CN103471135A - Jet-stream air suction and jet combustor - Google Patents
Jet-stream air suction and jet combustor Download PDFInfo
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- CN103471135A CN103471135A CN 201310383036 CN201310383036A CN103471135A CN 103471135 A CN103471135 A CN 103471135A CN 201310383036 CN201310383036 CN 201310383036 CN 201310383036 A CN201310383036 A CN 201310383036A CN 103471135 A CN103471135 A CN 103471135A
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Abstract
The invention relates to a jet-stream air suction and jet combustor. The combustor is characterized in that air is sucked by the aid of jet-stream and flows into a main combustion chamber via a fan-shaped guide isolator by the aid of rotation kinetic energy of the jet-stream, the sucked air and fuel are mixed with each other and are combusted to generate high-temperature and high-pressure gas, and the high-temperature and high-pressure gas is ejected via a nozzle. The jet-stream air suction and jet combustor has the advantages that the jet-stream air suction and jet combustor can be applied to jet engines of aircrafts and aspects with requirements on high-temperature and high-pressure gas streams and the like; the structure of the combustor without rotation components is simplified, the working pressure of the combustor is increased, and the reliability of the combustor is improved.
Description
Technical field
The present invention relates to a kind of jet flow air inlet steam-injector type burner, a kind of jet-stream wind air amount combustion fuel that utilizes particularly is provided, form the burner that in combustion chamber, high temperature and high pressure gas outwards sprays, be adapted at using in aircraft and other burning heating equipment.
Background technology
Burner needs oxygen and the rear HTHP jet-stream wind that forms of burning in consumed cabin air, and existing this kind equipment is widely used air blast provides pressure-air, needs consume extra energy and increase auxiliary device, has reduced the reliability of system.For example aero-jet engine need to adopt the turbofan rotating inlet, also will have and drive the high-temperature resistant gas blade of turbofan to obtain gas power.
Since aero-jet engine has been arranged, although all obtained in all fields larger progress, basic model does not have essential change, all needs to use compressor to provide and enters the air in combustion chamber.As the punching engine of Chinese patent 201120213212.X etc., although do not need to use compressor work, need to could continuous service under the high-speed flight condition.
Summary of the invention
The purpose of this invention is to provide a kind of jet flow air inlet steam-injector type burner, this burner utilizes the jet-stream wind air amount and utilizes the rotation function of air-flow to enter main chamber by fan-shaped guiding isolator, after the air of suction and fuel mix burning, forms high temperature and high pressure gas and sprays through spout.
Jet flow air inlet steam-injector type burner of the present invention, , in main chamber air inlet side, the spout that sprays the High Rotation Speed air-flow is installed, form local low pressure with the tight adjacent air inlet of spout in the space of nozzle divergence section, suck extraneous air and rotatablely move as circumference with the spout high velocity air, fan type guiding isolator is installed between nozzle divergence section and main chamber, each blade of fan type guiding isolator distributes in the shape of a spiral, the direction of rotation of spiral is identical with the direction of rotation of high velocity air, the fan type guiding interlobate space of isolator provides swirling eddy to enter the passage of main chamber, the gap of entrance is large, the gap of outlet is little.Fan type guiding isolator blade is fixedly mounted between combination inner cone and main chamber shell.The High Rotation Speed air-flow is provided by the startup spout with collapsible tube and feedback spout, and what with the startup spout, be connected is to start high-pressure burner, and starting the high-pressure burner outside provides pressure-air or oxygen and mix rear ignition with high pressure fuel.The high-pressure air source of feedback spout is from main chamber, and pressure tappings is opened near main chamber advances spout to obtain higher feedback pressure.Swirling eddy can generate in an end has the pyramid type cavity of pyramid type contracting nozzle, also can along the hand of spiral of fan type guide vane, directly jet in the front side of fan type guiding isolator blade.Starting spout and feedback spout at least respectively has one, when a plurality of startup spouts and feedback spout are arranged, should in the circumference that forms swirling eddy, be uniformly distributed.The effect that starts high-pressure burner and startup spout is not pass through combustion fuel before the main chamber internal pressure is not set up, spray High Rotation Speed air-flow air amount and enter main chamber, also can provide extra jet flow source of the gas in the situation that needs increase substantially the main chamber internal pressure.The switching valve is installed in connecting pipe between feedback spout and main chamber, starts this valve closing in front and start-up course, main chamber pressure is set up rear this valve open, and the ejection air-flow of feedback spout is provided by main chamber.
Jet flow air inlet steam-injector type burner of the present invention, can adopt the conical cavity body to form swirling eddy, High Rotation Speed air-flow spout is the pyramid type spout, with the pyramid type spout closely adjacent air inlet be round, air inlet can be positioned at pyramid type spout inboard and the outside, and air inlet can utilize pyramid type nozzle outlet rotary air-flow to produce centrifugal force in inboard forms the roughly the same low pressure at whirlpool center and strengthens the air inlet effect, the space of pyramid type cavity is large simultaneously, is conducive to the formation of swirling eddy.While adopting conical cavity to generate swirling eddy, startup spout and feedback spout are symmetrically distributed on the circumference of pyramid type cavity major diameter one end, the air-flow of these two spouts tangentially enters conical cavity and generates swirling eddy along the same of circumference, and swirling eddy moves and sprays from the pyramid type spout towards the pyramid type spout vertically under pressure.Adopt conical cavity and pyramid type spout can pyramid type throttling cone be installed in the air inlet outside, regulate the flow of air inlet.Jet flow air inlet steam-injector type burner of the present invention, also can adopt along the hand of spiral of fan type guide vane and directly jet, spout adopts rectangle, air inlet is in the outside of puff prot, puff prot is arranged on fan type guide vane the place ahead with the nested spout of rectangle that air inlet forms, the diametric(al) of the long edge fan type guide vane of spout is placed, and forms a radial air flow cylinder along the tangential winding-up of circumference.Spout is identical with the helical angle of fan type guide vane at the angle of inclination of axially installing, and is conducive to Jet Stream and enters main chamber along the space between fan type guide vane.
When jet flow air inlet steam-injector type burner of the present invention uses for aircraft, air inlet is installed in inlet channel and distributes blade valve and air induction conduit, pressure-air in air induction conduit can directly be guided and be entered main chamber, during low-speed operations, the air inlet open and close valve in air induction conduit is closed, prevent the pressure leakage of main chamber.During high-speed flight, the air inlet open and close valve in conduit is opened, by air inlet, distributed leaf valve shunting charge air flow directly to enter main chamber.Start between high-pressure burner and feedback high pressure draught pipeline communicating pipe is installed, install one on communicating pipe and open and close valve, main chamber starts early gate and closes.Can close gas and the fuel oil supply that starts high-pressure burner after main chamber pressure is set up, the valve of opening on connecting pipe is sent the feedback high pressure draught into the startup high-pressure burner, utilizes and starts the spout jet-stream wind.The cone that fan type guiding isolator blade is installed makes two interlobate spaces shrink to the main chamber direction, and the gap of entrance is large, and the gap of outlet is little, increases isolation effect and be conducive to swirling eddy to enter main chamber.The more isolation effect of quantity of fan type guiding isolator blade is good, but intake resistance increases.The helical angle of fan type guiding isolator blade is little, and isolation effect is good, but the stroke of air inlet increases resistance, increases.The size of fan type guiding isolator and the large I in blade screw angle and gap are according to consumption COMPREHENSIVE CALCULATING and the design of pressure and the fuel oxygen of main chamber.
The accompanying drawing explanation
Fig. 1. be structure and the operation principle schematic diagram of jet flow air inlet steam-injector type burner of the present invention;
Fig. 2. be the structural representation of jet flow air inlet steam-injector type burner air inlet of the present invention in the pyramid type spout outside;
Fig. 3. be the fan type guiding spacer structures schematic diagram of jet flow air inlet steam-injector type burner of the present invention;
Fig. 4. be the directly structural representation of winding-up of jet flow air inlet steam-injector type burner of the present invention;
Fig. 5. be directly nozzle exit area and the inclination angle schematic diagram of winding-up of jet flow air inlet steam-injector type burner of the present invention.
The specific embodiment
In conjunction with Fig. 1, form a pyramid type cavity between Outer Taper 2 and inner cone 3, the larger diameter end of pyramid type cavity is equipped with and starts spout 4 and feedback spout 5.Start spout and be connected with startup high-pressure burner 16, start in high-pressure burner and introduce fuel and oxygen by injection line 17 and hyperbaric oxygen tracheae 18, is ignited by initial igniter 19, high pressure draught sprays through starting spout 4.Feedback spout 5 is through pipeline and open and close valve 15 and be communicated with main chamber 23 through feedback pressure tappings 14, opening and closing valve 15 before combustion system starts and in start-up course closes, open and close valve 15 and open after main chamber pressure is set up, the high pressure draught in main chamber is imported and spray through feedback spout 5.Start spout 4 and feedback spout 5 and be symmetrically distributed in the large diameter end of formation pyramid type cavity between Outer Taper 2 and inner cone 3, the air-flow that starts spout and feedback spout tangentially enters the pyramid type cavity along circumference and generates swirling eddy, and Directional Sign 20 is flow rotation directions.The swirling eddy of pyramid type cavity is under pressure to pyramid type spout 1 motion of serrated end and through this spout ejection, the outside of pyramid type spout is expansion segment horn mouth 7, inboard closely adjacent be circular air inlet 21, air inlet is connected with the pyramid type inlet channel.The High Rotation Speed air-flow of pyramid type spout 1 ejection forms low-pressure area in the expansion segment space, extraneous air enters air inlet through inlet channel along direction 22 under the atmospheric pressure effect, and the High Rotation Speed air-flow of expansion segment is mixed and fed into the space between fan type guiding isolator 10 blades, under the effect of air rotary power, enters main chamber 23.The blades installation of fan type guiding isolator 10 is on combination inner cone 13, and excircle is fixed on the main chamber shell.The passage that the fan type guiding interlobate space of isolator provides swirling eddy to enter main chamber, the gap of entrance is large, and the gap of outlet is little, increases the effect of air inlet and isolation.Enter the air of main chamber and the fuel mix after-combustion of oil nozzle 9 ejections by fan type guiding isolator, the high-temperature high-pressure air flow of formation is from advancing spout 24 ejections.Advance the tail fiaring cone 30 of spout to adjust the effect that air-flow sprays.Main chamber fuel is carried through fuel feed pump 8.The flow of air inlet 21 air inlets is regulated with throttling cone 6, and the YE 11 of controlling the throttling cone is connected with peripheral control unit by control cables 12.Standby igniter 25 is arranged in main chamber, enter the main chamber gas temperature when low for lighting air mixture.It's communicating pipe 37 pasts the device for cleaning pipeline of feedback air-flow and open and close valve 38 is connected with startup high-pressure burner 16, and while starting high-pressure burner work, valve 38 is closed.When closing the fuel supply that starts high-pressure burner after main chamber pressure is set up, valve 38 is opened, and the feedback air-flow is introduced and started spout and utilize the startup spout to spray the feedback air-flow.
In Fig. 2, air inlet 21 is in the outside of pyramid type cavity, and the inside of pyramid type cavity increases a rotation inner cone 27, is conducive to the formation of swirling eddy in the pyramid type cavity.Be installed into airway 28 between inlet channel and main chamber, install on air induction conduit and open and close valve 36, at the installed inside air inlet distribution leaf valve 29 of inlet channel upper air catheter opening.Using jet flow air inlet steam-injector type burner to use as aircraft, after if aircraft movements speed is brought up to the pressure that the air pressure of inlet channel is greater than main chamber, open and open and close valve 36, regulate the aperture that air inlet distributes leaf valve 29, the distribution portion charge air flow directly enters main chamber by air induction conduit, can improve the air inflow of main chamber.Fig. 3 is the fan type guiding spacer structures schematic diagram of jet flow air inlet steam-injector type burner of the present invention, and fan type guiding isolator 10 guide vanes, by the spiral distribution of dextrorotation, are complementary with the swirling eddy direction of pyramid type spout.Guide vane is arranged on pyramid type combination inner cone 13, shrink to the direction of main chamber in two interlobate gaps, swirling eddy is formed to entrance large, go out young structure, be conducive to swirling eddy and enter main chamber, increase the hyperbar of main chamber and the effect of pyramid type nozzle divergence section space low-pressure area isolation.Radome fairing 26 is for increasing charge air flow.
In conjunction with Fig. 4 and Fig. 5, high velocity air is directly jetted to the guide vane of fan type guiding isolator 10, and feedback spout 32 is rectangle, and air inlet 21 is in the outside of feedback spout.Start spout 31 identical with the shape of feedback spout, be symmetrically distributed on the circumference adjoining with fan type guiding isolator front end, puff prot is arranged on fan type guide vane the place ahead with the nested spout of rectangle that air inlet forms, the diametric(al) of the long edge fan type guide vane of spout is placed, and forms a radial air flow cylinder along the tangential winding-up of circumference.Spout means at the angle of inclination 34 use α that axially install, and the helical angle 35 use β of fan type guiding isolator blade mean, should guarantee that the lead helical angle of isolator blade of axioversion angle that spout installs and fan type is identical.The bottom of inlet channel is equipped with air inlet division board 33, and on division board 33, the distribution wireway is for being communicated with each air inlet and inlet channel.
Claims (6)
1. a jet flow air inlet steam-injector type burner, it is characterized in that utilizing the High Rotation Speed air-flow air amount of contracting nozzle ejection and enter main chamber by fan-shaped guiding isolator under the rotation function effect of air-flow, form high temperature and high pressure gas after the air of main chamber and fuel mix burning also by advancing the spout ejection.
2. according to the jet flow air inlet steam-injector type burner of claim 1, the high velocity air that it is characterized in that the contracting nozzle ejection sucks extraneous air and forms swirling eddy at the low-pressure area of fan-shaped guiding isolator front end, and the direction of swirling eddy is consistent with the hand of spiral of fan-shaped guiding isolator blade.
3. according to the jet flow air inlet steam-injector type burner of claim 1, it is characterized in that the High Rotation Speed air-flow provides through the feedback pipeline by starting high-pressure burner and main chamber gases at high pressure, starting the high-pressure burner outside provides the fuel of high pressure oxygen or the ejection of pressure-air burning high-pressure oil pipe, gases at high pressure are by starting spout and the ejection of feedback spout, starting spout and feedback spout at least respectively has one, while having a plurality of startup spouts and feedback spout, should in the circumference that forms swirling eddy, be uniformly distributed.
4. according to the jet flow air inlet steam-injector type burner of claim 1, it is characterized in that swirling eddy can generate in a pyramid type cavity, the pyramid type spout ejection of shrinking by pyramid type cavity one end, air inlet is closely adjacent in the outside or the inboard of pyramid type spout.
5. according to the jet flow air inlet steam-injector type burner of claim 1, it is characterized in that adopting direct winding-up to produce the High Rotation Speed air-flow, spout adopts rectangle, air inlet is in the outside of puff prot, the nested spout of rectangle that puff prot forms with air inlet is arranged on the place ahead of fan-shaped guiding isolator blade, the diametric(al) of the long edge fan type guide vane of spout is placed, form a radial air flow cylinder along the tangential winding-up of circumference, spout is identical with the helical angle of fan type guide vane at the angle of inclination of axially installing.
6. according to the jet flow air inlet steam-injector type burner of claim 1, it is characterized in that the blades installation of fan-shaped guiding isolator is on the combination cone, each blade of fan type guiding isolator distributes in the shape of a spiral, the direction of rotation of spiral is identical with the direction of rotation of high velocity air, the gap of the gap entrance of fan type guiding isolator blade is large, the gap of outlet is little, and the size of fan type guiding isolator and the size in blade screw angle and gap are according to consumption COMPREHENSIVE CALCULATING and the design of pressure and the fuel oxygen of main chamber.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201310383036 CN103471135A (en) | 2013-08-22 | 2013-08-22 | Jet-stream air suction and jet combustor |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201310383036 CN103471135A (en) | 2013-08-22 | 2013-08-22 | Jet-stream air suction and jet combustor |
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| CN103471135A true CN103471135A (en) | 2013-12-25 |
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| CN 201310383036 Pending CN103471135A (en) | 2013-08-22 | 2013-08-22 | Jet-stream air suction and jet combustor |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112412625A (en) * | 2019-08-23 | 2021-02-26 | 周维平 | Novel aircraft engine system designed based on gas pressure dynamics principle |
| CN113154451A (en) * | 2021-04-27 | 2021-07-23 | 西北工业大学 | Guide spray pipe of rotary detonation combustion chamber |
| CN114837806A (en) * | 2022-04-19 | 2022-08-02 | 李久斌 | Flat jet engine |
-
2013
- 2013-08-22 CN CN 201310383036 patent/CN103471135A/en active Pending
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112412625A (en) * | 2019-08-23 | 2021-02-26 | 周维平 | Novel aircraft engine system designed based on gas pressure dynamics principle |
| CN113154451A (en) * | 2021-04-27 | 2021-07-23 | 西北工业大学 | Guide spray pipe of rotary detonation combustion chamber |
| CN113154451B (en) * | 2021-04-27 | 2022-09-06 | 西北工业大学 | Guide spray pipe of rotary detonation combustion chamber |
| CN114837806A (en) * | 2022-04-19 | 2022-08-02 | 李久斌 | Flat jet engine |
| CN114837806B (en) * | 2022-04-19 | 2023-11-21 | 李久斌 | Flat jet engine |
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Application publication date: 20131225 |
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| WD01 | Invention patent application deemed withdrawn after publication |