NON - AIRFIELD AIRCRAFT – PROBLEMS AND PROSPECT

Abstract

The possibility used of the last achievements of fundamental science for creation of the engine for vertical take-off and landing flying platform (FP) are discussed. FP intended for transportation goods and passengers in speed range of 0 - 700 km/hour. It is offered to equip with engine creating flat stream of exhaust. At take-off, landing and patrol FP used the vertical direction nozzle working on the slot-hole ejector amplifier of thrust, on the cruiser mode - the pulling propeller variable pitch airplane type. The design of the engine allows redistributed power between a nozzle and the propeller by means change of gas turbine rotor position. On take-off mode FP the power release on nozzle are needed to be enough for lifting. On transient mode the increasing of the power release is needed to be on propeller at conservation the power release on nozzle. It can be reached by means off the change of propellers pitch. In this case the reduction of vertical thrust it can be compensated by an aerodynamic lift force which arising on wing and hull FP. The engine has a compressor, creating the flat stream of the compressed air, flat combustion chamber and flat nozzle, that is the engine must be executed in linear geometry. The linear compressor made as a twin-rotor Ruts vacuum pump. The brush seals from nanocarbon tube used for preservation of axial clearance between rotors. The shape of helical trilobal rotor provides increased overlap of phases of suck up, carried and injection. The material of gas turbine blades can be made by the method of nonpiston low temperature extrusion. The method allows to simplify substantially one of the most difficult operations the production of shafts and radial blades of turbine of half-open type. Other most details of engine can be made by method of ordinary extrusion also. The seals from nanocarbon may be used for the existing constructions of GTE also. The specific features of engine are the following: work on the slot amplifier of thrust without hydrodynamic losses; choice of optimal speed of rotation of rotors for every stage of compressor; possibility cooling of compressive air and pin zone of brush seals; enhanceable operating manufacturability and cheapness of production.

Keywords

• вертикальний зліт і посадка, лінійний компресор, газотурбінний двигун, ежекторний підсилювач тяги