Turbine blade and gas turbine

By setting inclined suction and pressure ribs at the tip of the turbine blades to form a flow guide groove, the problem of leakage flow at the tip of the turbine blades is solved, and the aerodynamic efficiency and overall performance of the turbine are improved.

CN121205723APending Publication Date: 2025-12-26AECC COMML AIRCRAFT ENGINE CO LTD
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Patent Information

Application Number
CN202410824491.5
Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
Filing Date
2024-06-24
Publication Date
2025-12-26

AI Technical Summary

Technical Problem

Existing turbine blade tip leakage flow leads to reduced turbine aerodynamic efficiency, and existing tip structures have limited effectiveness in reducing leakage flow.

Method used

A turbine blade is designed by setting inclined suction side ribs and pressure side ribs at the blade tip to form suction side grooves and pressure side grooves, thereby increasing the inlet turning angle of the leakage flow, reducing the flow area between the top surface of the rib and the casing, and guiding the high-temperature gas to the trailing edge of the blade tip through the grooves, thus reducing the amount of leakage fluid.

Benefits of technology

It effectively reduces turbine tip leakage flow, improves turbine efficiency, reduces losses, and increases the amount of gas that provides useful work.

✦ Generated by Eureka AI based on patent content.

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    Figure CN121205723A_ABST
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Abstract

The invention provides a turbine blade and a gas turbine. The turbine blade includes a blade body. The blade body comprises a suction surface, a pressure surface, a suction side rib and a pressure side rib; the suction side rib is arranged on the suction surface at the blade tip of the turbine blade, the pressure side rib is arranged on the pressure surface at the blade tip of the turbine blade, and the suction side rib and the pressure side rib form a blade tip groove; the turbine blade further comprises an outer blade top face arranged at the blade tip of the turbine blade. The bottom edge of the suction side rib is connected with the blade top edge of the suction surface through the outer blade top surface, and the bottom edge of the pressure side rib is connected with the blade top edge of the pressure surface through the outer blade top surface; the suction side rib inclines from the outer blade top face to the suction face and forms a first included angle with the outer blade top face, and a suction side groove is formed between the outer side face of the suction side rib and the blade top face. The pressure side rib inclines from the outer blade top face to the pressure face to form a second included angle with the outer blade top face, and a pressure side groove is formed between the outer side face of the pressure side rib and the blade top face. According to the turbine blade, the blade tip leakage flow can be reduced.
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Citation Information

Patent Citations

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    CN110945210A

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    CN115964817A

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    CN223839199U

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