onderko

    发明人： Dale Bradley Elliott ,  Peter Nicholas Szucs ,  Nicholas Damlis ,  Kenneth Paul Onderko

    IPC分类号： F02K302

    CPC分类号： F02C9/18 ,  F01D17/105 ,  F02C6/08 ,  F04D27/023 ,  F04D29/545

    摘要： An air bleed assembly for extracting air from a flowpath in a gas turbine engine includes a casing for surrounding a row of circumferentially spaced apart rotor blades and defining at least in part the flowpath for receiving air compressed by the rotor blades. The casing includes a bleed port disposed downstream of a row of the blades for receiving a portion of the compressed air as bleed airflow and a bleed duct extending away from the bleed port. The bleed duct has an annular slot in the casing. The annular slot has annular slot leading and trailing edges and an annular bifurcated splitter disposed along at least a portion of the annular slot trailing edge. The bifurcated splitter has an annular leading edge forebody located upstream of and separated from an annular splitter wall by an annular return channel. In one embodiment of the invention, the rotor blades are fan blades and the annular bleed space is in the flowpath in a fan section of the engine. The annular bleed space is located between a fan variable vane disposed across the flowpath and one of the fan blades located downstream of the fan variable vane.

    摘要翻译： 用于从燃气涡轮发动机的流路中提取空气的排气组件包括用于围绕一排周向间隔开的转子叶片的壳体，并且至少部分限定用于接收由转子叶片压缩的空气的流路。 壳体包括设置在一排叶片下游的排出口，用于接收一部分压缩空气作为排出气流，以及从排出口延伸的排放管。 排气管在壳体中具有环形槽。 环形槽具有环形槽前缘和后缘以及沿着环形槽后缘的至少一部分设置的环形分叉分流器。 分叉式分流器具有通过环形返回通道位于环形分隔壁上游并与环形分隔壁分离的环形前缘前体。 在本发明的一个实施例中，转子叶片是风扇叶片，并且环形排出空间位于发动机的风扇部分的流路中。 环形排出空间位于跨过流路设置的风扇可变叶片和位于风扇可变叶片下游的风扇叶片之一之间。