Gas turbine stator blade and cooling structure thereof

Abstract

The invention discloses a gas turbine stator blade and a cooling structure thereof. The cooling structure comprises a first blade partition plate, a second blade partition plate spaced from the firstblade partition plate, a first cooling channel, a second cooling channel, a third cooling channel and an air film hole, wherein the first cooling channel, the second cooling channel and the third cooling channel are partitioned by the first blade partition plate and the second blade partition plate, and the air film hole communicates with the third cooling channel; and the ratio of the thickness delta1 of the first blade partition plate to T50% is 0.146-0.178, the draft angle theta1 ranges from -10 degrees to 10 degrees, the ratio of the thickness delta2 of the second blade partition plate toT50% is 0.146-0.178, and the draft angle theta2 ranges from -10 degrees to 10 degrees. The stator blade comprises an upper edge plate, the blade body and a lower edge plate, and the blade body comprises a blade suction surface, a blade pressure surface, a blade front edge, a blade tail edge and the blade cooling structure. The cooling effect is good, the pneumatic efficiency is high, and the requirements for blade cooling and cascade sealing can be met at the same time under the condition of less cold air.

Description

technical field [0001] The invention relates to the technical field of ground heavy-duty gas turbine blades, and in particular discloses a gas turbine stationary blade with good cooling effect and high aerodynamic efficiency and a cooling structure thereof. Background technique [0002] Gas turbine units are widely used in many fields such as ships and generator sets because of their advantages such as light weight, small size, fast start-up, and convenient control. It can be seen from the simple cycle mode of the gas turbine that the specific power and performance can be improved by increasing the initial temperature of the gas. The position where the turbine blades are located has high temperature, complex stress, and harsh working environment. Therefore, whether the turbine blades can work safely and reliably is very important for the operation of the gas turbine. The performance indicators of blades are also important indicators to measure the development level of gas t...

AI Technical Summary

Problems solved by technology

The cooling air of the low-pressure stage turbine stator blades comes from the air extraction in the middle stage of the compressor. The cooling air consumption of the blades has a great influence on the efficiency of the whole machine, so the cooling design of the blades is often limited by the amount of cooling air.

At the same time, because the high temperature area is concentrated in the leading edge and trailing edge of the blade, and in the trailing edge area of ​​the blade, it is difficult to arrange the cooling structure inside due to the limitation of the blade structure

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