http://rdf.ncbi.nlm.nih.gov/pubchem/patent/CA-2680634-C

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filingDate 2009-09-24-04:00^^<http://www.w3.org/2001/XMLSchema#date>
grantDate 2014-01-28-04:00^^<http://www.w3.org/2001/XMLSchema#date>
inventor http://rdf.ncbi.nlm.nih.gov/pubchem/patentinventor/MD5_837a2dec0f243800cfd2db58e08b95e1
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publicationDate 2014-01-28-04:00^^<http://www.w3.org/2001/XMLSchema#date>
publicationNumber CA-2680634-C
titleOfInvention Turbine frame assembly and method for a gas turbine engine
abstract A turbine frame assembly for a gas turbine engine includes: (a) a turbine frame (38) including: (i) an outer ring (48); (ii) a hub (42); (iii) a plurality of struts (54) extending between the hub (42) and the outer ring (48); (b) a two-piece strut fairing (72) surrounding each of the struts (54), including: (i) an inner band; (ii) an outer band; and (iii) an airfoil-shaped vane extending between the inner and outer bands; (c) a plurality of nozzle segments disposed between the outer ring (48) and the hub (42), each nozzle segment being an integral metallic casting including: (i) an arcuate outer band; (ii) an arcuate inner band; and (iii) an airfoil-shaped vane.
priorityDate 2008-11-29-04:00^^<http://www.w3.org/2001/XMLSchema#date>
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Total number of triples: 22.