CN107842423A - The pushing system of water spray or methanol suitable for small-size turbojet engine - Google Patents
The pushing system of water spray or methanol suitable for small-size turbojet engine Download PDFInfo
- Publication number
- CN107842423A CN107842423A CN201710949770.4A CN201710949770A CN107842423A CN 107842423 A CN107842423 A CN 107842423A CN 201710949770 A CN201710949770 A CN 201710949770A CN 107842423 A CN107842423 A CN 107842423A
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- China
- Prior art keywords
- turbojet
- intake duct
- air intake
- air
- liquid
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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
- F02C3/20—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products
- F02C3/30—Adding water, steam or other fluids for influencing combustion, e.g. to obtain cleaner exhaust gases
- F02C3/305—Increasing the power, speed, torque or efficiency of a gas turbine or the thrust of a turbojet engine by injecting or adding water, steam or other fluids
-
- 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
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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 present invention discloses a kind of turbojet, including：Air intake duct, air enter turbojet by air intake duct；Compressor, compressor are arranged on after air intake duct, to improve the pressure of the air entered by air intake duct；Combustion chamber, air enters after compressor in combustion chamber and fuel oil mixed combustion, expansion work；Turbine, turbine are co-axially mounted on engine shaft with compressor, and turbine rotation is promoted from the high-temperature high-pressure fuel gas of combustion chamber outflow；Jet pipe, the high-temperature high-pressure fuel gas flowed out from turbine continue to expand in jet pipe, and are discharged backward along engine shaft；With pushing device, pushing device sprays into liquid towards air intake duct, to increase the inlet flow rate of turbojet.
Description
Technical field
The present invention relates to a kind of aviation field, relates more specifically to aero-engine and its pushing system, is primarily adapted for use in
The spouted power apparatus of miniature high-speed unmanned plane and its whirlpool.
Background technology
The purposes such as miniature high-speed unmanned plane can be used as investigating, detect, attack, target, flying height it is more 12000 meters with
Under, the cruise time is shorter, is usually no more than 2 hours.Simultaneously because its special tactical purpose, it is desirable to which aircraft is in short-term up to 0.7
~0.9 Mach of high subsonic speed, indivedual supersonic speed types will even reach 1.2~1.5 Mach of supersonic flight, and this is just to flying
The dynamical system of machine proposes higher requirement, and, it is necessary to which engine possesses, cost is low, performance is high, the basic performance of short life, and
And high thrust output in short-term can be realized.This kind of unmanned plane is commonly provided with small-size turbojet engine as its power set, ground
Face normal rated thrust is more in below 200daN, and using the design of one-stage centrifugal rather than multistage axial flow, this design can improve as far as possible
Compressor pressure ratio, increase engine ceiling, while can also simplify engine structure, shorten rotor axial system, strengthen rotor rigidity.But
Using the design of centrifugal compressor, the external diameter of engine is relatively large, and windage area can be increased by being assemblied on unmanned plane, reduces
Unmanned plane during flying speed, the requirement of aircraft high-speed flight in short-term can not be met.
In order to solve the above problems, prior art proposes some feasible programs, and its core is to be pushed away to engine increase
The method of power, wherein generally use is engine afterburner scheme.The program is to increase one-level after engine turbine to add
Power combustion chamber, the second-time burning that gas is discharged by turbine continue to improve delivery temperature so as to increase jet pipe exhaust velocity, reached
To the purpose of pushing.The method that motor power is current main flow is improved by increasing afterbunring, on military aircraft
It is widely used.But this method is on SUAV using still there is certain limitation：Need to increase using reinforcing scheme and add
A series of parts such as power combustion chamber, igniter, flameholder, variable area nozzle, actuation mechanism, system architecture is greatly complicated,
Weight increase；And engine cost significantly improves, economy extreme difference on short-lived unmanned plane is especially used in.
Therefore, it is necessary to seek a kind of pushing system suitable for small-size turbojet engine, can for miniature high-speed nobody
The particular demands of machine, on the premise of power set its usage economy is ensured, motor power is effectively increased, meets that unmanned plane exists
Thrust requirements under different operating modes.
The content of the invention
The technical problems to be solved by the invention are to provide a kind of whirlpool reasonable in design, suitable for miniature high-speed unmanned plane and sprayed
Engine pushing method and system.
Technical scheme is that small-size turbojet engine water spray/methanol is increased used by the present invention solves above-mentioned technical problem
Pushing away, i.e., aircraft carries appropriate water or methanol, when flight, which approaches maximum speed, needs engine to provide extra high thrust,
A certain amount of water or methanol are sprayed into toward engine inlets, equivalent to increase engine intake flow, is started so as to reach increase
The purpose of machine thrust.Through experimental test, the water or methanol being fully atomized are sprayed into toward engine inlets, motor power significantly increases
Add, and do not influence engine reliability and life-span.For example, spray into the atomized water or first equivalent to 7% air mass flow toward air intake duct
Alcohol, motor power increase up to 35%, are entirely capable of meeting aircraft to the increased demand of engine power.
Water and methanol are industrially conventional raw material, are easily obtained, cheap, therefore as the spray of engine pushing
Penetrate raw material.And both different physical attribute also determines that it is respectively suitable for different types of unmanned plane.Water is than great, volume
Small, easy atomization, but freezing point is high, is easily frozen in high-altitude low temperature environment, suitable for low-latitude flying unmanned plane, for example plunders extra large target drone etc.；And
As little as -97 DEG C of methanol freezing point, suitable for high-altitude flight unmanned plane, for example high altitude reconnaissance plane, target missile etc..
In order to realize above technical scheme, water spray/methanol pushing system of small-size turbojet engine, including small-sized whirlpool are built
Fuel-injection engine, water/Methanol storage, pipeline, electric-motor pump, magnetic valve, filter, nozzle, ECU controllers etc..Aircraft normally flies
During row, the magnetic valve of system is closed, and when needing engine to provide high thrust, ECU control magnetic valves are opened, simultaneously
Controlled motor pump operates, and extracts water or methanol in storage box, spurts into engine inlets, pushed away so as to increase engine
Power.The flow of the water or methanol that spray into engine inlets is controlled by ECU regulation motors revolution speed, and then adjusts engine and pushes away
The increasing degree of power.
According to a kind of turbojet of the present invention, including：
Air intake duct, air enter the turbojet by the air intake duct；
Compressor, the compressor are arranged on after the air intake duct, to improve the air entered by the air intake duct
Pressure；
Combustion chamber, air enters after the compressor in the combustion chamber and fuel oil mixed combustion, expansion work；
Turbine, the turbine are co-axially mounted on engine shaft with the compressor, from the height of combustion chamber outflow
Warm high-pressure gas promotes the turbine rotation；With
Jet pipe, the high-temperature high-pressure fuel gas flowed out from the turbine continue to expand in the jet pipe, and along
Engine shaft is discharged backward.
According to a kind of turbojet of the present invention, in addition to：
Pushing device, the pushing device sprays into liquid towards the air intake duct, to increase entering for turbojet
Mouth flow.
According to a kind of turbojet of the present invention, the pushing device includes injection apparatus, the injection apparatus
It is arranged in front of the entrance of the air intake duct, with to the intake port injection liquid.
According to a kind of turbojet of the present invention, the liquid is water.
According to the present invention a kind of turbojet, when the turbojet use is in unmanned plane, and
And the unmanned plane is when being in low-latitude flying, water that the injection apparatus is atomized to the intake port injection.
According to a kind of turbojet of the present invention, the liquid is methanol.
According to the present invention a kind of turbojet, when the turbojet use is in unmanned plane, and
And the unmanned plane is when being in high-altitude flight, methanol that the injection apparatus is atomized to the intake port injection.
According to a kind of turbojet of the present invention, the injection apparatus includes row's atomizer, by liquid
It is atomized and is injected into the air intake duct.
According to a kind of turbojet of the present invention, the atomizer will enter the liquid mist of the air intake duct
Change so that atomizing particle size reaches less than 50 μm fully to be blended with incoming air.
According to a kind of turbojet of the present invention, in addition to：
Storage box, the storage box are provided for storing the liquid of such as water or methanol；With
Controller, liquid enters the flow of the air intake duct in controller control storage box.
Using scheme of the present invention compared to the pushing mode such as traditional afterbunring, simple in construction easily to realize, cost
Cheap and technical difficulty is low, on the premise of engine structure complexity is not increased, hardly consume electric energy, have effectively achieved
The particular/special requirement of some miniature high-speed unmanned plane pushings in short-term.The invention taken a flight test in certain SUAV high-altitude achieve it is good
Effect.
Brief description of the drawings
Fig. 1 is the system and device schematic diagram of the present invention.
Label declaration：
Water/Methanol storage 1；
Electric-motor pump 2；
Magnetic valve 3；
Pipeline 4；
Filter 5；
Nozzle 6；
Turbojet engine 7；
ECU controllers 8.
Embodiment
With reference to embodiment, the present invention is described in further detail, following examples be explanation of the invention and
The invention is not limited in following examples.
According to a kind of turbojet of the present invention, including：
Air intake duct, air enter the turbojet by the air intake duct；
Compressor, the compressor are arranged on after the air intake duct, to improve the air entered by the air intake duct
Pressure；
Combustion chamber, air enters after the compressor in the combustion chamber and fuel oil mixed combustion, expansion work；
Turbine, the turbine are co-axially mounted on engine shaft with the compressor, from the height of combustion chamber outflow
Warm high-pressure gas promotes the turbine rotation；With
Jet pipe, the high-temperature high-pressure fuel gas flowed out from the turbine continue to expand in the jet pipe, and along
Engine shaft is discharged backward.
According to a kind of turbojet of the present invention, in addition to：
Pushing device, the pushing device sprays into liquid towards the air intake duct, to increase entering for turbojet
Mouth flow.
According to a kind of turbojet of the present invention, the pushing device includes injection apparatus, the injection apparatus
It is arranged in front of the entrance of the air intake duct, with to the intake port injection liquid.
According to a kind of turbojet of the present invention, the liquid is water.
According to the present invention a kind of turbojet, when the turbojet use is in unmanned plane, and
And the unmanned plane is when being in low-latitude flying, water that the injection apparatus is atomized to the intake port injection.
According to a kind of turbojet of the present invention, the liquid is methanol.
According to the present invention a kind of turbojet, when the turbojet use is in unmanned plane, and
And the unmanned plane is when being in high-altitude flight, methanol that the injection apparatus is atomized to the intake port injection.
According to a kind of turbojet of the present invention, the injection apparatus includes row's atomizer, by liquid
It is atomized and is injected into the air intake duct.
According to a kind of turbojet of the present invention, the atomizer will enter the liquid mist of the air intake duct
Change so that atomizing particle size reaches less than 50 μm fully to be blended with incoming air.
According to a kind of turbojet of the present invention, in addition to：Storage box, the storage box are provided for storing all
Such as water or the liquid of methanol；And controller, liquid enters the flow of the air intake duct in controller control storage box.
As shown in figure 1, the present embodiment system is used for the spouted power apparatus of miniature high-speed unmanned plane and its whirlpool, including
Water/Methanol storage 1, electric-motor pump 2, magnetic valve 3, pipeline 4, filter 5, nozzle 6, turbojet engine 7, ECU controllers 8.
Installation settings nozzle 6 in the air intake duct of turbojet engine 7, according to aircraft instruction unpack magnetic valve 3 and driven by ECU controllers 8
Electric-motor pump 2, draw the water or methanol of water/Methanol storage 1, by the road 4, filter 5 enter nozzle 6, injection not same amount water or
Methanol, the incoming air blending with engine enter engine.
The present invention controls the opening and closing of pushing system and pushing amplitude by the ECU controllers 8 of turbojet engine 7.Needing
When improving thrust, ECU controllers open the magnetic valve 3 on pipeline, and motor pump 2 extracts the water or first of storage bin
Alcohol, supply nozzle 6 spurt into engine.The different rotating speed of ECU controller motor pumps is different by corresponding penetrating engine
Flow, while different environmental pressure can also influence injection flow to aircraft at various height, it is therefore desirable in advance for difference
Environmental working condition the injection flow of pushing system is demarcated.
Pipeline 4 used in system uses gapless stainless steel tube, needs with clean kerosene wash cycles and dries before use.In addition
Needing to set filter 5 in systems, filter the impurity dirt brought from water/Methanol storage 1, general filtering accuracy reaches 10~
20 μm, ensure the cleaning liquid into engine, be unlikely to pollute, corrode engine blade.
Nozzle 6 needs using the higher atomizer of precision, to ensure that the water of penetrating engine inlets or methanol can fill
Divide atomization, and along airflow direction.Typically require that atomizing particle size will reach less than 50 μm, nozzle atomization cone angle at 60~90 degree,
So that the water or methanol of atomization fully blend with incoming air, the liquid for ensureing to spray into can make full use of, and improve pushing efficiency.
Because usual miniature high-speed unmanned plane load and space are smaller, its water being carried by/Methanol storage volume has
Limit, therefore pushing system of the present invention is adapted only to the spouted Force system of miniature high-speed unmanned plane and its whirlpool of needs pushing in short-term.
Furthermore, it is necessary to illustrate, the specific embodiment described in this specification, the shape of its parts, it is named
Title etc. can be different.The equivalent or simple change that all construction, feature and principles according to described in inventional idea of the present invention are done, is wrapped
Include in the protection domain of patent of the present invention.Those skilled in the art can be to described specific implementation
Example is made various modifications or supplement or substituted using similar mode, structure without departing from the present invention or surmounts this
Scope as defined in the claims, protection scope of the present invention all should be belonged to.
Claims (10)
1. a kind of turbojet, including：
Air intake duct, air enter the turbojet by the air intake duct；
Compressor, the compressor are arranged on after the air intake duct, to improve the pressure of the air entered by the air intake duct
Power；
Combustion chamber, air enters after the compressor in the combustion chamber and fuel oil mixed combustion, expansion work；
Turbine, the turbine are co-axially mounted on engine shaft with the compressor, high from the high temperature of combustion chamber outflow
Compression ignition gas promotes the turbine rotation；With
Jet pipe, the high-temperature high-pressure fuel gas flowed out from the turbine continue to expand in the jet pipe, and along starting
Arbor is discharged backward.
2. turbojet according to claim 1, in addition to：
Pushing device, the pushing device sprays into liquid towards the air intake duct, to increase the inlet flow of turbojet
Amount.
3. turbojet according to claim 2, it is characterised in that：The pushing device includes injection apparatus,
The injection apparatus is arranged in front of the entrance of the air intake duct, with to the intake port injection liquid.
4. the turbojet according to Claims 2 or 3, it is characterised in that：
The liquid is water.
5. turbojet according to claim 4, it is characterised in that：
When the turbojet use is in unmanned plane, and when the unmanned plane is in low-latitude flying, the injection
The water that device is atomized to the intake port injection.
6. the turbojet according to Claims 2 or 3, it is characterised in that：
The liquid is methanol.
7. turbojet according to claim 6, it is characterised in that：
When the turbojet use is in unmanned plane, and when the unmanned plane is in high-altitude flight, the injection
The methanol that device is atomized to the intake port injection.
8. turbojet according to claim 3, it is characterised in that：The injection apparatus sprays including a fog dischargeization
Mouth, to atomize the liquid into and be injected into the air intake duct.
9. turbojet according to claim 8, it is characterised in that：The atomizer will enter the air inlet
The liquid atomization in road so that atomizing particle size reaches less than 50 μm fully to be blended with incoming air.
10. turbojet according to claim 2, in addition to：
Storage box, the storage box are provided for storing the liquid of such as water or methanol；With
Controller, liquid enters the flow of the air intake duct in controller control storage box.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710949770.4A CN107842423A (en) | 2017-10-12 | 2017-10-12 | The pushing system of water spray or methanol suitable for small-size turbojet engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710949770.4A CN107842423A (en) | 2017-10-12 | 2017-10-12 | The pushing system of water spray or methanol suitable for small-size turbojet engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107842423A true CN107842423A (en) | 2018-03-27 |
Family
ID=61661365
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710949770.4A Pending CN107842423A (en) | 2017-10-12 | 2017-10-12 | The pushing system of water spray or methanol suitable for small-size turbojet engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107842423A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111005820A (en) * | 2019-12-27 | 2020-04-14 | 哈尔滨工程大学 | High-pressure water supply device for engine |
| CN111852666A (en) * | 2020-07-24 | 2020-10-30 | 浙江吉利新能源商用车集团有限公司 | Cold start control method and system of methanol engine and vehicle |
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| US20050193714A1 (en) * | 2002-05-16 | 2005-09-08 | Rolls-Royce Plc | Gas turbine engine |
| CN103742295A (en) * | 2014-01-15 | 2014-04-23 | 苟仲武 | Turbojet engine and method for mixing liquid gas during operation of turbojet engine |
| CN103742294A (en) * | 2014-01-15 | 2014-04-23 | 苟仲武 | Liquid gas afterburner jet engine and method for realizing afterburning flying of jet plane |
| CN104389681A (en) * | 2014-11-26 | 2015-03-04 | 江西洪都航空工业集团有限责任公司 | Embedded type gas charging channel for supplementing gas for gas charging channel based on high-pressure gas cylinder |
| CN105888882A (en) * | 2014-12-25 | 2016-08-24 | 王正铉 | Device utilizing liquid carbon dioxide gasification to improve thrust of aircraft |
-
2017
- 2017-10-12 CN CN201710949770.4A patent/CN107842423A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050193714A1 (en) * | 2002-05-16 | 2005-09-08 | Rolls-Royce Plc | Gas turbine engine |
| CN103742295A (en) * | 2014-01-15 | 2014-04-23 | 苟仲武 | Turbojet engine and method for mixing liquid gas during operation of turbojet engine |
| CN103742294A (en) * | 2014-01-15 | 2014-04-23 | 苟仲武 | Liquid gas afterburner jet engine and method for realizing afterburning flying of jet plane |
| CN104389681A (en) * | 2014-11-26 | 2015-03-04 | 江西洪都航空工业集团有限责任公司 | Embedded type gas charging channel for supplementing gas for gas charging channel based on high-pressure gas cylinder |
| CN105888882A (en) * | 2014-12-25 | 2016-08-24 | 王正铉 | Device utilizing liquid carbon dioxide gasification to improve thrust of aircraft |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111005820A (en) * | 2019-12-27 | 2020-04-14 | 哈尔滨工程大学 | High-pressure water supply device for engine |
| CN111852666A (en) * | 2020-07-24 | 2020-10-30 | 浙江吉利新能源商用车集团有限公司 | Cold start control method and system of methanol engine and vehicle |
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Application publication date: 20180327 |