stator assembly

By designing an alternating distribution of non-overlapping root chords and overlapping tip chords in the stator assembly, the problem of insufficient blade root distance in turbine engines is solved, improving airflow straightening efficiency and reducing noise and engine mass.

CN116783117BActive Publication Date: 2026-03-03SAFRAN SA
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Patent Information

Application Number
CN202280009721.1
Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
Priority Date
2021-01-11
Filing Date
2022-01-04
Publication Date
2026-03-03
Estimated Expiration
2042-01-04

AI Technical Summary

Technical Problem

Existing stator assemblies present aerodynamic problems in turbine engines, requiring the maximization of blade root distance without increasing blade tip distance to reduce noise and improve airflow guidance efficiency.

Method used

Design a stator assembly such that the root chords of the stator blades do not overlap, while the tip chords overlap. By alternating the distribution of two sets of stator blades to increase the root distance while keeping the tip distance constant, the attachment of the blades at the hub is optimized.

Benefits of technology

It achieves an increase in blade root distance without increasing blade tip distance, reducing noise and improving airflow straightening efficiency, reducing engine main torque and mass, and providing more freedom in acoustic management.

✦ Generated by Eureka AI based on patent content.

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Abstract

Stator assembly for straightening an airflow, single-flow engine, double-flow engine and aircraft, the assembly comprising a plurality of stator vanes distributed around an axis of rotation of the stator assembly, for each stator vane, a chord of the stator vane taken at a root of the stator vane does not overlap a chord of an adjacent stator vane taken at a root of the adjacent stator vane in a direction of the axis of rotation, and a chord of the stator vane taken at a tip of the stator vane overlaps a chord of the adjacent stator vane taken at a tip of the adjacent stator vane in the direction of the axis of rotation.
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Citation Information

Patent Citations

  • TURBOMACHINE OUTLET AND BYPASS DIRECTOR VANES ASSEMBLY

    FR3090033A1

  • Turbomachine fan flow-straightener vane, turbomachine assembly comprising such a vane, and turbomachine equipped with said vane or with said assembly

    CN111108262A

  • A rotor blade for a gas turbine engine

    CN1607317A