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    Thus, this article examines two aspects of the use of air-water sprays for quenching aeroengine forgings.
          
    A series of neutron diffraction measurements have been carried out to determine the elastic residual strains deep within a large, 40-cm-diameter, forged and water-quenched IN718 aeroengine compressor disc.
          
    Industrial-scale manufacturing trials associated with the production of an INCONEL alloy 718 aeroengine turbine disc were used to validate the integrated model for grain size.
          
    In addition, excellent corrosion resistance, high fracture toughness, creep strength up to ~ 600°C make them a wanted material for aeroengine applications.
          
    The method is applied to CARS data from an isothermal furnace and a liquid kerosene fuelled aeroengine combustor sector rig.
          
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    The application of photoelastic stress-freezing method to the three-dimensional stress analyses for two configurations of aeroengine disks and drums is described. The simulation of the rotating centrifugal field during the free/ing period is considered, which contains utilization of the apparatus with a rotating cover, principles of choosing test speeds and simulation of boundary conditions, such as the configurafion, stiffness and connecting mode of the parts to be fitted.The features of the photoelastic...

    The application of photoelastic stress-freezing method to the three-dimensional stress analyses for two configurations of aeroengine disks and drums is described. The simulation of the rotating centrifugal field during the free/ing period is considered, which contains utilization of the apparatus with a rotating cover, principles of choosing test speeds and simulation of boundary conditions, such as the configurafion, stiffness and connecting mode of the parts to be fitted.The features of the photoelastic stress analysis are also discussed and the results are applied to primary strength analysis of compressor disks and drums. The severity of stress concentration in the areas of slots, the edge of eccentric holes and bolt holes of the compressor disk is stressed. Then, some measures of improvement are offered, which may be advantageous to structural design and development of new engines.

    644彩的新版网站benwenyongguangdanxingyinglidongjieqiepianfa,monilehangkongfadongjiyaqijizhuanzizaigaosuxuanzhuanshidelixinyinglichang,duiliangzhongjiegouxingshidelunpanjigutongjinxinglejiaoquanmiandesanxiangyinglifenxi。genjushiyanjieguo,duixuanzhuanlingjiandejiegoujinxingleqiangdufenxi。

    644彩的新版网站 the development of the second and the third generations of high by-pass ratio turbofan engines,as well as the technical measures for improving the performance of engine,are summarized and reviewed in this paper. compared with their predecessors,the second and the third generations of high by-pass ratio turbofan engines have much lower sfc,fewer parts, lower rate of performancedeterioration and superior maintainability and reliability as well as some other advantages. to achieve this,a lot of significant advanced...

    The development of the second and the third generations of high by-pass ratio turbofan engines,as well as the technical measures for improving the performance of engine,are summarized and reviewed in this paper. Compared with their predecessors,the second and the third generations of high by-pass ratio turbofan engines have much lower SFC,fewer parts, lower rate of performancedeterioration and superior maintainability and reliability as well as some other advantages. To achieve this,a lot of significant advanced technologies have been developed and put in practice which are presented in brief in this paper. Finally, some remarks on aeroengine development in China have been made.

    benwengaishubingpingjieledierdai、disandaidaliuliangbiwoshanfadongjidefazhantujing,yijiweitigaofadongjixingnengsuocaiqudezhuyaojishucuoshi。bingduiwoguofadongjidefazhantichuleyixieyijian。

    This paper describes the real time dynamic simulation research on the digital speed control system of an aeroengine644彩的新版网站 under small perturbation conditions. The control calculation approach has been programmed for a microcomputer. The proportional derivative control is applied to the large error region and the proportional control to the small error region. Furthermore, in the small error region, the large proportional constant control is adopted if the error increment tends to increase, and the small proportional...

    This paper describes the real time dynamic simulation research on the digital speed control system of an aeroengine644彩的新版网站 under small perturbation conditions. The control calculation approach has been programmed for a microcomputer. The proportional derivative control is applied to the large error region and the proportional control to the small error region. Furthermore, in the small error region, the large proportional constant control is adopted if the error increment tends to increase, and the small proportional costant control is employed when it tends to decrease. For the sake of normal operation in the digital speed control system, the influence of the high frequency disturbance, the overspeed and spillover in the microcomputer have been eliminated. Finally, the flow chart of the program and the real time simulation tests are demonstrated. The test results and some useful conclusions are also presented.

    benwenjieshaohangkongfadongjizhuansushukongxitongdedongtaishishimoniyanjiu,baokuoweijineikongzhisuanfadesheji,gaopinganraoxinhaoduixitongwendinggongzuodeyingxiang,chaozhuanheyichuguzhangdechulidengneirong。tongguomonishiyan,dechuleyixieyouyidejielun。

     
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