RAFAEL ALVES DE LIMA
Pilots at Kirkman Rd, Orlando, FL
License number
Florida C1043663
Issued Date
Oct 2016
Expiration Date
Oct 2017
Category
Airmen
Address
Address
1617 S Kirkman Rd APT 1202, Orlando, FL 32811
Professional information
Turbine Blade Self Locking Seal Plate System
US Patent:
7500832, Mar 10, 2009
Filed:
Jul 6, 2006
Appl. No.:
11/481722
Inventors:
Thomas W. Zagar - Winter Springs FL, US
Rafael A. De Cardenas - Orlando FL, US
Rafael A. De Cardenas - Orlando FL, US
Assignee:
Siemens Energy, Inc. - Orlando FL
International Classification:
F01D 5/32
US Classification:
416221, 416 96 R, 416220 R
Abstract:
A seal plate system () for a rotor in a turbine engine. The rotor includes a rotor disc () for supporting a plurality of blades (), and an annular groove () provided in the disc () adjacent at least one end () of the disc (). A plurality of plate structures () are provided supported between the annular groove () of the disc () and a groove () formed in a platform () of the blade () adjacent an end () of the disc (). The plate structure () includes a plate () and an elongated resilient locking pointer () extending from the plate () for engaging in a lock notch () formed in an outer wall () of the annular groove (). The locking pointer () forms a self-locking feature that is biased into the lock notch () as the plate structure () is moved into position on the disc ().
Turbine Airfoil Cooling System With Rotor Impingement Cooling
US Patent:
8128365, Mar 6, 2012
Filed:
Jul 9, 2007
Appl. No.:
11/825690
Inventors:
Rafael A. De Cardenas - Orlando FL, US
Assignee:
Siemens Energy, Inc. - Orlando FL
International Classification:
F01D 5/08
US Classification:
416 96R, 416193 A
Abstract:
A turbine airfoil cooling system of a turbine engine having a hollow, disc post body positioned between adjacent roots of turbine airfoils and aligned with the roots to cool inner aspects of the turbine engine. The hollow, disc post body may be configured to pass cooling fluids through impingement orifices in the hollow, disc post body to impinge on inner surfaces of platforms of the turbine airfoils. The cooling fluids may then be directed to the internal cooling systems of the turbine airfoils rather than being discharged as film cooling fluids through the platforms of the turbine airfoils.