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98 条记录 (耗时 0.012 秒)

    Divergent chevron nozzle and method
    11.
    发明申请
    Divergent chevron nozzle and method 审中-公开
    发散的V形喷嘴和方法

    公开(公告)号：US20040244357A1

    公开(公告)日：2004-12-09

    申请号：US10454888

    申请日：2003-06-05

    发明人： Mark L. Sloan

    IPC分类号： F02K001/38

    CPC分类号： F02K1/38 ,  F02K1/386 ,  F02K1/40

    摘要： A convergent/divergent chevron flow nozzle for use with a jet engine. The flow nozzle includes a converging portion that terminates at a throat portion. Extending from the throat portion is a plurality of chevrons spaced apart by ventilation areas. The chevrons diverge from the nozzle exit flow direction of the flow nozzle. The diverging chevrons serve to increase the thrust produced by a jet engine associated with the flow nozzle during and reduce shock related noise at cruise conditions. The ventilation areas prevent over-expansion of the nozzle flow at takeoff and resulting shock related noise from the plume, and increases plume mixing to reduce jet exhaust noise during takeoff without negatively affecting the thrust generated by the exhaust flow. The flow nozzle can be implemented at both the fan nozzle and exhaust nozzle areas of a dual flow jet engine.

    摘要翻译： 用于喷气发动机的会聚/发散的人字形流动喷嘴。 流动喷嘴包括终止于喉部的会聚部分。 从喉部延伸的是通过通风区间隔开的多个人字形。 人字纹从流动喷嘴的喷嘴出口流动方向发散。 发散的人字形用于增加与流动喷嘴相关联的喷气发动机产生的推力，并减少巡航条件下的冲击相关噪声。 通风区域可防止起飞时喷嘴流量的过度膨胀，并引起来自羽流的冲击相关噪声，并增加羽流混合，以减少起飞时的喷气排放噪声，而不会对排气流产生的推力产生不利影响。 流动喷嘴可以在双流喷气发动机的风扇喷嘴和排气喷嘴区域两者上实现。

    Jet engine noise suppressor
    12.
    发明授权
    Jet engine noise suppressor 失效
    喷气发动机噪声抑制器

    公开(公告)号：US3934675A

    公开(公告)日：1976-01-27

    申请号：US471476

    申请日：1974-05-20

    申请人： William P. Lear

    发明人： William P. Lear

    IPC分类号： F02K1/38 ,  F02K1/46 ,  F02K1/26

    CPC分类号： F02K1/386 ,  F02K1/38 ,  F02K1/46 ,  Y02T50/671

    摘要： The sound suppressor hereof significantly reduces the operational noise of jet engines, particularly on takeoff and approach of jet aircraft. The system hereof is simple, effective, and relatively low in cost. It adds relatively little weight to the engine assembly, and absorbs negligible power. The suppressor comprises convolutions of sheet metal that surround the exhaust nozzle, and direct cool air to the outer periphery of the engine exhaust gases. The result is a reduction of jet engine noise sufficient to meet the Federal Air Regulations Standards as currently established by the FAA. The suppressor is particularly advantageous for business-type executive jet aircraft.

    摘要翻译： 这种声压抑制器显着降低了喷气发动机的运行噪音，特别是在起飞和喷气式飞机方面。 其系统简单，有效，成本相对较低。 它对发动机组件的重量相对较小，并且吸收可忽略的功率。 抑制器包括围绕排气喷嘴的金属板卷绕体，并且将冷却空气直接引导到发动机废气的外周。 结果是减少了喷气发动机的噪音，足以符合FAA目前建立的联邦空气法规标准。 抑制器对于商务型行政喷气式飞机特别有利。

    Gas turbine exhaust nozzle
    13.
    发明授权
    Gas turbine exhaust nozzle 失效
    气体涡轮排气喷嘴

    公开(公告)号：US3780827A

    公开(公告)日：1973-12-25

    申请号：US3780827D

    申请日：1972-12-19

    申请人： NASA

    发明人： STRAIGHT D

    IPC分类号： F02K1/38 ,  F01N

    CPC分类号： F02K1/38 ,  Y02T50/671

    摘要： An elongated hollow string is disposed in an exhaust nozzle combustion chamber and communicates with a source of air through hollow struts at one end. The other end of the string is bellmouth shaped and extends over the front portion of a nozzle plug. The bell-mouth may be formed by pivotally mounted flaps or leaves which are used to vary the exhaust throat area and the area between the plug and the leaves. Air from the engine inlet flows into the sting and also between the combustion chamber and a housing disposed around the chamber. The sting air cools the plug and serves as a low velocity inner core of secondary gas to provide noise reduction for the primary exhaust gas while the other air, when it exits from the nozzle, forms an outer low velocity layer to further reduce noise. The structure produces increased thrust in a turbojet or turbofan engine.

    摘要翻译： 细长的中空线条设置在排气喷嘴燃烧室中，并且在一端通过中空支柱与空气源连通。 弦的另一端是喇叭形的并且在喷嘴塞的前部延伸。 喇叭口可以由用于改变排气喉部区域和塞子和叶子之间的区域的枢转安装的翼片或叶片形成。 来自发动机入口的空气流入燃烧室和设置在室周围的壳体之间。 刺激空气冷却塞子并用作二次气体的低速内芯，以为主废气提供降噪，而当其它空气从喷嘴出来时形成外部低速层以进一步降低噪声。 该结构在涡轮喷气发动机或涡轮风扇发动机中产生增加的推力。

    Aircraft propulsion system exhaust nozzle with ejector passage(s)
    18.
    发明授权
    Aircraft propulsion system exhaust nozzle with ejector passage(s) 有权

    公开(公告)号：US11754018B2

    公开(公告)日：2023-09-12

    申请号：US17554695

    申请日：2021-12-17

    申请人： Rohr, Inc.

    发明人： Timothy Gormley

    IPC分类号： F02K1/12 ,  F02K1/36 ,  F02K1/38 ,  F02K1/46 ,  F02K1/15

    CPC分类号： F02K1/1215 ,  F02K1/123 ,  F02K1/36 ,  F02K1/38 ,  F02K1/46 ,  F02K1/15 ,  F05D2250/323 ,  F05D2250/324 ,  F05D2260/56

    摘要： An apparatus is provided for an aircraft propulsion system. This apparatus includes an exhaust nozzle. The exhaust nozzle includes a flowpath, a passage, an outer door, an inner door and an actuator configured to move the outer door and the inner door between an open arrangement and a closed arrangement. The flowpath extends axially along a centerline through the exhaust nozzle. The passage extends laterally into the exhaust nozzle to the flowpath when the outer door and the inner door are in the open arrangement. The outer door is configured to pivot inwards towards the centerline when the outer door moves from the closed arrangement to the open arrangement. The inner door is configured to pivot outwards away from the centerline when the inner door moves from the closed arrangement to the open arrangement.