Turbine component having pin-fin cooling structure, and gas turbine including same
AssigneesDoosan Enerbility Co., Ltd., University-Industry Foundation, Yonsei University
InventorsYun Chang Jang, Jeong Ju Kim, Ki Don Lee, Hyung Hee Cho, Gyeong Ryun Kim, Jae Hyeong Kim
Life of this patent
Estimating the term…
Abstract
An airfoil of a turbine blade or turbine vane includes a coolant flow cavity formed in an inner trailing edge of the airfoil, and a plurality of pin-fin cooling structures formed to abut against opposite inner sides of the coolant flow cavity, the pin-fin cooling structures each including a cooling fin connected between the opposite inner sides to the coolant flow cavity, and a pair of guide fins formed on opposite sides of the cooling fin so as to be spaced a predetermined distance apart from each other to surround the cooling fin.
Claims23
An airfoil of a turbine blade or turbine vane, the airfoil comprising:
- a coolant flow cavity formed in an inner trailing edge of the airfoil;
- and
- a plurality of pin-fin cooling structures formed to abut against opposite inner sides of the coolant flow cavity, the pin-fin cooling structures each comprising:
- a cooling fin connected between the opposite inner sides to the coolant flow cavity, and
- a pair of guide fins formed on opposite sides of the cooling fin so as to be spaced a predetermined distance apart from each other to surround the cooling fin.
A turbine vane comprising:
- an airfoil;
- an inner end wall formed on a radially inner side of the airfoil;
- an outer end wall formed on a radially outer side of the airfoil, the inner end wall and the outer end wall each having an end wall cavity formed therein;
- and
- a plurality of pin-fin cooling structures formed to abut against opposite inner sides of the end wall cavities, the pin-fin cooling structures each comprising:
- a cooling fin connected between the opposite inner sides to the end wall cavities;
- and
- a pair of guide fins formed on opposite sides of the cooling fin so as to be spaced a predetermined distance apart from each other to surround the cooling fin.
A gas turbine comprising:
- a compressor configured to compress incoming air;
- a combustor configured to mix the compressed air with fuel and combust an air-fuel mixture;
- and
- a turbine having turbine blades and turbine vanes installed in a turbine housing so that the turbine blades are rotated by combustion gases discharged from the combustor, wherein an airfoil of the turbine blade or turbine vane comprises:
- a coolant flow cavity formed in an inner trailing edge of the airfoil;
- and
- a plurality of pin-fin cooling structures formed to abut against opposite inner sides of the coolant flow cavity, the pin-fin cooling structures each comprising:
- a cooling fin connected between the opposite inner sides to the coolant flow cavity, and
- a pair of guide fins formed on opposite sides of the cooling fin so as to be spaced a predetermined distance apart from each other to surround the cooling fin.
Dependencies are inferred from the claim text.