CN101929372A - Engine tail gas water collecting system - Google Patents
Engine tail gas water collecting system Download PDFInfo
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- CN101929372A CN101929372A CN 201010268174 CN201010268174A CN101929372A CN 101929372 A CN101929372 A CN 101929372A CN 201010268174 CN201010268174 CN 201010268174 CN 201010268174 A CN201010268174 A CN 201010268174A CN 101929372 A CN101929372 A CN 101929372A
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Abstract
The invention relates to an engine tail gas water collecting system, in particular to an airship engine tail gas water collecting system belonging to the field of energy source engineering. The engine tail gas water collecting system solves the problems that the buoyancy and the center of gravity of an airship are unbalanced due to fuel consumption in the running process of the airship so that the airship is shifted or generates ballasting to not normally work. The engine tail gas water collecting system comprises an air precooling heat exchanger, an air condenser and an air and liquid separator. After being precooled by the air precooling heat exchanger, airship engine tail gas is liquefied by the air condenser so that steam in the airship engine tail gas is condensed and liquefied, and then liquefied water working mediums are collected by a water storing container. The engine tail gas water collecting system can realize collection and storage for the water working medium of the engine tail gas and is used for the balance control of the airship.
Description
Technical field
The present invention is specifically related to a kind of dirigible engine tail gas water collecting system, belongs to the energy project field.
Background technique
Dirigible is as a kind ofly having advancing means, utilizing the aircraft of law of buoyancy lift-off, controllable flight, has that long-term fixed point suspends and the low-speed maneuver ability to work, load capacity is strong, effect and cost rate is high and advantage such as reusable.In a lot of fields, military field particularly, dirigible has remedied the deficiency of conventional aircraft effectively.By flying height, dirigible mainly contains troposphere dirigible (being the low latitude dirigible) and stratospheric airship at present.Wherein, the troposphere dirigible one below 8km, can someone drive or remote control distributor; Stratospheric airship one about 20km or higher high-altitude flight or hover, the control mode that one adopts remote control or combines from main control.The low latitude dirigible is widely used in in-flight test, scouting, exploration, alert with, advertisement, the military-civil fields such as photography, communication of taking pictures.Along with science and technology development, stratosphere becomes the focus of countries in the world research as desirable near space platform, is in the exploratory development stage at present.
The outstanding advantage of dirigible is to have the resident ability of fixed point, can be static with respect to earth standard for a long time, realize the dirigible resident work of fixing a point, and dirigible needs propulsion system that thrust is provided.The power propulsion system of current conventional dirigible comprises fuel, motor and propulsion device, adopts the propulsion mode of driving propeller cavitations such as diesel engine, petrol engine to advance usually.
Yet in the dirigible running, the fuel that carries along with dirigible constantly consumes, and will make the dirigible position drift about, if do not controlled, dirigible will be difficult to guarantee that its position does not exceed the desired the sphere of activities of finishing the work.In addition, along with the consumption of fuel can cause the counterweight imbalance of dirigible, dirigible centre-of gravity shift, make dirigible can't safety, stable operation.Be in the dirigible running, need to solve ballasting problems such as dirigible position excursion and counterweight.
Gas volume and pressure overcome its ballasting problem to dirigible in the major and minor air bag by adjusting.Yet can only realize that to the method that gas volume in the balloonet and pressure are adjusted the small size ballasting of dirigible regulates, with the dirigible operation highly is 5km, day consumption fuel oil 1000kg, continuous working period be 3 days for example, be buoyant equilibrium in the coupling dirigible running, the balloonet that needs diameter to surpass 50m is regulated control.
As can be seen, realize the ballasting control of dirigible at present by gas volume and pressure in the adjustment balloonet capsule, required balloonet volume is big, will greatly influence dirigible structure and covering intensity, increase difficulty and cost that dirigible is realized; And along with the consumption of fuel, the difficulty of controlling by the center of gravity of gas volume in the adjustment balloonet capsule and pressure realization dirigible is higher.
Summary of the invention
The present invention is in order to solve present dirigible in running, along with the consumption of fuel makes the buoyancy and the center of gravity imbalance of dirigible, causes the dirigible position that skew or ballasting problem that can't proper functioning take place, and then has proposed a kind of engine tail gas water collecting system.
The technological scheme that technical solution problem of the present invention is adopted is: engine tail gas water collecting system, it comprises the air precooling heat exchanger, air surface condenser, gas-liquid separator, first liquid level sensor, liquid pump, tank, second liquid level sensor, first valve, second valve, the 6th valve, the tenth valve, the 11 valve and second time end valve, the tail gas outlet end of dirigible aeroengine is communicated with the entrance point of first valve and the entrance point of second valve respectively, the outlet end of first valve is communicated with atmosphere environment, the outlet end of second valve is communicated with the entrance point of air precooling heat exchanger, the outlet end of air precooling heat exchanger is communicated with the entrance point that ends valve for second time, the outlet end that ends valve for second time is communicated with the entrance point of air surface condenser, the outlet end of air surface condenser is communicated with the entrance point of gas-liquid separator, the gas outlet end of gas-liquid separator is communicated with atmosphere environment by the 6th valve, the liquid outlet end of gas-liquid separator is communicated with the entrance point of liquid pump by the tenth valve, the outlet end of liquid pump is communicated with the entrance point of tank, the outlet end of tank is communicated with atmosphere environment, first liquid level sensor is arranged on the gas-liquid separator, and second liquid level sensor is arranged on the tank.
The present invention utilizes the condensation catching method to catch water vapour in the dirigible motor exhaust, can effectively solve in the dirigible running fuel consumption and cause ballasting problems such as dirigible buoyancy and center of gravity be unbalance, thereby realize the long-time safety of dirigible, stable operation.In addition, the present invention utilizes the direct condensation of high-altitude low temperature environment to catch water vapour in the dirigible motor exhaust, additionally energy consumption.
Description of drawings
The schematic representation of Fig. 1 embodiment one described engine tail gas water collecting system; The schematic representation of Fig. 2 embodiment two described engine tail gas water collecting systems; The schematic representation of Fig. 3 embodiment three described engine tail gas water collecting systems; The schematic representation of Fig. 4 embodiment four described engine tail gas water collecting systems; The schematic representation of Fig. 5 embodiment five described engine tail gas water collecting systems; The schematic representation of Fig. 6 embodiment six described engine tail gas water collecting systems.
Embodiment
Embodiment one: present embodiment is described in conjunction with Fig. 1.The described engine tail gas water collecting system of present embodiment, it comprises air precooling heat exchanger 6, air surface condenser 16, gas-liquid separator 24, first liquid level sensor 25, liquid pump 27, tank 28, second liquid level sensor 30, first valve 1, second valve 5, the 6th valve 15, the tenth valve 26, the 11 valve 29 and second time end valve 10, the tail gas outlet end of dirigible aeroengine 32 is communicated with the entrance point of first valve 1 and the entrance point of second valve 5 respectively, the outlet end of first valve 1 is communicated with atmosphere environment, the outlet end of second valve 5 is communicated with the entrance point of air precooling heat exchanger 6, the outlet end of air precooling heat exchanger 6 is communicated with the entrance point that ends valve 10 for second time, the outlet end that ends valve 10 for second time is communicated with the entrance point of air surface condenser 16, the outlet end of air surface condenser 16 is communicated with the entrance point of gas-liquid separator 24, the gas outlet end of gas-liquid separator 24 is communicated with atmosphere environment by the 6th valve 15, the liquid outlet end of gas-liquid separator 24 is communicated with the entrance point of liquid pump 27 by the tenth valve 26, the outlet end of liquid pump 27 is communicated with the entrance point of tank 28, the outlet end of tank 28 is communicated with atmosphere environment, first liquid level sensor 25 is arranged on the gas-liquid separator 24, and second liquid level sensor 30 is arranged on the tank 28.
The tail gas that the described air precooling heat exchanger 6 of present embodiment uses air that dirigible aeroengine 32 is discharged carries out precooling, the tail gas that dirigible aeroengine 32 is discharged is from the entrance point input of air precooling heat exchanger 6, and the direction that air flows in cooling tube and the flow direction of tail gas are contraries;
The described air surface condenser 16 of present embodiment uses air that the tail gas through 6 precoolings of air precooling heat exchanger is carried out condensation, described tail gas is from the entrance point input of air surface condenser 16, and the direction that air flows in cooling tube and the flow direction of tail gas are contraries;
The described gas-liquid separator 24 of present embodiment is used for process air surface condenser 16 condensed air-water mixtures are separated, water conservancy project matter under action of gravity in the tail gas is collected catches, be stored in the tank 28 through liquid pump 27, remaining tail gas is discharged in the atmosphere environment through the 6th valve 15;
Present embodiment is described ends valve 10 second time and is used to prevent back flow of gas.
Present embodiment utilizes cooling air mode to realize that the condensation of water vapour in the motor exhaust catches based on the space atmosphere environment, catches water vapour in the motor exhaust by the phase-change method condensation liquefaction.
When adopting the water vapour in the described engine tail gas water collecting system condensation of the present embodiment tail gas, with second valve 5, end valve 10, the 6th valve 15, the tenth valve the 26, the 11 valve 29 and liquid pump 27 and open for second time; First valve 1 is closed; Enter air surface condenser 16 after the adiabatic condensation temperature of aeroengine tail gas water vapour in air precooling heat exchanger 6 is chilled to a little more than motor exhaust in advance, after the aeroengine tail gas behind air surface condenser 16 condensation liquefactions enters gas-liquid separator 24, water conservancy project matter under action of gravity in the tail gas is collected to catch through liquid pump 27 and is stored in the tank 28, remaining tail gas in the gas-liquid separator 24 is discharged in the atmosphere environment through the 6th valve 15, when water conservancy project matter was too much in the tank 28, the 11 valve 29 was opened unnecessary water is discharged in the atmosphere environment.
During water vapour, second valve 5 is closed in need not the condensation motor exhaust, first valve 1 is opened, discharge motor exhaust.
Present embodiment utilizes the condensation catching method to catch water vapour in the dirigible motor exhaust, can effectively solve in the dirigible running fuel consumption and cause ballasting problems such as dirigible buoyancy and center of gravity be unbalance, thereby realize the long-time safety of dirigible, stable operation.In addition, present embodiment utilizes the direct condensation of high-altitude low temperature environment to catch water vapour in the dirigible motor exhaust, additionally energy consumption.
Embodiment two: present embodiment is described in conjunction with Fig. 2.The difference of present embodiment and embodiment one is: it also comprises the 3rd valve 7, auxiliary precool heat exchanger device 8 and ends valve 9 first time, the tail gas outlet end of dirigible aeroengine 32 also is communicated with the entrance point of the 3rd valve 7, the outlet end of the 3rd valve 7 is communicated with the entrance point of auxiliary precool heat exchanger device 8, the outlet end of auxiliary precool heat exchanger device 8 is communicated with the entrance point that ends valve 9 for first time, first time only the outlet end of valve 9 be communicated with the entrance point of air surface condenser 16.
Present embodiment is by assisting precool heat exchanger device 8, utilizing gas precooling motor exhaust in the dirigible balloonet, and in addition, gas has the effect of heating in auxiliary 8 pairs of dirigible balloonets of precool heat exchanger device, realizes the control of dirigible lift to a certain extent.Principle is: the inside and outside temperature difference greatly that exists of dirigible, when temperature is lower than ambient temperature in the ship, utilize gas precooling dirigible motor exhaust in the ship by auxiliary precool heat exchanger device 8, both reached the purpose of precooling, also can improve buoyance lift gas temperature in the ship, it is guaranteed in certain temperature range.
Adopt the described engine tail gas water collecting system of present embodiment,, then open the 3rd valve 7 and end valve 9 first time, close second valve 5 for making auxiliary precool heat exchanger device 8 proper functioning; For making auxiliary precool heat exchanger device 8 quit work, then close the 3rd valve 7.
Embodiment three: present embodiment is described in conjunction with Fig. 3.The difference of present embodiment and embodiment one and embodiment two is: it also comprises the 4th valve 11, the 5th valve 12 and blower 13, the outlet end that ends the outlet end of valve 9 for first time and end valve 10 second time is communicated with the entrance point of the 4th valve 11 and the entrance point of the 5th valve 12, the outlet end of the 4th valve 11 is communicated with the intake grill of blower 13, and the outlet end of the exhaust outlet of blower 13 and the 5th valve 12 is communicated with the entrance point of air surface condenser 16.
The 5th valve 12 is closed in the present embodiment, and the 4th valve 11 and blower 13 are opened, and its objective is the circulating resistance that overcomes gas by blower.
Embodiment four: present embodiment is described in conjunction with Fig. 4.The difference of present embodiment and embodiment three is: it also comprises auxiliary air condenser 21, the 7th valve 20, the 8th valve 22 and the 9th valve 23, the outlet end of air surface condenser 16 is communicated with the entrance point of the 7th valve 20 and the entrance point of the 8th valve 22 respectively, the outlet end of the 7th valve 20 is communicated with the entrance point of auxiliary air condenser 21, the outlet end of auxiliary air condenser 21 is communicated with the entrance point of the 9th valve 23, and the outlet end of the outlet end of the 8th valve 22 and the 9th valve 23 is communicated with the entrance point of gas-liquid separator 24 jointly.
The 8th valve 22 is closed in the present embodiment, the 7th valve 20 and the 9th valve 23 are opened, its objective is and overcome because factors such as flow increase cause the problem that water vapour can not fully condense in the air surface condenser 16 outlet tail gas, by adopting auxiliary air condenser 21 further cooled exhaust gas, improve the condensation rate of water vapour in the tail gas.
Embodiment five: present embodiment is described in conjunction with Fig. 5.Present embodiment and embodiment one, two and fours' difference is: described tank 28 is cellular tank.
The described tank 28 of present embodiment is cellular tank, can be used in combination with fuel tank, when dirigible is use up the oil consumption in the fuel tank, the described engine tail gas water collecting system of present embodiment is supplemented to the water of catching in this fuel tank, realize the dirigible counterweigh, adopt described tank 28 compact structures of present embodiment, reduce weight of equipment.
Embodiment six: present embodiment is described in conjunction with Fig. 6.The difference of present embodiment and embodiment five is: it also comprises first pressure transducer 2, first temperature transducer 3, first flow sensor 4, second pressure transducer 17, second temperature transducer 18 and second flow transducer 19, first pressure transducer 2, first temperature transducer 3 and first flow sensor 4 are arranged on the main line before the entrance point of the entrance point of second valve 5 and the 3rd valve 7, and second pressure transducer 17, second temperature transducer 18 and second flow transducer 19 are arranged on the main line of outlet end of air surface condenser 16.
Described first pressure transducer 2 of present embodiment, first temperature transducer 3 and first flow sensor 4 are respectively applied for pressure, temperature and the flow on the main line before the entrance point of the entrance point of measuring second valve 5 and the 3rd valve 7; Described second pressure transducer 17 of present embodiment, second temperature transducer 18 and second flow transducer 19 are respectively applied for pressure, temperature and the flow of the outlet end of measuring air surface condenser 16.
Claims (6)
1. engine tail gas water collecting system, it is characterized in that: it comprises air precooling heat exchanger (6), air surface condenser (16), gas-liquid separator (24), first liquid level sensor (25), liquid pump (27), tank (28), second liquid level sensor (30), first valve (1), second valve (5), the 6th valve (15), the tenth valve (26), the 11 valve (29) and second time end valve (10), the tail gas outlet end of dirigible aeroengine (32) is communicated with the entrance point of first valve (1) and the entrance point of second valve (5) respectively, the outlet end of first valve (1) is communicated with atmosphere environment, the outlet end of second valve (5) is communicated with the entrance point of air precooling heat exchanger (6), the outlet end of air precooling heat exchanger (6) is communicated with the entrance point that ends valve (10) for second time, the outlet end that ends valve (10) for second time is communicated with the entrance point of air surface condenser (16), the outlet end of air surface condenser (16) is communicated with the entrance point of gas-liquid separator (24), the gas outlet end of gas-liquid separator (24) is communicated with atmosphere environment by the 6th valve (15), the liquid outlet end of gas-liquid separator (24) is communicated with the entrance point of liquid pump (27) by the tenth valve (26), the outlet end of liquid pump (27) is communicated with the entrance point of tank (28), the outlet end of tank (28) is communicated with atmosphere environment, first liquid level sensor (25) is arranged on the gas-liquid separator (24), and second liquid level sensor (30) is arranged on the tank (28).
2. engine tail gas water collecting system according to claim 1, it is characterized in that: it also comprises the 3rd valve (7), auxiliary precool heat exchanger device (8) and ends valve (9) first time, the tail gas outlet end of dirigible aeroengine (32) also is communicated with the entrance point of the 3rd valve (7), the outlet end of the 3rd valve (7) is communicated with the entrance point of auxiliary precool heat exchanger device (8), the outlet end of auxiliary precool heat exchanger device (8) is communicated with the entrance point that ends valve (9) for first time, first time only the outlet end of valve (9) be communicated with the entrance point of air surface condenser (16).
3. engine tail gas water collecting system according to claim 1 and 2, it is characterized in that: it also comprises the 4th valve (11), the 5th valve (12) and blower (13), the outlet end that ends the outlet end of valve (9) for first time and end valve (10) second time is communicated with the entrance point of the 4th valve (11) and the entrance point of the 5th valve (12), the outlet end of the 4th valve (11) is communicated with the intake grill of blower (13), and the outlet end of the exhaust outlet of blower (13) and the 5th valve (12) is communicated with the entrance point of air surface condenser (16).
4. engine tail gas water collecting system according to claim 3, it is characterized in that: it also comprises auxiliary air condenser (21), the 7th valve (20), the 8th valve (22) and the 9th valve (23), the outlet end of air surface condenser (16) is communicated with the entrance point of the 7th valve (20) and the entrance point of the 8th valve (22) respectively, the outlet end of the 7th valve (20) is communicated with the entrance point of auxiliary air condenser (21), the outlet end of auxiliary air condenser (21) is communicated with the entrance point of the 9th valve (23), and the outlet end of the outlet end of the 8th valve (22) and the 9th valve (23) is communicated with the entrance point of gas-liquid separator (24) jointly.
5. according to claim 1,2 or 4 described engine tail gas water collecting systems, it is characterized in that: described tank (28) is cellular tank.
6. engine tail gas water collecting system according to claim 5, it is characterized in that: it also comprises first pressure transducer (2), first temperature transducer (3), first flow sensor (4), second pressure transducer (17), second temperature transducer (18) and second flow transducer (19), first pressure transducer (2), first temperature transducer (3) and first flow sensor (4) are arranged on the main line before the entrance point of the entrance point of second valve (5) and the 3rd valve (7), second pressure transducer (17), second temperature transducer (18) and second flow transducer (19) are arranged on the main line of outlet end of air surface condenser (16).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010268174 CN101929372A (en) | 2010-08-31 | 2010-08-31 | Engine tail gas water collecting system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010268174 CN101929372A (en) | 2010-08-31 | 2010-08-31 | Engine tail gas water collecting system |
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| CN101929372A true CN101929372A (en) | 2010-12-29 |
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| CN 201010268174 Pending CN101929372A (en) | 2010-08-31 | 2010-08-31 | Engine tail gas water collecting system |
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB373410A (en) * | 1931-05-23 | 1932-05-26 | Gloster Aircraft Company Ltd | Improvements in aircraft wings fitted with engine cooling devices |
| GB410199A (en) * | 1932-09-17 | 1934-05-17 | Fairey Aviat Co Ltd | Improvements in or relating to the cooling systems for internal combustion engines |
| GB654091A (en) * | 1941-06-06 | 1951-06-06 | Harry Alfred Mulvany | Method and apparatus for obtaining water vapor from the combustion products of internal combustion engines |
| CN1375662A (en) * | 2001-03-15 | 2002-10-23 | 王子介 | Air conditioners utilizing underground cold and head for precooling and preheating |
| CN2775568Y (en) * | 2004-12-11 | 2006-04-26 | 张新恒 | Evaporative condenser |
| CN2844796Y (en) * | 2005-11-16 | 2006-12-06 | 河南中轴集团有限公司 | Evaporating condenser with precooler |
| CN101451788A (en) * | 2007-12-05 | 2009-06-10 | 上海超滤压缩机净化设备有限公司 | Condensation purifier |
-
2010
- 2010-08-31 CN CN 201010268174 patent/CN101929372A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB373410A (en) * | 1931-05-23 | 1932-05-26 | Gloster Aircraft Company Ltd | Improvements in aircraft wings fitted with engine cooling devices |
| GB410199A (en) * | 1932-09-17 | 1934-05-17 | Fairey Aviat Co Ltd | Improvements in or relating to the cooling systems for internal combustion engines |
| GB654091A (en) * | 1941-06-06 | 1951-06-06 | Harry Alfred Mulvany | Method and apparatus for obtaining water vapor from the combustion products of internal combustion engines |
| CN1375662A (en) * | 2001-03-15 | 2002-10-23 | 王子介 | Air conditioners utilizing underground cold and head for precooling and preheating |
| CN2775568Y (en) * | 2004-12-11 | 2006-04-26 | 张新恒 | Evaporative condenser |
| CN2844796Y (en) * | 2005-11-16 | 2006-12-06 | 河南中轴集团有限公司 | Evaporating condenser with precooler |
| CN101451788A (en) * | 2007-12-05 | 2009-06-10 | 上海超滤压缩机净化设备有限公司 | Condensation purifier |
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Application publication date: 20101229 |