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Casing containment analysis method for blade offset loss

An analysis method and inclusive technology, applied in special data processing applications, instruments, electrical digital data processing, etc., can solve problems such as the complexity of the impact process

Pending Publication Date: 2021-03-23
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The impact of the blade lost at a certain deflection angle and the casing involves the role of the stator blade, the mounting edge, etc., and the impact process is more complicated

Method used

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  • Casing containment analysis method for blade offset loss
  • Casing containment analysis method for blade offset loss
  • Casing containment analysis method for blade offset loss

Examples

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Embodiment Construction

[0025] Such as figure 1 As shown, a casing inclusive analysis method for blade offset loss in this embodiment includes the following steps:

[0026] (1) Establish the finite element model of the blade and casing; in this embodiment, the casing model established includes the turbine casing and the fan casing. In the modeling process, in order to simplify the modeling and shorten the calculation time, the engine casing Simplify the real structure of the casing, remove unnecessary features and parts such as blade roots, discs, holes, chamfers, roundings, bosses, etc., but retain all the features of the impacted area of ​​the casing as much as possible.

[0027] Because the main research is on the impact process of the blade after it breaks off and the casing, and the impact mainly occurs at the blade tip and the blade body, the blade root does not participate in the impact, and the disc only plays the role of driving the rest of the blades to rotate. The blade 2 is cut from the ...

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Abstract

The invention discloses a casing containment analysis method for blade offset loss. The casing containment analysis method comprises the following steps: establishing a finite element model of a bladeand a casing; assigning the constitutive parameters according to the casing and blade materials, and establishing a constitutive model; setting boundary conditions and initial conditions of the finite element model; simulating the loss process of different offset angles of the flying-off blade relative to the casing; and performing finite element calculation, analyzing a simulation result, and judging whether the working condition of the simulated deflection angle is a dangerous working condition or not. Compared with the prior art, the invention has the remarkable advantages that different deflection angles of blade loss relative to the casing under the real condition are considered during numerical simulation analysis of the containment of the casing, dangerous states under different deflection angles are analyzed, and the blade loss process under the real condition is simulated more truly.

Description

technical field [0001] The invention relates to aero-engine inclusive analysis, in particular to a casing inclusive analysis method for blade offset loss. Background technique [0002] Affected by Foreign Object Damage (FOD), High Cycle Fatigue (HCF) and Low Cycle Fatigue (LCF), high-speed rotating fans, compressors and turbine blades in aero-engines will inevitably break and fail. If the casing is not enough to contain the flying broken blades, the broken blades will damage the engine room, fuel tank, electrical control circuit and hydraulic pipeline after breaking through the casing, which will lead to loss of pressure in the engine room, fuel tank leakage and fire, electrical failure, and hydraulic mechanism failure. Action and other secondary damage, eventually leading to the crash of the aircraft. Therefore, at present, great attention is paid to the inclusiveness of engine blades, and there are special provisions in various specifications and regulations to make stric...

Claims

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Application Information

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IPC IPC(8): G06F30/15G06F30/17G06F30/23G06F119/02
CPCG06F30/15G06F30/17G06F30/23G06F2119/02
Inventor 陆楷楠郑广东刘璐璐罗刚赵振华陈伟
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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