Patent ID: 11873733
Assignee: SIEMENS ENERGY GLOBAL GMBH & CO. KG
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 0:
1. A turbine blade in a gas turbine engine, the turbine blade comprising: a root; a platform coupled to the root; an airfoil extending from the platform to a tip surface in a radial direction, the airfoil comprising an outer wall delimiting an airfoil interior, the outer wall comprising a pressure sidewall and a suction sidewall joined at a leading edge and a trailing edge in a longitudinal direction; a first partition wall positioned in the airfoil interior and coupled to the pressure sidewall and the suction sidewall; a second partition wall positioned in the airfoil interior and coupled to the pressure sidewall and the suction sidewall, the second partition wall spaced apart from the first partition wall, a cooling cavity being defined by the pressure sidewall, the suction sidewall, the first partition wall, and the second partition wall; a flow blocking body disposed in the cooling cavity; a first strut coupling the flow blocking body to the pressure sidewall; a second strut coupling the flow blocking body to the suction sidewall, a cooling channel being defined by the pressure sidewall, the suction sidewall, the first partition wall, the flow blocking body, the first strut, and the second strut; and a turbulator disposed in the cooling channel, the turbulator comprising a first row including at least two turbulator ribs spaced apart in the longitudinal direction, the turbulator comprising a second row extending in the radial direction from the first row and including at least two turbulator ribs spaced apart in the longitudinal direction;
wherein the at least two turbulator ribs of the first row bisect to the at least two turbulator ribs of the second row.