CN106134397B - A kind of torch ignitor of nitrous oxide/hydrocarbon fuel rocket engine - Google Patents
A kind of torch ignitor of nitrous oxide/hydrocarbon fuel rocket engineInfo
- Publication number
- CN106134397B CN106134397B CN201010048628.0A CN201010048628A CN106134397B CN 106134397 B CN106134397 B CN 106134397B CN 201010048628 A CN201010048628 A CN 201010048628A CN 106134397 B CN106134397 B CN 106134397B
- Authority
- CN
- China
- Prior art keywords
- nitrous oxide
- propane
- torch
- spray orifice
- solenoid valve
- 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.)
- Expired - Fee Related
Links
Landscapes
- Fuel-Injection Apparatus (AREA)
Abstract
The open one of the present invention relates to space flight propulsion system Liquid Propellant Rocket Engine field, be specially a kind of nitrous oxide and propane rocket engine torch ignitor, by nitrous oxide solenoid valve seat, igniter seat, Nitrous Oxide Catalytic Decomposition chamber, propane solenoid valve seat, external core, inner core-body, flow straightener, propane liquid collecting cavity, upstream propane spray orifice, downstream propane spray orifice, nitrous oxide liquid collecting cavity, nitrous oxide spray orifice, torch burning chamber, nitrous oxide entrance, propane entrance composition, catalytic decomposition chamber catabolite and upstream propane form one-level torch, from radially nitrous oxide and the downstream propane of spray orifice form secondary torch, start for rocket motor ignition. the present invention can obtain stable and high-octane lighting-off torch, and the rocket engine reliable ignition that can realize nitrous oxide and the combination of propane propellant starts.
Description
Technical field
The present invention relates to Liquid Propellant Rocket Engine field, being particularly related to one can be applied inThe torch ignitor of space flight propulsion system nitrous oxide/hydrocarbon fuel rocket engine.
Background technology
The combination of nitrous oxide/hydrocarbon fuel propellant has acceptable than punching performance (vacuum specific impulse280s～330s), and safe, nontoxic, can store, be the important development of nontoxic space flight Push TechnologyOne of direction. Tight security and ease for operation exist nitrous oxide/hydrocarbon fuel rocket engineThere is application prospect widely in carrier rocket, missile armament and space transport field.
Current nitrous oxide/hydrocarbon fuel engine many places are in the conceptual phase of ground experiment, pointFirearm mainly adopts electric spark direct-fire, and this sparking mode is only applicable to low thrust testPart, for the rail control engine of high thrust, directly spark ignition is difficult, and ignitingReliability is poor. For realizing the reliable point of high thrust nitrous oxide/hydrocarbon fuel rail control engineFire, and meet the requirement repeatedly starting, need to seek novel igniter design.
Summary of the invention
Problem to be solved by this invention is the reliable point of nitrous oxide/hydrocarbon fuel rail control engineFire and repeatedly ignition trigger, the present invention proposes a kind of nitrous oxide and propane rocket engine fireTorch igniter. The present invention includes nitrous oxide solenoid valve seat (1), igniter seat (2), an oxygenChange phenodiazine catalytic decomposition chamber (3), propane solenoid valve seat (4), external core (5), inner core-body (6),Flow straightener (7), propane liquid collecting cavity (8), upstream propane spray orifice (9), downstream propane spray orifice (10),Nitrous oxide liquid collecting cavity (11), nitrous oxide spray orifice (12), torch burning chamber (13),Nitrous oxide entrance (14), propane entrance (15) composition: described nitrous oxide magnetic valveSeat (1), Nitrous Oxide Catalytic Decomposition chamber (3), propane solenoid valve seat (4) are arranged on igniterSeat (2) is upper, and Nitrous Oxide Catalytic Decomposition chamber (3) are positioned at igniter seat (2) axial location,Nitrous oxide solenoid valve seat (1) and propane solenoid valve seat (4) are positioned at Nitrous Oxide Catalytic DecompositionThe both sides of chamber (3); Described nitrous oxide solenoid valve seat (1), propane solenoid valve seat (4),Igniter seat (2) has the endoporus of connection, for the circulation of nitrous oxide and propane; DescribedIt is upper that external core (5) is arranged on igniter seat (2) vertically, and external core (5) has radial direction through holeFor the circulation of nitrous oxide and propane; Described inner core-body (6) is installed on external core vertically(5), in, form propane liquid collecting cavity (8) and nitrous oxide liquid collecting cavity (11); Described inner coreBody (6) has upstream propane spray orifice (9), downstream propane spray orifice (10) of footpath, an oxidation twoNitrogen spray orifice (12); Described upstream propane spray orifice (9) is two symmetrical radially spray orifices;Described downstream propane spray orifice (10) is multiple symmetrical radially spray orifices; A described oxygenChanging phenodiazine spray orifice (12) is multiple symmetrical radially spray orifices; Described torch burning chamber (13)Be the SMIS axial cavity of inner core-body (6), the outlet of cavity is convergent nozzle; Described flow straightener(7) be installed between igniter seat (2) and inner core-body (6), flow straightener (7) has multiple axlesTo small through hole.
Adopt the present invention can obtain stable and high-octane nitrous oxide/propane torch, Neng GoushiExisting nitrous oxide/propane rocket engine reliable ignition, and meet engine and repeatedly start requirement.
Brief description of the drawings
Fig. 1 is a kind of nitrous oxide/hydrocarbon fuel rocket engine of the present invention torch ignitor schematic diagram.
Detailed description of the invention
Below in conjunction with accompanying drawing, the present invention is further detailed explanation.
Nitrous oxide and a propane rocket engine torch ignitor as shown in Figure 1, by oneNitrous oxide solenoid valve seat (1), igniter seat (2), Nitrous Oxide Catalytic Decomposition chamber (3), thirdAlkane solenoid valve seat (4), external core (5), inner core-body (6), flow straightener (7), propane liquid collecting cavity (8),Upstream propane spray orifice (9), downstream propane spray orifice (10), nitrous oxide liquid collecting cavity (11),Nitrous oxide spray orifice (12), torch burning chamber (13), nitrous oxide entrance (14), thirdAlkane entrance (15) composition: the nitrous oxide by Nitrous Oxide Catalytic Decomposition chamber (3) is urgedChange and decompose, catabolite is the hot mixture of nitrogen and oxygen, passes through Nitrous Oxide Catalytic DecompositionThe nitrous oxide mass flow of chamber (3) is 1.5 Grams Per Seconds, and high-temperature decomposition product is by flow straightener (7)Axial aperture enter torch burning chamber (13), high-temperature decomposition product by after flow straightener (7) by allEven dispersion, strengthens the mixed effect with fuel; Propane enters and flows into propane by propane entrance (15)Liquid collecting cavity (8), propane spray orifice is divided into upstream propane spray orifice (9) and downstream propane spray orifice (10)Two groups, distribute two groups of spray orifice flows by spray orifice quantity and aperture, total by upstream spray orificeFlow is 0.1 Grams Per Second～0.15 Grams Per Second, the propane by upstream propane spray orifice (9) with pass throughThe nitrous oxide high-temperature catalytic catabolite that flow straightener (7) enters into torch burning chamber (13) mixesCombination burning forms one-level torch, and the mixing ratio 10～15 in one-level torch burning region, is oxygen-enriched combusting,The temperature of Nitrous Oxide Catalytic Decomposition product is not because the vaporization heat absorption of propane is reduced to mixture combustionBelow point; Nitrous oxide enters and flows into nitrous oxide liquid collecting from nitrous oxide entrance (14)Chamber (11), enters torch burning chamber by equally distributed radially nitrous oxide spray orifice (12)(13), and mix by the propane of downstream propane spray orifice (10), mixture is by one-level torch pointFire and form secondary torch, the mixing ratio 3～5 in secondary torch burning region, flow is that engine is total0.5%～1.0% of flow, secondary torch is fuel-rich torch, sends out for nitrous oxide/propane rocketMotivation ignition trigger.
Claims (4)
1. nitrous oxide and a propane rocket engine torch ignitor, is characterized in that,By nitrous oxide solenoid valve seat (1), igniter seat (2), Nitrous Oxide Catalytic Decomposition chamber (3),Propane solenoid valve seat (4), external core (5), inner core-body (6), flow straightener (7), propane liquid collecting cavity(8), upstream propane spray orifice (9), downstream propane spray orifice (10), nitrous oxide liquid collecting cavity(11), nitrous oxide spray orifice (12), torch burning chamber (13), nitrous oxide entrance (14),Propane entrance (15) composition: described nitrous oxide solenoid valve seat (1), Nitrous Oxide CatalyticIt is upper that decomposition chamber (3), propane solenoid valve seat (4) are arranged on igniter seat (2), and nitrous oxide is urgedChange decomposition chamber (3) and be positioned at igniter seat (2) axial location, nitrous oxide solenoid valve seat (1)Be positioned at the both sides of Nitrous Oxide Catalytic Decomposition chamber (3) with propane solenoid valve seat (4); Described oneNitrous oxide solenoid valve seat (1), propane solenoid valve seat (4), igniter seat (2) have connectionEndoporus, for the circulation of nitrous oxide and propane; Described external core (5) is arranged on verticallyIgniter seat (2) is upper, and external core (5) has the stream of radial direction through hole for nitrous oxide and propaneLogical; Described inner core-body (6) is installed in external core (5) vertically, forms propane liquid collecting cavity (8)With nitrous oxide liquid collecting cavity (11); Described inner core-body (6) has upstream propane spray orifice of footpath(9), downstream propane spray orifice (10), nitrous oxide spray orifice (12); Described upstream propaneSpray orifice (9) is two symmetrical radially spray orifices; Described downstream propane spray orifice (10) isMultiple symmetrical radially spray orifices; Described nitrous oxide spray orifice (12) is multiple symmetriesThe radially spray orifice distributing; Described torch burning chamber (13) is that the SMIS of inner core-body (6) is axialCavity, the outlet of cavity is convergent nozzle; Described flow straightener (7) is installed on igniter seat (2)And between inner core-body (6), flow straightener (7) has multiple axial small through hole.
2. a kind of nitrous oxide according to claim 1 and propane rocket engine torch pointFire device, is characterized in that, Nitrous Oxide Catalytic Decomposition chamber (3) catalytic decomposition nitrous oxide,Catabolite provides torch primary power.
3. a kind of nitrous oxide according to claim 1 and propane rocket engine torch pointFire device, is characterized in that, inner core-body (6) can distribute upstream and downstream, torch burning chamber (13)Propane flow, and adjust upstream and downstream, torch burning chamber mixing ratio.
4. a kind of nitrous oxide according to claim 1 and propane rocket engine torch pointFire device, it is characterized in that, torch ignitor is divided into I and II two-stage torch, one-level torch byNitrous Oxide Catalytic Decomposition product and upstream propane mixed combustion obtain.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201010048628.0A CN106134397B (en) | 2010-05-14 | 2010-05-14 | A kind of torch ignitor of nitrous oxide/hydrocarbon fuel rocket engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201010048628.0A CN106134397B (en) | 2010-05-14 | 2010-05-14 | A kind of torch ignitor of nitrous oxide/hydrocarbon fuel rocket engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106134397B true CN106134397B (en) | 2013-12-18 |
Family
ID=57251096
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201010048628.0A Expired - Fee Related CN106134397B (en) | 2010-05-14 | 2010-05-14 | A kind of torch ignitor of nitrous oxide/hydrocarbon fuel rocket engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106134397B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109184956A (en) * | 2018-09-21 | 2019-01-11 | 同济大学 | A kind of high-pressure gaseous hydrogen-oxygen jet engine device |
| CN109386400A (en) * | 2018-12-07 | 2019-02-26 | 上海空间推进研究所 | A kind of laser torch lighter for liquid oxygen/methane engine |
| CN109595097A (en) * | 2018-10-29 | 2019-04-09 | 上海空间推进研究所 | Using the liquid oxygen and methane engine and control method of inserted valve |
-
2010
- 2010-05-14 CN CN201010048628.0A patent/CN106134397B/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109184956A (en) * | 2018-09-21 | 2019-01-11 | 同济大学 | A kind of high-pressure gaseous hydrogen-oxygen jet engine device |
| CN109184956B (en) * | 2018-09-21 | 2024-04-09 | 同济大学 | High-pressure gaseous hydrogen-oxygen jet engine device |
| CN109595097A (en) * | 2018-10-29 | 2019-04-09 | 上海空间推进研究所 | Using the liquid oxygen and methane engine and control method of inserted valve |
| CN109386400A (en) * | 2018-12-07 | 2019-02-26 | 上海空间推进研究所 | A kind of laser torch lighter for liquid oxygen/methane engine |
| CN109386400B (en) * | 2018-12-07 | 2021-01-12 | 上海空间推进研究所 | Laser torch igniter for liquid oxygen/methane engine |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR03 | Grant of secret patent right | ||
| GRSP | Grant of secret patent right | ||
| DC01 | Secret patent status has been lifted | ||
| DCSP | Declassification of secret patent | ||
| 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: 20131218 Termination date: 20210514 |