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Multi-objective optimization method for turbine gas collection cavity structure

A multi-objective optimization, air collecting chamber technology, applied in the field of turbine air collecting chamber, can solve problems such as uneven outflow flow, and achieve the effect of small calculation load, high precision and reduced sensitivity

Pending Publication Date: 2021-06-11
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS +1
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The flow coefficient of the cold air delivered by the air collection chamber and the unevenness of the cold air flow are two main indicators for evaluating the performance of the air collection chamber. However, the increase of the flow coefficient may be accompanied by a more uneven flow rate

Method used

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  • Multi-objective optimization method for turbine gas collection cavity structure
  • Multi-objective optimization method for turbine gas collection cavity structure
  • Multi-objective optimization method for turbine gas collection cavity structure

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Experimental program
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Embodiment Construction

[0059] The multi-objective optimization method for the turbine air collection cavity provided by the present invention will be described in detail below in conjunction with the figures and specific implementation examples.

[0060] Step 1. Select the axial distance between the inlet and outlet, the inlet diameter, the circumferential angle between the inlet and outlet, and the inclination angle of the intake duct as the parameters to be optimized for the structure of the gas collection cavity; determine the optimization range of the parameters to be optimized: the optimal range of the inlet diameter is 30 ~46mm, the optimal range of the circumferential angle between the inlet and outlet is 0~8°, the optimal range of the axial distance between the inlet and outlet is 0~40mm, and the optimal range of the inclination angle of the intake duct is 20~90°.

[0061] Step 2. According to the experimental plan in Table 1, the axial spacing of the inlet and outlet, the diameter of the inl...

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Abstract

The invention discloses a multi-objective optimization method for a turbine gas collection cavity structure, which comprises the following steps: selecting to-be-optimized parameters of the gas collection cavity structure, and determining an optimization range of the to-be-optimized parameters; constructing a fitness function by taking the maximum flow coefficient and the minimum outflow unevenness as optimization targets; performing a variable working condition experiment to prepare a data sample of the support vector machine; establishing a support vector machine agent model of the gas collection cavity based on the training sample; and optimizing the gas collection cavity structure by using a chaos optimization algorithm, and determining the optimal value of the to-be-optimized parameter. The multi-objective optimization method overcomes the defects of an existing single-objective optimization method of the gas collection cavity, and the multi-objective optimization method which is high in proxy model precision, high in global optimization capability and high in robustness is provided.

Description

technical field [0001] The invention belongs to the technical field of turbine air collection chambers, in particular to a multi-objective optimization method suitable for the structure of turbine air collection chambers. Background technique [0002] Low fuel consumption, high thrust-to-weight ratio, high reliability and durability are the development trends of modern aviation gas turbine engines. In order to obtain higher performance and efficiency of the aero-engine, it is necessary to increase the temperature of the gas in front of the turbine, which also seriously intensifies the heat load on the turbine blades. At this stage, the limit temperature that the alloy materials of aero-engine turbine blades can withstand is much lower than the gas temperature before the turbine, so the research on efficient and high-performance cooling of turbine blades and aero-engine hot-end components is very important. [0003] The air collection chamber is an important part of the conf...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/27G06F30/17G06N20/10G06F111/06
CPCG06F30/27G06F30/17G06N20/10G06F2111/06
Inventor 王春华王振宇聂俊领张靖周
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS