Turbine integrated transition section blade and design method thereof

By optimizing the design working conditions and blade type parameters of the turbine integrated transition section blades, the problem of angle separation caused by high Mach number of high-pressure turbine outlets is solved, and a low loss and high efficiency transition section design is achieved, meeting the engine performance indicator requirements and shortening the engine length.

CN119754862AActive Publication Date: 2025-04-04ZHEJIANG UNIV
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Patent Information

Application Number
CN202411949066.5
Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
Filing Date
2024-12-27
Publication Date
2025-04-04
Estimated Expiration
2044-12-27

AI Technical Summary

Technical Problem

The existing turbine integrated transition section blade design is likely to lead to angle separation when the Mach number of high-pressure turbine outlets is high, resulting in large losses in the transition section and cannot meet the engine performance indicator requirements.

Method used

Determine the inlet flow parameters through the design working conditions, determine the leaf type parameters along the radial distribution, including the number of blades, the leaf type cross-sectional height, the inlet structural angle, etc., optimize the blade chord length and large blade design to reduce the residence time of the rapid deceleration of the airflow and adapt to the drift time of the drastic changes in the channel area.

Benefits of technology

The goal of low total pressure loss and high aerodynamic efficiency when the Mach number of the high-pressure turbine outlet is achieved, with both structural and pneumatic functions, effectively shortening the axial length of the engine and reducing weight.

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Abstract

The invention discloses a turbine integrated transition section blade and a design method thereof, and relates to the technical field of gas turbine engines, and the design method comprises the following steps: S1, determining corresponding inlet incoming flow parameters based on design working conditions; s2, according to given inlet incoming flow parameter changes, the distribution of different blade profile parameters in the radial direction is correspondingly designed, and then the blade profile of the blade of the transition section is determined; s3, the chord length of the blade with the blade height being 0.5 or above the cross section is lengthened; and S4, designing a turbine integrated transition section large blade. Under strong inlet non-uniform incoming flow (the Mach number is sharply increased on the middle upper portion of the blade along the way), the purposes of low total pressure loss and high pneumatic efficiency can be achieved, the structure and pneumatic functions are integrated, the axial length of an engine is effectively shortened, and the weight is effectively reduced.
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