RU2008110285A

RU2008110285A - VERTICAL TAKEOFF AND LANDING AIRCRAFT ENGINE

Info

Publication number: RU2008110285A
Application number: RU2008110285/06A
Authority: RU
Inventors: Николай Борисович Болотин (RU); Николай Борисович Болотин
Original assignee: Николай Борисович Болотин (RU); Николай Борисович Болотин
Priority date: 2008-03-17
Filing date: 2008-03-17
Publication date: 2009-09-27

Abstract

1. Двигатель самолета вертикального взлета и посадки, содержащий турбокомпрессор с внешним корпусом, компрессором, камерой сгорания, выход из которой соединен газовым трактом с турбиной, и реактивное сопло, отличающийся тем, что двигатель выполнен биротативным с двумя турбокомпрессорами, содержащими, в свою очередь, валы с рабочими колесами компрессоров и рабочими колесами турбин, а также внутренний цилиндрический корпус, который посредством по меньшей мере одной герметичной радиальной перегородки соединен с внешним корпусом, причем камера сгорания закреплена снаружи внешнего корпуса. ! 2. Двигатель самолета вертикального взлета и посадки по п.1, отличающийся тем, что реактивное сопло соединено с внешним корпусом. ! 3. Двигатель самолета вертикального взлета и посадки по п.1 или 2, отличающийся тем, что камера сгорания прикреплена к внешнему корпусу в его средней части между компрессорами и турбиной и соединена на входе с воздушным коллектором, а на выходе с газовым коллектором.1. The engine of the aircraft of vertical take-off and landing, comprising a turbocharger with an external casing, a compressor, a combustion chamber, the output of which is connected by a gas path to the turbine, and a jet nozzle, characterized in that the engine is made biotic with two turbocompressors, containing, in turn, shafts with impellers of the compressors and impellers of the turbines, as well as an inner cylindrical body, which is connected via an at least one sealed radial partition to the external housing, and The combustion measure is fixed outside the outer casing. ! 2. The engine of the aircraft vertical take-off and landing according to claim 1, characterized in that the jet nozzle is connected to the outer casing. ! 3. The engine of the aircraft vertical take-off and landing according to claim 1 or 2, characterized in that the combustion chamber is attached to the outer casing in its middle part between the compressors and the turbine and connected at the inlet to the air manifold, and at the outlet to the gas manifold.

Claims

1. The engine of the aircraft of vertical take-off and landing, comprising a turbocharger with an external casing, a compressor, a combustion chamber, the output of which is connected by a gas path to the turbine, and a jet nozzle, characterized in that the engine is made biotic with two turbocompressors, containing, in turn, shafts with impellers of the compressors and impellers of the turbines, as well as an inner cylindrical body, which is connected via an at least one sealed radial partition to the external housing, and The combustion measure is fixed outside the outer casing.

2. The engine of the aircraft vertical take-off and landing according to claim 1, characterized in that the jet nozzle is connected to the outer casing.

3. The engine of the aircraft vertical take-off and landing according to claim 1 or 2, characterized in that the combustion chamber is attached to the outer casing in its middle part between the compressors and the turbine and connected at the inlet to the air manifold, and at the outlet to the gas manifold.