CN102619642B - Efficient turbojet engine - Google Patents
Efficient turbojet engine Download PDFInfo
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- CN102619642B CN102619642B CN201110127356.8A CN201110127356A CN102619642B CN 102619642 B CN102619642 B CN 102619642B CN 201110127356 A CN201110127356 A CN 201110127356A CN 102619642 B CN102619642 B CN 102619642B
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- firing chamber
- power turbine
- gas
- turbojet engine
- space
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- 238000002485 combustion reaction Methods 0.000 claims abstract description 13
- 239000007789 gas Substances 0.000 claims description 74
- 238000010304 firing Methods 0.000 claims description 67
- 229940090046 jet injector Drugs 0.000 claims description 41
- 239000000446 fuel Substances 0.000 claims description 22
- 239000000567 combustion gas Substances 0.000 claims description 14
- 230000008676 import Effects 0.000 claims description 14
- 239000007921 spray Substances 0.000 abstract description 5
- 238000004519 manufacturing process Methods 0.000 abstract 1
- 230000006835 compression Effects 0.000 description 5
- 238000007906 compression Methods 0.000 description 5
- 238000005516 engineering process Methods 0.000 description 3
- 239000012530 fluid Substances 0.000 description 3
- 238000002347 injection Methods 0.000 description 3
- 239000007924 injection Substances 0.000 description 3
- 230000029058 respiratory gaseous exchange Effects 0.000 description 3
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005251 gamma ray Effects 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
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Abstract
The invention discloses an efficient 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, the power turbine outputs motive 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 spray pipe of the culvert. The efficient turbojet engine realizes the high efficiency, low emission and low manufacture price of the turbojet engine.
Description
Technical field
The present invention relates to jet propulsion field, especially a kind of air breathing engine.
Background technique
Conventional turbine air breathing engine and conventional turbofan motor are all to establish firing chamber between gas compressor and power turbine, although and after power turbine, have a structure of tail pipe burner, 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, therefore, the blade of power turbine is required also quite harsh, thereby the series of problems such as caused that this class motor involves great expense.For this reason, need to invent a kind of power turbine operating temperature is relatively low and/or power turbine working flow is less air breathing engine to reduce the cost of this class motor, improve the performance of 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 described duct, described power turbine is to described gas compressor outputting power, between described gas compressor and described power turbine, establish the first firing chamber, between described power turbine and the shrouded nozzle of described duct, establish the second firing chamber.
Described the first firing chamber and described the second firing chamber are made as continuous combustion chambers.
The amount that adjust to import the fuel of described the first firing chamber makes Temperature of Working in described the first firing chamber lower than 2300K.
The amount of adjusting the fuel that imports described the first firing chamber makes the mass flow rate of air and the ratio of quality of fuel flow that enter described the first firing chamber be greater than 20: 1.
Described shrouded nozzle is made as Laval nozzle.
At the place, suction port the place ahead of described duct, establish fan and form combustion chambers in tandem turbofan engine.
Described efficient turbojet engine also comprises bypass passageways, pressurized gas space between described gas compressor and described the first firing chamber is made as unburned gas space, space between described power turbine and described the 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 the second firing chamber by Partial shrinkage air without described the first firing chamber.
The amount of adjusting the fuel that imports described the first firing chamber makes the mass flow rate of air and the ratio of quality of fuel flow that enter described the first firing chamber be 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 invention is that gas compressor and power turbine are set in duct, power turbine is to gas compressor outputting power, two firing chambers are set in the front and back of power turbine, in firing chamber before being arranged on power turbine, only spraying into a small amount of fuel makes the temperature rise of working medium in reduced levels, thereby reduce the operating temperature of power turbine to realize the cost of material that reduces power turbine blade, can also make the rotating speed of power turbine have raising by a relatively large margin (Yin Wendu is lower simultaneously, so can bear larger centrifugal force), improve the compression ratio of motor, improve the efficiency of motor, in firing chamber after being arranged on power turbine, spray into a large amount of fuel, make it from jet pipe, to spray acquisition thrust after burning, 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 the high-pressure air after gas compressor compression directly enter the firing chamber being arranged on after power turbine, fuel and the mixed combustion in this firing chamber of this part air obtain thrust from ejection jet pipe under the prerequisite without any impeller class mechanism just as rocket chamber; In this structure, the working flow of power turbine can significantly reduce, and that is to say that the diameter of power turbine can significantly reduce, thereby reduces the effect of centrifugal force, can improve rotating speed, improves pressure ratio and efficiency.
So-called the first firing chamber refers to the firing chamber being arranged between power turbine and gas compressor; So-called the second firing chamber refers to the firing chamber being arranged between power turbine and shrouded nozzle; So-called shrouded nozzle refers to the jet pipe being communicated with the tail end of duct, and its function is to obtain reverse push power; So-called the place ahead refers to the gas access direction of duct, answers in contrast, and rear refers to the Way out of shrouded nozzle; The function of so-called bypass passageways is that the pressurized air after gas compressor compression is directly imported to the second firing chamber without the first firing chamber, and its shape can be pipe, can be also annular pass; So-called unburned gas space refers to the existing space of pressurized gas of not carrying out any combustion reaction after gas compressor compression; So-called half combustion gas body space has referred to carrying out after the gas compressor compression existing space of pressurized gas of partial combustion reaction (i.e. the inner aerobic that contains, the content of oxygen can be high or low); So-called " described power turbine is to described gas compressor outputting power " refers to that power turbine promotes 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 present invention, the amount that adjust to import the fuel of described the first firing chamber makes Temperature of Working in described the first firing chamber lower than 2200K, 2100K, 2000K, 1900K, 1800K, 1700K, 1600K, 1500K, 1400K, 1300K, 1200K, 1100K, 1000K or lower than 900K.
In the present invention, the amount that adjust to import the fuel of described the first firing chamber makes to enter the mass flow rate of air of described the first firing chamber and the ratio of quality of fuel flow is 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 be greater than 150: 1.
In the present invention, the amount that adjust to import the fuel of described the first firing chamber makes to enter the mass flow rate of air of described the first firing chamber and the ratio of quality of fuel flow is 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 be greater than 150: 1.
In the present invention, so-called continuous combustion chambers refers under the condition of engine work, and the firing chamber of combustion chemistry reaction occurs always.
In the present invention, so-called Jet injector refers to 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), can be also liquid-jet pump; So-called Jet injector can be traditional Jet injector, can be also non-traditional Jet injector.
In the present invention, so-called traditional Jet injector refers to that the pipe that arranged by two suits forms, to inner tube, provide high voltage power gas, inner tube high voltage power gas sprays within the outer tube, the device that makes other gases (gas entering from outer tube) between inner and outer pipes move along the injection direction generation of inner tube high voltage power gas under the acting in conjunction of the injection of inner tube high voltage power gas and outer tube; The outer tube of so-called Jet injector can have reducing and expansion district, and outer tube can be made as Venturi tube, and inner tube nozzle can be made as Laval nozzle, and so-called reducing and expansion district refers to the region that in outer tube, section area changes; Described Jet injector has three interfaces at least or claims passage, i.e. Jet injector power gas jetburner, Jet injector low-pressure gas entrance and Jet injector gas outlet.
In the present invention, so-called non-traditional Jet injector refers to that the pipe that arranged or be mutually set up in parallel by two or more mutual sheathing forms, wherein at least one pipe is communicated with motive gas source, and flowing of the power gas in motive gas source can cause the device of the γ-ray emission directional flow in other pipes; The pipe of so-called Jet injector can have 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 region that in vial, section area changes; Described Jet injector has three interfaces at least or claims passage, i.e. Jet injector power gas jetburner, Jet injector low-pressure gas entrance and Jet injector gas outlet; Described Jet injector can comprise a plurality of Jet injector power gas jetburners, in comprising the structure of 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 entrance, also can be arranged near the tube wall of described Jet injector low-pressure gas entrance, described Jet injector power gas jetburner can be also the annular spray mouth around described Jet injector low-pressure gas inlet pipe wall.
In the present invention, described Jet injector comprises Multi-stage jet pump, multiple jets pump and Pulsed Jet Pump etc.
In the present invention, so-called " described unburned gas space is communicated with described half combustion gas body space through Jet injector through described bypass passageways again " refers to 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 entrance of described Jet injector, and the Jet injector gas outlet of described Jet injector is communicated with described the second firing chamber; Or refer to that described bypass passageways is communicated with the Jet injector low-pressure gas entrance 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 the second firing chamber.
In the present invention, according to known technology, should in described the first firing chamber and described the second firing chamber, establish fuel introducing port and ignition mechanism.
In the present invention, according to known technology, in necessary place, establish necessary parts, unit or system.
Beneficial effect of the present invention is as follows:
The present invention has realized efficient, low emission and the low cost of turbojet engine.
Accompanying drawing explanation
Fig. 1 is the embodiment of the present invention 1 and embodiment's 2 structural representation;
Fig. 2 is the structural representation of the embodiment of the present invention 3;
Fig. 3 is the structural representation of the embodiment of the present invention 4;
Fig. 4 is the structural representation of the embodiment of the present invention 5.
In 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 duct 1,3 pairs of gas compressor 2 outputting powers of power turbine, between gas compressor 2 and power turbine 3, establish the first firing chamber 203, between power turbine 3 and the shrouded nozzle 4 of duct 1, establish the second firing chamber 204.Described the first firing chamber 203 and described the second firing chamber 204 are made as continuous combustion chambers.The amount that adjust to import the fuel of described the first firing chamber 203 makes Temperature of Working in described the first firing chamber 203 lower than 2300K, 2200K, 2100K, 2000K, 1900K, 1800K, 1700K, 1600K, 1500K, 1400K, 1300K, 1200K, 1100K, 1000K or 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 the first firing chamber 203 makes the mass flow rate of air and the ratio of quality of fuel flow that enter described the first firing chamber 203 be 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 be 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 the first firing chamber 203 is made as unburned gas space 2203, space between described power turbine 3 and described the 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, described bypass passageways 6 directly imports described the second firing chamber 204 by Partial shrinkage air without described the first firing chamber 203.
Embodiment 4
Efficient turbojet engine as shown in Figure 3, itself and embodiment's 2 difference is: at suction port 5 places, the place aheads of duct 1, establish fan 7 and form combustion chambers in tandem turbofan engines, described shrouded nozzle 4 is made as Laval nozzle 401.The amount of adjusting the fuel that imports described the first firing chamber 203 makes the mass flow rate of air and the ratio of quality of fuel flow that enter described the first firing chamber 203 be 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 be greater than 150: 1.
Efficient turbojet engine as shown in Figure 4, it is with embodiment 3 difference: 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 invention is not restricted to above embodiment, according to the known technology of related domain and technological scheme disclosed in this invention, can derive or association goes out many flexible programs, all these flexible programs, also should think protection scope of the present invention.
Claims (6)
1. an efficient turbojet engine, comprise duct (1), gas compressor (2) and power turbine (3), described gas compressor (2) and described power turbine (3) are arranged in 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 the first firing chamber (203), between described power turbine (3) and the shrouded nozzle (4) of described duct (1), establish the second firing chamber (204), it is characterized in that: described efficient turbojet engine also comprises bypass passageways (6), pressurized gas space between described gas compressor (2) and described the first firing chamber (203) is made as unburned gas space (2203), space between described power turbine (3) and described the 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), described bypass passageways (6) will partly press air directly to import described the second firing chamber (204) without described the first firing chamber (203), 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.
2. efficient turbojet engine as claimed in claim 1, is characterized in that: described the first firing chamber (203) and described the second firing chamber (204) are made as continuous combustion chambers.
3. efficient turbojet engine as claimed in claim 1, is characterized in that: the amount of adjusting the fuel that imports described the first firing chamber (203) makes Temperature of Working in described the first firing chamber (203) lower than 2300K.
4. efficient turbojet engine as claimed in claim 1, is characterized in that: the amount of adjusting the fuel that imports described the first firing chamber (203) makes the mass flow rate of air and the ratio of quality of fuel flow that enter described the first firing chamber (203) be greater than 20:1.
5. efficient turbojet engine as claimed in claim 1, is characterized in that: described shrouded nozzle (4) is made as Laval nozzle (401).
6. efficient turbojet engine as claimed in claim 1, is characterized in that: at the place, suction port (5) the place ahead of described duct (1), establish fan (7) and form combustion chambers in tandem turbofan engine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110127356.8A CN102619642B (en) | 2010-10-19 | 2011-05-17 | Efficient turbojet engine |
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 | ||
| CN201110060162 | 2011-03-14 | ||
| CN201110060162.0 | 2011-03-14 | ||
| CN201110127356.8A CN102619642B (en) | 2010-10-19 | 2011-05-17 | Efficient turbojet engine |
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| Publication Number | Publication Date |
|---|---|
| CN102619642A CN102619642A (en) | 2012-08-01 |
| CN102619642B true CN102619642B (en) | 2014-03-19 |
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| CN201110127356.8A Active CN102619642B (en) | 2010-10-19 | 2011-05-17 | Efficient turbojet engine |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN103206255B (en) * | 2013-01-25 | 2014-12-10 | 祥天控股（集团）有限公司 | Method for connecting air cylinders and air inlet pipelines of variable multi-cylinder aerodynamic engine |
| CN104832287B (en) * | 2014-03-25 | 2016-10-05 | 摩尔动力(北京)技术股份有限公司 | Speed holds turbine engine |
| CN106703993A (en) * | 2015-11-14 | 2017-05-24 | 熵零股份有限公司 | Engine |
| CN108626024A (en) * | 2018-06-13 | 2018-10-09 | 杨清太 | A kind of jet-propelled wind turbine enhancer constructive method |
| CN109305361A (en) * | 2018-09-30 | 2019-02-05 | 杨清太 | Umbellate form aerospace helicopter (flying saucer) constructive method |
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| US3289409A (en) * | 1964-07-13 | 1966-12-06 | Phillips Petroleum Co | Hiding condensation trails from high altitude aircraft |
| FR2672641B1 (en) * | 1991-02-13 | 1995-01-13 | Snecma | POST-COMBUSTION DEVICE WITH PIVOTING SHUTTERS. |
| WO1992021872A1 (en) * | 1991-05-29 | 1992-12-10 | Volvo Flygmotor Ab | A flame holder device in afterburner tubes of turbojet engines having an air fan rotor of by-pass type |
| CH687269A5 (en) * | 1993-04-08 | 1996-10-31 | Abb Management Ag | Gas turbine group. |
| CN1204005A (en) * | 1997-06-26 | 1999-01-06 | 亚瑞亚·勃朗勃威力有限公司 | Jet engine |
| IL164183A0 (en) * | 1999-03-10 | 2005-12-18 | Williams Int Co Llc | A rotor system for a rocket engine |
| US7730714B2 (en) * | 2005-11-29 | 2010-06-08 | General Electric Company | Turbofan gas turbine engine with variable fan outlet guide vanes |
| CN202091057U (en) * | 2010-10-19 | 2011-12-28 | 靳北彪 | Turbine jet engine with high efficiency |
| CN202116086U (en) * | 2011-05-16 | 2012-01-18 | 赵祖良 | Rotary plate type paper collection machine |
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Effective date of registration: 20200615 Address after: No.26, niqiao South Street, Xilai Town, Jingjiang City, Taizhou City, Jiangsu Province Patentee after: Jiangsu Jinyuan transportation facilities Co.,Ltd. Address before: 100101, Beijing, Chaoyang District Beiyuan Road, No. 168, Sheng Sheng building, 24 floor Patentee before: Jin Beibiao |