CN104848217B - A kind of head of combustion chamber of hypersonic high enthalpy ground-based simulation equipment - Google Patents
A kind of head of combustion chamber of hypersonic high enthalpy ground-based simulation equipment Download PDFInfo
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- CN104848217B CN104848217B CN201510209803.2A CN201510209803A CN104848217B CN 104848217 B CN104848217 B CN 104848217B CN 201510209803 A CN201510209803 A CN 201510209803A CN 104848217 B CN104848217 B CN 104848217B
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- hydrogen
- spout
- oxygen
- combustion chamber
- inner ring
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Abstract
The invention discloses a kind of head of combustion chamber of hypersonic high enthalpy ground-based simulation equipment, its greatly save space, reduction manufacturing cost, operate it is fairly simple.It includes hydrogen-oxygen spray ring, inner ring air insufflation unit and outer shroud air insufflation unit, hydrogen-oxygen spray ring protrudes from inner ring air insufflation unit and outer shroud air insufflation unit, and it is generally aligned in the same plane with igniter interior, hydrogen-oxygen spray ring has hydrogen runner, oxygen runner, and several are towards the hydrogen spout and oxygen spout of igniter, inner ring air insufflation unit has inner ring air flow channel, several inner ring air ports, each inner ring air port is located at the gap location of hydrogen spout and oxygen spout, outer shroud air insufflation unit has outer shroud air flow channel, several outer shroud air ports towards Inner Wall of Combustion Chamber.
Description
Technical field
The invention belongs to the technical field of hypersonic wind tunnel, set more particularly to the hypersonic high enthalpy ground simulation of one kind
Standby head of combustion chamber.
Background technology
The development of hypersonic aircraft and engine technology depend heavilys on ground wind-tunnel facilities (that is, free jet
Deng the equipment of ground simulation high-altitude high velocity environment) construction.Wherein, it is capable of the hypersonic high enthalpy ground simulation of long-play
The combustion chamber of equipment is essential equipment.
The equipment of the ground simulation such as free jet high-altitude high velocity environment has Gao Han, high speed, high pressure and the spy of long-term use
Point, heating air and supplemental oxygen are generally required in ground simulation high velocity environment, and the component needs of oxygen are consistent with high-altitude.It
Difficult point is that pressure is higher, typically to reach 10MPa pressure, and current combustion chamber only rocket chamber can reach that this sets
Pressure is counted, but the structure of rocket chamber is not to be designed according to long-play, and also the fuel of rocket is mostly liquid
Fuel, also there is the problem of burning not complete enough in it.And ground-based simulation equipment needs to use 10 years even longer times, and combustion
Burn complete.
And use the burning of hydrogen, oxygen and air to obtain the minimum high enthalpy gas of pollution generally acknowledged at present.But
The problem of these gases burn is that working range is narrower, that is, be can only operate in particular range, because once departing from this
Scope, flame will stop working.
And ground-based simulation equipment needs institute in simulation envelope stateful, so parameter variation range is larger, current one
Well matched standby multigroup heater solves this problem, has the disadvantage that space-consuming is big, manufacturing cost is high, complex operation.
The content of the invention
The technology of the present invention solves problem：Overcoming the deficiencies in the prior art, there is provided one kind hypersonic high enthalpy ground face mould
Propose standby head of combustion chamber, its greatly save space, reduction manufacturing cost, operate it is fairly simple.
The present invention technical solution be：The head of combustion chamber of this hypersonic high enthalpy ground-based simulation equipment, it is wrapped
Hydrogen-oxygen spray ring, inner ring air insufflation unit and outer shroud air insufflation unit are included, hydrogen-oxygen spray ring protrudes from inner ring air insufflation
Unit and outer shroud air insufflation unit, and in being generally aligned in the same plane with igniter, hydrogen-oxygen spray ring has hydrogen runner, oxygen
Runner and several towards the hydrogen spout and oxygen spout of igniter, inner ring air insufflation unit has inner ring air stream
Road, several inner ring air ports, each inner ring air port are located at the gap location of hydrogen spout and oxygen spout, outer shroud air
Spray unit have outer shroud air flow channel, several towards Inner Wall of Combustion Chamber outer shroud air port.
The present invention causes hydrogen-oxygen directly to burn by hydrogen-oxygen spray ring, and hydrogen-oxygen ratio is in ignition temperature 900-2100K scopes
Inside it can all stablize；Air enters combustion chamber core by being located at the inner ring air port of the gap location of hydrogen spout and oxygen spout
Position cools down the inwall of hydrogen-oxygen spray ring；Air cools down burning by the direct spray of outer shroud air port to Inner Wall of Combustion Chamber
Chamber interior walls, and the outer wall of hydrogen-oxygen spray ring is cooled down with the air of inner ring air port formation air film, so that combustion chamber
Heat loss it is small；So the present invention replaces multigroup heater only with this head of combustion chamber, it can simulate in envelope
Institute it is stateful, therefore greatly save space, reduction manufacturing cost, operate it is fairly simple.
Brief description of the drawings
Fig. 1 is the structural representation of the head of combustion chamber of the hypersonic high enthalpy ground-based simulation equipment according to the present invention.
Fig. 2 is the structural representation of the major part in Fig. 1.
Fig. 3 is Fig. 2 A-A to sectional view.
Embodiment
As Figure 1-3, the head of combustion chamber of this hypersonic high enthalpy ground-based simulation equipment, it includes hydrogen-oxygen spray
Ring, inner ring air insufflation unit and outer shroud air insufflation unit, hydrogen-oxygen spray ring protrude from inner ring air insufflation unit and outer shroud
Air insufflation unit, and in being generally aligned in the same plane with igniter (not shown), hydrogen-oxygen spray ring have hydrogen runner 1,
Oxygen runner 2 and several towards the hydrogen spout 11 and oxygen spout 21 of igniter, inner ring air insufflation unit has interior
Annular space flow channel 8, several inner ring air ports 81, each inner ring air port are located at the gap of hydrogen spout and oxygen spout
Place, outer shroud air insufflation unit have outer shroud air flow channel 3, several towards Inner Wall of Combustion Chamber outer shroud air port 31.Hydrogen
Gas and oxygen are mixed in hydrogen-oxygen passage 4, and outer shroud air passes through the outer wall of cooling hydrogen-oxygen spray ring and combustion after outer shroud air duct 5
Burn locular wall face, gap and inner ring air flow channel 8 and oxygen stream that inner ring air passes through inner ring air flow channel 8 and hydrogen runner 1
The gap in road 2 enters hydrogen-oxygen passage 4 to cool down the inwall of hydrogen-oxygen spray ring.
The present invention causes hydrogen-oxygen directly to burn by hydrogen-oxygen spray ring, and hydrogen-oxygen ratio is in ignition temperature 900-2100K scopes
Inside it can all stablize；Air enters combustion chamber core by being located at the inner ring air port of the gap location of hydrogen spout and oxygen spout
Position cools down the inwall of hydrogen-oxygen spray ring；Air cools down burning by the direct spray of outer shroud air port to Inner Wall of Combustion Chamber
Chamber interior walls, and the outer wall of hydrogen-oxygen spray ring is cooled down with the air of inner ring air port formation air film, so that combustion chamber
Heat loss it is small；So the present invention replaces multigroup heater only with this head of combustion chamber, it can simulate in envelope
Institute it is stateful, therefore greatly save space, reduction manufacturing cost, operate it is fairly simple.
Further, since the inner ring air port of inner ring air insufflation unit is located at the gap of hydrogen spout and oxygen spout
Place, and the outer shroud air port of outer shroud air insufflation unit is direct-injection, so the amount of outer shroud air insufflation is higher than inner ring
Air capacity, mainly cools down the outer wall of hydrogen-oxygen spray ring and is blended with high-temperature fuel gas.After final burning, hydrogen is completely converted into
Water and the molar content of oxygen is consistent with oxygen content in air, be 21%.When so arriving combustor exit, oxygen content mol ratio
Example is consistent with air.
In addition, the hydrogen-oxygen spray ring is located at the central area of combustion chamber.The wall thermic load of so combustion chamber is small.
In addition, the igniter is placed on the center of hydrogen-oxygen spray ring.Igniting is by hydrogen-oxygen spray ring center position
Igniter light hydrogen-oxygen spray ring hydrogen gas.Flame is lighted away from nozzle exit area, diffusion flame is intersected to form so that hydrogen
With oxygen mix it is more uniform, burn it is more abundant.
In addition, the hydrogen spout and oxygen spout are alternately arranged.So so that rapid, complete and temperature of burning is more equal
Even, stability range is wider.
In addition, in several hydrogen spouts and oxygen spout, majority is spout axis perpendicular to hydrogen-oxygen spray ring, minority
Hydrogen-oxygen spray ring is diagonal to for spout axis.So most of hydrogen and oxygen not only improve mixing equal along flow direction direct-injection
It is even, at the same hydrogen-oxygen directly burn also cause burning more fully and also stability is good, also small part hydrogen and oxygen spray to
Center convergence, this part be ensure reliable ignition and take into account center temperature it is uniform.
Further, in the hydrogen spout and oxygen spout alternately arranged, an adjacent hydrogen spout and one
Individual oxygen spout is one group, and spout axis has 8 groups perpendicular to hydrogen-oxygen spray ring, and spout axis is diagonal to having for hydrogen-oxygen spray ring
4 groups, this 4 groups of spouts are evenly distributed in hydrogen-oxygen spray ring.
In addition, each inner ring air port is located at the gap location of every group of hydrogen spout and oxygen spout.So can be more preferable
More uniformly cool down the inwall of hydrogen-oxygen spray ring.
Beneficial effects of the present invention are as follows：
1. the mode that hydrogen-oxygen directly burns, hydrogen-oxygen ratio can all be stablized in the range of ignition temperature 900-2100K.
2. flame is in burning chamber central zone, and wall thermic load is small.
3. air-impingement and the air film type of cooling are used, the heat loss of combustion chamber is small.
4. can be with long time continuous working.
It is described above, be only presently preferred embodiments of the present invention, any formal limitation not made to the present invention, it is every according to
Any simple modification, equivalent variations and the modification made according to the technical spirit of the present invention to above example, still belong to the present invention
The protection domain of technical scheme.
Claims (7)
1. a kind of head of combustion chamber of hypersonic high enthalpy ground-based simulation equipment, it is characterised in that：It includes hydrogen-oxygen spray ring, interior
Ring air insufflation unit and outer shroud air insufflation unit, hydrogen-oxygen spray ring protrude from inner ring air insufflation unit and the spray of outer shroud air
Note unit, and in hydrogen-oxygen spray the ring end face and the igniter that protrude be generally aligned in the same plane, hydrogen-oxygen spray ring has hydrogen runner
(1), oxygen runner (2) and several towards the hydrogen spout (11) and oxygen spout (21) of igniter, inner ring air insufflation
Unit has inner ring air flow channel (8), several inner ring air ports (81), each inner ring air port be located at hydrogen spout and
The gap location of oxygen spout, outer shroud air insufflation unit has outer shroud air flow channel (3), several are outer towards Inner Wall of Combustion Chamber
Ring air port (31).
2. the head of combustion chamber of hypersonic high enthalpy ground-based simulation equipment according to claim 1, it is characterised in that：It is described
Hydrogen-oxygen spray ring is located at the central area of combustion chamber.
3. the head of combustion chamber of hypersonic high enthalpy ground-based simulation equipment according to claim 2, it is characterised in that：It is described
Igniter is placed on the center of hydrogen-oxygen spray ring.
4. the head of combustion chamber of hypersonic high enthalpy ground-based simulation equipment according to claim 3, it is characterised in that：It is described
Hydrogen spout and oxygen spout are alternately arranged.
5. the head of combustion chamber of hypersonic high enthalpy ground-based simulation equipment according to claim 4, it is characterised in that：If
In dry hydrogen spout and oxygen spout, majority is spout axis perpendicular to hydrogen-oxygen spray ring, and minority is diagonal to for spout axis
Hydrogen-oxygen spray ring.
6. the head of combustion chamber of hypersonic high enthalpy ground-based simulation equipment according to claim 5, it is characterised in that：Handing over
In the hydrogen spout and oxygen spout arranged wrongly, an adjacent hydrogen spout and an oxygen spout is one group, spout axle
Line has 8 groups perpendicular to hydrogen-oxygen spray ring, and what spout axis was diagonal to hydrogen-oxygen spray ring has 4 groups, and this 4 groups of spouts are evenly distributed
In hydrogen-oxygen spray ring.
7. the head of combustion chamber of hypersonic high enthalpy ground-based simulation equipment according to claim 6, it is characterised in that：Each
Inner ring air port is located at the gap location of every group of hydrogen spout and oxygen spout.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510209803.2A CN104848217B (en) | 2015-04-29 | 2015-04-29 | A kind of head of combustion chamber of hypersonic high enthalpy ground-based simulation equipment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510209803.2A CN104848217B (en) | 2015-04-29 | 2015-04-29 | A kind of head of combustion chamber of hypersonic high enthalpy ground-based simulation equipment |
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| Publication Number | Publication Date |
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| CN104848217A CN104848217A (en) | 2015-08-19 |
| CN104848217B true CN104848217B (en) | 2017-09-26 |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106402865B (en) * | 2016-09-29 | 2018-11-09 | 中国科学院力学研究所 | A kind of heater igniter of hypersonic high enthalpy ground-based simulation equipment |
| CN106765102A (en) * | 2016-12-08 | 2017-05-31 | 中国科学院力学研究所 | A kind of heater combustion chamber of hypersonic enthalpy ground-based simulation equipment high |
| CN108343529A (en) * | 2018-03-01 | 2018-07-31 | 中国人民解放军国防科技大学 | Gas film cooling layer plate type injector |
| CN116398326A (en) * | 2023-04-11 | 2023-07-07 | 西安航天动力研究所 | Gas generator |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN2110139U (en) * | 1991-09-17 | 1992-07-15 | 石家庄市焊割炬厂 | Three-gas flame heating apparatus spray nozzle |
| US6145299A (en) * | 1998-11-19 | 2000-11-14 | Fasano; Timothy | Rocket engine |
| US6604937B1 (en) * | 2002-05-24 | 2003-08-12 | Praxair Technology, Inc. | Coherent jet system with single ring flame envelope |
| CN102678325A (en) * | 2012-05-14 | 2012-09-19 | 华中科技大学 | Microminiature thermoelectricity generating set based on combustion |
| CN103982332B (en) * | 2014-06-06 | 2016-01-27 | 葛明龙 | A kind of rocket thrust chamber and supply system thereof switching fuel |
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