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Turbine gas thermal performance uncertainty visual analysis method and system

A technology of uncertainty and analysis method, applied in the field of turbine blade tip cooling system design, it can solve the problem of uncertainty quantitative calculation of non-data sets, and achieve the effects of easy calculation convergence, improved calculation efficiency, and improved use efficiency

Active Publication Date: 2021-08-06
XI AN JIAOTONG UNIV
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  • Claims
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Problems solved by technology

It is impossible for traditional serial logic and deterministic algorithms to perform uncertainty quantification calculations on such a huge data set

Method used

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  • Turbine gas thermal performance uncertainty visual analysis method and system
  • Turbine gas thermal performance uncertainty visual analysis method and system
  • Turbine gas thermal performance uncertainty visual analysis method and system

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Embodiment Construction

[0041] The implementation of the present invention will be described in detail below in conjunction with the drawings and examples.

[0042] Example: Uncertainty visual analysis of gas-thermal characteristics for GE_E3 leaf shape. The geometric parameters of GE_E3 leaf shape are shown in Table 1.

[0043] Table 1 Geometric parameters of GE_E3 leaf shape

[0044] geometry parameter name value The coordinates of the starting point of the middle arc (40.00,13.57,-33.74) End point coordinates of the middle arc (124.80,-60.60,-33.74) Leaf height / mm 122.0

[0045] refer to figure 1 In this embodiment, the gas-heat performance uncertainty visual analysis system of the turbine is based on the data mining algorithm and the polynomial chaos method, specifically including:

[0046] 1. The multinomial chaotic expansion model and the sample point distribution generation module input the random variables to be studied to generate the sample point distribu...

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Abstract

The invention discloses a turbine gas thermal performance uncertainty visualization analysis method and system. The method comprises the following steps: carrying out mathematical modeling through a polynomial chaos theory, generating a to-be-solved polynomial chaos expansion, generating to-be-calculated sample point distribution data based on a Symolak sparse grid technology, mapping the uncertainty characteristics of a system to a polynomial chaos expansion coefficient, acquiring an initial field of a to-be-solved sample, carrying out turbine gas-heat performance numerical calculation, carrying out Hill sorting preprocessing on calculation result data, carrying out clustering analysis to gather grid nodes representing the same spatial position in all samples into one class, then solving class center coordinates, calculating turbine gas-heat parameters on the class center coordinates, and finally, calculating to obtain the mean value and deviation of the turbine gas-heat parameters on each class core and the sensitivity of the turbine gas-heat performance on each class core to each input variable. The uncertainty quantification of the turbine blade tip gas thermal performance can be carried out, and the research work of turbine designers is guided.

Description

technical field [0001] The invention belongs to the technical field of turbine blade top cooling system design, and in particular relates to a method and system for visually analyzing the uncertainty of turbine gas-thermal performance. Background technique [0002] The continuous increase in the inlet temperature of modern gas turbines requires the cooling system of turbine blades to have higher reliability. However, due to the unavoidable manufacturing tolerance and the extremely harsh working conditions of the turbine, the geometrical parameters of the turbine blade tip and the operating conditions of the turbine have random uncertainty distribution characteristics. According to Montomoli F, MassiniM, Salvadori S. Geometrical uncertainty In turbomachinery:Tip gap and filletradius[J].Computers&Fluids,2011,46(1):362-368.), these geometric and operating condition deviations will significantly change the flow field shape of the blade tip and affect its aerodynamic and The hea...

Claims

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Application Information

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IPC IPC(8): G06F30/27G06F30/28G06K9/62G06N7/08G06N3/12G06F30/23G06F111/10G06F113/08G06F119/14G06F119/08
CPCG06F30/27G06F30/28G06N7/08G06N3/126G06F30/23G06F2111/10G06F2113/08G06F2119/14G06F2119/08G06F18/231G06F18/24147
Inventor 李军黄明李志刚张垲垣姜世杰
Owner XI AN JIAOTONG UNIV
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