CN102338700A - Engine exhaust emission cooling system of high-altitude simulation test of piston engine - Google Patents

Engine exhaust emission cooling system of high-altitude simulation test of piston engine Download PDF

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Publication number
CN102338700A
CN102338700A CN2011101297810A CN201110129781A CN102338700A CN 102338700 A CN102338700 A CN 102338700A CN 2011101297810 A CN2011101297810 A CN 2011101297810A CN 201110129781 A CN201110129781 A CN 201110129781A CN 102338700 A CN102338700 A CN 102338700A
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CN
China
Prior art keywords
water
cooling
engine exhaust
simulation test
altitude simulation
Prior art date
Application number
CN2011101297810A
Other languages
Chinese (zh)
Inventor
刘猛
王浚
胡涛
董素君
袁领双
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北京航空航天大学
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Application filed by 北京航空航天大学 filed Critical 北京航空航天大学
Priority to CN2011101297810A priority Critical patent/CN102338700A/en
Publication of CN102338700A publication Critical patent/CN102338700A/en

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Abstract

The invention discloses an engine exhaust emission cooling system of a high-altitude simulation test of a piston engine. The engine exhaust emission cooling system is characterized in that: a joint cooling form of indirect evaporation cooling and indirect heat exchange cooling is adopted; and the temperature of gas which is emitted by the engine is reduced by adopting an indirect structure and using the boiling evaporation and heat absorption of water. The engine exhaust emission cooling system specifically comprises indirect evaporation coolers (7 and 9), an indirect heat exchanger (13) which adopts circulating cooling water as a cold source and/or an indirect heat exchanger (14) which adopts circulating chilled water as the cold source and the like. The invention has the advantages that: the final temperature of the cooled gas can be actively controlled; and the system is simple in structure, relatively higher in equipment reliability, low in investment cost and relatively lower in operation cost and maintenance cost.

Description

A kind of piston engine altitude simulation test engine exhaust cooling system
Technical field
The present invention relates to a kind of piston engine altitude simulation test engine exhaust cooling system, belong to the environmental simulation technical field.
Background technology
When piston engine was tested at simulated altitude, engine was discharged up to the low-voltage high-temperature combustion gas more than 800 ℃, just can enter atmosphere after need aspirating supercharging with vaccum-pumping equipment.And vaccum-pumping equipment generally only allows its intake air temperature to be about 40~80 ℃, thereby needs to use exhaust cooling system that the high-temperature exhaust air of engine is cooled to the intake air temperature scope that vaccum-pumping equipment allows.In available engine exhaust cooling technology, the modes that adopt directly water spray cooling and indirect heat exchange cooling more.Can make the steam partial pressure that gets into vaccum-pumping equipment increase greatly to directly the spray water mode of cooling of combustion gas; Thereby reduced the exhaust capacity of vacuum equipment; The trial stretch of the simulation of engine high-altitude experimental facilities of set pumping capacity is dwindled greatly, because this weakness has limited the application of the direct water spray type of cooling.The heat interchanger that the mode of indirect heat exchange cooling generally uses recirculated water to do heat eliminating medium cools off, and the shortcoming of this method is can be very big in order big heat to be taken away fast the circulating water flow that needs, thereby has increased the investment and the operating cost of circulation.
Summary of the invention
To the above-mentioned defective of prior art, the present invention proposes a kind of piston engine altitude simulation test engine exhaust cooling system, the methods for cooling that this system adopts indirect evaporation cooling and indirect heat exchange cooling to unite.
According to an aspect of the present invention, a kind of piston engine altitude simulation test engine exhaust cooling system is provided, has it is characterized in that comprising:
An indirect type devaporizer, one adopt indirect type heat interchanger that recirculated cooling water does low-temperature receiver with (or) one adopt circulated refrigerated water to make the indirect type heat interchanger of low-temperature receiver.
According to an aspect of the present invention, said indirect type devaporizer comprises: devaporizer body and devaporizer supply tank.This water tank is installed on eminence, and is connected through water pipe with the bottom of devaporizer body, to guarantee height such as both liquid levels.Recirculated water through softening carries out moisturizing to water tank, and rate of water make-up is controlled by ball-cock assembly automatically.
According to a further aspect of the present invention, said devaporizer body has liquid level gauge, and the top is provided with vapour-discharge tube and leads to outside atmosphere, and the caliber of vent pipe need satisfy the requirement of evaporation capacity.The devaporizer bottom is provided with blowoff valve and blow-off pipe.In order to guarantee that the engine high-temperature air inlet is sufficiently cooled, prevent that simultaneously high-temperature gas from assembling this equipment of infringement in devaporizer, engine exhaust gets into devaporizer from the bottom, in the process that rises, is cooled and discharges from top.The air intake opening of devaporizer and inner circulation of air sectional area and heat interchanging area need satisfy the requirement of flowing with heat.
According to an aspect of the present invention, adopt indirect type heat interchanger that recirculated cooling water does low-temperature receiver with (or) the indirect type heat interchanger that adopts circulated refrigerated water to do low-temperature receiver can be tubular type, board-like or extended surface formula heat interchanger.If the heat interchanger of two kinds of low-temperature receivers all adopts, then two heat exchanger core bodies can be integrated in the housing, also can separate independent one-tenth heat interchanger separately.A variable valve is set on the low-temperature receiver entrance pipe of heat interchanger, through the flow of regulating low-temperature receiver come control indirectly through the laggard fuel gas temperature of going into vaccum-pumping equipment of supercooling just near the highest intake air temperature that vacuum equipment allowed, in the hope of save the energy as far as possible.
Discharge after through indirect type heat interchanger cooled gas, thereby require the gas side of devaporizer and water cooling heat exchanger to bear to test desired minimum pressure by the vaccum-pumping equipment supercharging.
Advantage of the present invention comprises :-can the cooled combustion gas finishing temperature of ACTIVE CONTROL process.-system architecture is simple, and equipment dependability is higher.-practice thrift cost of investment, operation and maintenance cost is lower.
Description of drawings
Fig. 1 is the schematic flow sheet of piston engine altitude simulation test engine exhaust cooling system of the present invention;
Reference numeral:
1-high-temperature fuel gas draft tube, 2-high-temperature fuel gas intake air temperature sensor,
3-high-temperature fuel gas air inlet pressure sensor, 4-devaporizer water tank softening water filling pipe,
5-hand valve, the 6-ball-cock assembly, 7-devaporizer supply tank,
8-devaporizer liquid level gauge, 9-devaporizer body, the 10-steam exhaust pipe,
11-devaporizer blowoff valve, the 12-blow-off pipe, 13-recirculated cooling water heat interchanger,
14-circulating frozen water-to-water heat exchanger, 15-recirculated cooling water inlet tube and outlet tube, the 16-water meter,
17-circulated refrigerated water inlet tube and outlet tube, 18-chilled water variable valve, 19-pressure regulation blowdown pipe,
The 20-non-return valve, 21-vacuum unit, 22-vacuum unit gas outlet,
23-water tank and devaporizer connecting pipe, 24-devaporizer vertical tube structure,
25-devaporizer shell structure, 26-devaporizer gas outlet,
27-hand valve, 28-indirect type heat exchanger shell structure,
29-devaporizer outlet fuel gas temperature sensor,
30-indirect type heat exchanger outlet temperature sensor, 31-gaseous-pressure variable valve
Embodiment
The piston engine altitude simulation test engine exhaust cooling system of embodiment as shown in Figure 1 comprises according to the present invention: devaporizer body 9, water supply tank 7, recirculated cooling water heat interchanger 13, circulating frozen water-to-water heat exchanger 14; And the valve (5,6,11,18 that the said equipment of connection is installed; 20,27,31), sensor (2; 3,29,30), pipe fitting, web member, securing member and support member (not shown) etc.
According to one embodiment of present invention, devaporizer body 9 adopts indirect tubular structure, all adopts the high temperature resistant stainless steel material, and inside is intensive vertical tube structure 24, and water is arranged in the pipe, the engine exhaust of the shell structure 25 interior logical high temperature that pipe is outer.Draft tube 1 gets into devaporizer body 9 to the high-temperature fuel gas of temperature up to 800 ℃ from the bottom; In the process that rises, skim over the vertical tube 24 that water is housed; And with great amount of heat pass to vertical tube and cause managing in water heat absorption boiling become steam and discharge from the steam pipe 10 at top, the temperature of combustion gas simultaneously is reduced and from top outlet 26, discharges.In a specific embodiment according to the present invention; 950 ℃ of the maximum temperatures of engine exhaust (recording) by temperature sensor 2; Temperature behind the process evaporator cools device has dropped to below 180 ℃ and (has been recorded by temperature sensor 29), and the maximum flow of combustion gas is 600kg/h.
Devaporizer body 9 is equipped with liquid level gauge 8 and is used to observe liquid level in the devaporizer, and the moisturizing of devaporizer is accomplished by water supply tank 7.The height that water supply tank 7 is installed need make that both peak levels of water tank and devaporizer 9 are concordant.Water tank 7 has water pipe 23 to be connected with the devaporizer bottom, and linker of all logical atmosphere formation in both tops, and both flush by water level all the time.The rate of water make-up of water tank 7 is controlled by ball-cock assembly 6 automatically, and moisturizing comes from the recirculated cooling water after softening.
According to one embodiment of present invention, the 9 cooled combustion gas of process devaporizer are introduced into recirculated cooling water heat interchanger 13 and are further cooled off, and get into circulating frozen water-to-water heat exchanger 14 then again, further are cooled to the temperature of being scheduled to again.The low-temperature receiver of heat interchanger 13 is the chilled water from the recirculating cooling water system (not shown), a little higher than normal temperature of temperature; And the low-temperature receiver of heat interchanger 14 is the chilled water from circulating frozen water system (not shown), carries out cooling by the refrigeration plant (not shown), and the temperature of chilled water is generally 3-8 ℃.All be provided with hand valve 27 and water meter 16 on the water lateral line 15 and 17 of two heat interchanger; Be used for manually control and observe discharge; And also be provided with variable valve 18 on circulating frozen water-to-water heat exchanger 14 water inlet pipes; Thereby be used to regulate maximum temperature that the cooled fuel gas temperature of chilled-water flow indirect regulation just in time allowed in the vaccum-pumping equipment air inlet near 70 ℃, this temperature is monitored by sensor 30.According to concrete this instance of the present invention, the core body of used two heat interchanger is integrated in the housing 28, makes structure simpler, installs more convenient.
Through temperature after the supercooling meet the requirements of combustion gas through after variable valve 31 pressure regulation by vaccum-pumping equipment 21 superchargings after gas outlet 22 discharge.Thereby devaporizer 9 can bear infrabar with heat interchanger 13,14 requirements, and the low pressure that the requirement of this instance institute can tolerate is 18kPa.
Invention has been described more than to combine specific embodiment, describes used data and all be explanation but not determinate.Be to be understood that and the invention is not restricted to above-mentioned specifically described embodiment; Under the prerequisite that does not depart from the scope of the present invention with spirit; Can carry out various distortion, replacement and/or correction to the present invention, and these distortion, replacement and/or revise the scope of the present invention all belong to appended claims and limited.

Claims (9)

1. piston engine altitude simulation test engine exhaust cooling system is characterized in that adopting the methods for cooling of indirect type evaporative cooling and indirect heat exchange cooling associating to comprise:
Indirect type devaporizer (9),
Recirculated water indirect type cooling heat exchanger (13,14).
2. according to the piston engine altitude simulation test engine exhaust cooling system of claim 1, it is characterized in that indirect type devaporizer (9) comprising:
Shell structure (25),
Be arranged on the inner intensive vertical tube (24) of shell structure (25), vertical tube is equipped with chilled water in (24), and shell structure (25) inside outside the vertical tube (24) is used for the engine exhaust through high temperature.
3. according to the piston engine altitude simulation test engine exhaust cooling system of claim 2, it is characterized in that
The engine exhaust of high temperature gets into shell structure (25) inside from the draft tube (1) of shell structure (25) bottom; And in the process that rises, skim over the vertical tube (24) that water is housed; Thereby heat is passed to vertical tube (24) and caused water heat absorption boiling in the vertical tube (24) to become steam and discharge from the steam pipe (10) at the top of shell structure (25), and the temperature of engine exhaust is reduced and discharges from the top outlet (26) of shell structure (25) simultaneously.
4. according to the piston engine altitude simulation test engine exhaust cooling system of claim 2 or 3, it is characterized in that further comprising:
Be contained in the liquid level gauge (8) on the devaporizer (9), be used to observe the liquid level in the vertical tube (24),
Water supply tank (7), said water supply tank (7) is connected through the bottom of water pipe (23) with vertical tube (24),
Wherein, the setting height(from bottom) of water supply tank (7) makes water supply tank (7) concordant with both peak levels of vertical tube (24), thereby and all logical atmosphere in both tops make both constitute a linker.
5. according to the piston engine altitude simulation test engine exhaust cooling system of claim 4, it is characterized in that
The rate of water make-up of water supply tank (7) is controlled by a ball-cock assembly (6) automatically,
Moisturizing comes from the recirculated cooling water after softening.
6. according to the piston engine altitude simulation test engine exhaust cooling system of claim 1, it is characterized in that recirculated water indirect type heat interchanger (13,14) comprises recirculated cooling water heat interchanger (13) and/or circulating frozen water-to-water heat exchanger (14).
7. according to the piston engine altitude simulation test engine exhaust cooling system of claim 6, it is characterized in that
Engine exhaust through devaporizer (9) cooling successively enters into recirculated cooling water heat interchanger (13) and/or circulating frozen water-to-water heat exchanger (14), thereby is further cooled off.
8. according to the piston engine altitude simulation test engine exhaust cooling system of claim 7, it is characterized in that further comprising:
Be separately positioned on hand valve (27) and water meter (16) on the water lateral line (15,17) of recirculated cooling water heat interchanger (13), be used for manually control and observe cooling water flow,
Be arranged on the variable valve (18) on the water inlet pipe of circulating frozen water-to-water heat exchanger (14), be used to regulate chilled-water flow, thus the cooled fuel gas temperature of indirect regulation.
9. according to Claim 8 piston engine altitude simulation test engine exhaust cooling system is characterized in that
The core body of recirculated cooling water heat interchanger (13) and circulating frozen water-to-water heat exchanger (14) is integrated in the housing (28),
Wherein, devaporizer (9), recirculated cooling water heat interchanger (13), circulating frozen water-to-water heat exchanger (14) can bear infrabar.
CN2011101297810A 2011-05-19 2011-05-19 Engine exhaust emission cooling system of high-altitude simulation test of piston engine CN102338700A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
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Application Number Priority Date Filing Date Title
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Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102717886A (en) * 2012-06-27 2012-10-10 大连海事大学 Ship cooling system
CN103743572A (en) * 2014-01-08 2014-04-23 北京航空航天大学 Small-sized rocket engine test bed spray device
CN105067273A (en) * 2015-09-08 2015-11-18 清华大学苏州汽车研究院(相城) Cold-flow test apparatus for exhaust system back pressure tests and thermal state back pressure estimating method
CN106092590A (en) * 2016-08-29 2016-11-09 北京航天三发高科技有限公司 A kind of block testing stand discharge duct chiller
CN106338401A (en) * 2016-09-09 2017-01-18 西安航天动力试验技术研究所 Airspace-engine test-bed long-range exhaust system
CN107290166A (en) * 2017-07-31 2017-10-24 中国商用飞机有限责任公司 Simulate fluid temperature (F.T.) and/or the fast-changing pilot system of pressure and test method

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US920263A (en) * 1908-05-23 1909-05-04 Charles E Chrisman Film-developing machine.
CN2271613Y (en) * 1995-06-30 1997-12-31 应国华 Producer of refrigerating device of using I.C engine exhaust waste heat for refrigeration
JP2003097352A (en) * 2001-09-27 2003-04-03 Chugoku Electric Power Co Inc:The Cogeneration system utilizing lng cryogenics
CN201145371Y (en) * 2007-09-21 2008-11-05 姜堰奥斯康电器制造有限公司 Dual refrigeration fresh air conditioner
US20090020263A1 (en) * 2006-01-26 2009-01-22 Akihiro Ohsawa Cooling Apparatus for Fluid
CN102023096A (en) * 2010-11-15 2011-04-20 北京航空航天大学 Internal-flow high-altitude simulation test device and test method of aviation piston engine

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US920263A (en) * 1908-05-23 1909-05-04 Charles E Chrisman Film-developing machine.
CN2271613Y (en) * 1995-06-30 1997-12-31 应国华 Producer of refrigerating device of using I.C engine exhaust waste heat for refrigeration
JP2003097352A (en) * 2001-09-27 2003-04-03 Chugoku Electric Power Co Inc:The Cogeneration system utilizing lng cryogenics
US20090020263A1 (en) * 2006-01-26 2009-01-22 Akihiro Ohsawa Cooling Apparatus for Fluid
CN201145371Y (en) * 2007-09-21 2008-11-05 姜堰奥斯康电器制造有限公司 Dual refrigeration fresh air conditioner
CN102023096A (en) * 2010-11-15 2011-04-20 北京航空航天大学 Internal-flow high-altitude simulation test device and test method of aviation piston engine

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102717886A (en) * 2012-06-27 2012-10-10 大连海事大学 Ship cooling system
CN103743572A (en) * 2014-01-08 2014-04-23 北京航空航天大学 Small-sized rocket engine test bed spray device
CN103743572B (en) * 2014-01-08 2016-01-06 北京航空航天大学 Small rocket motor testing table spray equipment
CN105067273A (en) * 2015-09-08 2015-11-18 清华大学苏州汽车研究院(相城) Cold-flow test apparatus for exhaust system back pressure tests and thermal state back pressure estimating method
CN106092590A (en) * 2016-08-29 2016-11-09 北京航天三发高科技有限公司 A kind of block testing stand discharge duct chiller
CN106338401A (en) * 2016-09-09 2017-01-18 西安航天动力试验技术研究所 Airspace-engine test-bed long-range exhaust system
CN107290166A (en) * 2017-07-31 2017-10-24 中国商用飞机有限责任公司 Simulate fluid temperature (F.T.) and/or the fast-changing pilot system of pressure and test method
CN107290166B (en) * 2017-07-31 2020-07-21 中国商用飞机有限责任公司 Test system and test method for simulating rapid change of fluid temperature and/or pressure

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Application publication date: 20120201