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Information × Registration Number 0214U007509, 0111U005454 , R & D reports Title Adaptation of D-436-148 engine for An-148-200 aircraft. popup.stage_title Head MERKULOV VIACHESLAV, Registration Date 21-10-2014 Organization Zaporozhye Machine-Buiding Design Bureau Progress State Enterprise named after Academician A.G. Ivchenco popup.description2 Subject of research: D-436-148 turbo-fan engine for which Supplemental Type Certificate No. СТ194-АМД/Д05 was issued with specified data card, edition 06 of 20 December, 2008. Work objectives: 1. Development of work design documents on increasing the fan section effectiveness; 2. Development of work design documents on decreasing the aerodynamic losses at the engine core exhaust system; 3. Development of work design documents on improving the engine start on the aircraft; 4. Development and mutual approval of supplements to the Requirements specifications for modernizing the САУ-436-148 unit 5. Supplementary certification of the D-436-148 engine in connection with the main change - introduction of continuous takeoff power setting - engine operating power condition by using the takeoff power setting in flight with one engine-out during 30 minutes; 6. Experimental development of the modernized air turbine starter. Work results: 1. With the purpose of developing measures aimed for increasing the D-436-148 engine fan effectiveness, strength calculations of the fan rotor blade modification variants were carried out for ensuring aerodynamic damping of blades without anti-vibration platforms, drawn up was administrative documentation, the hardware was improved, and tests were carried out that confirmed the effectiveness of aerodynamic damping of the blades without anti-vibration platforms. For increasing the aerodynamic characteristics of the fan with rotor blades without anti-vibration platforms, it is necessary the investigation work to be continued. 2. For diminishing the gas flow swirl at the D-436-148 engine fan turbine outlet and decreasing losses in the main duct exhaust nozzle under the cruising flight conditions, three-dimensional calculations were carried out, as well as reshaping of the fan turbine stage 3 rotor blade; the administrative documentation was issued, the hardware wass debugged and the tests of the engine were carried out with the original and modified exhaust system profile under on-ground test-bench conditions. For estimating effectiveness of the measures it is necessary flight tests to be carried out. 3. Based on the analysis results of the D-436-148 engine flight tests on the An-148 aircraft under different atmospheric conditions, determined were the optimal parameters of starting regulation and control, the starting control algorithms and the starting fuel metering law were corrected, the engine bench tests were carried out. 4. Based on the analysis results of the bench and flight tests of a batch of air bleed valve control 4017.5В units determined was a possibility for increasing the hysteresis of the 4017.5В units and the effect of the hysteresis value on the engine parameters; determined was the optimal hysteresis value; specified was the Requirements Specifications No. 9351 for developing modified ACS units for D-436 engines as concerned increasing the 4017.5В unit hysteresis value. Based on the analysis results of the D-436-148 engine flight tests on the An-148 aircraft under different atmospheric conditions specified was the Requirements Specifications No. 17953 for developing the ЭСУ-436 electronic unit of the D-436-148 engine operation automatic control system, the ЭСУ-436 unit software correction was performed and the engine bench tests were carried out for checking functionality of the ЭСУ-436 unit corrected software. 5. A computational research was carried out about a possibility for increasing the СВ-36-1А air starter turbine efficiency factor, profiling the modified turbine rotor blade of the starter; developed was a mathematical model of the blade, calculations were performed concerning the temperature of the starter turbine working wheel with modified rotor blades, the axial thrust to the ball bearing, the radial clearance between the blade tip and the starter spacer, the maximal rotational speed of the modified turbine; substantiated was the possibility for increasing the turbine power efficiency factor from 0.705 for the serially produced starter up to 0.770 for the modified starter. Comparative tests on the laboratory facility were carried out for measuring the power characteristics of the serially produced starter and the starter with modified turbine, during which a power efficiency factor value of 0.76 was obtained. Determination of natural vibration shapes and frequencies of the modernized СВ-36-1А air starter turbine rotor blades was performed, strain measurement tests of the СВ-36-1А air starter modernized turbine working wheel blades were carried out, as well as comparative tests of the serially produced and upgraded СВ-36-1А air starters on the laboratory facility and during starting the D-436-148 engine under test bench conditions. For decreasing stresses in the rotor blades of the upgraded СВ-36-1А air starter turbine it is necessary the research works to be continued. Product Description popup.authors Зуев С.Л. Овчаренко П.К. Рудаменко В.М. Черкасов Ю.В. Чуприна К.А. Шереметьєв О.В. Якушев Ю.В. popup.nrat_date 2020-04-02 Close