Turbojet engine

Abstract

A turbojet engine comprises all structures of a turbojet engine such as an axial-flow air compressor, an evaporative combustion chamber, a turbine and a tail jet pipe. The turbojet engine is characterized in that a bypass pipe and an inner exhaust valve are further included, an outer exhaust valve is arranged or not arranged in a pipe outside the engine between an air inlet and an air outlet of the bypass pipe, after the engine is started and operates, the inner exhaust valve is opened, by opening and closing of the bypass pipe, the inner exhaust valve and the existing or nonexistent outer exhaust valve, the supercharge ratio of the axial-flow air compressor is increased and kept unchanged, the increased supercharge ratio is not higher than the limitation borne by the axial-flow air compressor and a turbine according to the mechanical strength, turbine inlet temperature is kept unchanged, namely the supercharge ratio and thrust-weight ratio are increased, oil consumption rate is lowered, the levels of the axial-flow air compressor and the turbine are not increased, and the turbine inlet temperature is not raised.

Description

technical field

[0001] The invention relates to a turbojet engine, in particular to a turbojet engine capable of increasing the supercharging ratio and the thrust-to-weight ratio, and belongs to the technical field of military turbojet engines. Background technique

[0002] Although most of the current military turbojet engines have been replaced by turbofan engines, turbojet engines still occupy a place in the field of military aircraft and missiles. In turbojet engines, increasing the boosting ratio of the compressor can increase thrust and reduce fuel consumption. , to increase the supercharging ratio, at present it is mainly to increase the number of stages of compressors and turbines or to increase the temperature of the gas in front of the turbines, but the former increases the weight and volume, which is not conducive to increasing the thrust-to-weight ratio, while the latter must use high-temperature resistant, high-performance compressors. It is very difficult to im...

Examples

Embodiment Construction

[0011] Refer to attached figure 1 and 2 , the turbojet engine of the present invention includes an axial flow compressor 1, a bypass pipe 2, an internal exhaust valve 3, an evaporative combustion chamber 4, a turbine 5, a tail nozzle 6, etc., wherein the bypass pipe 2 intake The port is between the rear of the axial flow compressor 1 and the front of the evaporative combustion chamber 4, and is connected to the engine through the internal exhaust valve 3 located between them. There can be no external exhaust valve 7 in the pipe outside the engine between the air inlet and outlet, such as figure 1 shown; there may also be an external exhaust valve 7, such as figure 2 Shown; its function is to adjust the pressure of the compressed air in the bypass pipe 2.

[0012] When described turbojet engine is the present invention figure 1 , 2 In the case of the turbojet engine shown, when running after starting, the internal exhaust valve 3 is opened, and there is or is not present ...

technical field

[0001] The invention relates to a turbojet engine, in particular to a turbojet engine capable of increasing the supercharging ratio and the thrust-to-weight ratio, and belongs to the technical field of military turbojet engines. Background technique

[0002] Although most of the current military turbojet engines have been replaced by turbofan engines, turbojet engines still occupy a place in the field of military aircraft and missiles. In turbojet engines, increasing the boosting ratio of the compressor can increase thrust and reduce fuel consumption. , to increase the supercharging ratio, at present it is mainly to increase the number of stages of compressors and turbines or to increase the temperature of the gas in front of the turbines, but the former increases the weight and volume, which is not conducive to increasing the thrust-to-weight ratio, while the latter must use high-temperature resistant, high-performance compressors. It is very difficult to im...

Examples

Embodiment Construction

[0011] Refer to attached figure 1 and 2 , the turbojet engine of the present invention includes an axial flow compressor 1, a bypass pipe 2, an internal exhaust valve 3, an evaporative combustion chamber 4, a turbine 5, a tail nozzle 6, etc., wherein the bypass pipe 2 intake The port is between the rear of the axial flow compressor 1 and the front of the evaporative combustion chamber 4, and is connected to the engine through the internal exhaust valve 3 located between them. There can be no external exhaust valve 7 in the pipe outside the engine between the air inlet and outlet, such as figure 1 shown; there may also be an external exhaust valve 7, such as figure 2 Shown; its function is to adjust the pressure of the compressed air in the bypass pipe 2.

[0012] When described turbojet engine is the present invention figure 1 , 2 In the case of the turbojet engine shown, when running after starting, the internal exhaust valve 3 is opened, and there is or is not present ...

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