A gas turbine engine (10) for an aircraft comprising: an engine core (11) comprising a turbine (19), a compressor (14), and a core shaft (26) connecting the turbine to the compressor; a fan (23) located upstream of the engine core, the fan comprising a plurality of fan blades; a gearbox (30) that receives an input from the core shaft (26) and outputs drive to the fan so as to drive the fan at a lower rotational speed than the core shaft, the gearbox (30) being an epicyclic gearbox (30) comprising a sun gear (28), a plurality of planet gears (32), a ring gear (38), and a planet carrier (34) arranged to have the plurality of planet gears (32) mounted thereon; and a gearbox support (40) arranged to at least partially support the gearbox within the engine. The gearbox (30) has a cross sectional area, the cross sectional area being greater than or equal to 2.4*10-1 m<2>; anda first gearbox support strength ratio of: the torsional strength of the gearbox support 40 the radial bending stiffness of the gearbox support 40 * the cross sectional area of the gearbox is greater than or equal to 7.0*10<-3>. A planet gear spacing angle in radians (beta) is defined as 2pi/N, where N is the number of planet gears (32). A second gearbox support strength ratio of: the torsional strength of the gearbox support 40 the tilt stiffness of the gearbox support 40 * the planet gear spacing angle beta is greater than or equal to 1.0*10<-1>.

    本发明题为齿轮传动气体涡轮引擎。本公开提供了一种用于飞行器的气体涡轮引擎(10),该气体涡轮引擎包括:引擎核心(11),该引擎核心包括涡轮(19)、压缩机(14)以及将该涡轮连接到该压缩机的芯轴(26);风扇(23),该风扇位于该引擎核心的上游,该风扇包括多个风扇叶片;齿轮箱(30),该齿轮箱接收来自该芯轴(26)的输入,并且将驱动输出至该风扇,以便以比该芯轴低的旋转速度驱动该风扇,该齿轮箱(30)是周转齿轮箱(30),该周转齿轮箱包括太阳齿轮(28)、多个行星齿轮(32)、环形齿轮(38)以及被布置用于将该行星齿轮(32)安装在其上的行星架(34);以及齿轮箱支撑件(40),该齿轮箱支撑件被布置用于至少部分地支撑该引擎内的齿轮箱。该齿轮箱(30)具有横截面积,该横截面积大于或等于2.4×10‑1m2;以及第一齿轮箱支撑件强度比率:大于或等于7.0×10‑3以弧度计的行星齿轮间距角(β)被定义为2π/N,其中N是行星齿轮(32)的数量。第二齿轮箱支撑件强度比:大于或等于1.0×10‑1。


    Access

    Download


    Export, share and cite



    Title :

    GEARED GAS TURBINE ENGINE


    Additional title:

    齿轮传动气体涡轮引擎


    Contributors:
    SPRUCE MARK (author)

    Publication date :

    2021-06-08


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    F16H Getriebe , GEARING / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / F02K JET-PROPULSION PLANTS , Strahltriebwerke



    GEARED GAS TURBINE ENGINE ACCESSORY GEARBOX

    CLOFT THOMAS G / GUKEISEN ROBERT L | European Patent Office | 2015

    Free access

    GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE

    KUPRATIS DANIEL BERNARD / SCHWARZ FREDERICK M | European Patent Office | 2020

    Free access

    GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE

    KUPRATIS DANIEL BERNARD / SCHWARZ FREDERICK M | European Patent Office | 2018

    Free access

    Geared gas turbine engine accessory gearbox

    CLOFT THOMAS G / GUKEISEN ROBERT L | European Patent Office | 2019

    Free access

    GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE

    KUPRATIS DANIEL BERNARD / SCHWARZ FREDERICK M | European Patent Office | 2017

    Free access