A high-efficiency gas turbine final guide vane with controlled reaction degree distribution

Abstract

The invention discloses a high-efficiency gas turbine last-stage guide vane for controlling reaction degree distribution, comprising: an upper edge plate, a blade body, a lower edge plate, an upper cover plate, a draft pipe, and a lower cover plate. The shape line of the airfoil is a twisted blade with variable section, and there is a relative twist between two adjacent sections, and the pitch and chord length from the root section to the top section of the airfoil, the axial width of the airfoil section, and the maximum thickness of the airfoil section And the cross-sectional area of ​​the airfoil has an optimized ratio range. The final guide vane of the present invention has the advantages of high aerodynamic efficiency, good strength and vibration performance, etc., and is suitable for a wide working environment temperature range.

Description

technical field [0001] The invention relates to the field of ground heavy-duty gas turbine turbine blades, in particular to a high-efficiency gas turbine final-stage guide vane for controlling reaction degree distribution. Background technique [0002] Gas turbine units are widely used in ships, generator sets and many other fields because of their advantages of light weight, small size, fast start-up, and convenient control. However, the working environment temperature of the turbine guide vanes is high, and the flow state of the working fluid is complicated. In the prior art, the blade profile design cannot control the degree of reaction well, thereby affecting the efficiency. [0003] Generally speaking, the gas turbine turbine final guide vane has the largest working height and end wall expansion angle among the turbine guide vanes of each stage. The large working height of the blade body will increase the difficulty of the reasonable distribution of the control paramet...

AI Technical Summary

Problems solved by technology

A large working height of the blade body will increase the difficulty of controlling the reasonable distribution of parameters along the radial direction. For example, when using the traditional flow pattern with equal outlet angle, it will cause a large difference in the reaction degree between the root and the top of the blade, too high or too low Both the degree of reaction will affect the aerodynamic efficiency; moreover, when the gas turbine operates under partial load, the degree of reaction at the root of the last stage of the turbine is easily reduced to a negative degree of reaction, which will worsen the flow condition at the root and reduce the efficiency of the cascade

In addition, a large end wall expansion angle is likely to cause flow separation and reduce aerodynamic efficiency

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