HYPERSONIC AIRCRAFT WITH COMPOUND PROPULSION SYSTEM AND COOLING SYSTEM OF SUCH AIRCRAFT TURBOJET HIGH-PRESSURE TURBINE Russian patent published in 2017 - IPC B64C30/00 B64D27/16 B64C15/14 B64D7/08 F01D25/12 

FIELD: aviation.

SUBSTANCE: hypersonic aircraft with a compound propulsion system includes a fuselage, wing folding console, two compound propulsion engines, two main rocket engines, folding canard panels and cockpit. Each main engine has two stages - a turbofan engine and turbojet engine. The fillet fairing is located in front part of the fuselage, inside of which there are the engines of lateral and vertical rotation. The front spoilers is located on the fillet fairing. In the rear part of the fuselage there is the central blast tube with the annular base, on which the intermediate blast tube, which is provided with guide vanes, is located. The intermediate blast tube drive body is installed at the central blast tube. The turbojet engine has a compressor, a high pressure turbine and a low pressure turbine, which are located on the outer circle of the turbojet engine body. The turbine of high pressure has a cooling system.

EFFECT: efficiency increase of the hypersonic aircraft turbojet engine high-pressure turbine cooling.

5 cl, 15 dwg