Persistent test run low-pressure turbine outlet fuel gas temperature control method and device

Through simulation, the proportion of the time of the gas temperature range of the low-pressure turbine outlet is determined and the lasting test run time is allocated, and the engine operation is controlled, which solves the problem of mismatch between the assessment and thermal load during actual use, and achieves reasonable assessment and actual engine use support.

CN119641496AActive Publication Date: 2025-03-18NORTHWESTERN POLYTECHNICAL UNIV +1
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Patent Information

Application Number
CN202411832042.1
Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
Filing Date
2024-12-12
Publication Date
2025-03-18
Estimated Expiration
2044-12-12

AI Technical Summary

Technical Problem

During the long-lasting test run, the gas temperature requirements for the low-pressure turbine outlet of the assessment and test are too high, exceeding the normal operating temperature range of the high-temperature components of the engine, resulting in the assessment that does not match the thermal load during actual use and is too strict.

Method used

Through simulation, the proportion of the gas temperature ranges in different low-pressure turbine outlets during the large-state working time of the engine, and the long-lasting test run time is allocated based on these proportions, the engine working speed and nozzle area are controlled, so that the engine can continue to operate within the specified low-pressure turbine outlet gas temperature range.

Benefits of technology

It effectively matches the thermal load during assessment and actual use, avoids too strict assessment, and supports the use of the engine's field flight.

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Abstract

The invention belongs to the technical field of engine tests, and relates to a persistent test run low-pressure turbine outlet gas temperature control method and device, and the method comprises the steps: S1, determining a plurality of persistent test run gas inlet temperatures according to an engine flight mission profile given by a demand side; s2, determining the large-state working time of the engine corresponding to each persistent test run air inlet temperature; s3, for each persistent test run air inlet temperature, the time proportion of different low-pressure turbine outlet gas temperature ranges in the large-state working time of the engine is determined through simulation; s4, for the given large-state lasting test run time at different air inlet temperatures, performing duration distribution according to a time proportion; and S5, the working rotating speed and the nozzle area of the engine are controlled, so that the engine continuously operates for the distributed duration within the specified low-pressure turbine outlet gas temperature range. According to the method, the problem that the exam test is not matched with the actual use thermal load in the persistent test run process is solved.
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