CN206477923U - A kind of small-sized fanjet - Google Patents
A kind of small-sized fanjet Download PDFInfo
- Publication number
- CN206477923U CN206477923U CN201720150177.9U CN201720150177U CN206477923U CN 206477923 U CN206477923 U CN 206477923U CN 201720150177 U CN201720150177 U CN 201720150177U CN 206477923 U CN206477923 U CN 206477923U
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- CN
- China
- Prior art keywords
- turbine
- anger
- flame tube
- housing
- detonation
- Prior art date
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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 is covered, 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 is communicated with turbine shroud inlet end, check valve is provided with the air inlet of detonation flame tube, it is equipped between fuel nozzle and igniter plug, fuel nozzle and is connected by total cartridge in every detonation flame tube.The utility model continuously promotes turbine body by the detonation successively of detonation flame tube using four kinds of thrusts, and detonation flame tube is gathered 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 utility model is related to a kind of engine, more particularly to a kind of small-sized fanjet.
Background technology
In fanjet, thrust can be increased by improving fan, the pressure ratio of compressor, improve pressure ratio, main at present
If increasing fan, axial-flow compressor, the series of turbine or improving turbine entrance temperature temperature, but by increase 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, to improving bypass ratio, compression ratio and the thrust-weight ratio of fanjet, is also that can not obtain significant effect, and existing
Have in technology and be not present by four kinds of coefficient engines of thrust.
The content of the invention
Technical problem to be solved in the utility model be in view of the shortcomings of the prior art there is provided one kind it is reasonable in design, by
The coefficient small-sized fanjet of four kinds of thrusts.
Technical problem to be solved in the utility model is realized by following technical scheme, and the utility model is
A kind of small-sized fanjet, is characterized in, including compressor, combustion chamber and the power turbine set gradually along airintake direction,
The compressor includes calm the anger housing and centrifugal impeller, and the power turbine is included in turbine body and turbine shroud, combustion chamber
Provided with the connector for connecting calm the anger housing and turbine shroud, connector is provided with calm the anger end cap and and the turbine connected with housing of calming the anger
The turbine end cap that housing connects, air end of booster, which is covered, is communicated with calm the anger housing and the intercommunicating pore of combustion chamber；
The detonation flame tube set in the combustion chamber provided with some diameter parallels with turbine body, detonation flame tube
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 is provided with the air inlet of detonation flame tube on check valve, every detonation flame tube and is equipped with fuel nozzle and igniter plug,
Connected between fuel nozzle by total cartridge；
Compressor sends into compressed air behind combustion chamber from intercommunicating pore, pushes check valve open, into detonation flame tube, fuel oil spray
Mouth sprays into atomized fuel, one of detonation flame tube of lighting a fire, and produces detonation wave, 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 continues to press on turbine body operating, with such
Push away, detonation occurs successively for detonation flame tube, make turbine body continuous running by continuous thrust.
What technical problem to be solved in the utility model can also be realized by following technical scheme, in the pressure
The periphery of gas end cap is provided with the projection being installed in groove provided with a circle groove, the housing of calming the anger.
What technical problem to be solved in the utility model can also be realized by following technical scheme, described recessed
The sealing ring being engaged with projection is provided with groove.
What technical problem to be solved in the utility model can also be realized by following technical scheme, in the whirlpool
Hub is provided with steam pipe coil in vitro, and the port of export of steam pipe coil connects with the inlet end of turbine shroud.
What technical problem to be solved in the utility model can also be realized by following technical scheme, described company
Through hole is provided with several, is uniformly distributed along the circumference for end cap of calming the anger.
What technical problem to be solved in the utility model can also be realized by following technical scheme, in the pressure
Fan blade is housed outside gas housing.
What technical problem to be solved in the utility model can also be realized by following technical scheme, described pressure
Planetary mechanism provided with connection centrifugal impeller and turbine body in gas housing, the planetary mechanism include 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, the wheel shaft and centrifugal impeller of sun gear
Wheel shaft, turbine body wheel shaft it is coaxial set.
What technical problem to be solved in the utility model can also be realized by following technical scheme, described pressure
Gas housing includes shell body, and the inlet end of shell body is provided with entry impeller, and the outlet side of shell body is rotated with connector to connect.
Compared with prior art, the utility model is by the detonation successively of detonation flame tube, and detonation flame tube is to detonation power
Gathered, it is to avoid thrust diffusion is difficult to enter in turbine shroud, and utilize the thrust of compressed air, detonation wave thrust, combustion vapour
Four kinds of thrusts of thrust and steam thrust promote turbo driving jointly, in the presence of check valve, it is to avoid in detonation process reversely
The smooth air inlet of impact influence compressor, its is reasonable in design, easy to operate, energy-saving and emission-reduction, improves bypass ratio, the pressure of engine
Contracting ratio and thrust-weight ratio, use scope of the present utility model are wide.
Brief description of the drawings
Fig. 1 is structural representation of the present utility model.
Embodiment
Referring to the drawings, concrete technical scheme of the present utility model is further described, in order to those skilled in the art
Member is further understood that the utility model, without constituting 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 includes calm the anger housing 1 and centrifugal impeller 2, and the power turbine includes turbine body 10 and turbine case
Provided with the connector 14 for connecting calm the anger housing 1 and turbine shroud 8 in body 8, combustion chamber 4, connector 14 is provided with and the phase of housing 1 of calming the anger
Calm the anger housing 1 and combustion are communicated with calm the anger end cap 15 and the turbine end cap 9 that connects with turbine shroud 8 connect, end cap 15 of calming the anger
Burn the intercommunicating pore 5 of room 4；
The detonation flame tube 6 set in the combustion chamber 4 provided with some diameter parallels with turbine body 10, detonation fire
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 communicated by communicating pipe 13 with the inlet end of turbine shroud 8, every detonation flame tube
It is equipped between fuel nozzle 7 and igniter plug 12, fuel nozzle 7 and is connected by total cartridge on 6；
Compressor sends into compressed air behind combustion chamber 4 from intercommunicating pore 5, pushes check valve open, into detonation flame tube 6, combustion
Oil burner nozzle 7 sprays into atomized fuel, one of detonation flame tube 6 of lighting a fire, and produces at detonation wave, correspondence 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, make 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.
In the periphery of the end cap 15 of calming the anger provided with a circle groove, 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 set 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 thrust to turbine, meanwhile, turbine temperature is reduced, in the closure periphery of calming the anger equipped with wind
Fan leaf, increases 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.
It is outer equipped with fan blade 16 in the housing 1 of calming the anger.
Planetary mechanism provided with connection centrifugal impeller and turbine body in 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
The wheel shaft of wheel shaft and centrifugal impeller, turbine body wheel shaft it is coaxial set, centrifugal impeller and sun gear are rotated forward, calm the anger housing and
Compression impellor is inverted, 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 utility model utilizes electronic spark control system and common rail electric-controlling fuel injection system, and the compression of compressor is empty
Gas, into combustion chamber 4, pushes check valve open through intercommunicating pore, and into detonation flame tube 6, fuel nozzle sprays into atomized fuel, lights a fire it
In a detonation flame tube 6, produce detonation wave, check valve closes automatically, detonation wave and combustion outlet of the vapour from detonation flame tube 6
Intraoral to spray, after promoting turbine body operating, detonation wave, compressor continues air inlet, meanwhile, next 6 points of detonation flame tube
It is hot to bang, turbine body operating is continued to press on, by that analogy, detonation occurs successively for detonation flame tube, continuously generates and pushes away to turbine
Power；Continuous detonation flame tube produces compressed air, thrust, detonation wave thrust, combustion vapour thrust and the steam thrust of compressed air
Four kinds of thrusts promote turbo driving jointly, reach that lightweight, small volume, horsepower are big, so as to improve thrust-weight ratio and bypass ratio.
Compressor of the present utility model uses multistage contrarotation centrifugal-flow compressor, the centrifugation leaf of the compressor
Wheel can be rushed using impeller inducer and the centrifugation double shrouded wheel of calming the anger, its pressure up to 80 atmospheric pressures, turbine using gas-saving type
Formula two-stage turbine is hit, throughput can be reduced, compression ratio can be effectively improved, combustion chamber can shorten the axle of central shaft using rear-mounted
Away from, manufacture difficulty is reduced, one layer of steam pipe coil of turbine outer wrapping can inject water, produce steam, and promote turbine to do work, and
The preceding temperature of turbine can be effectively improved with recycle and reuse, while reducing the operating temperature of turbine, reduce oil consumption, mitigate
The load weight of engine；The engine is big because of volume fraction horsepower, so bypass ratio can be improved.
Claims (8)
1. a kind of small-sized fanjet, it is characterised in that：Including the compressor set gradually along airintake direction, combustion chamber and dynamic
Power turbine, the compressor includes calm the anger housing and centrifugal impeller, and the power turbine includes turbine body and turbine shroud, combustion
Burn the connector of indoor calmed the anger provided with connection 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 connected with turbine shroud, air end of booster, which is covered, is communicated with calm the anger housing and the intercommunicating pore of combustion chamber；
The detonation flame tube set in the combustion chamber provided with some diameter parallels with turbine body, 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, it is provided with the air inlet of detonation flame tube on check valve, every detonation flame tube and is equipped with fuel nozzle and igniter plug, fuel oil
Connected between nozzle by total cartridge.
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 projection matching
The sealing ring of conjunction.
4. small-sized fanjet according to claim 1, it is characterised in that：Steam disc is externally provided with the turbine shroud
Pipe, the port of export of steam pipe coil connects with the inlet end of turbine shroud.
5. 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.
6. small-sized fanjet according to claim 1, it is characterised in that：Fan leaf is housed outside the housing of calming the anger
Piece.
7. small-sized fanjet according to claim 1, it is characterised in that：In described housing of calming the anger provided with connection from
The planetary mechanism of lobus cardiacus wheel and turbine body, the planetary mechanism includes planet carrier, planetary gear, sun gear and gear ring, calms the anger
Housing connects with gear ring, and planet carrier is fixed on air end of booster and covered, the wheel shaft of sun gear and the wheel shaft of centrifugal impeller, turbine body
Wheel shaft is coaxial to be set.
8. 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 is rotated with connector to connect.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720150177.9U CN206477923U (en) | 2017-02-20 | 2017-02-20 | A kind of small-sized fanjet |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720150177.9U CN206477923U (en) | 2017-02-20 | 2017-02-20 | A kind of small-sized fanjet |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206477923U true CN206477923U (en) | 2017-09-08 |
Family
ID=59748412
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720150177.9U Expired - Fee Related CN206477923U (en) | 2017-02-20 | 2017-02-20 | A kind of small-sized fanjet |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206477923U (en) |
-
2017
- 2017-02-20 CN CN201720150177.9U patent/CN206477923U/en not_active Expired - Fee Related
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170908 Termination date: 20190220 |