CN102128101A - Jet engine with parallel combustion chambers - Google Patents
Jet engine with parallel combustion chambers Download PDFInfo
- Publication number
- CN102128101A CN102128101A CN2011100458073A CN201110045807A CN102128101A CN 102128101 A CN102128101 A CN 102128101A CN 2011100458073 A CN2011100458073 A CN 2011100458073A CN 201110045807 A CN201110045807 A CN 201110045807A CN 102128101 A CN102128101 A CN 102128101A
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- Prior art keywords
- power turbine
- duct
- firing chamber
- jet propulsion
- described power
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/30—Arrangement of components
- F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
- F05D2250/311—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being in line
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a jet engine with parallel combustion chambers, comprising a power turbine culvert, a jet propulsion culvert, an air inlet channel, an air compressor and a power turbine, wherein the air compressor is arranged in the air inlet channel, the power turbine culvert is communicated with the air inlet channel, the power turbine culvert is internally provided with a power turbine combustion chamber, the power turbine is arranged inside the power turbine culvert behind the power turbine combustion chamber, the power turbine outputs power to the air compressor, and the jet propulsion culvert is communicated with the air inlet channel and is internally provided with a jet propulsion combustion chamber which is communicated with a jet propulsion nozzle. By means of the jet engine provided by the invention, a turbojet engine achieves the advantages of high efficiency, low emission and low manufacturing cost.
Description
Technical field
The present invention relates to heat energy, power and propelling field, especially a kind of firing chamber in parallel air breathing engine.
Background technique
Conventional turbine air breathing engine or turbofan engine still have very high temperature, pressure through the working medium of power turbine, obtain reaction thrust by the jet pipe ejection again, in other words, in this class motor, working medium by power turbine has two tasks: the one, and the rotation of propulsion power turbine, the 2nd, obtain reaction thrust through the jet pipe ejection.This structure setting must cause the impeller of power turbine all at high temperature to be worked, so the amount of the material that need involve great expense is bigger, finally causes the cost of this class motor to raise.Therefore, a part of impeller of being badly in need of a kind of power turbine of invention is worked under higher temperature, another part impeller is worked under relatively low temperature, perhaps all impellers of power turbine the turbojet engine or turbofan engine of all working at a lower temperature.
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 firing chamber in parallel air breathing engine, comprise the power turbine duct, the jet propulsion duct, intake duct, gas compressor and power turbine, described gas compressor is located in the described intake duct, described power turbine duct is communicated with described intake duct, in described power turbine duct, establish the power turbine firing chamber, described power turbine is arranged on the described power turbine duct inside of described power turbine rear combustion chamber, described power turbine is to described gas compressor outputting power, described jet propulsion duct is communicated with described intake duct, establish the jet propulsion firing chamber in described jet propulsion duct, described jet propulsion firing chamber is communicated with the jet propulsion jet pipe.
A kind of firing chamber in parallel air breathing engine, comprise the power turbine duct, the jet propulsion duct, intake duct, gas compressor and power turbine, described gas compressor is located in the described intake duct, described power turbine duct is communicated with described intake duct, in described power turbine duct, establish power turbine external combustion heating-up zone, described power turbine is arranged on the described power turbine duct inside at rear, described power turbine external combustion heating-up zone, described power turbine is to described gas compressor outputting power, described jet propulsion duct is communicated with described intake duct, establish the jet propulsion firing chamber in described jet propulsion duct, described jet propulsion firing chamber is communicated with the jet propulsion jet pipe.
Described power turbine duct suit is arranged in the described jet propulsion duct.
Described power turbine duct and described jet propulsion duct are set up in parallel.
A described power turbine duct and two or more described jet propulsion duct are set up in parallel.
Adjust air fuel ratio in the described power turbine firing chamber and make air fuel ratio in the described power turbine firing chamber, in the relatively low environment of temperature, work to realize described power turbine greater than the air fuel ratio in air fuel ratio in the conventional turbine air breathing engine firing chamber and the turbofan air breathing engine firing chamber.
The rotating speed of described power turbine is made as the rotating speed of the power turbine of the rotating speed of the power turbine that is higher than the conventional turbine air breathing engine and turbofan air breathing engine.
The diameter of described power turbine is less than the diameter of the power turbine of the conventional turbine air breathing engine with equal propelling force and the diameter of the power turbine of the traditional turbofan air breathing engine with equal propelling force.
The pressure of the output gas of described gas compressor is greater than the pressure of the blower outlet of the pressure of the blower outlet of conventional turbine air breathing engine and turbofan engine.
Fan is established in the place ahead at described gas compressor.
Among the present invention, the principle that is provided with the scheme of described power turbine firing chamber and described jet propulsion firing chamber is the high-pressure air that will be produced by a described gas compressor and described intake duct separated into two parts at least, wherein at least a portion enters described power turbine duct, all the other enter described jet propulsion duct, combustion chemistry reaction back takes place and promotes described power turbine rotation in the high-pressure air that enters described power turbine duct in described power turbine firing chamber, described power turbine promotes described gas compressor rotation, working medium by described power turbine is not had the requirement that advances, and the high-pressure air that enters described jet propulsion duct enters described propelling nozzle and produces propelling force after the combustion chemistry reaction takes place in described jet propulsion firing chamber.Among the present invention, the principle that is provided with the scheme of described power turbine external combustion heating-up zone and described jet propulsion firing chamber is the high-pressure air that will be produced by a described gas compressor and described intake duct separated into two parts at least, wherein at least a portion enters described power turbine duct, all the other enter described jet propulsion duct, the high-pressure air that enters described power turbine duct is heated the back and promotes described power turbine rotation in described power turbine external combustion heating-up zone, described power turbine promotes described gas compressor rotation, working medium by described power turbine there is not the requirement of propelling, the thermal source of described power turbine external combustion heating-up zone is the heat that the wall by described jet propulsion firing chamber imports into, and the high-pressure air that enters described jet propulsion duct enters described propelling nozzle and produces propelling force after the combustion chemistry reaction takes place in described jet propulsion firing chamber.
In these two schemes of the present invention, the working medium of described power turbine duct has only a task, be exactly to utilize all energy of working medium itself to promote described power turbine rotation as far as possible, to described gas compressor outputting power, do not bear or seldom become to bear the task of obtaining reaction thrust by spraying, so just can realize that a part of impeller of power turbine works under higher temperature, another part impeller is worked under relatively low temperature, perhaps all impellers of power turbine purpose of all working at a lower temperature, thus the cost of motor reduced; Moreover,, improve the pressure ratio of described gas compressor, finally reach the purpose of the efficient that improves motor because the reduction of described power turbine operating temperature can increase substantially the rotating speed of described power turbine, thereby increase substantially the rotating speed of described gas compressor.
Among the present invention because the working medium by described power turbine duct; just do not bear or seldom bear the task of obtaining reaction thrust by spraying by the working medium of described power turbine; so the flux of described power turbine duct can reduce significantly; for this reason; the impeller diameter of described power turbine also can reduce significantly; because the reduction of described power turbine impeller diameter; the required centrifugal force of bearing of impeller also can reduce significantly; so; can improve the rotating speed of described power turbine; realize the raising of described gas compressor rotating speed, reach more high pressure ratio, finally improve the efficient of motor.
What is called of the present invention " described power turbine is to described gas compressor outputting power " is meant that described power turbine promotes the rotation of described gas compressor, comprises coaxial setting, also comprises through the constant speed of gear etc. or the impetus of speed changing structure; So-called power turbine firing chamber is meant the firing chamber that is arranged in the described power turbine duct, and its effect is to produce the working medium that promotes described power turbine; So-called jet propulsion firing chamber be meant be arranged in the described jet propulsion duct the firing chamber, its effect is to produce the working medium that enters described propelling nozzle, produces propelling force by described propelling nozzle; So-called power turbine external combustion heating-up zone is meant the part of described power turbine duct wall, its effect is that the high-pressure air in the described power turbine duct is heated, its thermal source can be the heat that transmits from described jet propulsion chamber wall, also can be other thermals source.
Among the present invention,, can in the air breathing engine of firing chamber in parallel disclosed in this invention, all necessary parts, unit or system be set according to known technology.
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;
Fig. 4 is the structural representation of the embodiment of the invention 4;
Fig. 5 is the structural representation of the embodiment of the invention 5;
Fig. 6 is the structural representation of the embodiment of the invention 6;
Fig. 7 is the structural representation of the embodiment of the invention 7;
Fig. 8 is the structural representation of the embodiment of the invention 8;
Fig. 9 is the structural representation of the embodiment of the invention 9.
Embodiment
Firing chamber in parallel air breathing engine as shown in Figure 1, comprise power turbine duct 1, jet propulsion duct 2, intake duct 3, gas compressor 4 and power turbine 5, described gas compressor 4 is located in the described intake duct 3, described power turbine duct 1 is communicated with described intake duct 3, in described power turbine duct 1, establish power turbine firing chamber 6, described power turbine 5 is arranged on described power turbine duct 1 inside at 6 rears, described power turbine firing chamber, 5 pairs of described gas compressor 4 outputting powers of described power turbine, described jet propulsion duct 2 is communicated with described intake duct 3, in described jet propulsion duct 2, establish jet propulsion firing chamber 7, described jet propulsion firing chamber 7 is communicated with jet propulsion jet pipe 8, and described power turbine duct 1 suit is arranged in the described jet propulsion duct 2; Adjust air fuel ratios in the described power turbine firing chamber 6 and make air fuel ratio in the described power turbine firing chamber 6, in the relatively low environment of temperature, work to realize described power turbine 5 greater than the air fuel ratio in air fuel ratio in the conventional turbine air breathing engine firing chamber and the turbofan air breathing engine firing chamber.The rotating speed of described power turbine 5 is made as the rotating speed of the power turbine of the rotating speed of the power turbine that is higher than the conventional turbine air breathing engine and turbofan air breathing engine, the diameter of described power turbine 5 is less than the diameter of the power turbine of the conventional turbine air breathing engine with equal propelling force and have the diameter of power turbine of traditional turbofan air breathing engine of equal propelling force, and the pressure of the output gas of described gas compressor 4 is greater than the pressure of the blower outlet of the pressure of the blower outlet of conventional turbine air breathing engine and turbofan engine.
Firing chamber in parallel air breathing engine as shown in Figure 2, comprise power turbine duct 1, jet propulsion duct 2, intake duct 3, gas compressor 4 and power turbine 5, described gas compressor 4 is located in the described intake duct 3, described power turbine duct 1 is communicated with described intake duct 3, in described power turbine duct 1, establish power turbine external combustion heating-up zone 60, described power turbine 5 is arranged on described power turbine duct 1 inside at 60 rears, described power turbine external combustion heating-up zone, 5 pairs of described gas compressor 4 outputting powers of described power turbine, described jet propulsion duct 2 is communicated with described intake duct 3, in described jet propulsion duct 2, establish jet propulsion firing chamber 7, described jet propulsion firing chamber 7 is communicated with jet propulsion jet pipe 8, and described power turbine duct 1 suit is arranged in the described jet propulsion duct 2.The rotating speed of described power turbine 5 is made as the rotating speed of the power turbine of the rotating speed of the power turbine that is higher than the conventional turbine air breathing engine and turbofan air breathing engine, the diameter of described power turbine 5 is less than the diameter of the power turbine of the conventional turbine air breathing engine with equal propelling force and have the diameter of power turbine of traditional turbofan air breathing engine of equal propelling force, and the pressure of the output gas of described gas compressor 4 is greater than the pressure of the blower outlet of the pressure of the blower outlet of conventional turbine air breathing engine and turbofan engine.
Firing chamber in parallel air breathing engine as shown in Figure 3, itself and embodiment's 2 difference is: described power turbine duct 1 extends to the rear of described jet propulsion jet pipe 8, described gas compressor 4 and the 5 coaxial settings of described power turbine.
Firing chamber in parallel air breathing engine as shown in Figure 4, itself and embodiment's 1 difference is: establish fan 330 in the place ahead of described gas compressor 4.
Firing chamber in parallel air breathing engine as shown in Figure 5, itself and embodiment's 4 difference is: at described fan 330 peripheral hardware fan ducts 333.
Firing chamber in parallel air breathing engine as shown in Figure 6, its difference with embodiment 1 is: described firing chamber in parallel air breathing engine also comprises starting drive 10,10 pairs of described gas compressor 4 outputting powers of described starting drive.
Firing chamber in parallel air breathing engine as shown in Figure 7, its difference with embodiment 2 is: establish fan 330 in the place ahead of described gas compressor 4 and constitute described jet propulsion firing chamber 7 and described power turbine external combustion heating-up zone 60 turbofan engine in parallel.
Firing chamber in parallel air breathing engine as shown in Figure 8, itself and embodiment's 1 difference is: described power turbine duct 1 is set up in parallel with described jet propulsion duct 2.
Embodiment 9
Firing chamber in parallel air breathing engine as shown in Figure 9, itself and embodiment's 1 difference is: a described power turbine duct 1 and two described jet propulsion ducts 2 are set up in parallel.
Obviously, the invention is not restricted to above embodiment, many distortion can also be arranged.Those of ordinary skill in the art, all distortion that can directly derive or associate from content disclosed by the invention all should be thought protection scope of the present invention.
Claims (10)
1. firing chamber in parallel air breathing engine, comprise power turbine duct (1), jet propulsion duct (2), intake duct (3), gas compressor (4) and power turbine (5), it is characterized in that: described gas compressor (4) is located in the described intake duct (3), described power turbine duct (1) is communicated with described intake duct (3), in described power turbine duct (1), establish power turbine firing chamber (6), described power turbine (5) is arranged on described power turbine duct (1) inside at rear, described power turbine firing chamber (6), described power turbine (5) is to described gas compressor (4) outputting power, described jet propulsion duct (2) is communicated with described intake duct (3), establish jet propulsion firing chamber (7) in described jet propulsion duct (2), described jet propulsion firing chamber (7) is communicated with jet propulsion jet pipe (8).
2. firing chamber in parallel air breathing engine, comprise power turbine duct (1), jet propulsion duct (2), intake duct (3), gas compressor (4) and power turbine (5), it is characterized in that: described gas compressor (4) is located in the described intake duct (3), described power turbine duct (1) is communicated with described intake duct (3), in described power turbine duct (1), establish power turbine external combustion heating-up zone (60), described power turbine (5) is arranged on described power turbine duct (1) inside at rear, described power turbine external combustion heating-up zone (60), described power turbine (5) is to described gas compressor (4) outputting power, described jet propulsion duct (2) is communicated with described intake duct (3), establish jet propulsion firing chamber (7) in described jet propulsion duct (2), described jet propulsion firing chamber (7) is communicated with jet propulsion jet pipe (8).
3. firing chamber in parallel as claimed in claim 1 or 2 air breathing engine is characterized in that: described power turbine duct (1) suit is arranged in the described jet propulsion duct (2).
4. firing chamber in parallel as claimed in claim 1 or 2 air breathing engine is characterized in that: described power turbine duct (1) is set up in parallel with described jet propulsion duct (2).
5. firing chamber in parallel as claimed in claim 1 or 2 air breathing engine is characterized in that: a described power turbine duct (1) is set up in parallel with two or more described jet propulsion ducts (2).
6. firing chamber in parallel according to claim 1 air breathing engine, it is characterized in that: the air fuel ratio of adjusting in the described power turbine firing chamber (6) makes the interior air fuel ratio in described power turbine firing chamber (6) greater than the air fuel ratio in air fuel ratio in the conventional turbine air breathing engine firing chamber and the turbofan air breathing engine firing chamber, works in the relatively low environment of temperature to realize described power turbine (5).
7. firing chamber in parallel as claimed in claim 1 or 2 air breathing engine is characterized in that: the rotating speed of described power turbine (5) is made as the rotating speed of the power turbine of the rotating speed of the power turbine that is higher than the conventional turbine air breathing engine and turbofan air breathing engine.
8. firing chamber in parallel as claimed in claim 1 or 2 air breathing engine is characterized in that: the diameter of described power turbine (5) is less than the diameter of the power turbine of the conventional turbine air breathing engine with equal propelling force and the diameter of the power turbine of the traditional turbofan air breathing engine with equal propelling force.
9. firing chamber in parallel as claimed in claim 1 or 2 air breathing engine is characterized in that: the pressure of the output gas of described gas compressor (4) is greater than the pressure of the blower outlet of the pressure of the blower outlet of conventional turbine air breathing engine and turbofan engine.
10. firing chamber in parallel as claimed in claim 1 or 2 air breathing engine is characterized in that: establish fan (330) in the place ahead of described gas compressor (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011100458073A CN102128101A (en) | 2010-10-19 | 2011-02-25 | Jet engine with parallel combustion chambers |
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010511506 CN101975121A (en) | 2010-10-19 | 2010-10-19 | Culvert sleeved turbojet engine |
| CN201010511506.0 | 2010-10-19 | ||
| CN2011100458073A CN102128101A (en) | 2010-10-19 | 2011-02-25 | Jet engine with parallel combustion chambers |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102128101A true CN102128101A (en) | 2011-07-20 |
Family
ID=43575027
Family Applications (3)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201010511506 Pending CN101975121A (en) | 2010-10-19 | 2010-10-19 | Culvert sleeved turbojet engine |
| CN2011100458073A Pending CN102128101A (en) | 2010-10-19 | 2011-02-25 | Jet engine with parallel combustion chambers |
| CN 201120047791 Expired - Fee Related CN202055935U (en) | 2010-10-19 | 2011-02-25 | Jet engine with parallel combustion chambers |
Family Applications Before (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201010511506 Pending CN101975121A (en) | 2010-10-19 | 2010-10-19 | Culvert sleeved turbojet engine |
Family Applications After (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201120047791 Expired - Fee Related CN202055935U (en) | 2010-10-19 | 2011-02-25 | Jet engine with parallel combustion chambers |
Country Status (2)
| Country | Link |
|---|---|
| CN (3) | CN101975121A (en) |
| WO (1) | WO2012051783A1 (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104018952A (en) * | 2014-03-22 | 2014-09-03 | 张鑫宇 | Aircraft engine |
| CN110486171A (en) * | 2017-08-29 | 2019-11-22 | 熵零技术逻辑工程院集团股份有限公司 | A kind of outer injection-type engine cooling system of axis transmission |
| CN111779592A (en) * | 2020-06-01 | 2020-10-16 | 北京航空航天大学 | Mixed exhaust turbofan engine propulsion system introducing parallel combustion chambers |
Families Citing this family (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101975121A (en) * | 2010-10-19 | 2011-02-16 | 靳北彪 | Culvert sleeved turbojet engine |
| CN106677901A (en) * | 2015-11-10 | 2017-05-17 | 熵零股份有限公司 | Aeroengine |
| CN105697148B (en) * | 2016-04-11 | 2018-04-10 | 清华大学 | Turbogenerator |
| CN108087149B (en) * | 2016-11-22 | 2020-05-19 | 江西洪都航空工业集团有限责任公司 | Turbojet engine with high thrust-weight ratio and low oil consumption |
| CN108252935A (en) * | 2016-12-29 | 2018-07-06 | 上海鼓风机厂有限公司 | Multistage culvert type axial flow compressor |
| CN109538376B (en) * | 2018-11-07 | 2021-01-26 | 中国航发湖南动力机械研究所 | Aircraft and engine thereof |
| CN110985207A (en) * | 2019-12-30 | 2020-04-10 | 绵阳小巨人动力设备有限公司 | Miniature double-combustion-chamber variable-circulation turbojet engine |
| CN111636976B (en) * | 2020-06-08 | 2021-10-19 | 清华大学 | Three-duct high-thrust-weight-ratio efficient power propeller |
| CN112945306B (en) * | 2021-02-05 | 2022-06-07 | 中国航发沈阳发动机研究所 | Test platform for simultaneously measuring thrust and flow of double-duct spray pipe |
| CN114790955A (en) * | 2022-05-06 | 2022-07-26 | 哈尔滨工业大学 | Hybrid power engine capable of realizing oil-electricity range extension |
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|---|---|---|---|---|
| CN1046958A (en) * | 1989-04-26 | 1990-11-14 | 通用电气公司 | Reduce the apparatus and method of differential pressure loading in augmented gas turbine engine |
| US20050257528A1 (en) * | 2004-05-19 | 2005-11-24 | Dunbar Donal S Jr | Retractable afterburner for jet engine |
| EP1939438A2 (en) * | 2006-12-18 | 2008-07-02 | General Electric Company | Duct burning mixed flow turbofan |
| CN202055935U (en) * | 2010-10-19 | 2011-11-30 | 靳北彪 | Jet engine with parallel combustion chambers |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3296800A (en) * | 1967-01-10 | Gas turbine power plant | ||
| US4335573A (en) * | 1970-09-02 | 1982-06-22 | General Electric Company | Gas turbine engine mixer |
| US4813229A (en) * | 1985-03-04 | 1989-03-21 | General Electric Company | Method for controlling augmentor liner coolant flow pressure in a mixed flow, variable cycle gas |
| CN201818391U (en) * | 2010-10-19 | 2011-05-04 | 靳北彪 | Duct-suited turbojet engine |
-
2010
- 2010-10-19 CN CN 201010511506 patent/CN101975121A/en active Pending
-
2011
- 2011-02-25 CN CN2011100458073A patent/CN102128101A/en active Pending
- 2011-02-25 WO PCT/CN2011/000300 patent/WO2012051783A1/en active Application Filing
- 2011-02-25 CN CN 201120047791 patent/CN202055935U/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1046958A (en) * | 1989-04-26 | 1990-11-14 | 通用电气公司 | Reduce the apparatus and method of differential pressure loading in augmented gas turbine engine |
| US20050257528A1 (en) * | 2004-05-19 | 2005-11-24 | Dunbar Donal S Jr | Retractable afterburner for jet engine |
| EP1939438A2 (en) * | 2006-12-18 | 2008-07-02 | General Electric Company | Duct burning mixed flow turbofan |
| CN202055935U (en) * | 2010-10-19 | 2011-11-30 | 靳北彪 | Jet engine with parallel combustion chambers |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104018952A (en) * | 2014-03-22 | 2014-09-03 | 张鑫宇 | Aircraft engine |
| CN110486171A (en) * | 2017-08-29 | 2019-11-22 | 熵零技术逻辑工程院集团股份有限公司 | A kind of outer injection-type engine cooling system of axis transmission |
| CN111779592A (en) * | 2020-06-01 | 2020-10-16 | 北京航空航天大学 | Mixed exhaust turbofan engine propulsion system introducing parallel combustion chambers |
Also Published As
| Publication number | Publication date |
|---|---|
| CN101975121A (en) | 2011-02-16 |
| CN202055935U (en) | 2011-11-30 |
| WO2012051783A1 (en) | 2012-04-26 |
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Application publication date: 20110720 |