CN103967649A

CN103967649A - Turbojet engine

Info

Publication number: CN103967649A
Application number: CN201310656496.3A
Authority: CN
Inventors: 李吉光
Original assignee: Individual
Current assignee: Individual
Priority date: 2013-01-24
Filing date: 2013-12-09
Publication date: 2014-08-06

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

Turbojet engine

Technical field

The present invention relates to a kind of turbojet engine, is a kind of when turbojet engine of thrust weight ratio of supercharging that improves specifically, belongs to military turbojet engine technical field.

Background technique

Although current military turbojet engine major part is replaced by turbofan engine, but turbojet engine is in military secret, guided missile field still occupies a tiny space, the pressure ratio that improves gas compressor in turbojet engine can increase thrust, reduce oil consumption rate, improve pressure ratio, mainly to increase gas compressor at present, fuel gas temperature before the progression of turbine or raising turbine, but the former increases weight and volume, unfavorable to improving thrust weight ratio, latter must use high temperature resistant, the turbine blade material that performance is good, cladding material and advanced cool but technology, it is very difficult improving, and the pressure ratio of turbojet engine is all fixed at present, cannot improve.

Summary of the invention

The object of this invention is to provide a kind of in the case of not increasing in gas compressor, turbine the progression of any one, do not improve before turbine fuel gas temperature, improve the pressure ratio of gas compressor, thereby improve thrust weight ratio, reduce the turbojet engine of oil consumption rate.

The present invention is achieved in that turbojet engine, comprise axial-flow compressor, evaporation-combustion chamber, turbine, all structures of the turbojet engines such as jet pipe, wherein axial-flow compressor is coaxial with turbine, in jet pipe, can have or without afterburning fuel nozzle, it is characterized in that also comprising bypass tube, its suction port is after axial-flow compressor and between before evaporation-combustion chamber, by between them after engine start and pressure ratio lower than axial-flow compressor improve after pressure ratio time open, improving the exhaust gas inside valve of closing after axial-flow compressor pressure ratio is connected with motor, its air outlet or towards engine intake, the limit that pressure ratio after axial-flow compressor improves is not born higher than the mechanical strength of axial-flow compressor, turbine.

Guan Zhongwu between described bypass tube air inlet/outlet outside motor regulates the outside exhaust valve of compressed air pressure.

Guan Zhongyou between described bypass tube air inlet/outlet outside motor regulates the outside exhaust valve of compressed air pressure.

Adopt after said structure, owing to there being bypass tube, in pipe between exhaust gas inside valve and bypass tube air inlet/outlet outside motor, also have or the outside exhaust valve of nothing, while operation after engine start, exhaust gas inside valve is opened, send a part of pressurized air after axial-flow compressor back to engine intake by bypass tube, together with airborne air inlet, increase suction pressure with motor, continuously compress through gas compressor, evaporation-combustion chamber work by combustion, compressed air pressure after compression will increase gradually, in the time that the compressed air pressure after compression increases to needing of pressure ratio after raising, exhaust gas inside valve is closed, only with motor from airborne air inlet and without the air inlet of bypass tube, therebetween can with or need not the compressed air pressure in bypass tube be regulated outside exhaust valve, then use exhaust gas inside valve or in, the open and close of outside exhaust valve keep the pressure ratio after raising constant, pressure ratio after raising is not higher than axial-flow compressor, the limit that the mechanical strength of turbine is born, and before maintenance turbine, fuel gas temperature is constant, it is pressure ratio, thrust weight ratio improves, oil consumption rate reduces, but axial-flow compressor, the progression of turbine does not increase, before turbine, fuel gas temperature does not improve.

Brief description of the drawings

Below in conjunction with drawings and Examples, the present invention is explained in detail:

Fig. 1 is first structural representation of turbojet engine of the present invention.

Fig. 2 is second structural representation of turbojet engine of the present invention.

Embodiment

With reference to attached Fig. 1 and 2, turbojet engine of the present invention comprises axial-flow compressor 1, bypass tube 2, exhaust gas inside valve 3, evaporation-combustion chamber 4, turbine 5, jet pipe 6 etc., wherein bypass tube 2 suction ports are after axial-flow compressor 1 and between before evaporation-combustion chamber 4, be connected with motor by the exhaust gas inside valve 3 between them, its air outlet or towards engine intake, can be without outside exhaust valve 7, as shown in Figure 1 in pipe between bypass tube 2 air inlet/outlets outside motor; Also can there is outside exhaust valve 7, as shown in Figure 2; Its effect is to regulate compressed-air actuated pressure in bypass tube 2.

When described turbojet engine is Fig. 1 of the present invention, when turbojet engine shown in 2, while operation after starting, exhaust gas inside valve 3 is opened, by bypass tube 2, in pipe between exhaust gas inside valve 3 and bypass tube 2 air inlet/outlets outside motor, also have or the open and close of the outside exhaust valve 7 of nothing, the pressure ratio of axial-flow compressor 1 is improved and increases and remain unchanged, pressure ratio after increase is not higher than axial-flow compressor 1, the limit that the mechanical strength of turbine 5 is born, and keep the front fuel gas temperature of turbine 5 constant, its process as mentioned before, the combination of axial-flow compressor 1 and bypass tube 2 in the present embodiment has the effect of cyclotron in physics, the pressure ratio of axial-flow compressor 1 can be improved to increase easily in theory.

In the present embodiment, the progression of axial-flow compressor 1, turbine 5 can be selected as required, the quantity of bypass tube 2 is 1 to multiple, exhaust gas inside valve 3, outside exhaust valve 7 can be the air bleed valves that meets the current known various structures of service condition, the original air bleed valve of motor still retains as anti-asthma air bleed valve etc., the decisions such as the pressure ratio after the exhaust pressure of outside exhaust valve 7 is improved by axial-flow compressor 1; The present invention can be used for current various turbojet engines, as motors such as whirlpool spray 7, whirlpool spray 13, whirlpool sprays 14.

Claims

1. turbojet engine, comprise axial-flow compressor (1), evaporation-combustion chamber (4), turbine (5), all structures of the turbojet engines such as jet pipe (6), wherein axial-flow compressor (1) is coaxial with turbine (5), it is characterized in that also comprising bypass tube (2), its suction port after the axial-flow compressor (1) and evaporation-combustion chamber (4) front between, by between them after engine start and pressure ratio lower than axial-flow compressor (1) improve after pressure ratio time open, improving the exhaust gas inside valve (3) of closing after axial-flow compressor (1) pressure ratio is connected with motor, its air outlet or towards engine intake, the limit that pressure ratio after axial-flow compressor (1) improves is not born higher than the mechanical strength of axial-flow compressor (1), turbine (5).

2. turbojet engine according to claim 1, is characterized in that the Guan Zhongwu outside motor between described bypass tube (2) air inlet/outlet regulates the outside exhaust valve (7) of compressed air pressure.

3. turbojet engine according to claim 1, is characterized in that the Guan Zhongyou outside motor between described bypass tube (2) air inlet/outlet regulates the outside exhaust valve (7) of compressed air pressure.