http://rdf.ncbi.nlm.nih.gov/pubchem/patent/GB-1015060-A
Outgoing Links
| Predicate | Object |
|---|---|
| assignee | http://rdf.ncbi.nlm.nih.gov/pubchem/patentassignee/MD5_e71ceee88045962115ff1db837e14116 |
| classificationCPCInventive | http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02K9-70 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/C06D5-00 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/C06B23-001 |
| classificationIPCInventive | http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/F02K9-70 http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/C06B23-00 http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/C06D5-00 |
| filingDate | 1962-11-05-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| publicationDate | 1965-12-31-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| publicationNumber | GB-1015060-A |
| titleOfInvention | Gas generator |
| abstract | 1,015,060. Rocket motors. ATLANTIC RESEARCH CORPORATION. Nov. 5, 1962 [Nov. 7, 1961], No. 41842/62. Heading F3A. [Also in Division F1] A combustion gas generator for use as a rocket motor burning an extrudible paste-like fuel which is fluid under stress at ambient temperatures comprises an extrusion member having at least one passage through which the fuel is extruded, means associated with the passage for dividing the fuel into a particulate spray, and a combustion chamber positioned downstream of the extrusion member in which the fuel spray is burned. As shown in Fig. 1, a piston 12 mounted in the forward end of a storage chamber 10 extrudes monopropellant 11 through an extrusion member 13 into a combustion chamber 14. The extrusion member 13, shown in detail in Figs. 2 and 4, has seven orifices 27 for positioning nozzle assemblies which have at their upstream ends retainer sections 28 each having a passageway in the form of a truncated cone 29 through which the propellant 11 is extruded. Swirl vanes 30 mounted in the cones 29 cause rotation of the propellant 11. Pressurized inert gas, such as nitrogen, is admitted into taps 21 and passes to a peripheral slot 22 in the extrusion member 13, from where it proceeds into passageways 23, 32 and 33 before being divided into two flows. The first or primary flow is directed into slots 36 tangential to vortex chambers 37 where it contacts the swirling propellant 11 leaving the cones 29 and prevents it from adhering to or clogging the sides of the chambers. The primary flow also imparts further rotational movement to the propellant 11 which begins to break up. The secondary flow is directed down passages 39 and out through openings 42 to atomize the propellant 11 emerging from the vortex chambers 37. The spray cone formed by the atomized propellant 11 can be varied by regulating the pressure of the gas admitted to the taps 21 and by varying the extrusion rate of the propellant 11. The secondary flow serves the additional function of blocking any burn-back of the flame in the combustion chamber 14 into the vortex chambers 37. Both primary and coolant flows also function as a coolant for the propellant 11 and extrusion member 13 to reduce the danger of auto-ignition of the upstream portion of the extruding propellant because of heat transfer and additionally protect the nozzle structure. The invention is not limited to using a monopropellant but can be used in a bipropellant system requiring only the substitution of an oxidizer such as oxygen or air for the inert gas. |
| priorityDate | 1961-11-07-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| type | http://data.epo.org/linked-data/def/patent/Publication |
Incoming Links
Total number of triples: 20.