A worm wheel blade surface air film hole optimization structure and a detection tool and method thereof

By designing air film pores on the surface of turbine blades to optimize the structure and testing fixtures, the problems of uneven air film cooling, insufficient structural strength, and testing difficulties have been solved. This has resulted in improved cooling effect, enhanced structure, and improved testing accuracy, ensuring efficient cooling and safety of turbine blades.

CN121932241BActive Publication Date: 2026-06-05TIANKAI (TIANJIN) AVIATION POWER TECH CO LTD
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Patent Information

Application Number
CN202610405048.3
Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
Filing Date
2026-03-31
Publication Date
2026-06-05
Estimated Expiration
2046-03-31

AI Technical Summary

Technical Problem

Existing turbine blade film cooling structures suffer from problems such as uneven film coverage that is easy to peel off, insufficient blade structural strength, low efficiency of cooling gas utilization, and outdated detection methods, resulting in poor cooling performance and safety hazards.

Method used

An optimized structure for the film gas pores on the surface of a worm gear blade is designed, including film gas pores on the pressure-bearing side facing the trailing edge, internal support ribs and blade tip baffles. Combined with a detection fixture, the actual working state is simulated through a turbine disk and a mounting shaft, and colored smoke detection is used.

Benefits of technology

It achieves a significant improvement in cooling effect, enhanced structural strength, maximized utilization of cooling gas, and improved detection accuracy, ensuring the high-temperature tolerance of the blades and the consistency of product quality.

✦ Generated by Eureka AI based on patent content.

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Abstract

This invention relates to an optimized structure for film cooling holes on the surface of a worm gear blade, along with its testing fixture and method. The structure includes a fixed base and a blade body. The fixed base has an air inlet on one side and a connecting tenon at the bottom. One side of the blade body is a concave pressure-bearing side, and the other side is a convex back-pressure side. Several sets of film cooling holes are formed on the pressure-bearing side, all facing the trailing edge of the blade body. The blade body has an internal cavity with several supporting ribs that divide the cavity into several flow channels. Each set of film cooling holes is connected to a corresponding flow channel, and each flow channel is connected to the air inlet. A blade tip baffle is fixedly installed on the top of the supporting ribs. The testing fixture of this invention includes components such as a turbine disk, a front fixing ring, a front retaining ring, a rear fixing ring, a rear retaining ring, and a mounting shaft. By inputting colored smoke into the main air passage on the mounting shaft, the flow state of the gas on the blade surface is observed, and the product is classified according to quality. This invention improves the blade cooling efficiency and service life.
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Citation Information

Patent Citations

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  • Turbine blade with air film hole cooling structure based on eddy current effect

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    CN114810216A

  • Combined film hole and turbine blade

    CN115434757A

  • Molded metallic blade and manufacturing process for the blade

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