RU2010111080A

RU2010111080A - ATOMIC TURBIN SCREW GAS-TURBINE ENGINE

Info

Publication number: RU2010111080A
Application number: RU2010111080/06A
Authority: RU
Inventors: Николай Борисович Болотин (RU); Николай Борисович Болотин
Original assignee: Николай Борисович Болотин (RU); Николай Борисович Болотин
Priority date: 2010-03-23
Filing date: 2010-03-23
Publication date: 2011-09-27
Also published as: RU2435049C1

Abstract

1. Атомный турбовинтовой газотурбинный двигатель, содержащий ядерный реактор, винт, корпус двигателя, воздухозаборник, компрессор, камеру сгорания, турбину, теплообменник-подогреватель и реактивное сопло, отличающийся тем, что двигатель выполнен по трехвальной схеме с внешним, промежуточным и внутренним валами, компрессор выполнен из каскадов низкого и высокого давления, турбина содержит каскады высокого, среднего и низкого давления, ротор турбины низкого давления соединен внутренним валом с винтом, ротор турбины среднего давления соединен промежуточным валом с ротором компрессора низкого давления, а ротор турбины высокого давления соединен внешним валом с ротором компрессора высокого давления, между турбинами высокого и среднего давления и между турбинами среднего и низкого давления установлены радиальные перегородки, вне корпуса двигателя установлены теплообменник-подогреватель, первый и второй дополнительные теплообменники, соединенные трубопроводами рециркуляции с ядерным реактором и подводящими и отводящими воздушными трубопроводами, соответственно с полостями после компрессора и перед турбиной высокого давления, после турбины высокого давления и перед турбиной среднего давления, после турбины среднего давления и перед турбиной низкого давления. ! 2. Атомный турбовинтовой газотурбинный двигатель по п.1, отличающийся тем, что в подводящих воздушных трубопроводах установлены регуляторы расхода. ! 3. Атомный турбовинтовой газотурбинный двигатель по п.1, отличающийся тем, что воздушный винт соединен с внутренним валом через редуктор. ! 4. Атомный турбовинтовой газотурбинный двигатель по п.1 и� 1. An atomic turboprop gas turbine engine containing a nuclear reactor, a screw, an engine casing, an air intake, a compressor, a combustion chamber, a turbine, a heat exchanger-heater and a jet nozzle, characterized in that the engine is designed according to a three-shaft scheme with external, intermediate and internal shafts, a compressor made of cascades of low and high pressure, the turbine contains cascades of high, medium and low pressure, the rotor of the low pressure turbine is connected by an internal shaft with a screw, the rotor of the medium pressure turbine is connected inen by the intermediate shaft with the rotor of the low pressure compressor, and the rotor of the high pressure turbine is connected by an external shaft to the rotor of the high pressure compressor, radial partitions are installed between the high and medium pressure turbines and between the medium and low pressure turbines, a heat exchanger-heater is installed outside the engine casing, the first and the second additional heat exchangers connected by recirculation pipelines with a nuclear reactor and inlet and outlet air pipelines, respectively, with the floor remain after the compressor and before the high pressure turbine, after the high pressure turbine and before the medium pressure turbine, after the medium pressure turbine and before the low pressure turbine. ! 2. Atomic turboprop gas turbine engine according to claim 1, characterized in that flow regulators are installed in the supplying air pipelines. ! 3. The atomic turboprop gas turbine engine according to claim 1, characterized in that the propeller is connected to the internal shaft through a gearbox. ! 4. Atomic turboprop gas turbine engine according to claim 1 and�

Claims

1. An atomic turboprop gas turbine engine containing a nuclear reactor, a screw, an engine casing, an air intake, a compressor, a combustion chamber, a turbine, a heat exchanger-heater and a jet nozzle, characterized in that the engine is designed according to a three-shaft scheme with external, intermediate and internal shafts, a compressor made of cascades of low and high pressure, the turbine contains cascades of high, medium and low pressure, the rotor of the low pressure turbine is connected by an internal shaft with a screw, the rotor of the medium pressure turbine is connected inen by the intermediate shaft with the rotor of the low pressure compressor, and the rotor of the high pressure turbine is connected by an external shaft to the rotor of the high pressure compressor, radial partitions are installed between the high and medium pressure turbines and between the medium and low pressure turbines, a heat exchanger-heater is installed outside the engine casing, the first and the second additional heat exchangers connected by recirculation pipelines with a nuclear reactor and inlet and outlet air pipelines, respectively, with the floor remain after the compressor and before the high pressure turbine, after the high pressure turbine and before the medium pressure turbine, after the medium pressure turbine and before the low pressure turbine.

2. Atomic turboprop gas turbine engine according to claim 1, characterized in that flow regulators are installed in the supplying air pipelines.

3. The atomic turboprop gas turbine engine according to claim 1, characterized in that the propeller is connected to the internal shaft through a gearbox.

4. Atomic turboprop gas turbine engine according to claim 1 or 2, characterized in that the propeller contains two rows of blades.

5. The atomic turboprop gas turbine engine according to claim 3, characterized in that the second row of blades is connected to the intermediate shaft.