RU2011110890A

RU2011110890A - PULSING GAS TURBINE ENGINE (PUGTD)

Info

Publication number: RU2011110890A
Application number: RU2011110890/06A
Authority: RU
Inventors: Виктор Серафимович Бахирев (RU); Виктор Серафимович Бахирев
Original assignee: Виктор Серафимович Бахирев (RU); Виктор Серафимович Бахирев
Priority date: 2011-03-22
Filing date: 2011-03-22
Publication date: 2012-09-27
Also published as: RU2478804C2

Abstract

Газотурбинный двигатель, состоящий из корпуса, камеры сгорания, ротора, турбины, компрессора, системы питания и зажигания двигателя, отличающийся тем, что в корпусе двигателя по окружности расположены камеры сгорания в количестве кратно 5, ввиде равных секторов с окнами входа и выхода предыдущей камеры над ними, прилегающие к торцевой части диска ротора, выполненного перед окнами выхода симметрично чередующими по 1/4 окружности его выступами и впадинами, где находятся лопатки турбины, а на уровне окон входа диаметрально расположены 2 продувочных окна и между ними и впадинами диска имеется по каналу сообщения, то с противоположной стороны ротора против окон выхода к диску соответственно прилегают выхлопные патрубки, а диаметром менее к диску примыкает центробежный компрессор и обозначенные элементы при вращении ротора создают в той или иной камере определенные рабочие процессы ярко выраженной формы, обеспечивая рабочее состояние двигателя. A gas turbine engine, consisting of a housing, a combustion chamber, a rotor, a turbine, a compressor, a power supply and ignition system, characterized in that the combustion chamber is surrounded by a circumference of a multiple of 5 in the circumference of the engine, in view of equal sectors with the entrance and exit windows of the previous chamber above adjacent to the end part of the rotor disk, made in front of the exit windows symmetrically alternating along the 1/4 circumference of its protrusions and depressions, where the turbine blades are located, and 2 products are diametrically located at the level of the entrance windows full-time windows and between them and the hollows of the disk there is a communication channel, then on the opposite side of the rotor against the exit windows the exhaust pipes are adjacent to the disk, and with a diameter less than the disk, the centrifugal compressor adjoins and the designated elements create certain working objects in this or that chamber during rotation of the rotor pronounced processes, ensuring the working condition of the engine.

Claims

A gas turbine engine, consisting of a housing, a combustion chamber, a rotor, a turbine, a compressor, a power supply and ignition system, characterized in that the combustion chamber is surrounded by a circumference of a multiple of 5 in the circumference of the engine, in view of equal sectors with the entrance and exit windows of the previous chamber above adjacent to the end part of the rotor disk, made in front of the exit windows symmetrically alternating along the 1/4 circumference of its protrusions and depressions, where the turbine blades are located, and 2 products are diametrically located at the level of the entrance windows full-time windows and between them and the hollows of the disk there is a communication channel, then on the opposite side of the rotor against the exit windows the exhaust pipes are adjacent to the disk, and with a diameter less than the disk, the centrifugal compressor adjoins and the designated elements create certain working objects in this or that chamber during rotation of the rotor pronounced processes, ensuring the working condition of the engine.