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    GEAR REDUCTION FOR LOWER THRUST GEARED TURBOFAN
    53.
    发明申请
    GEAR REDUCTION FOR LOWER THRUST GEARED TURBOFAN 审中-公开
    减速齿轮减速机

    公开(公告)号：US20160230674A1

    公开(公告)日：2016-08-11

    申请号：US14616922

    申请日：2015-02-09

    申请人： United Technologies Corporation

    发明人： Frederick M. Schwarz ,  William G. Sheridan

    IPC分类号： F02C7/36 ,  F02C3/04

    CPC分类号： F02C7/36 ,  F02C3/04 ,  F02C3/107 ,  F02K3/06 ,  F05D2250/00 ,  F05D2260/4031 ,  F05D2260/40311

    摘要： A gas turbine engine comprises a fan rotor having a hub and a plurality of fan blades extending radially outwardly of the hub. A compressor is positioned downstream of the fan rotor, and has a first compressor blade row defined along a rotational axis of the fan rotor and the compressor rotor. A gear reduction is positioned axially between the first compressor blade row and the fan rotor, and includes a ring gear and a carrier. The carrier has an axial length and the ring gear has an outer diameter. A ratio of the axial length to the outer diameter may be greater than or equal to about 0.20 and less than or equal to about 0.40. The gear reduction is connected to drive the hub to rotate. A method of designing a gas turbine engine is also disclosed.

    摘要翻译： 燃气涡轮发动机包括具有轮毂的风扇转子和沿轮毂径向向外延伸的多个风扇叶片。 压缩机位于风扇转子的下游，并且具有沿着风扇转子和压缩机转子的旋转轴线限定的第一压缩机叶片排。 齿轮减速轴向地定位在第一压缩机叶片排和风扇转子之间，并且包括齿圈和载体。 载体具有轴向长度，并且齿圈具有外径。 轴向长度与外径的比可以大于或等于约0.20且小于或等于约0.40。 齿轮减速器连接以驱动轮毂旋转。 还公开了一种设计燃气涡轮发动机的方法。

    TURBOFAN ENGINE FRONT SECTION
    56.
    发明申请
    TURBOFAN ENGINE FRONT SECTION 审中-公开
    涡轮发动机前部分

    公开(公告)号：US20160138425A1

    公开(公告)日：2016-05-19

    申请号：US15007263

    申请日：2016-01-27

    申请人： United Technologies Corporation

    发明人： Frederick M. Schwarz ,  William G. Sheridan

    IPC分类号： F01D25/24 ,  F04D29/32 ,  F01D17/10 ,  F01D5/12 ,  F01D5/02

    CPC分类号： F01D25/24 ,  F01D5/02 ,  F01D5/12 ,  F01D17/105 ,  F02C3/107 ,  F02C7/36 ,  F02K3/06 ,  F04D29/321 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2230/60 ,  F05D2240/24 ,  F05D2250/51 ,  F05D2260/40311 ,  F16H1/28

    摘要： A front section for a gas turbine engine according to an example of the present disclosure includes, among other things, a fan section including a fan hub. The fan hub includes a hub diameter supporting a plurality of fan blades including a tip diameter. A transitional entrance passage is configured to communicate flow between the fan section and a compressor section. The transitional entrance passage includes an inlet disposed at an inlet diameter and an outlet to the compressor section disposed at an outlet diameter. A method of designing a gas turbine engine is also disclosed.

    摘要翻译： 根据本公开的示例的用于燃气涡轮发动机的前部部分包括除了别的以外的包括风扇轮毂的风扇部分。 风扇毂包括支撑包括尖端直径的多个风扇叶片的轮毂直径。 过渡入口通道构造成在风扇部分和压缩机部分之间传递流动。 过渡入口通道包括设置在入口直径处的入口和设置在出口直径处的压缩机部分的出口。 还公开了一种设计燃气涡轮发动机的方法。

    GAS TURBINE ENGINE WITH MOUNT FOR LOW PRESSURE TURBINE SECTION
    58.
    发明申请
    GAS TURBINE ENGINE WITH MOUNT FOR LOW PRESSURE TURBINE SECTION 审中-公开
    用于低压涡轮部分的气体涡轮发动机

    公开(公告)号：US20160053631A1

    公开(公告)日：2016-02-25

    申请号：US14933440

    申请日：2015-11-05

    申请人： United Technologies Corporation

    发明人： Frederick M. Schwarz ,  Jorn A. Glahn

    IPC分类号： F01D15/12 ,  F01D17/10 ,  F01D25/30 ,  F01D25/24 ,  F01D5/06 ,  F01D25/16

    CPC分类号： F01D25/162 ,  F02C7/06 ,  F02C7/36 ,  F02K3/072 ,  F05D2240/50 ,  F05D2260/40311

    摘要： A turbine section of a gas turbine engine according to an example of the present disclosure includes, among other things, a first turbine section and a second turbine section. The first turbine section has a first exit area and rotates at a first speed. The second turbine section has a second exit area and rotates at a second speed. A first performance quantity is defined as the product of the first speed squared and the first exit area. A second performance quantity is defined as the product of the second speed squared and the second exit area.

    摘要翻译： 根据本公开的示例的燃气涡轮发动机的涡轮部分包括第一涡轮部分和第二涡轮部分。 第一涡轮部分具有第一出口区域并以第一速度旋转。 第二涡轮部分具有第二出口区域并以第二速度旋转。 第一性能数量被定义为第一速度平方和第一出口区域的乘积。 第二性能量被定义为第二速度平方和第二出口区的乘积。

    HYBRID COMPRESSOR BLEED AIR FOR AIRCRAFT USE
    59.
    发明申请
    HYBRID COMPRESSOR BLEED AIR FOR AIRCRAFT USE 审中-公开
    混合压缩机用于飞机使用的空气

    公开(公告)号：US20160009399A1

    公开(公告)日：2016-01-14

    申请号：US14737580

    申请日：2015-06-12

    申请人： United Technologies Corporation

    发明人： Frederick M. Schwarz ,  Stephen G. Pixton

    IPC分类号： B64D13/02 ,  F01D17/10 ,  B64D27/10 ,  F01D5/06

    摘要： A gas turbine engine comprises at least two compressor rotors, including a first lower pressure compressor rotor and a second higher pressure compressor rotor. At least two corresponding air taps include a low tap for tapping low pressure compressor air from a location downstream of a first stage of the lower pressure compressor rotor, and upstream of a first stage of the higher pressure compressor rotor, and a high tap to tap air downstream of the first stage of the higher pressure compressor rotor. an air handling system selectively communicates both the low tap and the high tap to an air use destination. Air is selectively supplied from the low tap to the air handling system at a high power operation and from the high tap to the air handling system at a low power operation.

    摘要翻译： 燃气涡轮发动机包括至少两个压缩机转子，包括第一低压压缩机转子和第二高压压缩机转子。 至少两个对应的空气抽头包括用于从低压压缩机转子的第一级下游的位置以及高压压缩机转子的第一级的上游排出低压压缩机空气的低抽头，以及高抽头 高压压缩机转子第一级下游的空气。 空气处理系统选择性地将低抽头和高抽头通信到空气使用目的地。 空气在低功率操作下从低抽头选择性地供应到空气处理系统，并且在低功率操作下从高抽头到空气处理系统。

    GAS TURBINE ENGINE WITH SHORT TRANSITION DUCT
    60.
    发明申请
    GAS TURBINE ENGINE WITH SHORT TRANSITION DUCT 审中-公开
    气体涡轮发动机与短路过渡管

    公开(公告)号：US20160003163A1

    公开(公告)日：2016-01-07

    申请号：US14751274

    申请日：2015-06-26

    申请人： United Technologies Corporation

    发明人： Frederick M. Schwarz ,  William K. Ackermann

    IPC分类号： F02C7/36

    CPC分类号： F02C7/36 ,  F01D5/142 ,  F01D5/225 ,  F05D2220/327 ,  F05D2260/40311 ,  Y02T50/671 ,  Y02T50/673

    摘要： A turbine section for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan drive turbine including a fan drive duct, the fan drive turbine being configured to drive a fan section through a geared architecture at a speed that is less than an input speed to the geared architecture. A fan drive turbine includes a fan drive duct, the fan drive turbine being configured to drive a fan section through a geared architecture at a speed that is less than an input speed to the geared architecture. At least one upstream turbine is configured to drive at least one compressor. The at least one upstream turbine includes a turbine duct defining a conical flow path having a conical inlet defined by a first diameter and a conical outlet defined by a second diameter greater than the first diameter. The conical outlet is in fluid communication with the fan drive duct downstream of the conical outlet. At least one row of shrouded rotor blades defines at least a portion of the conical flow path. A method of designing a gas turbine engine is also disclosed.

    摘要翻译： 根据本公开的示例性方面的用于燃气涡轮发动机的涡轮机部分包括除了别的以外的包括风扇驱动管道的风扇驱动涡轮机，所述风扇驱动涡轮机构造成通过齿轮架构驱动风扇部分， 速度小于齿轮架构的输入速度。 风扇驱动涡轮机包括风扇驱动管道，所述风扇驱动涡轮机构造成以低于所述齿轮架构的输入速度的速度通过齿轮架构驱动风扇部分。 至少一个上游涡轮被配置成驱动至少一个压缩机。 所述至少一个上游涡轮机包括限定具有由第一直径限定的锥形入口和由大于第一直径的第二直径限定的锥形出口的锥形流动路径的涡轮机管道。 锥形出口与锥形出口下游的风扇驱动管道流体连通。 至少一排被覆盖的转子叶片限定了锥形流动路径的至少一部分。 还公开了一种设计燃气涡轮发动机的方法。