| Predicate |
Object |
| assignee |
http://rdf.ncbi.nlm.nih.gov/pubchem/patentassignee/MD5_c72d118f5664072de841f9c5c34b9d99 |
| classificationCPCAdditional |
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/B64D2013-0696
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/B64D2013-0648
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/Y02T50-50
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/Y02T50-10
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/Y02T50-60
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/B64D2013-0622
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/B64D2013-0659 |
| classificationCPCInventive |
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/B64D13-06
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02C6-08
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02C7-32
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/B64C21-00
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02C7-277 |
| classificationIPCInventive |
http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/F02C6-08
http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/B64D13-06
http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/B64C21-00
http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/B64C21-02
http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/B64D13-08
http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/B64C21-06
http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/F02C7-32
http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/F02C7-277
http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/F02C9-18
http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/B64D31-02 |
| filingDate |
1991-05-09-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| inventor |
http://rdf.ncbi.nlm.nih.gov/pubchem/patentinventor/MD5_b974399f0716e40d169350ee356c496a |
| publicationDate |
1991-12-02-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| publicationNumber |
CA-2042201-A1 |
| titleOfInvention |
Gas turbine engine powered aircraft environmental control system and boundary layer bleed |
| abstract |
Patent, ABSTRACT An aircraft gas turbine engine is provided with a starting air turbine that is directly connected through the starter gearbox to the high pressure (HP) shaft and is provided with a means to extract excess energy from engine compressor bleed air, return it to the engine, and to start the engine with compressed air from starting air sources, and to cool and provide compressed air for powering the Environmental Control System (ECS) and using the bleed air for cabin refreshening. The air turbine may be connected to a nacelle boundary layer bleed compressor to bleed boundary layer air from a forward portion of the nacelle to reduce nacelle surface drag. The ECS may be provided with a wing boundary layer bleed means which uses a cooling air fan in the ECS to draw cooling air through the heat exchangers in the ECS pack from the boundary layer air from a forward portion of the aircraft's wing to reduce its surface drag. |
| priorityDate |
1990-06-01-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| type |
http://data.epo.org/linked-data/def/patent/Publication |