公开(公告)号：US20110296813A1

公开(公告)日：2011-12-08

申请号：US12672565

申请日：2008-08-07

申请人： Joel Hudson Frank ,  Norman John James ,  Shunshen Richard Wang ,  Bryant Lynoel Mckleny ,  David A. Baer ,  Stephen Michael Roberts ,  Steven Andrew Wylie ,  Tony Jones ,  John H. Harvey ,  Peter W. Bacon ,  Mark Hubberstey ,  Brett J. Wharton ,  Neil C. Davies

发明人： Joel Hudson Frank ,  Norman John James ,  Shunshen Richard Wang ,  Bryant Lynoel Mckleny ,  David A. Baer ,  Stephen Michael Roberts ,  Steven Andrew Wylie ,  Tony Jones ,  John H. Harvey ,  Peter W. Bacon ,  Mark Hubberstey ,  Brett J. Wharton ,  Neil C. Davies

IPC分类号： F02K1/00

CPC分类号： F02K1/763 ,  F02K1/09 ,  F02K1/30 ,  F02K1/70 ,  F02K1/72 ,  F02K3/06 ,  F05D2250/34 ,  Y10T74/18576 ,  Y10T74/18648

摘要： The exit area of a nozzle assembly is varied by translating a ring assembly located at a rear of the engine nacelle. The ring may be axially translatable along the axis of the engine. As the ring translates, the trailing edge of the ring defines a variable nozzle exit area. Translation of the ring creates an upstream exit at a leading edge of the ring assembly. The upstream exit can be used to bleed or otherwise spill flow excess from the engine bypass duct. As the engine operates in various flight conditions, the ring can be translated to obtain lower fan pressure ratios and thereby increase the efficiency of the engine. Fairings partially enclose actuator components for reduced drag.

摘要翻译： 喷嘴组件的出口区域通过平移位于发动机机舱后部的环组件来改变。 环可以沿着发动机的轴线轴向平移。 当环转动时，环的后缘限定可变的喷嘴出口区域。 环的翻译在环组件的前缘形成上游出口。 上游出口可用于排放或以其他方式溢出来自发动机旁通管道的流量。 当发动机在各种飞行条件下运行时，可以平移环以获得较低的风扇压力比，从而提高发动机的效率。 整流罩部分地包围致动器部件以减少阻力。

公开(公告)号：US09970387B2

公开(公告)日：2018-05-15

申请号：US12672565

申请日：2008-08-07

申请人： Joel Hudson Frank ,  Norman John James ,  Shunshen Richard Wang ,  Bryant Lynoel McKleny ,  David A. Baer ,  Tony Jones ,  John H. Harvey ,  Peter W. Bacon ,  Mark Hubberstey ,  Brett J. Wharton ,  Neil C. Davies ,  Stephen Michael Roberts ,  Steven Andrew Wylie

发明人： Joel Hudson Frank ,  Norman John James ,  Shunshen Richard Wang ,  Bryant Lynoel McKleny ,  David A. Baer ,  Tony Jones ,  John H. Harvey ,  Peter W. Bacon ,  Mark Hubberstey ,  Brett J. Wharton ,  Neil C. Davies ,  Stephen Michael Roberts ,  Steven Andrew Wylie

IPC分类号： F02K1/72 ,  F02K1/76 ,  F02K1/30 ,  F02K3/06 ,  F02K1/09

CPC分类号： F02K1/763 ,  F02K1/09 ,  F02K1/30 ,  F02K1/70 ,  F02K1/72 ,  F02K3/06 ,  F05D2250/34 ,  Y10T74/18576 ,  Y10T74/18648

摘要： The exit area of a nozzle assembly is varied by translating a ring assembly located at a rear of the engine nacelle. The ring may be axially translatable along the axis of the engine. As the ring translates, the trailing edge of the ring defines a variable nozzle exit area. Translation of the ring creates an upstream exit at a leading edge of the ring assembly. The upstream exit can be used to bleed or otherwise spill flow excess from the engine bypass duct. As the engine operates in various flight conditions, the ring can be translated to obtain lower fan pressure ratios and thereby increase the efficiency of the engine. Fairings partially enclose actuator components for reduced drag.