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Burst speed simulative analysis method for bolt-free structure turbine disk baffle

A technology of fracture speed and simulation analysis, applied in design optimization/simulation, special data processing applications, instruments, etc., can solve problems such as insufficient baffle strength reserve, baffle damage failure, loss of positioning or fastening, etc., to reduce damage The risk of failure, the reduction of hidden troubles, and the effect of improving technical quality

Inactive Publication Date: 2016-04-13
SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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  • Abstract
  • Description
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  • Application Information

AI Technical Summary

Problems solved by technology

Because its connection is not as stable and reliable as the bolt structure, if the strength reserve of the baffle is insufficient, or the positioning or fastening is lost during work, it may cause damage to the baffle.

Method used

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  • Burst speed simulative analysis method for bolt-free structure turbine disk baffle
  • Burst speed simulative analysis method for bolt-free structure turbine disk baffle
  • Burst speed simulative analysis method for bolt-free structure turbine disk baffle

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Embodiment Construction

[0042] The present invention will be further elaborated below in conjunction with the accompanying drawings of the description.

[0043] Such as figure 1 As shown, the simulation analysis method of the rupture speed of a kind of boltless structure turbine disc baffle of the present invention comprises the following steps:

[0044] Establish a two-dimensional cross-sectional model that can accurately reflect the overall blisk structure;

[0045] Set up the elastic material model;

[0046] Create axisymmetric units and plane stress units based on model features;

[0047] Set boundary conditions and loads;

[0048] Calculate solver parameters;

[0049] Judging whether the calculation and solution process is convergent;

[0050] If the solution process converges, the post-processing outputs the stress calculation results;

[0051] The rupture speed of the baffle is calculated according to the rupture criterion.

[0052] If the solution procedure does not converge, return to...

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Abstract

The invention relates to a burst speed simulative analysis method for a bolt-free structure turbine disk baffle. The method comprises the following steps: establishing a two-dimensional section model capable of accurately reflecting a blisk structure form; arranging an elastic material model; according to model features, creating an axial symmetric unit and a plane stress unit; setting a boundary condition and a load; calculating solving parameters; judging whether a solving process is converged or not; if the solving process is converged, performing post-processing to output a stress calculation result; and according to a burst criterion, calculating a baffle burst speed. According to the method, the burst speed simulative analysis is carried out for the bolt-free structure baffle, so that the baffle is ensured to work safely and reliably within a design speed range, the hidden troubles of faults in aero-engine design are reduced, and decision bases and technical support are provided for analyzing occurred engine shroud faults.

Description

technical field [0001] The invention relates to a simulation analysis technology for the structural strength of an aero-engine, in particular to a simulation analysis method for a rupture speed of a boltless structure turbine disk baffle. Background technique [0002] The connection form between the turbine disk and the front and rear baffles of early aero-engines is usually bolted connection. Although this connection is simple and reliable, it needs to process bolt holes on the turbine disk and baffle, which reduces the low circulation of related parts. fatigue life. The boltless connection structure between the turbine disk and the baffle is one of the key structural design technologies for high thrust-to-weight ratio and long-life gas turbine engines. It has the advantages of no or less holes on the turbine disk. Once the positioning and fastening of the baffle loses its positioning or fastening, the centering relationship is destroyed, which will inevitably lead to a sh...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/23G06F2117/06
Inventor 侯东旭陈勇黄兴刘志张勇
Owner SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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