CN101975121A - Culvert sleeved turbojet engine - Google Patents
Culvert sleeved turbojet engine Download PDFInfo
- Publication number
- CN101975121A CN101975121A CN 201010511506 CN201010511506A CN101975121A CN 101975121 A CN101975121 A CN 101975121A CN 201010511506 CN201010511506 CN 201010511506 CN 201010511506 A CN201010511506 A CN 201010511506A CN 101975121 A CN101975121 A CN 101975121A
- Authority
- CN
- China
- Prior art keywords
- duct
- gas compressor
- power turbine
- turbojet engine
- pass air
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
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Classifications
-
- 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
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- 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 culvert sleeved turbojet engine, comprising an inner culvert, an outer culvert, a compressor and a power turbine, wherein the inner culvert is sleeved in the outer culvert; the compressor is arranged at the front of the air inlet of the inner culvert in the outer culvert; the power turbine is arranged in the inner culvert and outputs power to the compressor, and the outer culvert is communicated with a spray pipe; and an outer culvert combustion chamber is arranged at the rear part of the compressor in the outer culvert, the wall of the inner culvert between the compressor and the power turbine is taken as a heat transfer area, or the space at the rear part of the compressor in the outer culvert is taken as the outer culvert combustion chamber, and a space between the compressor and the power turbine in the inner culver is provided with an inner culvert combustion chamber. By the invention, high efficiency, low emission and low manufacture cost of the turbojet engine can be realized.
Description
Technical field
The present invention relates to heat energy, power and propelling field, especially a kind of duct suit turbojet 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 duct suit turbojet engine, comprise main duct, by-pass air duct, gas compressor and power turbine, described main duct is set in the described by-pass air duct, the place, the place ahead that is positioned at described main duct suction port in described by-pass air duct is provided with described gas compressor, described power turbine is set in described main duct, described power turbine is to described gas compressor outputting power, and described by-pass air duct is communicated with jet pipe;
The by-pass air duct firing chamber is established at the rear portion that is positioned at described gas compressor in described by-pass air duct, the wall of the described main duct between described gas compressor and described power turbine is made as heat transfer zone, or the back space that is positioned at described gas compressor in described by-pass air duct establishes the by-pass air duct firing chamber, establishes the main duct firing chamber in the space in described main duct between described gas compressor and described power turbine.
The pressure of the output gas of described gas compressor is greater than the pressure of the firing chamber of conventional turbine air breathing engine.
Described main duct extends to the rear of described jet pipe.
Described gas compressor and the coaxial setting of described power turbine.
Establish fan constitutes firing chamber parallel turbine Duct-Burning Turbofan or constitutes the firing chamber turbofan engine in parallel with heat transfer zone in the place ahead of described gas compressor.
At described fan peripheral hardware fan duct.
Described duct suit turbojet engine also comprises starting drive, and described starting drive is to described gas compressor outputting power.
The principle of the first string is with the setting of two duct suits among the present invention, power turbine is set in main duct, gas compressor is set in by-pass air duct, described power turbine is to described gas compressor outputting power, the tail end of described by-pass air duct is communicated with jet pipe, the by-pass air duct firing chamber is set after described gas compressor in the space between two ducts, pressurized air after the gas compressor compression heats after the ejection of described jet pipe with the reaction of fuel generation combustion chemistry in the by-pass air duct firing chamber, obtain reaction thrust, the main duct wall that will be between by-pass air duct firing chamber and the power turbine is made as heat transfer zone, utilize the heat of by-pass air duct firing chamber will be in the heating of the pressurized air between gas compressor and power turbine in the main duct, heated pressurized air expansion propulsion power turbine is to the gas compressor work done.The principle of second scheme is with the setting of two duct suits among the present invention, power turbine is set in main duct, gas compressor is set in by-pass air duct, described power turbine is to described gas compressor outputting power, the tail end of described by-pass air duct is communicated with jet pipe, the by-pass air duct firing chamber is set after described gas compressor in the space between two ducts, and the pressurized air after the gas compressor compression heats after the ejection of described jet pipe obtains reaction thrust with the reaction of fuel generation combustion chemistry in the by-pass air duct firing chamber; Establish the main duct firing chamber in described main duct between gas compressor and power turbine, the pressurized air and the reaction of fuel generation combustion chemistry that enter main duct heat back expansion propulsion power turbine to the gas compressor work done.In these two schemes of the present invention; the working medium of main duct has only a task; be exactly all energy propulsion power turbine rotations that utilize working medium itself as far as possible; to the gas compressor outputting power; do not bear or seldom become to bear to see through and spray the task of obtaining reaction thrust; 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; thereby reduce the cost of motor, raise the efficient of motor.
Among the present invention owing to pass through main duct, just do not bear the task of obtaining reaction thrust by spraying by the working medium of power turbine, so the flux of main duct can reduce significantly, the impeller diameter of power turbine also can reduce significantly, because the reduction of power turbine impeller diameter, the required centrifugal force of bearing of impeller also can reduce significantly, for this reason, can improve the rotating speed of power turbine, realize the raising of gas compressor rotating speed, reach more high compression ratio, finally raise the efficient of motor.
What is called of the present invention " 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 through the constant speed of gear etc. or the impetus of speed changing structure; So-called main duct firing chamber is meant the firing chamber that is arranged in the main duct; So-called by-pass air duct firing chamber is meant and is arranged in the by-pass air duct or is arranged on firing chamber between main duct and the by-pass air duct; So-called starting drive is meant the device that promotes the gas compressor rotation before light the firing chamber, make the air that enters the firing chamber have certain pressure, particularly only be provided with in the present invention in the mechanism of by-pass air duct firing chamber, starting drive be set the starting time that can shorten motor significantly.
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.
Embodiment
Duct suit turbojet engine as shown in Figure 1, comprise main duct 1, by-pass air duct 2, gas compressor 3 and power turbine 4, main duct 1 is set in the by-pass air duct 2, the place, the place ahead that is positioned at main duct 1 suction port in by-pass air duct 2 is provided with gas compressor 3, power turbine 4 is set in main duct 1,4 pairs of gas compressor 3 outputting powers of power turbine, by-pass air duct 2 is communicated with jet pipe 5, by-pass air duct firing chamber 200 is established at the rear portion that is positioned at gas compressor 3 in by-pass air duct 2, and the wall of the main duct 1 between gas compressor 3 and power turbine 4 is made as heat transfer zone 134.The pressure of the output gas of gas compressor 3 is greater than the pressure of the firing chamber of conventional turbine air breathing engine.
Duct suit turbojet engine as shown in Figure 2, itself and embodiment's 1 difference is: the back space that is positioned at gas compressor 3 in by-pass air duct 2 is established by-pass air duct firing chamber 200, establishes main duct firing chamber 100 in the space in main duct 1 between gas compressor 3 and power turbine 4.
Duct suit turbojet engine as shown in Figure 3, itself and embodiment's 1 difference is: main duct 1 extends to the rear of jet pipe 5, gas compressor 3 and power turbine 4 coaxial settings.
Duct suit turbojet engine as shown in Figure 4, itself and embodiment's 2 difference is: establish fan 330 in the place ahead of gas compressor 3 and constitute firing chamber parallel turbine Duct-Burning Turbofans.
Duct suit turbojet engine as shown in Figure 5, itself and embodiment's 4 difference is: at fan 330 peripheral hardware fan ducts 6.
Embodiment 6
Duct suit turbojet engine as shown in Figure 6, itself and embodiment's 2 difference is: duct suit turbojet engine also comprises starting drive 10,10 pairs of gas compressor 3 outputting powers of starting drive.
Embodiment 7
Duct suit turbojet engine as shown in Figure 7, its difference with embodiment 1 is: establish fan in the place ahead of described gas compressor and constitute the firing chamber turbofan engine in parallel with heat transfer zone.
Claims (7)
1. duct suit turbojet engine, comprise main duct (1), by-pass air duct (2), gas compressor (3) and power turbine (4), it is characterized in that: described main duct (1) is set in the described by-pass air duct (2), the place, the place ahead that is positioned at described main duct (1) suction port in described by-pass air duct (2) is provided with described gas compressor (3), described power turbine (4) is set in described main duct (1), described power turbine (4) is to described gas compressor (3) outputting power, and described by-pass air duct (2) is communicated with jet pipe (5);
By-pass air duct firing chamber (200) is established at the rear portion that is positioned at described gas compressor (3) in described by-pass air duct (2), the wall of the described main duct (1) between described gas compressor (3) and described power turbine (4) is made as heat transfer zone (134), or the back space that is positioned at described gas compressor (3) in described by-pass air duct (2) establishes by-pass air duct firing chamber (200), and main duct firing chamber (100) is established in the space that is positioned in described main duct (1) between described gas compressor (3) and the described power turbine (4).
2. duct suit turbojet engine according to claim 1, it is characterized in that: the pressure of the output gas of described gas compressor (3) is greater than the pressure of the firing chamber of conventional turbine air breathing engine.
3. duct suit turbojet engine according to claim 1, it is characterized in that: described main duct (1) extends to the rear of described jet pipe (5).
4. duct suit turbojet engine according to claim 1 is characterized in that: described gas compressor (3) and the coaxial setting of described power turbine (4).
5. duct suit turbojet engine according to claim 1 is characterized in that: establish fan (330) in the place ahead of described gas compressor (3) and constitute firing chamber parallel turbine Duct-Burning Turbofan or constitute the firing chamber turbofan engine in parallel with heat transfer zone.
6. as duct suit turbojet engine as described in the claim 5, it is characterized in that: at described fan (330) peripheral hardware fan duct (6).
7. duct suit turbojet engine according to claim 1, it is characterized in that: described duct suit turbojet engine also comprises starting drive (10), described starting drive (10) is to described gas compressor (3) outputting power.
Priority Applications (4)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010511506 CN101975121A (en) | 2010-10-19 | 2010-10-19 | Culvert sleeved turbojet engine |
| CN2011100458073A CN102128101A (en) | 2010-10-19 | 2011-02-25 | Jet engine with parallel combustion chambers |
| PCT/CN2011/000300 WO2012051783A1 (en) | 2010-10-19 | 2011-02-25 | Jet engine with parallel combustion chambers |
| CN 201120047791 CN202055935U (en) | 2010-10-19 | 2011-02-25 | Jet engine with parallel combustion chambers |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010511506 CN101975121A (en) | 2010-10-19 | 2010-10-19 | Culvert sleeved turbojet engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101975121A true CN101975121A (en) | 2011-02-16 |
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 After (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| 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 |
Country Status (2)
| Country | Link |
|---|---|
| CN (3) | CN101975121A (en) |
| WO (1) | WO2012051783A1 (en) |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2012051783A1 (en) * | 2010-10-19 | 2012-04-26 | Jin Beibiao | Jet engine with parallel combustion chambers |
| CN105697148A (en) * | 2016-04-11 | 2016-06-22 | 清华大学 | Turbine engine |
| CN106677901A (en) * | 2015-11-10 | 2017-05-17 | 熵零股份有限公司 | Aeroengine |
| CN108087149A (en) * | 2016-11-22 | 2018-05-29 | 江西洪都航空工业集团有限责任公司 | A kind of turbojet engine of the low oil consumption of high thrust-weight ratio |
| CN108252935A (en) * | 2016-12-29 | 2018-07-06 | 上海鼓风机厂有限公司 | Multistage culvert type axial flow compressor |
| 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 |
| 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 |
| WO2020093578A1 (en) * | 2018-11-07 | 2020-05-14 | 中国航发湖南动力机械研究所 | Aircraft and engine thereof |
| CN111636976A (en) * | 2020-06-08 | 2020-09-08 | 清华大学 | Three-duct high-thrust-weight-ratio efficient power propeller |
| CN112945306A (en) * | 2021-02-05 | 2021-06-11 | 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 |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104018952A (en) * | 2014-03-22 | 2014-09-03 | 张鑫宇 | Aircraft engine |
| 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 |
Family Cites Families (8)
| 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 |
| US5070690A (en) * | 1989-04-26 | 1991-12-10 | General Electric Company | Means and method for reducing differential pressure loading in an augmented gas turbine engine |
| US7334409B2 (en) * | 2004-05-19 | 2008-02-26 | Alltech, Inc. | Retractable afterburner for jet engine |
| US7770381B2 (en) * | 2006-12-18 | 2010-08-10 | General Electric Company | Duct burning mixed flow turbofan and method of operation |
| CN201818391U (en) * | 2010-10-19 | 2011-05-04 | 靳北彪 | Duct-suited turbojet engine |
| CN101975121A (en) * | 2010-10-19 | 2011-02-16 | 靳北彪 | Culvert sleeved 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
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2012051783A1 (en) * | 2010-10-19 | 2012-04-26 | Jin Beibiao | Jet engine with parallel combustion chambers |
| CN106677901A (en) * | 2015-11-10 | 2017-05-17 | 熵零股份有限公司 | Aeroengine |
| CN105697148A (en) * | 2016-04-11 | 2016-06-22 | 清华大学 | Turbine engine |
| 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 |
| CN108087149A (en) * | 2016-11-22 | 2018-05-29 | 江西洪都航空工业集团有限责任公司 | A kind of turbojet engine of the low oil consumption of high thrust-weight ratio |
| CN108252935A (en) * | 2016-12-29 | 2018-07-06 | 上海鼓风机厂有限公司 | Multistage culvert type axial flow compressor |
| 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 |
| WO2020093578A1 (en) * | 2018-11-07 | 2020-05-14 | 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 |
| CN111636976A (en) * | 2020-06-08 | 2020-09-08 | 清华大学 | Three-duct high-thrust-weight-ratio efficient power propeller |
| CN112945306A (en) * | 2021-02-05 | 2021-06-11 | 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 |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102128101A (en) | 2011-07-20 |
| WO2012051783A1 (en) | 2012-04-26 |
| CN202055935U (en) | 2011-11-30 |
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Open date: 20110216 |