FIELD: aviation.SUBSTANCE: invention relates to aircraft engineering and can be used in tests of aircraft with turbojet engines to determine the adequacy of oil cooling in design temperature conditions. Proposed method consists in performing flight at selected mode, during flight measuring fuel temperature at fuel-and-oil heat exchanger outlet (FOHE) and oil temperature at engine output, after flight determining parameters of mathematical model, determining fuel temperature at engine inlet under design temperature conditions and initial oil temperature at engine output, then, by successive approximations method, when solving system of differential equations, calculating maximum oil temperature at engine output and comparing it with maximum permissible temperature, if maximum oil temperature at engine outlet does not exceed maximum permissible temperature, conclusion is made on oil cooling sufficiency.EFFECT: technical result of invention makes it possible to increase reliability of determination of sufficiency of oil cooling in FOHE turbojet engine.1 cl, 2 dwg

Method of determining the sufficiency of cooling oil in a turbojet engine

FIELD: test technology.SUBSTANCE: invention relates to the aircraft engine building, and in particular to the gas turbine engines (GTE) testing methods. GTE testing method includes the parameters values adjustment to standard atmospheric conditions, taking into account of changes in the working fluid properties and the gas turbine engine flow part geometric characteristics with the atmospheric conditions changing. According to the invention, performing the engine testing at the selected engine operating mode at the same barometric pressures and the same air humidity with different air temperatures at the engine input, measuring the parameters at the number of air temperatures at the engine input, including t=+15 °C temperature, bringing them to the standard atmospheric conditions by the known method, calculating correction factors that take into account of changes in the engine particular type characteristics during the ambient temperature change: Ki=A/A, where Ais the parameter value measured at the air to the engine input temperature of t=+15 °C, Ais the parameter value measured at the air input temperature that differs from t=+15 °C, and brought to the standard atmospheric conditions, forming the correction factors dependences on the measured parameters from the air temperature at the engine input Ki=f(t), and during bringing parameters on the other engines, additionally multiplying the brought parameters values by the Ki coefficients.EFFECT: enabling the possibility of the test results more correctly bringing to the standard atmospheric conditions and increase in the test results representativeness.1 cl, 2 dwg, 2 tbl

Gas-turbine engine testing method

FIELD: engine building.SUBSTANCE: invention relates to aircraft engine building and can be used in electrohydromechanical systems for automatic control of gas turbine engines. Disclosed is a device for implementing a method of controlling position of guiding devices of a gas turbine engine compressor, including parametric identification of non-linearity of electrohydromechanical drive of "insensitivity" type in real time and compensation of nonlinearity, providing asymptotic stability of control and astatic accuracy of positioning of guide vanes of compressor with allowance for found nonlinearity parameters, comprising an electrohydromechanical drive and an automatic control and monitoring unit, comprising an electrohydromechanical drive control device and a nonlinearity compensator which performs conversion of the control device output signal by formulawhere Iis a control signal from the control device output; Iis the control current supplied to the input of the electrohydromechanical drive signal converter; N is maximum value of control current variation range; ΔZ=z-zis width of dead zone (specified in electro-hydromechanical drive certificate); d=(z+z)/2 is the dead zone center of hydromechanical system of electrohydromechanical drive, which is identified in real time by formulawhere Y(t) is a task by the position of the compressor guide apparatus; Y(t) is the actual position of the compressor guide vanes; d– current value d at time t1; e(t) is current error by the position of the compressor guiding device; k, g are tuning parameters depending on gas turbine engine operation mode.EFFECT: design of a method for controlling the position of guide vanes of a gas turbine engine compressor, providing asymptotic stability and astatic accuracy of positioning of guide vanes of a compressor taking into account non-linear characteristics of electrohydromechanical units.2 cl, 2 dwg

Control method of gas turbine engine

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

Test method of gas turbine engine

FIELD: engines and pumps.SUBSTANCE: invention relates to the field of aircraft engine construction, namely to methods for testing aviation gas turbine engines (GTE). GTE test method comprises pre-testing a representative number of engines of three to five in the selected engine operating mode, measuring the gas temperature in front of and behind the turbine at different positions of the angle of installation of guiding apparatus of the high-pressure compressor, determining the gas temperature change value in front of and behind the turbine when the position of the angle of installation of guiding apparatus of the high-pressure compressor changes, and measuring the gas temperature in front of and behind the turbine, during acceptance testing of the engine in the selected operating mode, and if the measured temperatures do not match the set values, the angle of installation of guiding apparatus of the high-pressure compressor is changed until the set gas temperature values reached in front of and behind the turbine.EFFECT: method provides the same operation mode of the gas generator on all manufactured engine samples, which will allow obtaining the same resource on all manufactured engine samples and preventing premature failure, malfunctions and repairs during operation.1 cl, 1 tbl

Method for testing a gas turbine engine

FIELD: airpower.SUBSTANCE: method for controlling an aircraft turbojet engine, in which two or more programs for adjusting the installation angles of the compressor guiding devices are formed in addition in the working range of the installation angles of the compressor guide devices in advance for this type of engine, depending on its reduced speed. During the flight of the aircraft, when switching to the cruising mode of the engine operation, the switching signal of the compressor control units is switched on depending on the reduced speed of the program, which ensures the minimum fuel consumption in the given thrust range.EFFECT: invention allows to increase the reliability of switching by the engine regulator to the control program of the compressor directing devices, which ensures a minimum fuel consumption in the given thrust range, during the transition to the cruising mode of the engine, and also allows to reduce fuel consumption in this mode.2 dwg, 1 tbl

Method for controlling an aircraft turbojet engine

FIELD: engines and pumps.SUBSTANCE: in the method, the parameters are brought to the standard atmospheric conditions taking into account the humidity of the ambient air, preliminary testing the engine with different atmospheric humidity, measuring the parameters of the engine under different atmospheric humidity, calculating the correction factors for the measured parameters, depending on the humidity of the ambient air and upon parameters reducing to standard atmospheric conditions multiplying the parameter values by coefficients taking into account the deviation of atmospheric air humidity from the standard one. The coefficients obtained are used to calculate engine parameters under different climatic conditions of specific areas of engine operation.EFFECT: increased representativeness of test results.2 tbl

Method of turbojet engine testing

FIELD: testing equipment.SUBSTANCE: testing method of turbojet engines (TJE) includes heating and air pressurization at the entrance to the engine. For the engine containing fuel-oil heat exchanger, previously create the engine mathematical model, adjust it according to the results of the tests of the representative number from three to five engines, define the fuel consumption according to mathematical model, supplied to heat exchanger on the specified mode under the given conditions of flight, and when testing the engine with air pressurization and heating at the inlet into the engine, provide the extra fuel supply to the fuel-oil heat exchanger with flow rate corresponding to the simulated flight conditions.EFFECT: provision of optimum temperature and oil consumption values during testing and increase of its results reliability.1 dwg

Testing method of aviation turbojet engine

FIELD: airpower.SUBSTANCE: method of testing an aviation gas turbine engine, which includes running-in of parts and assemblies in stationary and transient modes in the process of bearer testing of the engine. To run-in the engine at negative ambient temperatures, the diameter of the critical section of the jet nozzle and the installation angle of the high-pressure compressor guiding devices are reduced to achieve the set values of the high-pressure rotor speed and the gas temperature in front of the turbine and open the air samplings to the aircraft systems.EFFECT: invention allows to conduct bearer tests at any air temperature at the entrance to the engine with the possibility of running-in the gas turbine engine in stationary and transient modes in the winter season at negative temperatures of the air at the entrance to the engine.1 cl

Method of testing aviation gas turbine engine

FIELD: engine devices and pumps.SUBSTANCE: expected technical result is achieved by the fact that in the known method of controlling the aircraft jet turbine engine, which includes maintaining the preset rotational speeds and gas temperature behind the turbine by means of a regulator, depending on the air inlet temperature, according to the present invention, the regular regulation program conducts its tests in full afterburner mode (engine operation mode with maximum fuel consumption through afterburner collectors) with thrust measurement, then the regulator is adjusted to increase the rotors rotation speed and the gas temperature behind the turbine, not exceeding the maximum permissible values for this type of engine, until a predetermined thrust gain is reached, and regulator values are fixed, and if the predetermined thrust gain is not attained, the values of the regulator are also fixed for the maximum thrust gain, then, on the basis of the obtained data, an additional regulation program for rotors rotation frequencies and the gases temperature behind the turbine is made, it is installed into the engine regulator, then during engine operation, if it is necessary to increase the thrust in excess of the nominal modes, involve an additional program for regulating the rotors rotation frequencies and the gases temperature behind the turbine.EFFECT: possibility of increasing the thrust beyond the normal modes during the engine operation.2 tbl, 2 ex

Perepelitsa Sergej Andreevich

Papers

Method for controlling an aircraft turbojet engine

Method of turbojet engine testing

Testing method of aviation turbojet engine

Method of testing aviation gas turbine engine

Control method of aircraft jet turbine engine