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    LOW NOISE COMPRESSOR ROTOR FOR GEARED TURBOFAN ENGINE
    31.
    发明申请
    LOW NOISE COMPRESSOR ROTOR FOR GEARED TURBOFAN ENGINE 审中-公开

    公开(公告)号：US20200173370A1

    公开(公告)日：2020-06-04

    申请号：US16667326

    申请日：2019-10-29

    Applicant: United Technologies Corporation ,  MTU Aero Engines AG

    Inventor： David A. Topol ,  Bruce L. Morin ,  Detlef Korte

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

    Abstract: A gas turbine engine has a fan section including a fan, a compressor section including a low pressure compressor and a high pressure compressor, a turbine section including a low pressure turbine and a high pressure turbine, and a gear reduction. The low pressure compressor and the low pressure turbine have a number of blades in each of at least one of a plurality of blade rows. The blades are rotatable at least some of the time at a rotational speed in operation. The number of 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)/60s≥5500 Hz, and the rotational speed is in revolutions per minute.

    LOW NOISE COMPRESSOR ROTOR FOR GEARED TURBOFAN ENGINE
    36.
    发明申请
    LOW NOISE COMPRESSOR ROTOR FOR GEARED TURBOFAN ENGINE 审中-公开
    用于齿轮式涡轮发动机的低噪声压缩机转子

    公开(公告)号：US20160138474A1

    公开(公告)日：2016-05-19

    申请号：US14967478

    申请日：2015-12-14

    Applicant: United Technologies Corporation

    Inventor： David A. Topol ,  Bruce L. Morin

    IPC: F02C7/24 ,  F02C7/32 ,  F02K3/06 ,  F02C3/10

    CPC classification number: G01P3/48 ,  F01D5/02 ,  F01D5/12 ,  F02C3/04 ,  F02C3/10 ,  F02C7/24 ,  F02C7/32 ,  F02C7/36 ,  F02K3/06 ,  F05D2200/13 ,  F05D2200/14 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2260/40311 ,  F05D2260/96 ,  Y02T50/673 ,  Y10T29/49236 ,  Y10T29/4932

    Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan and a turbine section having a fan drive turbine rotor, and a compressor rotor. A gear reduction effects a reduction in a speed of the fan relative to an input speed from the fan drive turbine rotor. The compressor rotor has a number of compressor blades in at least half of a plurality of blade rows of the compressor rotor. The blades are configured to operate at least some of the time at a rotational speed. The number of compressor blades in the at least half of the blade rows and the rotational speed is such that the following formula holds true for each row of the at least half of the blade rows of the compressor rotor: (the number of blades×the rotational speed)/60 s≧about 5500 Hz.

    Abstract translation: 根据本公开的示例的燃气涡轮发动机尤其包括具有风扇驱动涡轮机转子和压缩机转子的风扇和涡轮部分。 相对于来自风扇驱动涡轮转子的输入速度，齿轮减速实现风扇速度的降低。 压缩机转子在压缩机转子的多个叶片列的至少一半中具有多个压缩机叶片。 叶片被构造成在转速下至少一些时间运行。 叶片行的至少一半中的压缩机叶片的数量和转速使得对于压缩机转子的至少一半叶片行的每一行，以下公式成立：（叶片数× 转速）/ 60s≧约5500Hz。

    Low noise compressor rotor for geared turbofan engine
    37.
    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：US08632301B2

    公开(公告)日：2014-01-21

    申请号：US13630276

    申请日：2012-09-28

    Applicant: United Technologies Corporation

    Inventor： David A. Topol ,  Burce L. Morin

    IPC: F01D1/02

    CPC classification number: F02C3/107 ,  F02K3/06 ,  F05D2260/961 ,  F05D2270/333

    Abstract: A gas turbine engine has a fan, a compressor section having a low pressure portion and a high pressure portion, a combustor section, and a turbine having a low pressure portion. The low pressure turbine portion drives the low pressure compressor portion and the fan. A gear reduction effects a reduction in the speed of the fan relative to a speed of the low pressure turbine and the low pressure compressor portion. At least one of the low pressure turbine portion and low pressure compressor portion has a number of blades in each of a plurality of rows. The blades operate at least some of the time at a rotational speed. The number of blades and the rotational speed are such that the following formula holds true for at least one of the blade rows of the at least one of the low pressure turbine portion and/or the low pressure compressor sections: (number of blades×rotational speed)/60≧5500. The rotational speed is an approach speed in revolutions per minute.

    Abstract translation: 燃气涡轮发动机具有风扇，具有低压部分和高压部分的压缩机部分，燃烧器部分和具有低压部分的涡轮机。 低压涡轮部分驱动低压压缩机部分和风扇。 齿轮减速实现风扇相对于低压涡轮机和低压压缩机部分的转速的降低。 低压涡轮机部分和低压压缩机部分中的至少一个在多行中的每一行中具有多个叶片。 叶片在旋转速度下至少运行一些时间。 叶片的数量和转速使得对于低压涡轮部分和/或低压压缩机部分中的至少一个的至少一个叶片排，以下公式成立：（叶片数×旋转数 速度）/ 60> = 5500。 旋转速度是每分钟转数的接近速度。

    LOW NOISE COMPRESSOR ROTOR FOR GEARED TURBOFAN ENGINE
    38.
    发明申请
    LOW NOISE COMPRESSOR ROTOR FOR GEARED TURBOFAN ENGINE 有权
    用于齿轮式涡轮发动机的低噪声压缩机转子

    公开(公告)号：US20140003915A1

    公开(公告)日：2014-01-02

    申请号：US14016436

    申请日：2013-09-03

    Applicant: United Technologies Corporation

    Inventor： David A. Topol ,  Bruce L. Morin

    IPC: F02C7/24

    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，以及 旋转速度为每分钟转数。 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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