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    LOW NOISE COMPRESSOR ROTOR FOR GEARED TURBOFAN ENGINE
    12.
    发明申请
    LOW NOISE COMPRESSOR ROTOR FOR GEARED TURBOFAN ENGINE 审中-公开

    公开(公告)号：US20170321611A1

    公开(公告)日：2017-11-09

    申请号：US15437069

    申请日：2017-02-20

    Applicant: United Technologies Corporation

    Inventor： David A. Topol ,  Bruce L. Morin

    IPC: F02C7/36 ,  F01D5/02 ,  F01D5/12

    CPC classification number: F02C7/36 ,  F01D5/02 ,  F01D5/12 ,  F05D2220/36 ,  F05D2260/40311 ,  F05D2260/96 ,  Y02T50/673 ,  Y10T29/49236 ,  Y10T29/4932

    Abstract: A gas turbine engine has a fan and a turbine having a fan drive turbine rotor. The fan drive turbine rotor drives a compressor rotor. A gear reduction effects a reduction in the speed of the fan relative to an input speed from the fan drive turbine rotor that drives the compressor rotor, and having a gear reduction ratio of greater than 2.5:1. The compressor rotor has a number of compressor blades in at least one of a plurality of rows of the compressor rotor. The blades operate at least some of the time at a rotational speed. The number of compressor blades in at least one row and the rotational speed are such that the following formula holds true for at least one row of the compressor rotor: (number of blades×rotational speed)/60 sec≧5500 Hz, and the rotational speed is in revolutions per minute. A method of designing a gas turbine engine also disclosed.

    LOW NOISE COMPRESSOR FOR GEARED GAS TURBINE ENGINE
    15.
    发明申请
    LOW NOISE COMPRESSOR FOR GEARED GAS TURBINE ENGINE 审中-公开
    用于齿轮式涡轮发动机的低噪声压缩机

    公开(公告)号：US20160040598A1

    公开(公告)日：2016-02-11

    申请号：US14774273

    申请日：2014-02-19

    Applicant: United Technologies Corporation

    Inventor： Bruce L. Morin ,  David A. Topol

    IPC: F02C7/24 ,  F02C7/36 ,  F02C3/04

    CPC classification number: F02C7/24 ,  F02C3/04 ,  F02C3/107 ,  F02C7/36 ,  F02K3/06 ,  F05D2260/40311 ,  F05D2260/96

    Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan, a compressor section having a low pressure compressor and a high pressure compressor, a combustor section, and a turbine section having a low pressure turbine, the low pressure turbine for driving the low pressure compressor and the fan; a gear reduction effecting a reduction in the speed of the fan relative to a speed of the low pressure turbine and the low pressure compressor; and at least one stage of the compressor section having a ratio of vanes to blades that is greater than or equal to 1.8. The corrected tip speed of the blades is greater than or equal to 480 ft/sec at an approach speed.

    Abstract translation: 根据本公开的示例性方面的燃气涡轮发动机包括风扇，具有低压压缩机和高压压缩机的压缩机部分，燃烧器部分和具有低压涡轮机的涡轮部分， 用于驱动低压压缩机和风扇的低压涡轮机; 齿轮减速相对于低压涡轮机和低压压缩机的速度降低风扇的速度; 并且所述压缩机部分的至少一个级具有大于或等于1.8的叶片与叶片的比率。 在接近速度下，叶片的修正的叶尖速度大于或等于480英尺/秒。

    LOW NOISE TURBINE FOR GEARED TURBOFAN ENGINE
    16.
    发明申请
    LOW NOISE TURBINE FOR GEARED TURBOFAN ENGINE 审中-公开
    用于齿轮涡轮发动机的低噪音涡轮机

    公开(公告)号：US20160032756A1

    公开(公告)日：2016-02-04

    申请号：US14795931

    申请日：2015-07-10

    Applicant: United Technologies Corporation ,  MTU Aero Engines AG

    Inventor： Bruce L. Morin ,  Detlef Korte

    IPC: F01D15/12 ,  F01D5/12 ,  F01D5/02

    CPC classification number: F02K3/04 ,  F02C3/107 ,  F05D2220/32 ,  F05D2260/40311 ,  F05D2260/96 ,  F05D2270/304 ,  F05D2270/333 ,  G06F17/5086

    Abstract: A gas turbine engine comprises a fan and a turbine having a fan drive rotor. There is also a second turbine rotor. A gear reduction effects a reduction in the speed of the fan relative to an input speed from the fan drive rotor. The fan drive rotor has a number of turbine blades in at least one of a plurality of rows of the fan drive rotor, and the turbine blades operate at least some of the time at a rotational speed. The number of turbine blades in the at least one row and the rotational speed are such that the following formula holds true for the at least one row of the fan drive turbine: (number of blades×speed)/60≧5500 Hz. The rotational speed is in revolutions per minute. A method of designing a gas turbine engine, and a turbine module are also disclosed.

    Abstract translation: 燃气涡轮发动机包括风扇和具有风扇驱动转子的涡轮机。 还有第二个涡轮转子。 齿轮减速实现风扇驱动转子相对于输入速度的降低。 风扇驱动转子在风扇驱动转子的多排中的至少一行中具有多个涡轮叶片，涡轮叶片以至少一些时间以转速运行。 至少一行中的涡轮机叶片的数量和转速使得对于风扇驱动涡轮机的至少一排，以下公式成立：（叶片数×速度）/60≥5500Hz。 转速为每分钟转数。 还公开了一种设计燃气涡轮发动机的方法和涡轮模块。

    Gas Turbine Engine with Low Fan Noise
    17.
    发明申请
    Gas Turbine Engine with Low Fan Noise 审中-公开
    具有低风扇噪音的燃气轮机发动机

    公开(公告)号：US20150361824A1

    公开(公告)日：2015-12-17

    申请号：US14761689

    申请日：2014-03-11

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Bruce L. Morin ,  Wesley K. Lord

    IPC: F01D25/04 ,  F01D17/14 ,  F01D9/02 ,  F01D5/02 ,  F01D5/14

    Abstract: In accordance with one aspect of the disclosure, a gas turbine engine, method of using and designing such is disclosed. The gas turbine engine may comprise a fan including a plurality of blades, and a variable area fan nozzle. The fan may be configured to have a design point fan tip leading edge relative flow angle βADP, and may be further configured to have an off-design point fan tip leading edge relative flow angle β at an off-design fan operating point. The variable area fan nozzle may be configured to manipulate the amount of air flowing through the fan so that the absolute value of a difference between the design point fan tip leading edge relative flow angle βADP and the off-design point fan tip leading edge relative flow angle β is in a specified range.

    Abstract translation: 根据本公开的一个方面，公开了一种燃气涡轮发动机，其使用和设计方法。 燃气涡轮发动机可以包括包括多个叶片的风扇和可变区域风扇喷嘴。 风扇可以被配置成具有设计点风扇顶端前缘相对流动角度ADP，并且还可以被配置为具有偏离设计点的风扇尖端前缘相对流动角度＆bgr; 在设计外的风扇工作点。 可变区域风扇喷嘴可以被配置为操纵流过风扇的空气量，使得设计点风扇叶片前缘相对流动角度与ADP和偏离设计点之间的差异的绝对值 相对流角 在指定范围内。

    Low noise compressor rotor for geared turbofan engine
    18.
    发明授权
    Low noise compressor rotor for geared turbofan engine 有权
    用于齿轮涡扇发动机的低噪声压缩机转子

    公开(公告)号：US08714913B2

    公开(公告)日：2014-05-06

    申请号：US14016436

    申请日：2013-09-03

    Applicant: United Technologies Corporation

    Inventor： David A. Topol ,  Bruce L. Morin

    IPC: F01D1/02

    CPC classification number: F02C3/10 ,  F01D5/02 ,  F01D5/12 ,  F02C7/24 ,  F02C7/36 ,  F05D2260/96 ,  Y02T50/673 ,  Y10T29/49236 ,  Y10T29/4932

    Abstract: A gas turbine engine has a fan and a turbine having a fan drive turbine rotor. The fan drive turbine rotor drives a compressor rotor. A gear reduction effects a reduction in the speed of the fan relative to an input speed from the fan drive turbine rotor that drives the compressor rotor. The compressor rotor has a number of compressor blades in at least one of a plurality of rows of the compressor rotor. The blades operate at least some of the time at a rotational speed. The number of compressor blades in at least one row and the rotational speed are such that the following formula holds true for at least one row of the compressor rotor turbine: (number of blades×rotational speed)/60 s≧5500 Hz, and the rotational speed is in revolutions per minute. A method of designing a gas turbine engine and a compressor module are also disclosed.

    Abstract translation: 燃气涡轮发动机具有风扇和具有风扇驱动涡轮机转子的涡轮机。 风扇驱动涡轮转子驱动压缩机转子。 齿轮减速实现了风扇相对于来自驱动压缩机转子的风扇驱动涡轮转子的输入速度的降低。 压缩机转子在压缩机转子的多排中的至少一排中具有多个压缩机叶片。 叶片在旋转速度下至少运行一些时间。 至少一行中的压缩机叶片的数量和转速使得至少一排压缩机转子涡轮机的以下公式成立：（叶片数×转速）/60s≥5500Hz， 转速为每分钟转。 还公开了一种设计燃气涡轮发动机和压缩机组件的方法。

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