FIELD: aviation.
SUBSTANCE: invention relates to aircraft engine building, particularly, to testing of gas turbine engines (GTE). When implementing the proposed method, the gas turbine engine is brought to maximum operating conditions. For a motor with an uncontrolled jet nozzle prior to testing for at least three main controlled parameters characterizing engine operation at maximum mode, the boundary of their maximum and minimum allowable values is set, based on its design features; further during the tests, each of the selected main controlled parameters is measured at the maximum mode determined by the rotor rpm and at least four modes close to it; then performing revaluation of selected parameters and rotor rpm with construction of dependence of specified selected parameters on reduced rotor rpm, at that rotor axis is covered with boundaries defined by maximum and minimum values from used modes; for the specified selected engine parameters, also the boundaries of their maximum and minimum permissible values established earlier; further determining required rotor rpm, which satisfies condition of simultaneous finding of all specified selected parameters, corresponding to this required frequency, within their limits of allowable values; then obtained rotor rpm and corresponding selected parameters are entered into engine controller; if the frequencies satisfying the condition are several, then the dependence of specific fuel consumption on the specified rotor rpm is additionally constructed and the frequency at which the least specific fuel consumption is realized is selected; if rotor rpm does not meet the condition, uncontrolled jet nozzle is dismounted from engine and nozzle is installed with other geometrical characteristics, after which all test stages are repeated.
EFFECT: optimization of traction-and-economic characteristics of the engine with an uncontrolled nozzle and high accuracy of determining parameters.
4 cl, 1 dwg, 1 tbl
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Authors
Dates
2019-11-19—Published
2019-01-16—Filed