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    FAN BY-PASS DUCT FOR INTERCOOLED TURBO FAN ENGINES
    24.
    发明申请
    FAN BY-PASS DUCT FOR INTERCOOLED TURBO FAN ENGINES 审中-公开
    风扇旁路导管用于混合涡轮风扇发动机

    公开(公告)号：US20160222886A1

    公开(公告)日：2016-08-04

    申请号：US14709826

    申请日：2015-05-12

    申请人： Rolls-Royce North American Technologies, Inc.

    发明人： Bradford J. Riehle ,  James C. Loebig

    IPC分类号： F02C7/143 ,  F02K3/02 ,  F02C7/18 ,  F02K3/105

    CPC分类号： F02C7/143 ,  F02C7/18 ,  F02K3/02 ,  F02K3/077 ,  F02K3/105 ,  F02K3/115 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2260/204 ,  F05D2260/211 ,  F05D2260/213 ,  Y02T50/676

    摘要： An improved system, apparatus and method for intercooling a turbo fan engine, and more specifically, a system for intercooling a turbo fan engine employing a secondary bypass duct that minimizes pressure losses. The secondary bypass duct is radially inwardly disposed from a fan bypass duct and receives fan bypass air through an inlet. The portion of fan bypass air flows through one or more microchannel or minichannel heat exchangers. The secondary bypass duct has an outlet in communication with the bypass air stream downstream of the throat of a fan bypass nozzle. The secondary bypass air is accelerated at the exit to create thrust.

    摘要翻译： 一种用于中间冷却涡轮风扇发动机的改进的系统，装置和方法，更具体地说，一种用于使使用最小化压力损失的次级旁通管道的涡轮风扇发动机中间冷却的系统。 次级旁通管道从风扇旁路管径向向内设置，并通过入口接收风扇旁路空气。 风扇旁路空气的一部分流过一个或多个微通道或微通道热交换器。 次级旁通管道具有与风扇旁路喷嘴的喉部下游的旁路空气流连通的出口。 次级旁路空气在出口加速以产生推力。

    Gas Turbine Engine with Variable Overall Pressure Ratio
    25.
    发明申请
    Gas Turbine Engine with Variable Overall Pressure Ratio 有权
    具有可变总压力比的燃气轮机发动机

    公开(公告)号：US20130145769A1

    公开(公告)日：2013-06-13

    申请号：US13316058

    申请日：2011-12-09

    申请人： James W. Norris ,  Daniel B. Kupratis ,  Gary M. Stetson

    发明人： James W. Norris ,  Daniel B. Kupratis ,  Gary M. Stetson

    IPC分类号： F02C3/06 ,  F02C7/00

    CPC分类号： F02C7/36 ,  F02C3/145 ,  F02C7/32 ,  F02K3/105 ,  F05D2220/76 ,  F05D2260/4023 ,  F05D2260/96

    摘要： A gas turbine engine has a variable overall pressure rate (“OPR”). The engine includes a high pressure compressor having at least a primary stage having a set of primary rotors and a secondary stage having a set of secondary rotors. A clutch is provided to selectively engage the secondary rotors with the primary rotors. Engagement of the clutch may be controlled based on the vehicle travel mode, such as disengaging during a takeoff mode to reduce turbine entry temperature and engaging during a loiter mode to increase OPR.

    摘要翻译： 燃气涡轮发动机具有可变的总压力（“OPR”）。 发动机包括具有至少一个初级级的高压压缩机，该初级级具有一组初级转子和具有一组次级转子的次级级。 提供离合器以选择性地将副转子与主转子接合。 可以基于车辆行驶模式来控制离合器的接合，例如在起飞模式期间分离以降低涡轮进入温度并且在升降机模式期间接合以增加OPR。

    Turbomachine with low noise emissions for aircraft
    27.
    发明授权
    Turbomachine with low noise emissions for aircraft 有权
    涡轮机，飞机低噪音排放

    公开(公告)号：US07237378B2

    公开(公告)日：2007-07-03

    申请号：US10914132

    申请日：2004-08-10

    申请人： Alain Marie Joseph Lardellier

    发明人： Alain Marie Joseph Lardellier

    IPC分类号： F02K1/48 ,  F02K3/06 ,  F02K3/072

    CPC分类号： F02K1/48 ,  F02K3/06 ,  F02K3/105 ,  F05D2260/96 ,  Y02T50/671

    摘要： The invention relates to a turbomachine (1) for an aircraft comprising a gas generator (4) designed such that hot gases are ejected from a combustion chamber (28) towards the upstream side of the turbomachine, and also comprising a plurality of hollow mixer struts (40) connected to an output (36) from the gas generator through which hot gases can pass, each mixer strut comprising an output mixer portion (40c) located inside the annular fan duct (8) so as to mix the secondary air and the hot gases ejected by these output mixer portions towards the downstream side of the turbomachine.

    摘要翻译： 本发明涉及一种用于飞行器的涡轮机（1），其包括气体发生器（4），其被设计成使得热气体从燃烧室（28）朝向涡轮机的上游侧喷射，并且还包括多个中空混合器支柱 （40），其连接到来自气体发生器的输出（36），热气可通过所述输出端（36），每个混合器支柱包括位于环形风扇通道（8）内部的输出混合器部分（40c），以便将二次空气和 由这些输出混合器部分喷射的热气体朝向涡轮机的下游侧。

    Gas turbine engine with pulverized coal firing
    28.
    发明授权
    Gas turbine engine with pulverized coal firing 失效
    燃气涡轮发动机采用粉煤燃烧

    公开(公告)号：US4651522A

    公开(公告)日：1987-03-24

    申请号：US837369

    申请日：1986-03-07

    申请人： Jakob Huber

    发明人： Jakob Huber

    IPC分类号： F01D25/32 ,  F02C3/14 ,  F02C3/26 ,  F02K3/105

    CPC分类号： F02K3/105 ,  F01D25/32 ,  F02C3/14 ,  F02C3/26

    摘要： In order to be able to run a gas turbine engine with pulverized coal as fuel on an industrial basis an arrangement is provided for utilizing the energy contained in the bypass flow with the help of which the solid combustion particles in the combustible gas are removed prior to its entry to the gas turbine blading. If the engine is used for an aircraft this arrangement consists of a thrust nozzle impinged upon by the bypass flow which augments the action of the main thrust nozzle. For use in a stationary power plant this arrangement consists of a heat exchanger in which the heat of the bypass flow is utilized. Thus no unused energy gets lost by way of the bypass flow, so that the heat exchanger need not be kept extremely small for economic reasons. The result is a well cleaned combustible gas and the blades of the gas turbine are to a large extent protected from erosion caused by combustible residues.

    摘要翻译： 为了能够以工业基础的方式运行具有粉煤作为燃料的燃气涡轮发动机，提供了用于利用旁路流中所含的能量的装置，借助于这些能量，在可燃气体中除去固体燃烧颗粒之前， 其进入燃气轮机叶片。 如果发动机用于飞行器，则该布置包括由旁路流动的推力喷嘴，该推力喷嘴增加主推力喷嘴的作用。 为了在固定式发电厂中使用，该装置由热交换器组成，其中利用旁路流的热量。 因此，通过旁路流动不会损耗未使用的能量，所以由于经济原因，热交换器不需要保持极小。 结果是清洁良好的可燃气体，燃气轮机的叶片在很大程度上受到可燃残留物的侵蚀。

    Increased or variable bypass ratio engines
    29.
    发明授权
    Increased or variable bypass ratio engines 失效
    增加或可变的旁路比率发动机

    公开(公告)号：US3792584A

    公开(公告)日：1974-02-19

    申请号：US3792584D

    申请日：1972-02-16

    申请人： BOEING CO

    发明人： KLEES G

    IPC分类号： F02K3/02 ,  F02K3/04 ,  F02K3/075 ,  F02K3/077 ,  F02K3/105 ,  F02K7/16

    CPC分类号： F02K7/16 ,  F02K3/025 ,  F02K3/04 ,  F02K3/075 ,  F02K3/077 ,  F02K3/105 ,  F05D2220/80 ,  Y02T50/671

    摘要： Air breathing gas turbine engine design concepts, methods and apparatus for economically increasing the bypass ratio of conventional engine designs and/or for providing a variable bypass ratio feature. The disclosed preferred embodiments each involve a flow control system for internal management of intake and exhaust air within the engine comprising separated annular first and second duct means shaped and arranged to cross-over or invert air flow patterns within the confines of an annular passageway having an area substantially equal to the combined area of the two separated flow patterns. In this manner the quantities of air which pass to or from the various engine components can be routed without interference, necking down, or departure from the confines of the annular passageway. The system may be modified to achieve variable bypass ratio by providing a means for switching flow patterns between adjacent duct means of separated upstream and downstream portions to switch from inverted to straight through flow. The duct means comprise a plurality of conformably nesting basic duct elements of unique configuration and have utility in solving a variety of engine air flow control problems. The disclosed variable bypass engine concepts can be used in present aircraft propulsion systems to reduce jet and turbomachinery noise, to improve the installed drag characteristics of multimission propulsion units, and to improve fuel consumption rates.

    摘要翻译： 空气呼吸燃气涡轮发动机设计概念，用于经济地增加常规发动机设计的旁路比率和/或用于提供可变旁路比特征的方法和装置。 所公开的优选实施例各自包括用于内部管理发动机内的进气和排气空气的流量控制系统，包括分离的环形第一和第二管道装置，其形状和布置成跨越或反转在具有 面积基本上等于两个分离的流动模式的组合面积。 以这种方式，通往或来自各种发动机部件的空气的量可以不受干扰，收缩或离开环形通道的范围而布置。 可以通过提供用于切换分离的上游和下游部分的相邻管道装置之间的流动模式以从反向切换到直通流动的装置来修改系统以实现可变旁路比。 管道装置包括具有独特构造的多个顺应嵌套的基本管道元件，并且可用于解决各种发动机气流控制问题。 所公开的可变旁路引擎概念可用于当前的飞行器推进系统中以减少喷射和涡轮机械噪声，以改善多重推进装置的安装阻力特性，并提高燃油消耗率。

    Gas turbine engine
    30.
    发明授权
    Gas turbine engine 失效

    公开(公告)号：US3589132A

    公开(公告)日：1971-06-29

    申请号：US3589132D

    申请日：1969-06-04

    申请人： GARRETT CORP

    发明人： PONT ANTHONY A DU

    IPC分类号： F02K3/105 ,  F02K3/06

    CPC分类号： F02K3/105

    摘要： A gas turbine engine of the jet propulsion type wherein an intake fan on a first spool assembly draws air through an air inlet. Part of the air passes into an outer annular bypass duct and part passes through a second spool assembly compressor to be compressed to an intermediate pressure. The compressed air is ducted through a tubular duct to the aft end of the engine and turned through an angle of 180* inwardly into the inlet of a third spool assembly centrifugal compressor to be further compressed. The high-pressure air is then heated within a combustor and the combustion gases are expanded through three separate turbines that power the centrifugal compressor, the axial compressor, and the fan of the respective spool assemblies. The expanded gases are turned, approximately 125* outwardly and backwardly through an injector means into the outer annular bypass duct where they are intermixed with the air flowing therethrough. The mixture is jetted aft through a nozzle to produce forward thrust.