A turbine blade film cooling structure with pre-swirl function and gradient aperture

By introducing a pre-swirl function and a gradient aperture film cooling structure on the turbine blades, active regulation and flow matching of the cooling airflow are achieved, solving the problems of low cooling efficiency and poor structural reliability in the existing technology, and improving the cooling effect and overall performance of the turbine blades.

CN122304820APending Publication Date: 2026-06-30AVIC GUIYANG ENGINE DESIGN & RES INST
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
AVIC GUIYANG ENGINE DESIGN & RES INST
Filing Date
2026-04-28
Publication Date
2026-06-30

AI Technical Summary

Technical Problem

Existing film cooling structures for turbine blades suffer from problems such as difficulty in improving cooling efficiency, insufficient ability to control the direction of cooling airflow, mismatch between cooling airflow distribution and blade surface heat load distribution, and insufficient structural reliability.

Method used

The turbine blade film cooling structure, which employs pre-swirl function and gradient aperture, imparts circumferential rotational momentum at the source of the cooling gas. By utilizing the design of the pre-swirl chamber, stepped orifice, and outlet recess, it achieves active regulation of the cooling airflow and on-demand distribution of the flow rate, forming a protective flow field.

Benefits of technology

It significantly enhances the film adhesion performance and spanwise diffusion capability, improves cooling efficiency and structural reliability, optimizes cooling efficiency and overall cycle efficiency, and extends the service life of turbine blades.

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Abstract

This invention discloses a film cooling structure for turbine blades with pre-swirl function and gradient aperture, belonging to the field of cooling technology for hot-end components of aero-engines and gas turbines. The structure includes film cooling holes penetrating the turbine blade wall, which are integrated along the cooling airflow direction as a pre-swirl chamber, stepped holes, a transition section, and an outlet recess. A helical guide plate is installed within the pre-swirl chamber to actively guide the cooled air into a circumferential rotating flow; the aperture of the stepped holes decreases gradually along the flow direction to achieve precise matching between the cooled air flow rate and the heat load on the blade surface; the outlet recess captures the rotating jet and forms a local low-speed recirculation zone to stabilize the film cooling system and block high-temperature combustion gases. This invention effectively solves the technical problems of easy film blow-off and uneven spanwise coverage in existing technologies by actively controlling the momentum direction of the cooled air from the source, and achieves a synergistic improvement in cooling efficiency and structural reliability through gradient flow distribution and stress dispersion design.
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