Turbine guide vane end wall composite cooling structure

Abstract

The invention discloses a turbine guide vane end wall composite cooling structure. Multiple rows of first air film holes are included, the first air film holes are formed in a guide vane end wall at intervals, the guide vane end wall is connected with an impact plate through an impact cavity leading edge side plate and an impact cavity trailing edge side wall, multiple rows of impact holes are formed in the impact plate, and the impact holes and the first air film holes are arranged in a staggered manner. Second air film holes are formed in the impact cavity trailing edge side wall, cooling air impacts the inner side of the guide vane end wall through the impact holes to form impact transverse flow, and the impact transverse flow achieves end wall external air film cooling and secondary cooling of the downstream end wall through the first air film holes and the second air film holes. Performance improvement of internal impact cooling and external air film cooling of the end wall is taken into consideration, the synergistic effect of internal impact cooling and external air film cooling is brought into full play, the comprehensive cooling performance of the end wall is effectively improved, meanwhile, the secondary cooling effect of cold air to the downstream moving vane end wall is utilized, the cold air use amount of the end wall is reduced, and the overall performance of an aero-engine is improved easily.

Description

technical field [0001] The invention belongs to the technical field of blade cooling, and in particular relates to a composite cooling structure of a turbine guide vane end wall. Background technique [0002] As the turbine inlet temperature of advanced aero-engines continues to increase and the outlet temperature of the high-efficiency and low-emission combustion chamber becomes more flat along the blade span, the high-pressure turbine end wall, especially the first-stage guide vane end wall, is facing increasingly severe high-temperature ablation problems. Therefore, an efficient cooling structure must be designed for the end wall for thermal protection. However, in the cascade channel, the flow structure near the end wall is very complex, and there are complex and diverse strong three-dimensional secondary flows, which bring huge technical challenges to the cooling structure design of the end wall. In the early days, end wall cooling technology generally used a single ex...

AI Technical Summary

Problems solved by technology

However, in these common layout methods, the outlet pressure of each exhaust membrane hole is quite different. If it is used together with internal impingement cooling, it will lead to very uneven output of cold air, which will degrade the performance of internal impingement cooling. At the same time, the external air The performance of film cooling also degrades

In terms of impingement cooling inside the end wall, the biggest defect of traditional impingement cooling is that the cross flow formed by the impingement jet will deflect the impingement jet downstream of the cross flow, which will reduce the heat transfer level of the impingement cooling. Therefore, the development of an impingement cooling structure that can effectively prevent the cross flow from affecting Improving the performance of impingement cooling is critical

The existing one is to extend the impingement hole into the impingement cavity on the simple flat model to prevent the deflection of the cross flow, but the extended impingement cooling structure and the film cooling layout are co-designed and applied to the high-efficiency composite cooling of the turbine guide vane end wall The cooling structure has not been reported yet

Images