CN205560841U - Dedicated spacecraft combustion chamber of aerospace - Google Patents
Dedicated spacecraft combustion chamber of aerospace Download PDFInfo
- Publication number
- CN205560841U CN205560841U CN201620266386.5U CN201620266386U CN205560841U CN 205560841 U CN205560841 U CN 205560841U CN 201620266386 U CN201620266386 U CN 201620266386U CN 205560841 U CN205560841 U CN 205560841U
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- Prior art keywords
- combustor
- fuel
- combustion chamber
- spacecraft
- outer casing
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Abstract
The utility model discloses a dedicated spacecraft combustion chamber of aerospace, including shell body, fuel entry, combustion chamber and turbopump, the top at first support frame is installed to the combustion chamber, the surface of combustion chamber shell is provided with electronic heat sink, the right side of nozzle is provided with the swirler, the top in the combustion chamber is installed to the fuel entry. Compared with the prior art, the beneficial effects of the utility model are that: the utility model relates to a dedicated spacecraft combustion chamber of aerospace structure scientific and reasonable, the operation is safe convenient, is provided with electronic heat sink on the surface of combustion chamber shell, can leave the inside waste heat that produces of engine combustion chamber during operation through using electronic heat sink, can protect the combustion chamber shell like this, and be provided with the turbopump in the top of combustion chamber, can go into the combustion chamber with the convenient conveying of fuel through the turbopump pressure boost inside, simple and practical.
Description
Technical field
This utility model relates to field of aerospace technology, the spacecraft combustor that a kind of Aero-Space are special.
Background technology
Combustor is that fuel or propellant burn wherein and generate the device of high-temperature fuel gas.It is the vitals of gas-turbine unit, punching engine, rocket engine.
Vane type typically made by the swirler of combustor, and it makes air-flow direction on request flow, and is beneficial to igniting and burning, and makes burning be continued.Igniter only works when electromotor starts, and after once fuel-air mixture is lighted, i.e. quits work.Nozzle is used for minimum oil droplet, fuel (aerial kerosene) is sprayed into burner inner liner, and making fuel can quickly evaporate after heat absorption becomes oil gas, forms the most incendive combustion mixture with air.Conventional nozzle has swirl atomizer, evaporation nozzle, air-blast atomizer etc..In some put-puts, the disc of high speed rotating is also used to get rid of fuel oil into combustor.Burner inner liner is the place that fuel-air mixture carries out burning.Here temperature is the highest, and the general strip using resistant to elevated temperatures nickel-base alloy plate or cold rolling molding is welded, and also has and uses forging machining.Burner inner liner typically uses gaseous film control mode to reduce barrel temperature.
The combustor of existing spacecraft electromotor also exists some problems during using, such as, substantial amounts of steam can be produced the when of the work of spacecraft electromotor, thermal current ejection produces power and drives spacecraft flight, but still can remain substantial amounts of steam in the combustor of electromotor, steam too much can destroy combustor outer casing, and the electromotor of existing liquid fuel is also not provided with heat dissipation equipment, so it is proposed that the special spacecraft combustor of a kind of Aero-Space that can distribute heat.
Utility model content
The purpose of this utility model is the spacecraft combustor providing a kind of Aero-Space special, the problem that can destroy combustor outer casing with the residual steam solving to propose in above-mentioned background technology.
nullFor achieving the above object，This utility model following technical scheme of offer: the spacecraft combustor that a kind of Aero-Space are special，Including shell body、Fuel inlet、Combustor and turbine pump，Described shell body be internally provided with the first bracing frame，Described combustor is arranged on the top of the first bracing frame，And combustor be internally provided with combustor outer casing，The surface configuration of described combustor outer casing has electronic heat sink，And the surface configuration of combustor outer casing has air inlet，Described combustor outer casing be internally provided with nozzle，The right side of described nozzle is provided with swirler，The left side of described combustor is provided with primary air inlet，And the surface configuration of combustor has protective jacket，The right side of described combustor is provided with sealing ring，The right side of described sealing ring is provided with air stream outlet，Described fuel inlet is arranged on the top of combustor，And the right side of fuel inlet is provided with igniter，Described fuel inlet be provided above fuel access tube，Described turbine pump is arranged on the right side of fuel access tube，And turbine pump is provided above turbine pump support，Described fuel access tube be provided above fuel cassette，Described fuel cassette be provided above the second bracing frame，Described electronic heat sink and turbine pump are all electrically connected with external control panel.
Preferably, described first bracing frame is provided with four altogether, and four the first bracing frames are separately mounted to the lower section of combustor.
Preferably, described electronic heat sink is provided with two altogether, and two electronic heat sinks are separately mounted to the surface of combustor outer casing.
Preferably, described nozzle is provided with two altogether, and two nozzles are separately mounted to the right side of fuel inlet.
Preferably, described swirler is provided with two altogether, and two swirlers are separately mounted to the right side of nozzle.
Compared with prior art; the beneficial effects of the utility model are: the special spacecraft chamber structure of a kind of Aero-Space of this utility model is scientific and reasonable; easy-to-operate; surface configuration at combustor outer casing has electronic heat sink; during by using electronic heat sink to be worked by engine chamber, the internal waste heat produced disperses, and so can protect combustor outer casing；And it is provided above turbine pump at combustor, by turbine pump supercharging, fuel can be transmitted easily into combustion chamber, simple and practical.
Accompanying drawing explanation
Fig. 1 is structural representation of the present utility model；
In figure: 1-shell body, 2-fuel access tube, 3-fuel inlet, 4-combustor, 5-combustor outer casing, 6-primary air inlet, 7-the first bracing frame, 8-nozzle, 9-swirler, 10-electronic heat sink, 11-protective jacket, 12-air stream outlet, 13-air inlet, 14-sealing ring, 15-igniter, 16-the second bracing frame, 17-turbine pump, 18-turbine pump support, 19-fuel cassette.
Detailed description of the invention
Below in conjunction with the accompanying drawing in this utility model embodiment, the technical scheme in this utility model embodiment is clearly and completely described, it is clear that described embodiment is only a part of embodiment of this utility model rather than whole embodiments.Based on the embodiment in this utility model, the every other embodiment that those of ordinary skill in the art are obtained under not making creative work premise, broadly fall into the scope of this utility model protection.
nullRefer to Fig. 1，The spacecraft Combustor Technologies scheme that a kind of Aero-Space of this utility model offer are special: the spacecraft combustor that a kind of Aero-Space are special，Including shell body 1、Fuel inlet 3、Combustor 4 and turbine pump 17，Shell body 1 be internally provided with the first bracing frame 7，Combustor 4 is arranged on the top of the first bracing frame 7，And combustor 4 be internally provided with combustor outer casing 5，The surface configuration of combustor outer casing 5 has electronic heat sink 10，And the surface configuration of combustor outer casing 5 has air inlet 13，Combustor outer casing 5 be internally provided with nozzle 8，The right side of nozzle 8 is provided with swirler 9，The left side of combustor 4 is provided with primary air inlet 6，And the surface configuration of combustor 4 has protective jacket 11，The right side of combustor 4 is provided with sealing ring 14，The right side of sealing ring 14 is provided with air stream outlet 12，Fuel inlet 3 is arranged on the top of combustor 4，And the right side of fuel inlet 3 is provided with igniter 15，Fuel inlet 3 be provided above fuel access tube 2，Turbine pump 17 is arranged on the right side of fuel access tube 2，And turbine pump 17 is provided above turbine pump support 18，Fuel access tube 2 be provided above fuel cassette 19，Fuel cassette 19 be provided above the second bracing frame 16，Electronic heat sink 10 and turbine pump 17 are all electrically connected with external control panel.
First bracing frame 7 is provided with four altogether, and four the first bracing frames 7 are separately mounted to the lower section of combustor 4.Electronic heat sink 10 is provided with two altogether, and two electronic heat sinks 10 are separately mounted to the surface of combustor outer casing 5.Nozzle 8 is provided with two altogether, and two nozzles 8 are separately mounted to the right side of fuel inlet 3.Swirler 9 is provided with two altogether, and two swirlers 9 are separately mounted to the right side of nozzle 8.
Operation principle: after this utility model installs, connect external power source, by using turbine pump 17 supercharging to be sent at fuel inlet 3 by the fuel within fuel cassette 19 by fuel access tube 2, then fuel enters the inside of combustor 4 by nozzle 8 and swirler 9, air enters the inside of combustor 4 at primary air inlet 6 simultaneously, the thermal current that combustor 4 work of electromotor produces sprays at air stream outlet 12, and the waste heat in combustor 4 is then dispelled the heat by the electronic heat sink 10 on the surface of combustor outer casing 5.
Embodiment the most of the present utility model, for the ordinary skill in the art, being appreciated that in the case of without departing from principle of the present utility model and spirit and these embodiments can carry out multiple change, revise, replace and modification, scope of the present utility model is defined by the appended claims and the equivalents thereof.
Claims (5)
- null1. the spacecraft combustor that Aero-Space are special，Including shell body (1)、Fuel inlet (3)、Combustor (4) and turbine pump (17)，It is characterized in that: described shell body (1) be internally provided with the first bracing frame (7)，Described combustor (4) is arranged on the top of the first bracing frame (7)，And combustor (4) be internally provided with combustor outer casing (5)，The surface configuration of described combustor outer casing (5) has electronic heat sink (10)，And the surface configuration of combustor outer casing (5) has air inlet (13)，Described combustor outer casing (5) be internally provided with nozzle (8)，The right side of described nozzle (8) is provided with swirler (9)，The left side of described combustor (4) is provided with primary air inlet (6)，And the surface configuration of combustor (4) has protective jacket (11)，The right side of described combustor (4) is provided with sealing ring (14)，The right side of described sealing ring (14) is provided with air stream outlet (12)，Described fuel inlet (3) is arranged on the top of combustor (4)，And the right side of fuel inlet (3) is provided with igniter (15)，Described fuel inlet (3) be provided above fuel access tube (2)，Described turbine pump (17) is arranged on the right side of fuel access tube (2)，And turbine pump (17) is provided above turbine pump support (18)，Described fuel access tube (2) be provided above fuel cassette (19)，Described fuel cassette (19) be provided above the second bracing frame (16)，Described electronic heat sink (10) and turbine pump (17) are all electrically connected with external control panel.
- The spacecraft combustor that a kind of Aero-Space the most according to claim 1 are special, it is characterised in that: described first bracing frame (7) is provided with four altogether, and four the first bracing frames (7) are separately mounted to the lower section of combustor (4).
- The spacecraft combustor that a kind of Aero-Space the most according to claim 1 are special, it is characterised in that: described electronic heat sink (10) is provided with two altogether, and two electronic heat sinks (10) are separately mounted to the surface of combustor outer casing (5).
- The spacecraft combustor that a kind of Aero-Space the most according to claim 1 are special, it is characterised in that: described nozzle (8) is provided with two altogether, and two nozzles (8) are separately mounted to the right side of fuel inlet (3).
- The spacecraft combustor that a kind of Aero-Space the most according to claim 1 are special, it is characterised in that: described swirler (9) is provided with two altogether, and two swirlers (9) are separately mounted to the right side of nozzle (8).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620266386.5U CN205560841U (en) | 2016-04-04 | 2016-04-04 | Dedicated spacecraft combustion chamber of aerospace |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620266386.5U CN205560841U (en) | 2016-04-04 | 2016-04-04 | Dedicated spacecraft combustion chamber of aerospace |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205560841U true CN205560841U (en) | 2016-09-07 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620266386.5U Expired - Fee Related CN205560841U (en) | 2016-04-04 | 2016-04-04 | Dedicated spacecraft combustion chamber of aerospace |
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| Country | Link |
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| CN (1) | CN205560841U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107587943A (en) * | 2017-08-31 | 2018-01-16 | 贵州航天朝阳科技有限责任公司 | A kind of sway in both directions mechanism for airspace engine |
-
2016
- 2016-04-04 CN CN201620266386.5U patent/CN205560841U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107587943A (en) * | 2017-08-31 | 2018-01-16 | 贵州航天朝阳科技有限责任公司 | A kind of sway in both directions mechanism for airspace engine |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160907 Termination date: 20170404 |