CN101968012A

CN101968012A - High-efficiency turbojet engine

Info

Publication number: CN101968012A
Application number: CN2010105115075A
Authority: CN
Inventors: 靳北彪
Original assignee: Individual
Current assignee: Individual
Priority date: 2010-10-19
Filing date: 2010-10-19
Publication date: 2011-02-09

Abstract

The invention discloses a high-efficiency turbojet engine which comprises a culvert, a gas compressor and a power turbine, wherein the gas compressor and the power turbine are arranged in the culvert, and the power turbine outputs power to the gas compressor; a first combustion chamber is arranged between the gas compressor and the power turbine, and a second combustion chamber is arranged between the power turbine and a culvert jet pipe of the culvert. The turbojet engine has the advantages of high efficiency, low emission and low cost.

Description

Efficient turbojet engine

Technical field

The present invention relates to heat energy, power and propelling field, especially a kind of efficient turbojet engine.

Background technique

Conventional turbine air breathing engine and conventional turbofan motor all are to establish the firing chamber between gas compressor and power turbine, though and the structure of tail pipe burner arranged after power turbine, not as the firing chamber of continuous operation.The temperature requirement of the firing chamber of this conventional construction between power turbine and gas compressor is very high, and is therefore also quite harsh to the blade requirement of power turbine, thereby caused a series of problems such as this class motor involves great expense.For this reason, need the invention air breathing engine that a kind of power turbine operating temperature is relatively low and/or the power turbine working flow is less, improve the performance of motor to reduce the cost of this class motor.

Summary of the invention

In order to address the above problem, the technological scheme that the present invention proposes is as follows:

A kind of efficient turbojet engine, comprise duct, gas compressor and power turbine, described gas compressor and described power turbine are arranged in the described duct, described power turbine is to described gas compressor outputting power, between described gas compressor and described power turbine, establish first firing chamber, between the shrouded nozzle of described power turbine and described duct, establish second firing chamber.

Described efficient turbojet engine also comprises bypass passageways, pressurized gas space between described gas compressor and described first firing chamber is made as the unburned gas space, space between described power turbine and described second firing chamber is made as half combustion gas body space, described bypass passageways is communicated with described unburned gas space and described half combustion gas body space, and described bypass passageways directly imports described second firing chamber with part pressurized air without described first firing chamber.

Establish fan at the place, suction port the place ahead of described duct and constitute the combustion chambers in tandem turbofan engine.

Principle of the present invention is that gas compressor and power turbine are set in duct, power turbine is to the gas compressor outputting power, two firing chambers are set in the front and back of power turbine, only spraying into small amount of fuel in the firing chamber before being arranged on power turbine makes the temperature rise of working medium be in reduced levels, thereby the operating temperature that reduces power turbine is to realize reducing the cost of material of power turbine blade, (Yin Wendu is lower can also to make simultaneously the rotating speed of power turbine that by a relatively large margin raising is arranged, so can bear bigger centrifugal force), improve the compression ratio of motor, improve the efficient of motor, spray into a large amount of fuel in the firing chamber after being arranged on power turbine, make it the ejection from jet pipe of burning back and obtain thrust; In this structure, the operating temperature of power turbine is lower, but working flow does not reduce significantly.In order to reduce the working flow of power turbine, thereby reduce the diameter of power turbine, the present invention is provided with bypass passageways, make high-pressure air after gas compressor compression directly enter firing chamber after being arranged on power turbine, fuel and the mixed combustion in this firing chamber of this part air, under the prerequisite of any impeller class mechanism from jet pipe ejection just as rocket chamber, obtain thrust; In this structure, the working flow of power turbine can reduce significantly, that is to say that the diameter of power turbine can reduce significantly, thereby reduces action of centrifugal force, can improve rotating speed, improves pressure ratio and efficient.

So-called first firing chamber is meant the firing chamber that is arranged between power turbine and the gas compressor; So-called second firing chamber is meant the firing chamber that is arranged between power turbine and the shrouded nozzle; So-called shrouded nozzle is meant the jet pipe that is communicated with the tail end of duct, and its function is to obtain reverse Driving force; So-called the place ahead is meant the gas access direction of duct, and is corresponding with it, and the rear is meant the Way out of shrouded nozzle; The function of so-called bypass passageways is that the pressurized air after the gas compressor compression is directly imported second firing chamber without first firing chamber, and its shape can be a pipe, also can be the annular pass; So-called unburned gas space is meant through the existing space of pressurized gas of not carrying out any combustion reaction after the gas compressor compression; So-called half combustion gas body space has been meant through the carrying out after the gas compressor compression the existing space of pressurized gas of partial combustion reaction (be that inside contains aerobic, the content of oxygen can height can be low); So-called " described power turbine is to described gas compressor outputting power " is meant that power turbine promotes the gas compressor rotation, comprises coaxial setting, also comprises the set-up mode that constant speed or speed changing structure through gear etc. promote.

Beneficial effect of the present invention is as follows:

The present invention has realized efficient, the low emission and the low cost of turbojet engine.

Description of drawings

Fig. 1 is the structural representation of the embodiment of the invention 1;

Fig. 2 is the structural representation of the embodiment of the invention 2;

Fig. 3 is the structural representation of the embodiment of the invention 3.

Embodiment

Embodiment 1

Efficient turbojet engine as shown in Figure 1, comprise duct 1, gas compressor 2 and power turbine 3, it is characterized in that: gas compressor 2 and power turbine 3 are arranged in the

duct

1,3 pairs of gas compressor 2 outputting powers of power turbine, between gas compressor 2 and power turbine 3, establish first firing chamber 203, between the shrouded nozzle 4 of power turbine 3 and duct 1, establish second firing chamber 204.

Embodiment 2

Efficient turbojet engine as shown in Figure 2, itself and embodiment's 1 difference is: efficient turbojet engine also comprises bypass passageways 6, pressurized gas space between the gas compressor 2 and first firing chamber 203 is made as unburned gas space 2203, space between the power turbine 3 and second firing chamber 204 is made as half combustion gas body space 3204, bypass passageways 6 is communicated with unburned gas space 2203 and half combustion gas body space 3204, and bypass passageways 6 directly imports second firing chamber 204 with the part pressurized air in the unburned gas space 2203 without first firing chamber 203.

Embodiment 3

Efficient turbojet engine as shown in Figure 3, itself and embodiment's 2 difference is: establish fan 7 at the place, suction port 5 the place aheads of duct 1 and constitute the combustion chambers in tandem turbofan engines.

Claims

1. efficient turbojet engine, comprise duct (1), gas compressor (2) and power turbine (3), it is characterized in that: described gas compressor (2) and described power turbine (3) are arranged in the described duct (1), described power turbine (3) is to described gas compressor (2) outputting power, between described gas compressor (2) and described power turbine (3), establish first firing chamber (203), between the shrouded nozzle (4) of described power turbine (3) and described duct (1), establish second firing chamber (204).

2. efficient according to claim 1 turbojet engine, it is characterized in that: described efficient turbojet engine also comprises bypass passageways (6), pressurized gas space between described gas compressor (2) and described first firing chamber (203) is made as unburned gas space (2203), space between described power turbine (3) and described second firing chamber (204) is made as half combustion gas body space (3204), described bypass passageways (6) is communicated with described unburned gas space (2203) and described half combustion gas body space (3204), and described bypass passageways (6) directly imports described second firing chamber (204) with part pressurized air without described first firing chamber (203).

3. efficient according to claim 1 turbojet engine is characterized in that: establish fan (7) at the place, suction port (5) the place ahead of described duct (1) and constitute the combustion chambers in tandem turbofan engine.