中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

21 records (took 0.022 seconds)

    LOW NOISE COMPRESSOR ROTOR FOR GEARED TURBOFAN ENGINE
    11.
    发明专利
    LOW NOISE COMPRESSOR ROTOR FOR GEARED TURBOFAN ENGINE 未知

    公开(公告)号：CA2915233A1

    公开(公告)日：2016-07-08

    申请号：CA2915233

    申请日：2015-12-11

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： TOPOL DAVID A ,  MORIN BRUCE L

    IPC: F01D5/02 ,  F01D5/12 ,  F02C3/04 ,  F02C7/36

    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 x rotational speed)/60s >= 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.

    motor de turbina a gás, e, método para projetar um motor de turbina a gás
    12.
    发明专利
    motor de turbina a gás, e, método para projetar um motor de turbina a gás 未知

    公开(公告)号：BR102016000211A2

    公开(公告)日：2016-10-04

    申请号：BR102016000211

    申请日：2016-01-06

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： MORIN BRUCE L ,  TOPOL DAVID A

    IPC: F02C7/045

    Abstract: motor de turbina a gás, e, método para projetar um motor de turbina a gás um motor de turbina a gás possui uma ventoinha e uma turbina tendo um rotor de turbina de acionamento de ventoinha. o rotor de turbina de acionamento de ventoinha aciona um rotor de compressor. uma engrenagem de redução efetua uma redução na velocidade da ventoinha em relação a uma velocidade de entrada do rotor de turbina de acionamento de ventoinha que aciona o rotor de compressor. o rotor de compressor tem um número de lâminas de compressor em pelo menos uma dentre uma pluralidade de linhas do rotor de compressor. as lâminas operam pelo menos alguma parte do tempo em uma velocidade de rotação. o número de lâminas de compressor em pelo menos uma linha e a velocidade de rotação são de tal modo que a fórmula a seguir se faz verdadeira para pelo menos uma linha da turbina do rotor de compressor: (número de lâminas × velocidade de rotação)/60 s = 5500 hz; e a velocidade de rotação sendo em rotações por minuto. um método para projetar um motor de turbina a gás e um módulo de compressor também é divulgado.

    LOW NOISE COMPRESSOR ROTOR FOR GEARED TURBOFAN ENGINE
    13.
    发明专利
    LOW NOISE COMPRESSOR ROTOR FOR GEARED TURBOFAN ENGINE 未知

    公开(公告)号：CA2879244A1

    公开(公告)日：2015-07-21

    申请号：CA2879244

    申请日：2015-01-20

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： TOPOL DAVID A ,  MORIN BRUCE L

    IPC: F01D5/02 ,  F01D5/06 ,  F01D5/10 ,  F02C7/24 ,  F02C7/36

    Abstract: A gas turbine engine comprises a fan and a turbine section having a first turbine rotor. The first turbine rotor drives a compressor rotor. A gear reduction effects a reduction in the speed of the fan relative to an input speed from a fan drive turbine 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: (the number of blades x the rotational speed)/ (60 seconds/minute) >= 5500 Hz; and the rotational speed being in revolutions per minute. A compressor module and a method of designing a gas turbine engine are also disclosed.

    LOW NOISE COMPRESSOR ROTOR FOR GEARED TURBOFAN ENGINE
    15.
    发明专利
    LOW NOISE COMPRESSOR ROTOR FOR GEARED TURBOFAN ENGINE 未知

    公开(公告)号：CA2863620A1

    公开(公告)日：2013-08-22

    申请号：CA2863620

    申请日：2013-01-18

    Applicant: UNITED TECHNOLOGIES CORP ,  MTU AERO ENGINES AG

    Inventor： TOPOL DAVID A ,  MORIN BRUCE L ,  KORTE DETLEF

    IPC: F01D1/02 ,  F02C7/262 ,  F02K3/02

    Abstract: A gear reduction effects a reduction in the speed of a fan relative to a speed of a low pressure turbine and a 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 x rotational speed)/60 ? 5500 Hz. The rotational speed is an approach speed in revolutions per minute.

Patent Agency Ranking