A design method of stiffness coefficient of elastic buffer casing

A technology of elastic cushioning and stiffness coefficient, applied in mechanical equipment, design optimization/simulation, engine components, etc., can solve the problems of rotor system and load-bearing casing impact damage, etc., to prolong the action time, reduce the impact force, The effect of ensuring safe and smooth work

Active Publication Date: 2022-08-09
AECC HUNAN AVIATION POWERPLANT RES INST
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AI Technical Summary

Problems solved by technology

[0003] On the one hand, the present application provides an elastic buffer casing to solve the problem of rigid collision between the rotor system and the casing due to the disappearance of the oil film gap caused by the elastic support when the existing engine rotor system is impacted or greatly vibrated, which eventually causes damage to the rotor system and Technical issues of impact damage caused by load-bearing receivers

Method used

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  • A design method of stiffness coefficient of elastic buffer casing
  • A design method of stiffness coefficient of elastic buffer casing
  • A design method of stiffness coefficient of elastic buffer casing

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Embodiment Construction

[0065] It should be noted that the embodiments in the present application and the features of the embodiments may be combined with each other in the case of no conflict. The present application will be described in detail below with reference to the accompanying drawings and in conjunction with the embodiments.

[0066] refer to figure 1 and figure 2 , the preferred embodiment of the present application provides an elastic buffer casing, the elastic buffer casing includes a flange section 9, a first bearing seat section 3, a transition section 5, and a second bearing seat section 7 in sequence along the axial direction ,

[0067] The flange section 9 is provided with a flange edge 2, and the flange edge 2 is fixedly connected with the outer casing 1 through bolts, so as to fix one end of the elastic buffer casing on the outer casing 1;

[0068] The inner hole of the first bearing seat segment 3 matches the outer circle of the first bearing 4 mounted on the power output sha...

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Abstract

This application disclosed a elastic buffer case and its stiffness design method.Some sections of the orchid are set up by flanges, which are fixed with the outer case by bolts to fix the elastic buffer casing on the outer box through the outer case;The first bearing of the power output shaft component is matched; the inner holes of the second bearing section are matched with the outer circle of the second bearing installed on the power output bearing component;The diameter of the diameter of the first bearing section of the first bearing section gradually transitions.By reducing the stiffness coefficient of the elastic buffer casing, the time of the impact force is extended, so as to achieve the effect of making the power turbine pistol system from vibrating impact damage, and ensuring the safe and stable work of the aviation engine.

Description

technical field [0001] The present application relates to the field of aeronautical turboshaft engines, in particular, to a stiffness coefficient design method of an elastic buffer casing. Background technique [0002] At present, the turboshaft engine adopts the front output form, and its power is transmitted from the power turbine to the output shaft through the power turbine shaft, so that the power turbine shaft is slender, has a large aspect ratio and is "soft", and has elastic supports at both ends. Generally, it is necessary to design the squeeze oil film to reduce vibration. When the rotor system of the engine has an impact or a large vibration moment, the oil film gap will disappear and cause a rigid collision between the rotor system and the casing. damage to the box. Therefore, it is necessary to design an elastic buffer casing, which can play the role of flexible protection and avoid or reduce the vibration and impact damage of the rotor system and the rigid cas...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F01D25/24F01D25/04F01D25/16G06F30/17G06F30/23
CPCF01D25/24F01D25/243F01D25/04F01D25/16G06F30/17G06F30/23Y02E10/20
Inventor 陈冰蔡明先黄兴黄健李鑫
Owner AECC HUNAN AVIATION POWERPLANT RES INST
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