US 11,788,418 B2
Gas turbine vane and assembly in lattice-structure cooling type
Hyung Hee Cho, Seoul (KR); Ho Seop Song, Seoul (KR); Minho Bang, Gimpo-si (KR); Heeseung Park, Seoul (KR); Taehyun Kim, Suwon-si (KR); Seungyeong Choi, Seoul (KR); and Jeong Ju Kim, Seoul (KR)
Assigned to Industry-Academic Cooperation Foundation, Yonsei University, Seoul (KR)
Filed by Industry-Academic Cooperation Foundation, Yonsei University, Seoul (KR)
Filed on May 12, 2022, as Appl. No. 17/742,935.
Claims priority of application No. 10-2021-0061763 (KR), filed on May 13, 2021.
Prior Publication US 2023/0016532 A1, Jan. 19, 2023
Int. Cl. F01D 5/18 (2006.01); B33Y 10/00 (2015.01); B33Y 80/00 (2015.01)
CPC F01D 5/187 (2013.01) [B33Y 10/00 (2014.12); B33Y 80/00 (2014.12); F05D 2230/30 (2013.01); F05D 2260/201 (2013.01)] 6 Claims
OG exemplary drawing
 
1. A gas turbine vane and blade assembly in a lattice-structure cooling type, which is a vane and blade assembly applied to a gas turbine, the gas turbine vane and blade assembly comprising:
an impingement plate disposed on an inner side and having a plurality of injection holes arranged in a linear pattern;
an effusion plate disposed on an outer side and having a plurality of effusion holes arranged in a linear pattern that is offset from the plurality of injections holes, the impingement plate and the effusion plate forming a double partition wall having a cavity therein; and
a plurality of lattice structures positioned in the cavity to have a flow structure while supporting the impingement plate and the effusion plate, wherein the plurality of lattice structures are positioned between the plurality of injection holes and the plurality of effusion holes.