METHOD FOR REGULATING AN AVIATION TURBOJET TWO-CIRCUIT ENGINE Russian patent published in 2022 - IPC F02C9/28 

FIELD: aviation technology.

SUBSTANCE: invention relates to methods for regulating a turbojet engine to ensure that the rotational speeds of low- and high-pressure rotors and the temperature of gases behind the turbine in the engine regulator do not exceed the maximum permissible values. A method for regulating an aviation turbojet two-circuit engine, in which, previously for this type of engines with a standard program for maintaining operational limits of maximum values of low (n_1LIM) and high-pressure (n_2LIM) rotor speeds and the temperature of gases behind the turbine (T_4LIM) at maximum engine operation mode, a program for limiting the low-pressure rotor speed (n_1LIM) is formed, as well as a program for limiting the rotation speed of the low-pressure rotor with an increase by 1% relative to the original (n_1LIM+1%), then, a representative number of samples of engines of this type are tested, in which the rotation speed of the low- and-high pressure rotor and the temperature of gases behind the turbine are measured at the maximum mode with the programs n_1LIM (n₁, n₂, T₄) and n_1LIM+1% (n_1+1%, n_{2+ 1%}, T_4+1%), then the change in the rotation speed of the high-pressure rotor and the change in the temperature of the gases behind the turbine are determined by the formulas: (Δn₂=n_2+1%/n₂); (ΔT₄=Τ_4+1%/T₄), then for an engine that has at least one of the following exceeded at maximum mode during the standard program values (n_1LIM), (n_2LIM), (T_4LIM), the rotation frequency of the low-pressure rotor (n_1INI), the rotation frequency of the high-pressure rotor (n_2INI) and the temperature of the gases behind the turbine (T_4INI) are measured at maximum mode, then the relative magnitude of the deviation of the initial parameter (n_1LIM), (n_2LIM), (T_4LIM) is determined from the limit setting δn₁ according to the formulas:

,

,

, then the smallest value is selected from δn₁ (by n1), δn₁ (by n2) and δn₁ (by T4) by absolute value, which is then taken as δn₁, then the formulas determine the settings of the limitations of the rotation frequencies of the rotors of low (n_1SET) and high pressure (n_2SET) and gas temperature for turbine (T_4SET): n_1SEY=n_1ИINI*(1+δn₁); n_2SET=n_2INI*(1+Δn₂*δn₁); T_4SET=T_4INI*(1+Δt₄*δn₁), on the basis of which the standard program for maintaining the operational limits of the maximum values of the rotational speeds of the rotors of low and high pressure and the temperature of gases behind the turbine is adjusted at the maximum operating mode of the engine.

EFFECT: invention provides an increase in the reliability of engine operation during a given resource.

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