US 11,655,716 B2
Cooling structure for trailing edge of turbine blade
Chang Yong Lee, Sejong (KR); Hyung Hee Cho, Seoul (KR); JeongJu Kim, Seongnam (KR); Seungyeong Choi, Seoul (KR); and Hee Seung Park, Seoul (KR)
Assigned to DOOSAN ENERBILITY CO., LTD., Changwon (KR)
Filed by DOOSAN ENERBILITY CO., LTD., Changwon (KR)
Filed on Jul. 21, 2021, as Appl. No. 17/381,313.
Claims priority of application No. 10-2020-0137964 (KR), filed on Oct. 23, 2020.
Prior Publication US 2022/0127964 A1, Apr. 28, 2022
Int. Cl. F01D 5/18 (2006.01)
CPC F01D 5/186 (2013.01) [F05D 2220/32 (2013.01); F05D 2240/24 (2013.01); F05D 2240/304 (2013.01); F05D 2260/202 (2013.01); F05D 2260/22141 (2013.01)] 18 Claims
OG exemplary drawing
 
1. A cooling structure comprising:
an airfoil shaped blade part including a leading edge, a trailing edge, a pressure surface and a suction surface connecting the leading edge and the trailing edge,
a cavity channel formed in the blade part and through which a cooling fluid flows,
slots and lands arranged alternately on the trailing edge along a span direction of the pressure surface by cutting a portion of the pressure surface, the slots communicating with the cavity channel and defined by adjacent lands where the pressure surface remains,
wherein a pin-fin structure is disposed in the cavity channel on an upstream side of the slot,
wherein the cooling fluid is introduced through a micro channel formed inside the pin-fin structure and is discharged through film cooling holes formed in the pressure surface,
wherein an impingement jet space is formed inside the pressure surface connecting the micro-channel in the pin-fin structure and the film cooling holes, and
wherein a cross-sectional area of the impingement jet space decreases from a closed upstream end to a downstream end.