METHOD OF TURBOJET BATCH MANUFACTURING AND TURBOJET MANUFACTURED ACCORDING TO THIS METHOD Russian patent published in 2015 - IPC G01M15/14 

FIELD: engines and pumps.

SUBSTANCE: invention relates to air-engine building, namely to air turbojets. In the method of batch manufacturing of the turbojet the details are manufactured and assembly units, elements and assemblies of modules and systems of the engine are completed. The modules are assembled in minimum number of eight - from the low pressure compressor to all-mode rotational jet nozzle. The engine is assembled module-by-module which is designed as double-circuit with two shafts. On a process skid an intermediate housing, a gas generator, including a high pressure compressor, a main combustion chamber and a high pressure turbine are mounted. Upstream the intermediate housing a low pressure compressor is installed, and downstream the gas generator a low pressure turbine, a mixer, a front device, an afterburner and a rotary jet nozzle are installed coaxially in series. The rotary jet nozzle includes a rotary device and an adjustable jet nozzle. Meanwhile the rotary device is detachably attached through fixed element to the afterburner, and the adjustable jet nozzle is attached similarly to a mobile element of the rotary device with a possibility of performance of rotation for change of the direction of the traction vector. During fabrication the inlet guiding device is fitted with aerodynamically transparent power array from radial stands. Stands are placed with even distribution around the entrance section of inlet guide vane and with the aerodynamic shading formed by the named array together with the frontal spinner of the inlet guide vane, amounting less than 30% of the total area of inlet circle of the inlet guide vane. After assembly the engine is tested for gas dynamic stability of the compressor operation. Specific or three-five copies, identical for a statistical representativeness of results, taken from a lot of batch manufactured engines are tested at the bench. The bench is fitted with an input aerodynamic device with adjusting by crossing of air flow, mainly remote controlled sliding intertseptor. The intertseptor comprises the graduated scale of intertseptor positions, with the fixed critical point separating the engine by 2-5% from transition into a surge. In case of necessity the tests are repeated with the set of modes corresponding to the modes of real work of turbojets in flight conditions according to regulations.

EFFECT: simplification of technology and reduction of labour costs and power consumption of turbojet test process at the phase of mass industrial production at improvement of reliability of identification of allowable range of thrust variation.

12 cl, 4 dwg