Statics And Modal Analysis Of Aero-engine Compressor Blades

The blades are one of the main parts of aircraft engines, plays in the work to convert the role of energy, often referred to as launchThe heart of the machine. Its quality directly affects the engine’s efficiency and operational reliability. The work environment of leaves is relatively poor, to withstand high-speed rotation of the aerodynamic force, centrifugal force and vibration loads, but also by the thermal stress. Its structural design quality is directly related to engine performance, durability, reliability and longevity. Compressor blades, not only quantity but also of different sizes, when engine works in a large speed, the centrifugal force of the blades is great, If there are cracks in the leaves, the leaves prone to fracture, broken leaves usually injured, interrupted the some other stator and rotor blades, or to produce serious deformation. Fracture of large leaves will breakdown the cartridge, broken aircraft parts and may cause the aircraft engine can not continue to work, causing a major accident. About structural failure of the engine, failure in the leaves accounted for a rather high percentage. Military aviation engine which are being used and being developed, almost without exception, been the failure of the blade, and has seriously affected the safe use of the engine, that is the most prominent problem in the engine quality issues,in china. By analyzing the reasons of the blade failures, the nature of the failure:oxidation corrosion and damage from the other objects、creep deformation and creep stress fracture、high cycle fatigue caused by vibration、low-cycle fatigue which include thermal fatigue、Stress fracture etc.and high cycle fatigue problems caused by vibration are particularly common, accounting for25%of the total accident. Therefore, in the design process of the leaves, it is necessary to establish an appropriate finite element model, and then analyze the static strength, vibration modes and response.The main contents of this article can be roughly classified into the following areas:First, understand the research status of the blade strength at home and abroad, research new technologies and new methods in the blade strength, fully learn from foreign advanced blade strength design system, and then analysis blades intensity.Second, for an engine compressor blades, establish a detailed three-dimensional finite element analysis model, evaluate reserves of the static strength, to see that Whether it meets the design criteria, and then optimize the intensity of the leaf structure. Given deformation and stress distribution map of the blades, to provide more detailed and reliable data for analysising to reversion recovery angle and clearance of blade.Third, for an engine fan blades, using the conventional finite element method and a kind of method which considering the dry friction non-linear response,analysing the vibration response of leaf. Comparing these two calculations, analyze the advantages and disadvantages of these two methods, to provide a reference for engineering calculations.