Tt45 correction-based aeroengine starting control method and system

By real-time monitoring and correction of fuel supply parameters and optimization of fuel supply patterns, the problem of repeated oscillations after Tt45 reaches its limit during the start-up of aero engines was solved, improving the start-up success rate and reducing the risk of thermal suspension.

CN121854250BActive Publication Date: 2026-06-05AECC HUNAN AVIATION POWERPLANT RES INST
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Patent Information

Authority / Receiving Office
CN Β· China
Patent Type
Patents(China)
Current Assignee / Owner
AECC HUNAN AVIATION POWERPLANT RES INST
Filing Date
2026-03-18
Publication Date
2026-06-05

AI Technical Summary

Technical Problem

In existing aero-engine start-up control methods, the fuel supply acceleration is designed to be at its maximum value, which causes repeated oscillations after Tt45 reaches its limit, increasing the risk of thermal suspension and reducing the start-up success rate.

Method used

After real-time monitoring of Tt45 reaching its limit, fuel flow rate and Tt45 measurement values ​​are collected at multiple times. The fuel supply acceleration and deceleration are calculated and corrected, a temperature margin is reserved, the upper and lower limits of fuel flow are adjusted, and the fuel supply pattern is optimized.

Benefits of technology

By gradually slowing down the acceleration and deceleration rates, the Tt45 is prevented from hitting the limit again, thus improving the starting success rate and reducing the risk of hot suspension.

✦ Generated by Eureka AI based on patent content.

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Abstract

The application discloses an aero-engine starting control method and system based on Tt45 correction. After the Tt45 first touches the limit, the fuel supply acceleration before the limit and the fuel supply deceleration after the limit are calculated, and the fuel supply acceleration before the limit and the fuel supply deceleration after the limit are corrected, so that the fuel supply process after the limit and the fuel supply process after the limit are gradually slowed down. The gradual slowing down of the fuel supply process is beneficial to the full combustion of fuel, which can make ng quickly rise on one hand and effectively avoid the Tt45 from touching the limit again on the other hand. The gradual slowing down of the fuel supply deceleration can avoid the fuel flow from rapidly decreasing to the lower limit of the fuel flow after the Tt45 touches the limit again, so that the ng can be prevented from quickly decreasing after the Tt45 touches the limit again, the ng decreasing process after the Tt45 touches the limit again is delayed, the risk of thermal suspension of the Tt45 after touching the limit in the engine starting process is reduced, and the starting success rate is improved.
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Citation Information

Patent Citations

  • Low-pressure turbine noise test method and improved method thereof

    CN108760329A

  • Method for limiting turbine rear temperature in aeroengine starting process

    CN111927636A