US 12,435,635 B2
Turbine component for gas turbine engine
Philipp Cavadini, Berlin (DE)
Assigned to SIEMENS ENERGY GLOBAL GMBH & CO. KG, Munich (DE)
Filed by Siemens Energy Global GmbH & Co. KG, Munich (DE)
Filed on Aug. 23, 2024, as Appl. No. 18/813,053.
Claims priority of application No. 2313562 (GB), filed on Sep. 6, 2023.
Prior Publication US 2025/0075624 A1, Mar. 6, 2025
Int. Cl. F01D 5/18 (2006.01); F01D 5/14 (2006.01); F01D 9/04 (2006.01)
CPC F01D 5/18 (2013.01) [F05D 2230/50 (2013.01); F05D 2260/20 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A turbine component comprising:
an inner platform having an inner platform cooling passage;
an outer platform;
an airfoil extending between the inner platform and the outer platform, the airfoil having a pressure side wall, a suction side wall, a leading edge, a trailing edge, a leading edge region, a trailing edge region, and a middle region defined between the leading edge region and the trailing edge region;
a leading edge rib positioned in the leading edge region and between the pressure side wall and the suction side wall, a plurality of leading edge rib openings formed in the leading edge rib, each leading edge rib opening positioned nearer to one of the pressure side wall and the suction side wall than the other of the pressure side wall and the suction side wall;
a rear rib positioned in the trailing edge region and between the pressure side wall and the suction side wall;
a first cooling path extending from a flow inlet formed in one of the inner platform and the outer platform, through the leading edge region, through the inner platform cooling passage, and into the trailing edge region; and
a second cooling path extending from the flow inlet, through the middle region, and into the trailing edge region.