HIGH-PRESSURE TURBINE BLADE WITH COOLING AIR OUTLET PORTS, BLADE FORMING ELEMENT, TURBINE AND GUIDE-VANE ASSEMBLY OF TURBOMACHINE Russian patent published in 2007 - IPC F01D5/18 

FIELD: mechanical engineering; turbines.

SUBSTANCE: turbine blade of turbomachine, working or nozzle one, has feather arranged in radial direction between root and end face of blade, and in axial direction between its leading edge and trailing edge, at least one lower flange connected with root of blade by connecting zone, and cooling circuit. Cooling circuit consists of at least one space arranged in radial direction between end face and root of blade, at least one air admission port arranged in radial direction at end of one of spaces, and several air outlet ports arranged along blade trailing edge. Lower air outlet port is located near blade root and it has side wall with hole communicating with said space or with spaces, deepened wall, lower wall arranged from side of blade root, lower butt formed between deepened wall and lower wall, lower rib formed between lower wall and connecting zone. Lower butt and lower rib of lower air outlet port have rounded off cross section with no projecting angles between hole of lower port and connecting zone. Forming element has main part designed for forming blade cooling space with flat projections for forming air admission ports. Lower projections has form reverse to form of lower port.

EFFECT: prevention of formation of cracks, provision of cooling of zone of blade flange-to-feather connection.

13 cl, 7 dwg