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Reverse design method of rotor structure dynamics based on failure genes

A technology of rotor structure and reverse design, applied in computing, special data processing applications, instruments, etc., to achieve the effect of saving development costs, reducing possibilities, and shortening development cycles

Active Publication Date: 2017-08-18
NORTHWESTERN POLYTECHNICAL UNIV
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Problems solved by technology

[0010] In order to overcome the problem that in the current design method of aero-engine structural dynamics, the design conditions are only normal working conditions, the present invention proposes a reverse design method of rotor structural dynamics based on fault genes

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  • Reverse design method of rotor structure dynamics based on failure genes
  • Reverse design method of rotor structure dynamics based on failure genes
  • Reverse design method of rotor structure dynamics based on failure genes

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Embodiment Construction

[0049] This embodiment is a method for reverse design of rotor structure dynamics based on fault genes proposed for a certain type of engine rotor failure simulation experimenter, and the design of the rotor experimenter is carried out on an existing test bench. Such as Figure 2a , 2b As shown, the guide groove 1 on the test bench is used to embed the support 2, but it is difficult to accurately control the misalignment in the horizontal direction, and the resulting horizontal offset can reach up to 10mm. This method is used to design the rotor to improve the tolerance of the rotor to misalignment faults. The specific process is:

[0050] Step 1: Determining the initial structure of the aeroengine rotor

[0051] Preliminary design of the mechanical characteristics of the initial structure of the aeroengine rotor. Simplify the rotor structure to image 3 The single-span double-disc rotor model shown in the figure, l is the length of the rotor shaft 4, l 1 is the span of ...

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Abstract

The invention discloses a reverse design method of rotor structure dynamics based on failure genes. The method comprises the steps of designing an initial rotor structure according to rotor speed and power function design requirements to obtain a critical speed and a vibration mode, performing failure gene screening, establishing a failure gene pool of a rotor-supporting system, determining a dominant gene of the initial rotor structure and an expression of the dominant gene, estimating failure response of a dominant failure of the initial rotor structure, adjusting rotor structure parameters according to genetic factors if the failure response is prominent, and estimating the failure response again till a requirement is met. According to the method, a potential vibration failure is preestimated in a design process, and structure adjustment and optimization are performed on a specific failure, so that the possibility of failure occurrence is reduced to the greatest extent; the containment capacity of a design result of aeroengine structure dynamics to a typical failure is improved; a direction is pointed for characteristic optimization of rotor dynamics; a development cycle of a rotor system is shortened; and the development cost is saved.

Description

technical field [0001] The invention relates to the field of aero-engine dynamics design, and relates to a design method for aero-engine rotor structure dynamics. [0002] technical background [0003] Structural dynamics design is an important content in aeroengine design. If the design is improper, it will cause the vibration of the whole machine to exceed the standard, which will bring about reliability problems of the aero-engine. Even cause structural damage to components, resulting in flight accidents. [0004] The structural dynamics design of aero-engines in the past mainly adopts the idea of ​​forward design, that is, the design point is the normal working condition of the rotor. The current design process is: starting from the overall parameters of the engine, the preliminary design of the rotor structure is carried out, and then the dynamic characteristics under normal conditions are calculated to obtain the critical speed and mode shape of the engine. After the...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/17Y02T90/00
Inventor 王俨剀廖明夫王鑫程盼李波邓炜坤
Owner NORTHWESTERN POLYTECHNICAL UNIV
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