CN202091057U - Turbine jet engine with high efficiency - Google Patents
Turbine jet engine with high efficiency Download PDFInfo
- Publication number
- CN202091057U CN202091057U CN2011201570409U CN201120157040U CN202091057U CN 202091057 U CN202091057 U CN 202091057U CN 2011201570409 U CN2011201570409 U CN 2011201570409U CN 201120157040 U CN201120157040 U CN 201120157040U CN 202091057 U CN202091057 U CN 202091057U
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- firing chamber
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- power turbine
- space
- turbojet engine
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Abstract
The utility model discloses a turbine jet engine with high efficiency, comprising a duct, a compressor and a power turbine. The compressor and the power turbine are disposed in the duct. The power turbine outputs power to the compressor. A first combustion chamber is disposed between the compressor and the power turbine, and a second combustion chamber is disposed between the power turbine and a duct jet pipe. The turbine jet engine is high in efficiency, and low in emission and cost.
Description
Technical field
The utility model relates to the jet propulsion field, especially a kind of air breathing 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 utility model 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 first firing chamber and described second firing chamber are made as continuous combustion chambers.
The amount of adjusting the fuel that imports described first firing chamber makes the working medium temperature in described first firing chamber be lower than 2300K.
The amount that adjust to import the fuel of described first firing chamber makes the ratio of the mass flow rate of the air that enters described first firing chamber and quality of fuel flow greater than 20: 1.
Described shrouded nozzle is made as Laval nozzle.
Establish fan at the place, suction port the place ahead of described duct and constitute the combustion chambers in tandem turbofan engine.
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 unburned gas space is communicated with described half combustion gas body space through described bypass passageways, and described bypass passageways directly imports described second firing chamber with part pressurized air without described first firing chamber.
The amount that adjust to import the fuel of described first firing chamber makes the ratio of the mass flow rate of the air that enters described first firing chamber and quality of fuel flow greater than 20: 1.
Described unburned gas space is communicated with described half combustion gas body space through Jet injector through described bypass passageways again.
Principle of the present utility model 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 utility model 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.
In the utility model, the amount of adjusting the fuel that imports described first firing chamber makes the working medium temperature in described first firing chamber be lower than 2200K, 2100K, 2000K, 1900K, 1800K, 1700K, 1600K, 1500K, 1400K, 1300K, 1200K, 1100K, 1000K or be lower than 900K.
In the utility model, the amount that adjust to import the fuel of described first firing chamber makes the ratio of the mass flow rate of the air that enters described first firing chamber and quality of fuel flow greater than 25: 1,30: 1,35: 1,40: 1,45: 1,50: 1,55: 1,60: 1,65: 1,70: 1,75: 1,80: 1,85: 1,90: 1,95: 1,100: 1,105: 1,110: 1,115: 1,120: 1,125: 1,130: 1,135: 1,140: 1,145: 1 or greater than 150: 1.
In the utility model, the amount that adjust to import the fuel of described first firing chamber makes the ratio of the mass flow rate of the air that enters described first firing chamber and quality of fuel flow greater than 25: 1,30: 1,35: 1,40: 1,45: 1,50: 1,55: 1,60: 1,65: 1,70: 1,75: 1,80: 1,85: 1,90: 1,95: 1,100: 1,105: 1,110: 1,115: 1,120: 1,125: 1,130: 1,135: 1,140: 1,145: 1 or greater than 150: 1.
In the utility model, so-called continuous combustion chambers is meant under the condition of motor proper functioning, and the firing chamber of combustion chemistry reaction takes place always.
In the utility model, so-called Jet injector is meant by the non-motive fluid of motive fluid injection, the device that two fluid interactions are discharged from an outlet, and it can be gas jet pump (being jet pump), also can be liquid-jet pump; So-called Jet injector can be traditional Jet injector, also can be non-traditional Jet injector.
In the utility model, so-called traditional Jet injector is meant what the pipe by two suit settings constituted, inwardly pipe provides high voltage power gas, in pipe high voltage power gas in outer tube, spray, under the acting in conjunction of gas blowing of interior pipe high voltage power and outer tube, make other gases between the inner and outer pipes (gas that enters from outer tube) produce the device that moves along the injection direction of interior pipe high voltage power gas; The outer tube of so-called Jet injector can have the reducing and expansion district, and outer tube can be made as Venturi tube, and interior pipe nozzle can be made as Laval nozzle, and so-called reducing and expansion district is meant the zone that section area changes in the outer tube; Described Jet injector has three interfaces at least or claims passage, i.e. Jet injector power gas jetburner, Jet injector low-pressure gas inlet and Jet injector gas outlet.
In the utility model, so-called non-traditional Jet injector is meant and is made of two or more mutual sheathing settings or the pipe that is set up in parallel mutually, wherein at least one pipe is communicated with motive gas source, and flowing of the power gas in the motive gas source can cause that the gas in other pipes produces the device of directional flow; The pipe of so-called Jet injector can have the reducing and expansion district, can be made as Venturi tube, and the nozzle of pipe can be made as Laval nozzle, and so-called reducing and expansion district is the zone that section area changes in the vial; Described Jet injector has three interfaces at least or claims passage, i.e. Jet injector power gas jetburner, Jet injector low-pressure gas inlet and Jet injector gas outlet; Described Jet injector can comprise a plurality of Jet injector power gas jetburners, in the structure that comprises a plurality of Jet injector power gas jetburners, described Jet injector power gas jetburner can be arranged in the pipeline center district of described Jet injector low-pressure gas inlet, also can be arranged near the tube wall of described Jet injector low-pressure gas inlet, described Jet injector power gas jetburner also can be the annular spray mouth around described Jet injector low-pressure gas inlet pipe wall.
In the utility model, described Jet injector comprises multistage Jet injector, multiple jets pump and pulsing jet pump etc.
In the utility model, so-called " described unburned gas space is communicated with described half combustion gas body space through Jet injector through described bypass passageways again " is meant that described bypass passageways is communicated with the Jet injector power gas jetburner of described Jet injector, described half combustion gas body space is communicated with the Jet injector low-pressure gas inlet of described Jet injector, and the Jet injector gas outlet of described Jet injector is communicated with described second firing chamber; Or refer to that described bypass passageways is communicated with the Jet injector low-pressure gas inlet of described Jet injector, and described half combustion gas body space is communicated with the Jet injector power gas jetburner of described Jet injector, and the Jet injector gas outlet of described Jet injector is communicated with described second firing chamber.
In the utility model,, should in described first firing chamber and described second firing chamber, establish fuel introducing port and ignition mechanism according to known technology.
In the utility model,, establish necessary parts, unit or system in the place of necessity according to known technology.
The beneficial effects of the utility model are as follows:
The utility model has been realized efficient, the low emission and the low cost of turbojet engine.
Description of drawings
Fig. 1 is the utility model embodiment 1 and embodiment's 2 a structural representation;
Fig. 2 is the utility model embodiment 3 a structural representation;
Fig. 3 is the utility model embodiment 4 a structural representation;
Fig. 4 is the utility model embodiment 5 a structural representation.
Among the figure:
1 duct, 2 gas compressors, 3 power turbines, 4 shrouded nozzles, 5 suction ports, 6 bypass passageways,
7 fans, 203 first firing chambers, 204 second firing chambers, 401 Laval nozzles,
2203 unburned gas spaces, 3,204 half combustion gas body spaces, 8 Jet injectors
Embodiment
Efficient turbojet engine as shown in Figure 1, comprise duct 1, gas compressor 2 and power turbine 3, 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.Described first firing chamber 203 and described second firing chamber 204 are made as continuous combustion chambers.The amount of adjusting the fuel that imports described first firing chamber 203 makes the working medium temperature in described first firing chamber 203 be lower than 2300K, 2200K, 2100K, 2000K, 1900K, 1800K, 1700K, 1600K, 1500K, 1400K, 1300K, 1200K, 1100K, 1000K or be lower than 900K.
Efficient turbojet engine as shown in Figure 1, itself and embodiment's 1 difference is: the amount of adjusting the fuel that imports described first firing chamber 203 makes the ratio of the mass flow rate of the air that enters described first firing chamber 203 and quality of fuel flow greater than 20: 1,25: 1,30: 1,35: 1,40: 1,45: 1,50: 1,55: 1,60: 1,65: 1,70: 1,75: 1,80: 1,85: 1,90: 1,95: 1,100: 1,105: 1,110: 1,115: 1,120: 1,125: 1,130: 1,135: 1,140: 1,145: 1 or greater than 150: 1.
Efficient turbojet engine as shown in Figure 2, itself and embodiment's 1 difference is: 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 unburned gas space 2203 is communicated with described half combustion gas body space 3204 through described bypass passageways 6, and described bypass passageways 6 directly imports described second firing chamber 204 with part pressurized air without described first firing chamber 203.
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, described shrouded nozzle 4 is made as Laval nozzle 401.The amount that adjust to import the fuel of described first firing chamber 203 makes the ratio of the mass flow rate of the air that enters described first firing chamber 203 and quality of fuel flow greater than 20: 1,25: 1,30: 1,35: 1,40: 1,45: 1,50: 1,55: 1,60: 1,65: 1,70: 1,75: 1,80: 1,85: 1,90: 1,95: 1,100: 1,105: 1,110: 1,115: 1,120: 1,125: 1,130: 1,135: 1,140: 1,145: 1 or greater than 150: 1.
Efficient turbojet engine as shown in Figure 4, its difference with embodiment 3 is: described unburned gas space 2203 is communicated with described half combustion gas body space 3204 through Jet injector 8 through described bypass passageways 6 again.
Obviously; the utility model is not limited to above embodiment, according to the known technology and the technological scheme disclosed in the utility model of related domain, can derive or association goes out many flexible programs; all these flexible programs also should be thought protection domain of the present utility model.
Claims (6)
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 first firing chamber (203) and described second firing chamber (204) are made as continuous combustion chambers.
3. efficient according to claim 1 turbojet engine, it is characterized in that: described shrouded nozzle (4) is made as Laval nozzle (401).
4. 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.
5. 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 unburned gas space (2203) is communicated with described half combustion gas body space (3204) through described bypass passageways (6), and described bypass passageways (6) directly imports described second firing chamber (204) with part pressurized air without described first firing chamber (203).
6. as efficient turbojet engine as described in the claim 5, it is characterized in that: described unburned gas space (2203) is communicated with described half combustion gas body space (3204) through Jet injector (8) through described bypass passageways (6) again.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011201570409U CN202091057U (en) | 2010-10-19 | 2011-05-17 | Turbine jet engine with high efficiency |
Applications Claiming Priority (5)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010105115075A CN101968012A (en) | 2010-10-19 | 2010-10-19 | High-efficiency turbojet engine |
| CN201010511507.5 | 2010-10-19 | ||
| CN201120064941 | 2011-03-14 | ||
| CN201120064941.3 | 2011-03-14 | ||
| CN2011201570409U CN202091057U (en) | 2010-10-19 | 2011-05-17 | Turbine jet engine with high efficiency |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202091057U true CN202091057U (en) | 2011-12-28 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011201570409U Expired - Lifetime CN202091057U (en) | 2010-10-19 | 2011-05-17 | Turbine jet engine with high efficiency |
Country Status (1)
| Country | Link |
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| CN (1) | CN202091057U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102619642A (en) * | 2010-10-19 | 2012-08-01 | 靳北彪 | Efficient turbojet engine |
| TWI504538B (en) * | 2013-05-31 | 2015-10-21 | Nat Applied Res Laboratories | Dual-vortical-flow hybrid rocket engine |
-
2011
- 2011-05-17 CN CN2011201570409U patent/CN202091057U/en not_active Expired - Lifetime
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102619642A (en) * | 2010-10-19 | 2012-08-01 | 靳北彪 | Efficient turbojet engine |
| TWI504538B (en) * | 2013-05-31 | 2015-10-21 | Nat Applied Res Laboratories | Dual-vortical-flow hybrid rocket engine |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20111228 Effective date of abandoning: 20140319 |
|
| AV01 | Patent right actively abandoned |
Granted publication date: 20111228 Effective date of abandoning: 20140319 |
|
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |