CN102121441A - Pure liquid oxygen aeroengine - Google Patents
Pure liquid oxygen aeroengine Download PDFInfo
- Publication number
- CN102121441A CN102121441A CN2011100384281A CN201110038428A CN102121441A CN 102121441 A CN102121441 A CN 102121441A CN 2011100384281 A CN2011100384281 A CN 2011100384281A CN 201110038428 A CN201110038428 A CN 201110038428A CN 102121441 A CN102121441 A CN 102121441A
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- CN
- China
- Prior art keywords
- oxygen
- aeroengine
- outlet
- inlet connecting
- heat exchanger
- 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.)
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
Abstract
The invention provides a pure liquid oxygen aeroengine. The aeroengine comprises a liquid oxygen tank 1, a heat exchanger 2, a heater 3, a pressure buffer tank 4, an oxygen flow controller 5, an aeroengine 6 and connecting pipelines, wherein the connecting pipelines include an aeroengine air inlet and oxygen flow controller oxygen outlet connecting pipe 7, a pressure buffer tank oxygen outlet and oxygen flow controller oxygen inlet connecting pipe 8, an aeroengine tail gas outlet and heater heated gas inlet connecting pipe 9, a heater oxygen outlet and pressure buffer tank oxygen inlet connecting pipe 10, a tail gas outlet escape pipe 11 passing through the heater, an aeroengine radiator cooling media outlet and heat exchanger heating carrier inlet connecting pipe 12, a heat exchanger heating carrier outlet and aeroengine radiator cooling media inlet connecting pipe 13, a heat exchanger oxygen outlet and heater oxygen inlet connecting pipe 14 and a liquid oxygen tank oxygen outlet and heat exchanger oxygen inlet connecting pipe 15. The aeroengine has the following advantages: the energy is saved by 80% and the emission is reduced by 95%.
Description
Technical field
The present invention relates to various aeroengines.
Background technique
The Aviation Fuel that existing aeroengine is used is the organic compound of long carbochain, because the burning of a fuel molecule, need a plurality of, dozens of, hundreds of, even polyoxy molecule more, yet use in the combustion improver air, only contain 21% oxygen, in thousands of meters high-altitudes, rarefaction of air, oxygenous just still less, in the aeroengine working procedure, fuel oil is excessive, the oxygen wretched insufficiency, the result causes oil inflame insufficient, oxygen and airborne nitrogen at high temperature react, and produce nitrogen oxide, poor efficiency, pollute, the energy resource waste, the cost height, problems such as deficiency in economic performance.
Summary of the invention
Main purpose of the present invention solves aeroengine in the course of the work exactly, the oxygen wretched insufficiency, it is combustion-supporting that the past air for supporting combustion is changed into excessive pure liquid oxygen, make the oxygen deficiency, fuel oil is excessive, and to become oxygen excessive, there is sufficient excess of oxygen moment in burning, makes the instantaneous effective rate of combustion of fuel oil reach the upper limit (UL) value; Gas medium reduces 79% in the combustion reaction, and the heat that tail gas is taken away reduces 79%; Do not have nitrogen in the combustion reaction, just do not have nitrogen oxide to produce in the tail gas.Advantage of the present invention: energy-conservation 80%, reduce discharging 95%.The scheme of specifically dealing with problems: the air supply system that removes aeroengine, form by liquid oxygen jar, heat exchanger, heater, pressure surge tank, oxygen flow modulator, aeroengine and connecting tube, the oxygen outlet pipe is connected with aeroengine air inlet pipe, oxygen is directly supplied with the aeroengine combustor buring chamber; Cooling medium in the aeroengine radiator is fed heat exchanger as heat medium,, reclaim heat energy, improve cooling effectiveness with oxygen generation heat exchange from the liquid oxygen jar; Aeroengine tail gas is fed heater as heat medium, improve oxygen temperature, reclaim heat energy once more, improve the heat energy utilization rate, reduce cost.
Description of drawings
Fig. 1 is a main structure schematic representation of the present invention, description of reference numerals is as follows: the 1st, and the liquid oxygen jar, the 2nd, heat exchanger, the 3rd, heater, the 4th, pressure surge tank, the 5th, the oxygen flow modulator, the 6th, aeroengine, the 7th, aeroengine air intlet and oxygen flow modulator oxygen outlet connecting tube, the 8th, pressure surge tank oxygen outlet and oxygen flow modulator oxygen inlet connecting tube, the 9th, outlet of aeroengine tail gas and heater heats gas inlet connecting tube, the 10th, heater oxygen outlet and pressure surge tank oxygen inlet connecting tube, the 11st, through the tail gas blow-down pipe of heater, the 12nd, the cooling medium outlet and the heat exchanger heating carrier inlet connecting branch of aeroengine radiator, the 13rd, the inlet connecting branch of cooling medium in outlet of heat exchanger heating carrier and the aeroengine radiator, the 14th, heat exchanger oxygen outlet and heater oxygen inlet connecting tube, the 15th, liquid oxygen jar oxygen outlet and heat exchanger oxygen inlet connecting tube, arrow is represented the media flow direction among the figure.
Embodiment
As shown in Figure 1, a kind of pure liquid oxygen aeroengine is by liquid oxygen jar 1, heat exchanger 2, heater 3, pressure surge tank 4, oxygen flow modulator 5, aeroengine 6 and connecting tube are formed, wherein 7 is aeroengine air intlet and oxygen flow modulator oxygen outlet connecting tube, the 8th, pressure surge tank oxygen outlet and oxygen flow modulator oxygen inlet connecting tube, the 9th, outlet of aeroengine tail gas and heater heats gas inlet connecting tube, the 10th, heater oxygen outlet and pressure surge tank oxygen inlet connecting tube, the 11st, through the tail gas blow-down pipe of heater, the 12nd, in the aeroengine radiator outlet of cooling medium be connected with the import of heat exchanger heating carrier and, the 13rd, the inlet connecting branch of cooling medium in outlet of heat exchanger heating carrier and the aeroengine radiator, the 14th, heat exchanger oxygen outlet and heater oxygen inlet connecting tube, the 15th, liquid oxygen jar oxygen outlet and heat exchanger oxygen inlet connecting tube.
Claims (1)
1. pure liquid oxygen aeroengine, it is characterized in that: by liquid oxygen jar (1), heat exchanger (2), heater (3), pressure surge tank (4), oxygen flow modulator (5), aeroengine (6) and connecting tube are formed, wherein aeroengine air intlet and oxygen flow modulator oxygen outlet connecting tube (7), pressure surge tank oxygen outlet and oxygen flow modulator oxygen inlet connecting tube (8), outlet of aeroengine tail gas and heater heats gas inlet connecting tube (9), heater oxygen outlet and pressure surge tank oxygen inlet connecting tube (10), tail gas outlet blow-down pipe (11) through heater, outlet of aeroengine radiator cooling medium and heat exchanger heating carrier inlet connecting branch (12), the outlet of heat exchanger heating carrier and aeroengine cooling medium inlet connecting tube (13), heat exchanger oxygen outlet and heater oxygen inlet connecting tube (14), liquid oxygen jar oxygen outlet and heat exchanger oxygen inlet connecting tube (15).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011100384281A CN102121441B (en) | 2011-01-31 | 2011-01-31 | Pure liquid oxygen aeroengine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011100384281A CN102121441B (en) | 2011-01-31 | 2011-01-31 | Pure liquid oxygen aeroengine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102121441A true CN102121441A (en) | 2011-07-13 |
| CN102121441B CN102121441B (en) | 2012-07-11 |
Family
ID=44250079
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011100384281A Expired - Fee Related CN102121441B (en) | 2011-01-31 | 2011-01-31 | Pure liquid oxygen aeroengine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102121441B (en) |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2052441U (en) * | 1989-08-03 | 1990-02-07 | 薛殿甲 | Recovery device for waste heat of internal-combustion engine |
| CN101526035A (en) * | 2009-03-11 | 2009-09-09 | 天津大学 | Automobile pure oxygen combustion engine system |
| CN201925052U (en) * | 2011-01-31 | 2011-08-10 | 赵军政 | Pure liquid oxygen aviation engine |
-
2011
- 2011-01-31 CN CN2011100384281A patent/CN102121441B/en not_active Expired - Fee Related
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2052441U (en) * | 1989-08-03 | 1990-02-07 | 薛殿甲 | Recovery device for waste heat of internal-combustion engine |
| CN101526035A (en) * | 2009-03-11 | 2009-09-09 | 天津大学 | Automobile pure oxygen combustion engine system |
| CN201925052U (en) * | 2011-01-31 | 2011-08-10 | 赵军政 | Pure liquid oxygen aviation engine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102121441B (en) | 2012-07-11 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20120711 Termination date: 20220131 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |