CN106837602B - Small-sized fanjet - Google Patents
Small-sized fanjet Download PDFInfo
- Publication number
- CN106837602B CN106837602B CN201710089734.5A CN201710089734A CN106837602B CN 106837602 B CN106837602 B CN 106837602B CN 201710089734 A CN201710089734 A CN 201710089734A CN 106837602 B CN106837602 B CN 106837602B
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- CN
- China
- Prior art keywords
- anger
- turbine
- calming
- housing
- flame tube
- Prior art date
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
-
- 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
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
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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
A kind of small-sized fanjet, including compressor, combustion chamber and power turbine, compressor include calm the anger housing and centrifugal impeller, power turbine includes turbine body and turbine shroud, connector is provided with combustion chamber, connector is provided with calm the anger end cap and turbine end cap, and air end of booster, which covers, is communicated with hole；Some detonation flame tubes are provided with combustion chamber, air inlet and gas outlet are equipped with every detonation flame tube, gas outlet communicates with turbine shroud inlet end, check valve is provided with the air inlet of detonation flame tube, fuel nozzle and igniter plug are equipped with every detonation flame tube, is connected between fuel nozzle by total cartridge.The present invention continuously promotes turbine body by the detonation successively of detonation flame tube using four kinds of thrusts, and detonation flame tube gathers to detonation power, and in the presence of check valve, smooth air inlet, improves the bypass ratio and compression ratio of engine.
Description
Technical field
The present invention relates to a kind of engine, more particularly to a kind of small-sized fanjet.
Background technology
In fanjet, fan is improved, the pressure ratio of compressor can increase thrust, improve pressure ratio, current master
If increasing fan, axial-flow compressor, the series of turbine or raising turbine entrance temperature temperature, but by increasing fuel oil, increase
The series of mechanism of qi of pressurizeing increases thrust, it is difficult to the pressure of compressor, the volume for reducing engine, increase horsepower are improved, these
Improved procedure and can not obtain significant effect to improving bypass ratio, compression ratio and the thrust-weight ratio of fanjet, and existing
Have in technology and be not present by four kinds of coefficient engines of thrust.
The content of the invention
The technical problems to be solved by the invention are in view of the shortcomings of the prior art, there is provided it is a kind of reasonable in design, by four kinds
The coefficient small-sized fanjet of thrust.
The technical problems to be solved by the invention are realized by following technical scheme, and the present invention is a kind of small-sized
Fanjet, it is characterized in, including compressor, combustion chamber and the power turbine set gradually along airintake direction, it is described to calm the anger
Machine includes calm the anger housing and centrifugal impeller, and the power turbine includes turbine body and turbine shroud, connection is provided with combustion chamber
Calm the anger the connector of housing and turbine shroud, connector is provided with calming the anger of connecting with housing of calming the anger and end cap and connected with turbine shroud
Turbine end cap, air end of booster, which covers, is communicated with calm the anger housing and the intercommunicating pore of combustion chamber；
Some detonation flame tubes set with the diameter parallel of turbine body, detonation flame tube are provided with the combustion chamber
Along the circumferentially distributed of connector, air inlet and gas outlet, gas outlet and turbine shroud air inlet are equipped with every detonation flame tube
End is communicated, and check valve is provided with the air inlet of detonation flame tube, fuel nozzle and igniter plug are equipped with every detonation flame tube,
Connected between fuel nozzle by total cartridge；
Compressor after intercommunicating pore is sent into combustion chamber, pushes compressed air open check valve, into detonation flame tube, fuel oil spray
Mouth sprays into atomized fuel, one of detonation flame tube of lighting a fire, produces detonation wave, and check valve is closed automatically, detonation wave, combustion vapour
Sprayed with gases at high pressure out of detonation flame tube gas outlet, these three thrusts promote turbine body to operate jointly, detonation wave mistake
Afterwards, compressor continues air inlet, meanwhile, next detonation flame tube igniting detonation, turbine body operating is continued to press on, with such
Push away, detonation occurs successively for detonation flame tube, makes turbine body continuous running by continuous thrust.
The technical problems to be solved by the invention can also be realized by following technical scheme, in the air end of booster
The periphery of lid is provided with a circle groove, and the housing of calming the anger is provided with the projection being installed in groove.
The technical problems to be solved by the invention can also be realized by following technical scheme, in the groove
Provided with the sealing ring being engaged with projection.
The technical problems to be solved by the invention can also be realized by following technical scheme, in the turbine case
Steam pipe coil is provided with vitro, the port of export of steam pipe coil connects with the inlet end of turbine shroud.
The technical problems to be solved by the invention can also be realized by following technical scheme, described intercommunicating pore
Provided with several, it is uniformly distributed along the circumference for end cap of calming the anger.
The technical problems to be solved by the invention can also be realized by following technical scheme, in the shell of calming the anger
Fan blade is housed in vitro.
The technical problems to be solved by the invention can also be realized by following technical scheme, described shell of calming the anger
Connection centrifugal impeller and the planetary mechanism of turbine body are provided with vivo, and the planetary mechanism includes planet carrier, planetary gear, the sun
Wheel and gear ring, housing of calming the anger connect with gear ring, and planet carrier is fixed on air end of booster and covered, the wheel shaft of sun gear and the wheel of centrifugal impeller
Axle, the coaxial setting of the wheel shaft of turbine body.
The technical problems to be solved by the invention can also be realized by following technical scheme, described shell of calming the anger
Body includes shell body, and the inlet end of shell body is provided with entry impeller, and the outlet side of shell body rotates with connector to connect.
Compared with prior art, the present invention is by the detonation successively of detonation flame tube, and detonation flame tube is to detonation power progress
Accumulation, avoid thrust diffusion from being difficult to enter in turbine shroud, and utilize the thrust of compressed air, detonation wave thrust, combustion vapour thrust
And four kinds of thrusts of steam thrust promote turbo driving jointly, in the presence of check valve, avoid reverse impact in detonation process
The smooth air inlet of compressor is influenceed, its is reasonable in design, easy to operate, energy-saving and emission-reduction, improves bypass ratio, the compression ratio of engine
And thrust-weight ratio, use range of the invention are wide.
Brief description of the drawings
Fig. 1 is the structural representation of the present invention.
Embodiment
Referring to the drawings, the concrete technical scheme of the present invention is further described, in order to which those skilled in the art enters
One step the present invention is understood, without forming the limitation to its right.
Reference picture 1, a kind of small-sized fanjet, including set gradually along airintake direction compressor, combustion chamber 4 and dynamic
Power turbine, the compressor include calm the anger housing 1 and centrifugal impeller 2, and the power turbine includes turbine body 10 and turbine case
Body 8, combustion chamber 4 is interior to be provided with the connector 14 for connecting calm the anger housing 1 and turbine shroud 8, and connector 14 is provided with and the phase of housing 1 of calming the anger
Calm the anger end cap 15 and the turbine end cap 9 that connects with turbine shroud 8 connect, is communicated with calm the anger housing 1 and combustion on end cap 15 of calming the anger
Burn the intercommunicating pore 5 of room 4；
Provided with some detonation flame tubes 6 set with the diameter parallel of turbine body 10, detonation fire in the combustion chamber 4
Flame tube 6 is circumferentially distributed along connector 14, and air inlet 11 and gas outlet, detonation flame tube 6 are equipped with every detonation flame tube 6
Air inlet 11 at be provided with check valve, gas outlet is communicated by communicating pipe 13 with the inlet end of turbine shroud 8, every detonation flame tube
Fuel nozzle 7 and igniter plug 12 are equipped with 6, is connected between fuel nozzle 7 by total cartridge；
Compressor after intercommunicating pore 5 is sent into combustion chamber 4, pushes compressed air open check valve, into detonation flame tube 6, combustion
Oil burner nozzle 7 sprays into atomized fuel, one of detonation flame tube 6 of lighting a fire, produces detonation wave, corresponds at detonation flame tube 6
Check valve is closed automatically, and detonation wave, combustion vapour and gases at high pressure spray out of detonation flame tube gas outlet, and these three thrusts are common
Turbine body 10 is promoted to operate, after detonation wave, compressor continues air inlet, meanwhile, the next igniting of detonation flame tube 6 detonation,
Continue to press on turbine body 10 to operate, by that analogy, detonation occurs successively for detonation flame tube 6, makes turbine body 10 by continuous
Thrust and continuous running；
The centrifugal impeller 2 is multistage centrifugal impeller, and housing 1 of calming the anger is that multistage is calmed the anger housing, and the ignition system can be adopted
Use plasma ignition.
A circle groove is provided with the periphery of the end cap 15 of calming the anger, the housing 1 of calming the anger, which is provided with, to be installed in groove
It is raised；The sealing ring being engaged with projection is provided with the groove.
Steam pipe coil 18 is externally provided with the turbine shroud 8, the entrance point of steam pipe coil is arranged to water inlet, steam pipe coil
The port of export connect with the inlet end of turbine shroud, make full use of detonation flame tube discharge waste heat, high pressure steam is sent into whirlpool
Take turns in housing, can produce steam increases turbine thrust, meanwhile, turbine temperature is reduced, wind is housed in the closure periphery of calming the anger
Fan leaf, increase the thrust of engine.
Described intercommunicating pore 5 is provided with several, is uniformly distributed along the circumference for end cap 15 of calming the anger.
Fan blade 16 is housed outside the housing 1 of calming the anger.
Connection centrifugal impeller and the planetary mechanism of turbine body are provided with described housing of calming the anger, the planetary mechanism includes
Planet carrier, planetary gear, sun gear and gear ring, housing of calming the anger connect with gear ring, and planet carrier is fixed on air end of booster and covered, sun gear
Wheel shaft and centrifugal impeller the coaxial setting of wheel shaft, the wheel shaft of turbine body, centrifugal impeller and sun gear rotate forward, calm the anger housing and
Compression impellor inverts, and produces gases at high pressure；
Described housing of calming the anger includes shell body, and the inlet end of shell body is provided with compression impellor 17, the outlet side of shell body
Rotate and connect with connector 14.
The present invention utilizes electronic spark control system and common rail electric-controlling fuel injection system, the compressed air warp of compressor
Intercommunicating pore, into combustion chamber 4, push check valve open, into detonation flame tube 6, fuel nozzle sprays into atomized fuel, and igniting is therein
One detonation flame tube 6, detonation wave is produced, check valve is closed automatically, and detonation wave and combustion vapour are out of, detonation flame tube 6 gas outlet
Spraying, promote turbine body to operate, after detonation wave, compressor continues air inlet, meanwhile, next 6 points of detonation flame tube is hot
Hong, turbine body operating is continued to press on, by that analogy, detonation occurs successively for detonation flame tube, and thrust is continuously generated to turbine；Even
Continuous detonation flame tube produces compressed air, and four kinds of thrust, detonation wave thrust, combustion vapour thrust and the steam thrust of compressed air push away
Power promotes turbo driving jointly, and it is big to reach in light weight, small volume, horsepower, so as to improve thrust-weight ratio and bypass ratio.
The compressor of the present invention is adopted using multistage contrarotation centrifugal-flow compressor, the centrifugal impeller of the compressor
With calming the anger, impeller inducer and centrifugation double shrouded wheel, its pressure can use gas-saving type impact type up to 80 atmospheric pressures, turbine
Two-stage turbine, throughput can be reduced, compression ratio can be effectively improved, combustion chamber uses the rear-mounted wheelbase that can shorten central shaft, drop
Low manufacture difficulty, one layer of steam pipe coil of turbine outer wrapping, water can be injected, produce steam, and promote turbine to do work, and can returned
Receipts recycle, and can effectively improve the preceding temperature of turbine, while reduce the operating temperature of turbine, reduce oil consumption, mitigate engine
Load weight；The engine is because volume fraction horsepower is big, so bypass ratio can be improved.
Claims (6)
- A kind of 1. small-sized fanjet, it is characterised in that：Including set gradually along airintake direction compressor, combustion chamber and dynamic Power turbine, the compressor include calm the anger housing and centrifugal impeller, and the power turbine includes turbine body and turbine shroud, fire Burn it is indoor be provided with connection and calm the anger the connector of housing and turbine shroud, connector be provided with connect with housing of calming the anger calm the anger end cap and The turbine end cap to connect with turbine shroud, air end of booster, which covers, is communicated with calm the anger housing and the intercommunicating pore of combustion chamber；Some detonation flame tubes set with the diameter parallel of turbine body are provided with the combustion chamber, detonation flame tube is along even Junctor it is circumferentially distributed, air inlet and gas outlet, gas outlet and turbine shroud inlet end phase are equipped with every detonation flame tube It is logical, check valve is provided with the air inlet of detonation flame tube, fuel nozzle and igniter plug, fuel oil are equipped with every detonation flame tube Connected between nozzle by total cartridge；Steam pipe coil is externally provided with the turbine shroud, the port of export of steam pipe coil connects with the inlet end of turbine shroud；Connection centrifugal impeller and the planetary mechanism of turbine body are provided with described housing of calming the anger, the planetary mechanism includes planet Frame, planetary gear, sun gear and gear ring, housing of calming the anger connect with gear ring, and planet carrier is fixed on air end of booster and covered, the wheel of sun gear The coaxial setting of the wheel shaft of axle and centrifugal impeller, the wheel shaft of turbine body.
- 2. small-sized fanjet according to claim 1, it is characterised in that：One is provided with the periphery of the end cap of calming the anger Groove is enclosed, the housing of calming the anger is provided with the projection being installed in groove.
- 3. small-sized fanjet according to claim 2, it is characterised in that：It is provided with the groove and matches with projection The sealing ring of conjunction.
- 4. small-sized fanjet according to claim 1, it is characterised in that：Described intercommunicating pore is provided with several, edge The circumference of end cap of calming the anger is uniformly distributed.
- 5. small-sized fanjet according to claim 1, it is characterised in that：Fan leaf is housed outside the housing of calming the anger Piece.
- 6. small-sized fanjet according to claim 1, it is characterised in that：Described housing of calming the anger includes shell body, The inlet end of shell body is provided with the compression impellor being fixedly connected with shell body, and the outlet side of shell body rotates with connector to connect.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710089734.5A CN106837602B (en) | 2017-02-20 | 2017-02-20 | Small-sized fanjet |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710089734.5A CN106837602B (en) | 2017-02-20 | 2017-02-20 | Small-sized fanjet |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106837602A CN106837602A (en) | 2017-06-13 |
| CN106837602B true CN106837602B (en) | 2018-03-27 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710089734.5A Active CN106837602B (en) | 2017-02-20 | 2017-02-20 | Small-sized fanjet |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106837602B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108256275B (en) * | 2018-03-12 | 2021-02-23 | 北京理工大学 | A numerical simulation method for ignition and detonation of rotary detonation engine |
| CN112502834B (en) * | 2020-12-12 | 2024-12-20 | 赵军 | Rotary combustion jet engine |
| CN115638050B (en) * | 2022-08-30 | 2024-07-05 | 潘日国 | Ship power system |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2481989A2 (en) * | 2011-01-28 | 2012-08-01 | General Electric Company | Pulse detonation turbine engine using turbine shaft speed for monitoring combustor tube operation |
| CN104718354A (en) * | 2012-07-24 | 2015-06-17 | 布兰特·W-T·李 | Internal detonation engine, composite engine including internal detonation engine, and methods of making and using same |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2005257206A (en) * | 2004-03-12 | 2005-09-22 | Toho Gas Co Ltd | Gas turbine device |
| US8341932B2 (en) * | 2009-03-19 | 2013-01-01 | General Electric Company | Rotary air valve firing patterns for resonance detuning |
| US8539752B2 (en) * | 2010-11-30 | 2013-09-24 | General Electric Company | Integrated deflagration-to-detonation obstacles and cooling fluid flow |
-
2017
- 2017-02-20 CN CN201710089734.5A patent/CN106837602B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2481989A2 (en) * | 2011-01-28 | 2012-08-01 | General Electric Company | Pulse detonation turbine engine using turbine shaft speed for monitoring combustor tube operation |
| CN104718354A (en) * | 2012-07-24 | 2015-06-17 | 布兰特·W-T·李 | Internal detonation engine, composite engine including internal detonation engine, and methods of making and using same |
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| Publication number | Publication date |
|---|---|
| CN106837602A (en) | 2017-06-13 |
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