US 9,810,151 B2
Turbine last stage rotor blade with forced driven cooling air
Joseph D Brostmeyer, Jupiter, FL (US)
Assigned to Florida Turbine Technologies, Inc., Jupiter, FL (US)
Filed by Joseph D Brostmeyer, Jupiter, FL (US)
Filed on Oct. 10, 2014, as Appl. No. 14/512,070.
Claims priority of provisional application 61/869,675, filed on Aug. 24, 2013.
Prior Publication US 2016/0195018 A1, Jul. 7, 2016
Int. Cl. F02C 7/18 (2006.01); F01D 5/08 (2006.01)
CPC F02C 7/18 (2013.01) [F01D 5/082 (2013.01); F05D 2220/3215 (2013.01); F05D 2260/20 (2013.01)] 3 Claims
OG exemplary drawing
 
1. A gas turbine engine comprising:
a turbine with a rotor and a stator;
a turbine rotor blade extending from the rotor;
a centrifugal impeller rotatably connected to the rotor;
a rim cavity formed between the rotor and the stator;
a seal formed between the rotor and the stator to form a seal between the rim cavity and a hot gas path through the turbine;
a cooling air channel formed in the rotor and the turbine rotor blade with an opening into the rim cavity;
the centrifugal impeller located on the rotor such that rotation of the rotor and centrifugal impeller discharges pressurized cooling air into the rim cavity and then through the cooling air channel formed in the rotor and turbine rotor blade; and,
the centrifugal impeller having an axial inlet and a radial outlet.