CN106741967A - A kind of controllable air circulation system of injection radiating - Google Patents
A kind of controllable air circulation system of injection radiating Download PDFInfo
- Publication number
- CN106741967A CN106741967A CN201611085692.XA CN201611085692A CN106741967A CN 106741967 A CN106741967 A CN 106741967A CN 201611085692 A CN201611085692 A CN 201611085692A CN 106741967 A CN106741967 A CN 106741967A
- Authority
- CN
- China
- Prior art keywords
- air
- injection
- injector
- cooling
- radiator
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000002347 injection Methods 0.000 title claims abstract description 34
- 239000007924 injection Substances 0.000 title claims abstract description 34
- 238000001816 cooling Methods 0.000 claims abstract description 40
- 238000000926 separation method Methods 0.000 claims description 5
- 239000002775 capsule Substances 0.000 claims description 3
- 230000008676 import Effects 0.000 claims description 2
- 230000007613 environmental effect Effects 0.000 abstract description 2
- 239000003570 air Substances 0.000 description 58
- 238000005057 refrigeration Methods 0.000 description 4
- 230000008901 benefit Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 230000006870 function Effects 0.000 description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 239000000243 solution Substances 0.000 description 2
- 239000007921 spray Substances 0.000 description 2
- 238000004378 air conditioning Methods 0.000 description 1
- 239000012080 ambient air Substances 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000008450 motivation Effects 0.000 description 1
- 238000005086 pumping Methods 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
- B64D13/08—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned the air being heated or cooled
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
- B64D2013/0603—Environmental Control Systems
Landscapes
- Health & Medical Sciences (AREA)
- General Health & Medical Sciences (AREA)
- Pulmonology (AREA)
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention provides a kind of controllable air circulation system of injection radiating, belong to helicopter environmental control system design field.The passage air outlet where being provided with cooling radiator (2) is also extended to by the first pipeline by the high temperature and high pressure gas of absolute pressure regulator (1), and the first pipeline tail end is provided with injector (10), injector (10) spout direction is consistent with air outlet wind direction.By injector take the lead in injection extravehicular environment air cool down radiator, reduce cooling turbine unit entering air temperature, advantageously ensure that system helicopter hover or ground handling without ram-air when can smooth working, be conducive to improve cooling turbine unit service life.Because fan has turned on, and the radiator of air cooling out of my cabin is aspirated, close injector, to reduce engine bleed amount, reduce engine power consumption.
Description
Technical field
The invention belongs to helicopter environmental control system design field, and in particular to a kind of controllable air circulation system of injection radiating
System.
Background technology
The simple-type air circulation system of fixed wing aircraft is main by absolute pressure regulator 1, radiator 2, turbine 3, wind
Fan 4, separator 5, sprayer 6, it is cold in air inlet duct 7, it is cold while the composition such as exhaust passage 8, its general principle is：Sent by engine
High temperature and high pressure gas, through absolute pressure regulator 1 adjust after, cooled to radiator 2, flow into cooling turbine unit 3, turbine
To the expansion work of fan 4, air is expanded into required cabin air pressure to cooler in cooling turbine unit, through separator 5
After separation, dry air enters cockpit, and aqueous water is sprayed onto the cooling of radiator appearance surface strengthening, wherein fan 4 sometimes by sprayer 6
As the load (see Fig. 2) of simple power consumption；Sometimes it is used (see Fig. 3) as radiator exhausting, injection air again.
In the prior art, the aircraft environment control system with modulated low-temperature receiver directly applies to helicopter, it will
Because hovering or ground drive cannot radiate and still lose function, because high temperature hot gas damage the cooling turbine unit such as patent No.
CN103249643A refer to a kind of air handling system for aircraft includes at least one air-conditioning package, the air
Adjusting part in order to the purpose that radiates can be connected at least one cooling air intake of aircraft and being designed to be used to it is right
Air is cooled down and is used in the main cabin that air is incorporated into aircraft under cabin pressure.It is capable of the cooling of independent operation
Equipment is designed as being cooled down to the surrounding air of convection current cooling air intake.For another example the hair of Patent No. CN103612761A
A kind of open type air refrigeration cycle device of Passive intake cold, including the sky being connected with engine bleed are refer in bright patent
Air turbine refrigerating channel and Passive intake cold passage.Wherein, the Passive intake cold passage includes primary heat sink, secondary
Radiator, cold valve, condensator outlet air are through in cold valve and cold air duct, hot side is located at Refrigeration by air turbine passage.Pass through
Passive intake cold component is set, the circulating cooling of cockpit is used for from engine high pressure bleed, reduce special ram-air
Air inlet open area, can significantly sharp mountain aircraft performance panelty, meet the stealthy demand of high-performance operational aircraft, and with system
The advantage that cold is big, small volume, reliability are high.For another example refer to one in the Chinese invention patent of Patent No. CN103612760A
Plant the open type air refrigeration cycle device of Passive intake cold, including the Refrigeration by air turbine passage being connected with engine bleed
With actively reclaim cold passage.Wherein, the cold passage that actively reclaims is including primary heat sink, secondary radiator, cold valve,
Pressure tank, air register, engine high pressure bleed are connected through cold valve, pressure tank with cold air duct successively, are contained outside engine
Bleed is connected through air register with cold air duct, and primary heat sink and secondary radiator cold side are located in cold air duct, and hot side is located at sky
Air turbine refrigerating channel, cold component is actively reclaimed by setting, and the circulating cooling of cockpit is used for from engine high pressure bleed, no
Special ram-air air inlet is needed, aircraft performance panelty can be greatly decreased, high-performance operational aircraft can be met
Stealthy demand, and have the advantages that big refrigerating capacity, small volume, reliability are high.
Helicopter is different from fixed wing aircraft, its energy hovering, if the air circulation that will be mentioned in the above-mentioned patent
System directly applies to helicopter, it will because hovering or ground drive cannot radiate and still lose function, because high temperature hot gas damage whirlpool
Wheel cooler.
The content of the invention
In view of the above problems, patent of the present invention provides a kind of controllable air circulation system of injection radiating, makes helicopter
When hovering or ground are driven, can normally use.
The controllable air circulation system of injection radiating of the present invention, flows through by the high temperature and high pressure gas of absolute pressure regulator
Injection cooling radiator out of my cabin, afterwards by cooling turbine unit to being arranged on injection cooling radiator side out of my cabin
Fan do work, meanwhile, by cooling turbine unit gas further by being conveyed to helicopter capsule after the separation of separator,
Also extended to by the first pipeline by the high temperature and high pressure gas of absolute pressure regulator be provided with it is logical where cooling radiator
Road air outlet, and the first pipeline tail end is provided with injector, injector spout direction is consistent with air outlet wind direction.
Preferably, injection control valve is provided with first pipeline.
In such scheme preferably, the fan is arranged between the cooling radiator and injector.
In such scheme preferably, also extended by second pipe by the high temperature and high pressure gas of absolute pressure regulator
To the import of separator.
In such scheme preferably, it is provided with the second pipe plus temperature control valve.
The key technology of patent of the present invention mainly have it is following some：
1) injector is arranged in cold side exhaust passage in the system, for injection surrounding air；
2) injection control valve is arranged in the system before injector, injection is radiated controllable；
3) cooling turbine unit does work to fan in the system, fan draws ambient air cooling radiator, makes turbine cold
But the output work of device is utilized effectively；
4) water separated by separator in the system passes through atomizers spray on a heat sink, strengthens heat radiation energy
Power.
The present invention by injector take the lead in injection extravehicular environment air cool down radiator, reduce cooling turbine unit intake air
Temperature, advantageously ensures that system energy smooth working when helicopter hovering or ground handling are without ram-air, is conducive to improving whirlpool
Take turns the service life of cooler.Because fan has turned on, and the radiator of air cooling out of my cabin is aspirated, injector is closed, to reduce hair
Motivation amount of air entrainment, reduces engine power consumption.
Brief description of the drawings
Fig. 1 is the controllable air circulation system schematic diagram of patent injection radiating of the present invention.
Fig. 2 be in the prior art fan as simple dissipative load air circulation system schematic diagram.
Fig. 3 be in the prior art fan as radiator pumping, injection air air circulation system schematic diagram.
Wherein, 1- absolute pressure regulators；2- cools down radiator；3- cooling turbine units；4- fans；5- separators；6-
Sprayer；The cold side air inlet ducts of 7-；The cold side exhaust passages of 8-；9- injections control valve；10- injectors；11- adds temperature control valve.
Specific embodiment
To make the purpose, technical scheme and advantage of present invention implementation clearer, below in conjunction with the embodiment of the present invention
Accompanying drawing, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from start to finish or class
As label represent same or similar element or the element with same or like function.Described embodiment is the present invention
A part of embodiment, rather than whole embodiments.Embodiment below with reference to Description of Drawings is exemplary, it is intended to used
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiment in the present invention, ordinary skill people
The every other embodiment that member is obtained under the premise of creative work is not made, belongs to the scope of protection of the invention.Under
Face is described in detail with reference to accompanying drawing to embodiments of the invention.
In the description of the invention, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instruction such as "left", "right", " vertical ", " level ", " top ", " bottom " " interior ", " outward " are based on accompanying drawing institute
The orientation or position relationship for showing, are for only for ease of the description present invention and simplify description, rather than the dress for indicating or implying meaning
Put or element with specific orientation, with specific azimuth configuration and operation, therefore it is not intended that must be protected to the present invention
The limitation of scope.
The present invention is described in further details below by embodiment.
The controllable air circulation system as shown in figure 1, a kind of injection radiates, including absolute pressure regulator 1, radiator 2,
Cooling turbine unit 3, fan 4, separator 5, sprayer 6, it is cold in air inlet duct 7, it is cold while exhaust passage 8, injection control valve 9, injection
Device 10 and plus temperature control valve 11 etc..
The high temperature and high pressure gas drawn by engine bleed mouthful, are adjusted into absolute pressure regulator 1, export it
Pressure is steady state value, and two-way is divided into afterwards, and all the way into injector 10, another road enters main system.Specifically, by absolute pressure
The high temperature and high pressure gas of draught control mechanism 1 flow through injection cooling radiator 2 out of my cabin, afterwards by cooling turbine unit 3 pairs be arranged on
The fan 4 of injection cooling radiator 2 side out of my cabin does work, meanwhile, the gas by cooling turbine unit 3 further passes through
Helicopter capsule is conveyed to after the separation of separator 5, it is characterised in that by the HTHP gas of absolute pressure regulator 1
Body also extends to the passage air outlet where being provided with cooling radiator 2 by the first pipeline, and in the first pipeline tail end
Injector 10 is provided with, the spout direction of injector 10 is consistent with air outlet wind direction
System takes the lead in opening the injection control valve 9 being arranged on the first pipeline before starting, high-speed gas pass through injector 10
Aperture sprays, injection extravehicular environment air, cools down radiator 2, the air themperature of the entrance of cooling turbine unit 3 is unlikely to too high,
After 3min, injection control valve 9 is closed, and injector 10 is stopped.
Into the high temperature and high pressure gas of main system, cooled after radiator 2, it is swollen to fan 4 in cooling turbine unit 3
Swollen acting, fan 4 suction extravehicular environment air and radiator 2 carry out heat exchange, the outlet air of cooling turbine unit 3 be changed into low temperature,
Dry air enters cockpit, liquid after the gas-fluid two-phase mixture of low pressure, the configured gas-liquid separation of separator 5 on second pipe
State water is sprayed onto the outer surface of radiator 2 by sprayer 6.When cold day is heated, plus temperature control valve 11 is opened, and high temperature air flows through heating
After control valve 11, the cryogenic gas for coming is exported with cooling turbine unit 3 and is mixed, entered after mixed gas temperature reaches setting value
Cockpit, is cockpit heating demisting.
It is last it is to be noted that：The above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations.To the greatest extent
Pipe has been described in detail to the present invention with reference to the foregoing embodiments, it will be understood by those within the art that：It is still
Technical scheme described in foregoing embodiments can be modified, or which part technical characteristic is equally replaced
Change；And these modifications or replacement, do not make the essence of the essence disengaging various embodiments of the present invention technical scheme of appropriate technical solution
God and scope.
Claims (5)
1. a kind of controllable air circulation system of injection radiating, flows through by the high temperature and high pressure gas of absolute pressure regulator (1)
Injection cooling radiator (2) out of my cabin, afterwards by cooling turbine unit (3) to being arranged on injection cooling radiator out of my cabin
(2) fan (4) acting of side, meanwhile, by the gas of cooling turbine unit (3) further by the separation of separator (5)
After be conveyed to helicopter capsule, it is characterised in that by absolute pressure regulator (1) high temperature and high pressure gas also by first pipe
Road extends to the passage air outlet where being provided with cooling radiator (2), and the first pipeline tail end is provided with injector
(10), injector (10) spout direction is consistent with air outlet wind direction.
2. injection as claimed in claim 1 radiates controllable air circulation system, it is characterised in that set on first pipeline
It is equipped with injection and controls valve (9).
3. injection as claimed in claim 1 radiates controllable air circulation system, it is characterised in that the fan (4) is set
Between cooling radiator (2) and injector (10).
4. injection as claimed in claim 1 radiates controllable air circulation system, it is characterised in that adjusted by absolute pressure
The high temperature and high pressure gas of device (1) are also extended at the import of separator (5) by second pipe.
5. injection as claimed in claim 4 radiates controllable air circulation system, it is characterised in that set on the second pipe
It is equipped with plus temperature control valve (11).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611085692.XA CN106741967A (en) | 2016-11-30 | 2016-11-30 | A kind of controllable air circulation system of injection radiating |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611085692.XA CN106741967A (en) | 2016-11-30 | 2016-11-30 | A kind of controllable air circulation system of injection radiating |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106741967A true CN106741967A (en) | 2017-05-31 |
Family
ID=58913983
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611085692.XA Pending CN106741967A (en) | 2016-11-30 | 2016-11-30 | A kind of controllable air circulation system of injection radiating |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106741967A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108915845A (en) * | 2018-07-19 | 2018-11-30 | 青岛理工大学 | Spray cooling type multistage injection system for armored vehicle |
| CN109533343A (en) * | 2018-11-15 | 2019-03-29 | 中国直升机设计研究所 | A kind of helicopter bleed control system |
| CN115573815A (en) * | 2022-10-09 | 2023-01-06 | 中国航空工业集团公司西安飞机设计研究所 | Heat exchange device for injecting by utilizing air-entraining jet flow of aircraft engine |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040195448A1 (en) * | 2002-12-14 | 2004-10-07 | Flatman Richard J. | Environmental control system |
| EP1790568A2 (en) * | 2005-11-29 | 2007-05-30 | Hamilton Sundstrand Corporation | Cabin air conditioning system with liquid cooling for power electronics |
| CN102874410A (en) * | 2012-09-14 | 2013-01-16 | 北京航空航天大学 | High-speed motor driven air circulating refrigeration system |
| CN205381408U (en) * | 2016-02-18 | 2016-07-13 | 江西洪都航空工业集团有限责任公司 | Ejector device |
| CN105857618A (en) * | 2015-02-11 | 2016-08-17 | 哈米尔顿森德斯特兰德公司 | Environmental control system utilizing parallel ram heat exchangers |
-
2016
- 2016-11-30 CN CN201611085692.XA patent/CN106741967A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040195448A1 (en) * | 2002-12-14 | 2004-10-07 | Flatman Richard J. | Environmental control system |
| EP1790568A2 (en) * | 2005-11-29 | 2007-05-30 | Hamilton Sundstrand Corporation | Cabin air conditioning system with liquid cooling for power electronics |
| CN102874410A (en) * | 2012-09-14 | 2013-01-16 | 北京航空航天大学 | High-speed motor driven air circulating refrigeration system |
| CN105857618A (en) * | 2015-02-11 | 2016-08-17 | 哈米尔顿森德斯特兰德公司 | Environmental control system utilizing parallel ram heat exchangers |
| CN205381408U (en) * | 2016-02-18 | 2016-07-13 | 江西洪都航空工业集团有限责任公司 | Ejector device |
Non-Patent Citations (2)
| Title |
|---|
| 杨国茹等: "直升机热管空气循环制冷技术研究", 《2016年第三十二届全国直升机年会学术论文集》 * |
| 梁相文: "《未来试飞新技术挑战》", 31 July 2014 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108915845A (en) * | 2018-07-19 | 2018-11-30 | 青岛理工大学 | Spray cooling type multistage injection system for armored vehicle |
| CN109533343A (en) * | 2018-11-15 | 2019-03-29 | 中国直升机设计研究所 | A kind of helicopter bleed control system |
| CN115573815A (en) * | 2022-10-09 | 2023-01-06 | 中国航空工业集团公司西安飞机设计研究所 | Heat exchange device for injecting by utilizing air-entraining jet flow of aircraft engine |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20170531 |
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| RJ01 | Rejection of invention patent application after publication |