Optimizing method of simplified model cooling structure of transition section

Abstract

The invention relates to an optimizing method of a simplified model cooling structure of a transition section. The method comprises the steps of building a double-cavity simplified model according to the function and structure characteristic of the transition section of a combustor of a gas turbine; providing optimally-designed initial similar model for modeling according to the commonly-used orthogonal design in engineering application; performing optimization analysis by the interior point method according to optimal model built based on the wall surface average temperature T and the minimum pressure P and the limitation; calculating the wall surface average temperature, minimum pressure and cooling efficiency of the transition section of the simplifying structure. With the adoption of the method, the demands on simple molding of the transition section structure and analyzing cooling performance in the gas turbine design stage can be met well; design people can be assisted to quickly extract the impact cooling characteristics of such structure, and therefore, the cockamamie works of the traditional finite element analysis and test can be avoided, and as a result, the quick performance evaluation and rapid modification of the primary design scheme can be achieved, and the design cycle is also reduced.

Description

technical field [0001] The invention relates to the field of gas turbine structure design, in particular to a cooling structure optimization method for a simplified model of a transition section. Background technique [0002] Gas turbine is the power machine with the most market application potential in modern times. Its thermal efficiency and power increase with the increase of gas temperature at the inlet of turbine blades. The high-temperature gas generated in the combustion chamber must pass through the transition section of the combustion chamber before reaching the turbine blades. As the temperature of the gas continues to increase, in order to prevent the surface of the transition section from being corroded by high temperature, an efficient cooling system must be designed to improve its cooling performance. Impingement cooling is the most widely used in the current wall cooling of the transition section of the combustion chamber. The high-speed fluid is used to direc...

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Problems solved by technology

As an important factor affecting cooling efficiency, impingement cooling holes have become one of the research hotspots of scholars at home and abroad. However, the existing research results mostly focus on specific structures such as air film cooling and turbine blades, and there is little research on the transition section structure. The angle of impact hole, the inclination angle of wind direction, etc. lack the reference results suitable for the impact cooling method of the transition section structure

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