http://rdf.ncbi.nlm.nih.gov/pubchem/patent/US-6138450-A

Outgoing Links

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classificationCPCInventive http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02K9-62
classificationIPCInventive http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/F02K9-62
filingDate 1998-05-11-04:00^^<http://www.w3.org/2001/XMLSchema#date>
grantDate 2000-10-31-04:00^^<http://www.w3.org/2001/XMLSchema#date>
inventor http://rdf.ncbi.nlm.nih.gov/pubchem/patentinventor/MD5_1f217536e4f71e7eda3db4e8ab00ef88
http://rdf.ncbi.nlm.nih.gov/pubchem/patentinventor/MD5_a556f47324caf0e892f0feb1de2d40d3
publicationDate 2000-10-31-04:00^^<http://www.w3.org/2001/XMLSchema#date>
publicationNumber US-6138450-A
titleOfInvention Rocket engine with integral combustion chamber step structure and its fabrication
abstract A rocket engine is prepared by fabricating a combustion chamber having an annular wall as a single piece of material. The wall has a first axial region with a first inner diameter, a second axial region with a second inner diameter greater than the first inner diameter, and an inner wall step transition between the first axial region and the second axial region. The combustion chamber is attached to an injector by bonding an annular metallic deposit to the first axial region of the combustion chamber, providing an annular adaptor ring, first welding the adaptor ring to the metallic deposit, and second welding the adaptor ring to the injector.
isCitedBy http://rdf.ncbi.nlm.nih.gov/pubchem/patent/US-6705076-B1
http://rdf.ncbi.nlm.nih.gov/pubchem/patent/US-6588199-B2
http://rdf.ncbi.nlm.nih.gov/pubchem/patent/US-9404441-B2
http://rdf.ncbi.nlm.nih.gov/pubchem/patent/US-2010037590-A1
http://rdf.ncbi.nlm.nih.gov/pubchem/patent/US-6397580-B1
http://rdf.ncbi.nlm.nih.gov/pubchem/patent/US-6269630-B1
http://rdf.ncbi.nlm.nih.gov/pubchem/patent/US-6381949-B1
priorityDate 1998-05-11-04:00^^<http://www.w3.org/2001/XMLSchema#date>
type http://data.epo.org/linked-data/def/patent/Publication

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Total number of triples: 26.