CN104819467B - A kind of aircraft fire protection test burn device air supply system - Google Patents
A kind of aircraft fire protection test burn device air supply system Download PDFInfo
- Publication number
- CN104819467B CN104819467B CN201510212147.1A CN201510212147A CN104819467B CN 104819467 B CN104819467 B CN 104819467B CN 201510212147 A CN201510212147 A CN 201510212147A CN 104819467 B CN104819467 B CN 104819467B
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- China
- Prior art keywords
- valve
- energy storage
- storage tank
- pipeline
- gas outlet
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- 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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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
- F23D14/46—Details, e.g. noise reduction means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
- F23D14/46—Details, e.g. noise reduction means
- F23D14/72—Safety devices, e.g. operative in case of failure of gas supply
- F23D14/78—Cooling burner parts
Abstract
The invention belongs to Aeronautical Test Technology, it is related to the improvement to aircraft fire protection test burn device air supply system.Including compressor (1), pressure-reducing valve (2), the first energy storage tank (3), first throttle valve (4), second throttle (5), the 3rd choke valve (6) and burner (7)；It is characterized in that：There are a pressure maintaining valve (8) and second energy storage tank (9) between compressor (1) and pressure-reducing valve (2).The present invention proposes a kind of improved aircraft fire protection test burn device air supply system, substantially reduces the flame temperature fluctuation of burner, improves temperature stability and cooling gas temperature regulation effect.
Description
Technical field
The invention belongs to Aeronautical Test Technology, it is related to the improvement to aircraft fire protection test burn device air supply system.
Background technology
, referring to Fig. 1, it is by compressor 1, pressure-reducing valve 2, first for a kind of current aircraft fire protection test burn device air supply system
Energy storage tank 3, first throttle valve 4, second throttle 5, the 3rd choke valve 6 and burner 7 are constituted.The air supply opening of compressor 1 passes through
Pipeline is connected with the air inlet of pressure-reducing valve 2, and the gas outlet of pressure-reducing valve 2 is connected by pipeline with the air inlet 3a of the first energy storage tank 3, the
First gas outlet 3b of one energy storage tank 3 is connected by pipeline with the air inlet of second throttle 5, the gas outlet of second throttle 5
Connected with the combi inlet port 7b of burner 7 by pipeline, the second gas outlet 3c of the first energy storage tank 3 passes through pipeline and Section three
The air inlet connection of valve 6 is flowed, the gas outlet of the 3rd choke valve 6 is connected by pipeline with the cooling gas import 7c of burner 7, first
The air inlet of choke valve 4 is connected by pipeline with coal gas source, and the gas outlet of first throttle valve 4 is by pipeline and the coal of burner 7
Gas import 7a is connected.Its operation principle is：Compressor 1 provides compressed air (pressure fluctuates between 0.4MPa-0.7MPa), warp
Cross after air reducing valve 2 and obtain the compressed air (pressure is about 0.35MPa) of pressure stability, be stored in the first energy storage tank 3, the
Compressed air in one energy storage tank 3 is by entering the combustion gas mixing that burner 7 is provided with first throttle valve 4 after second throttle 5
Form gaseous mixture；Compressed air in first energy storage tank 3 is made by entering burner 7 after the 3rd choke valve 6 as cooling gas
With.The key of homogeneous flame temperature stabilization is that the pressure of combustion gas and air, flow will be stablized.It has the disadvantage：
1st, the flame temperature fluctuation of burner is big, and temperature stability is poor, and flame temperature often exceeds 1100 DEG C ± 80 DEG C
Scope.This is larger mainly due to the pressure oscillation of air compressor 1, makes pressure in the first energy storage tank 3 also small amplitude wave therewith
It is dynamic, the air mass flow of its supplied burner 7 is fluctuated what is caused therewith.
2nd, the flame temperature regulation of burner is difficult.This is relatively low mainly due to the pressure in the first energy storage tank 3, there is provided
Cooling gas flow is not enough, causes cooling gas temperature regulation effect unobvious.Because gaseous mixture and cooling gas are all by the first energy storage canister 3
In confess, pressure is relatively low, make cooling gas almost do not have regulation flame temperature effect.
The content of the invention
The purpose of the present invention is：A kind of improved aircraft fire protection test burn device air supply system is proposed, to reduce burning
The flame temperature fluctuation of device, improves temperature stability and cooling gas temperature regulation effect.
The technical scheme is that：A kind of aircraft fire protection test burn device air supply system, including compressor 1, pressure-reducing valve
2nd, the first energy storage tank 3, first throttle valve 4, second throttle 5, the 3rd choke valve 6 and burner 7；The first of first energy storage tank 3
Gas outlet 3b is connected by pipeline with the air inlet of second throttle 5, and the gas outlet of second throttle 5 passes through pipeline and burner
7 combi inlet port 7b connections, the air inlet of first throttle valve 4 is connected by pipeline with coal gas source, the outlet of first throttle valve 4
Mouth is connected by pipeline with the gas inlet 7a of burner 7；It is characterized in that：There is one between compressor 1 and pressure-reducing valve 2 surely
Pressure valve 8 and second energy storage tank 9, the air supply opening of compressor 1 are connected by pipeline with the air inlet of pressure maintaining valve 8, pressure maintaining valve 8
Gas outlet is connected by pipeline with the air inlet 9a of the second energy storage tank 9, the first gas outlet 9b of the second energy storage tank 9 by pipeline with
The air inlet connection of pressure-reducing valve 2, the second gas outlet 9c of the second energy storage tank 9 is connected by the air inlet of pipeline and the 3rd choke valve 6
Logical, the gas outlet of the 3rd choke valve 6 is connected by pipeline with the cooling gas import 7c of burner 7；The second of first energy storage tank 3 goes out
Gas port 3c is closed.
It is an advantage of the invention that：A kind of improved aircraft fire protection test burn device air supply system is proposed, is substantially reduced
The flame temperature fluctuation of burner, improves temperature stability and cooling gas temperature regulation effect.One embodiment of the present of invention,
Tests prove that, the flame temperature fluctuation of burner significantly reduces, and flame temperature stabilization is in the range of 1100 DEG C ± 60 DEG C.
Brief description of the drawings
Fig. 1 is a kind of structural principle block diagram of current aircraft fire protection test burn device air supply system.
Fig. 2 is structural principle block diagram of the invention.
Specific embodiment
The present invention is described in further details below.Referring to Fig. 2, a kind of aircraft fire protection test burn device air supply system,
Including compressor 1, pressure-reducing valve 2, the first energy storage tank 3, first throttle valve 4, second throttle 5, the 3rd choke valve 6 and burner 7；
First gas outlet 3b of the first energy storage tank 3 is connected by pipeline with the air inlet of second throttle 5, the outlet of second throttle 5
Mouth is connected by pipeline with the combi inlet port 7b of burner 7, and the air inlet of first throttle valve 4 is connected by pipeline with coal gas source
Logical, the gas outlet of first throttle valve 4 is connected by pipeline with the gas inlet 7a of burner 7；It is characterized in that：In compressor 1
There are a pressure maintaining valve 8 and second energy storage tank 9 and pressure-reducing valve 2 between, the air supply opening of compressor 1 is by pipeline and pressure maintaining valve 8
Air inlet connection, the gas outlet of pressure maintaining valve 8 connected by pipeline with the air inlet 9a of the second energy storage tank 9, the second energy storage tank 9
First gas outlet 9b is connected by pipeline with the air inlet of pressure-reducing valve 2, the second gas outlet 9c of the second energy storage tank 9 by pipeline with
The air inlet connection of the 3rd choke valve 6, the gas outlet of the 3rd choke valve 6 is connected by pipeline with the cooling gas import 7c of burner 7
It is logical；The second gas outlet 3c closings of the first energy storage tank 3.
Operation principle of the invention is：Lift flame temperature stability it is critical only that stabilization source of the gas.Supplied in compressor 1
Increase a pressure maintaining valve 8 at mouthful, further stabilization of export pressure is further added by a storing compressed air of the second energy storage tank 9, it is maximum
The pressure oscillation of compressor 1 is eliminated to limit, so as to be obviously improved the uniformity and Stability index of flame.The opposing party
Face, cooling gas leading point is drawn by changing after the first energy storage tank 3 by after increased second energy storage tank 9, improves the supply of cooling gas
Pressure, improves the effect of flame temperature regulation and control.
One embodiment of the present of invention, the structure of the second energy storage tank 9 and the first energy storage tank 3 are identical, and pressure maintaining valve 8 uses finished product
Part.
Claims (1)
1. a kind of aircraft fire protection test burn device air supply system, including compressor (1), pressure-reducing valve (2), the first energy storage tank (3),
One choke valve (4), second throttle (5), the 3rd choke valve (6) and burner (7)；First gas outlet of the first energy storage tank (3)
(3b) is connected by pipeline with the air inlet of second throttle (5), and the gas outlet of second throttle (5) passes through pipeline and burner
(7) combi inlet port (7b) connection, the air inlet of first throttle valve (4) is connected by pipeline with coal gas source, first throttle valve
(4) gas outlet is connected by pipeline with the gas inlet (7a) of burner (7)；It is characterized in that：In compressor (1) and decompression
The air supply opening for having a pressure maintaining valve (8) and second energy storage tank (9), compressor (1) between valve (2) passes through pipeline and pressure maintaining valve
(8) air inlet connection, the gas outlet of pressure maintaining valve (8) is connected by pipeline with the air inlet (9a) of the second energy storage tank (9), and second
First gas outlet (9b) of energy storage tank (9) is connected by pipeline with the air inlet of pressure-reducing valve (2), and the second of the second energy storage tank (9)
Gas outlet (9c) is connected by pipeline with the air inlet of the 3rd choke valve (6), the gas outlet of the 3rd choke valve (6) by pipeline with
Cooling gas import (7c) connection of burner (7)；Second gas outlet (3c) closing of the first energy storage tank (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510212147.1A CN104819467B (en) | 2015-04-29 | 2015-04-29 | A kind of aircraft fire protection test burn device air supply system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510212147.1A CN104819467B (en) | 2015-04-29 | 2015-04-29 | A kind of aircraft fire protection test burn device air supply system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104819467A CN104819467A (en) | 2015-08-05 |
| CN104819467B true CN104819467B (en) | 2017-06-06 |
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ID=53729848
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510212147.1A Active CN104819467B (en) | 2015-04-29 | 2015-04-29 | A kind of aircraft fire protection test burn device air supply system |
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| CN (1) | CN104819467B (en) |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201000341Y (en) * | 2007-01-30 | 2008-01-02 | 宝钢集团有限公司教育培训中心工会委员会 | Adjustable constant voltage precision air source device |
| CN101280887B (en) * | 2007-06-06 | 2012-01-11 | 中国人民解放军总后勤部军需装备研究所 | Pipe gas pressure stabilizing regulation system |
| US8418732B2 (en) * | 2011-07-06 | 2013-04-16 | Air Products And Chemicals, Inc. | Blending compressed gases |
| CN203363652U (en) * | 2013-05-15 | 2013-12-25 | 中国科学院等离子体物理研究所 | Quantitative gas supply system |
| CN203477892U (en) * | 2013-09-02 | 2014-03-12 | 凌云工业股份有限公司 | Gas storage device with function of gas supercharging |
| CN103697961B (en) * | 2013-12-26 | 2017-01-11 | 武汉理工大学 | Gas fuel nozzle flow measurement pressurizer |
| CN204008098U (en) * | 2014-07-24 | 2014-12-10 | 江苏神通阀门股份有限公司 | A kind of non-return valve opening pressure proving installation |
| CN104315514B (en) * | 2014-11-18 | 2017-01-18 | 中冶南方(武汉)威仕工业炉有限公司 | Partially premixed gas fuel burner of bi-layer porous foamed ceramic plate |
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- 2015-04-29 CN CN201510212147.1A patent/CN104819467B/en active Active
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| CN104819467A (en) | 2015-08-05 |
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