Title:
TURBOMACHINE AIRFOIL HAVING VARIABLE THICKNESS THERMAL BARRIER COATING
Document Type and Number:
Japanese Patent JP2021162016
Kind Code:
A
Abstract:
To provide an airfoil for turbomachines such as stator vanes or rotor blades thereof.SOLUTION: An airfoil (100) includes a root (102) and a tip (104), which define a span (128) of the airfoil (100) therebetween. The airfoil (100) also includes a leading edge (124) and a trailing edge (126) downstream of the leading edge (124) along a flow direction. The leading edge (124) and the trailing edge (126) each extend across the span (128) of the airfoil (100) from the root (102) to the tip (104). The airfoil (100) further includes a pressure side surface (120) and a suction side surface (122). The airfoil (100) also includes a thermal barrier coating (108) on the pressure side surface (120) and the suction side surface (122). The thermal barrier coating (108) includes a base layer (110) and a top coat (112). A thickness of the base layer (110) varies across each of the pressure side surface (120) and the suction side surface (122) with a maximum thickness of the base layer (110) at the leading edge (124).SELECTED DRAWING: Figure 2
Inventors:
MARTIN JAMES JASPER
JAN AGUDO
MELBOURNE JAMES MYERS
RICHARD RYAN PILSON
CHRISTOPHER W KESTER
JAN AGUDO
MELBOURNE JAMES MYERS
RICHARD RYAN PILSON
CHRISTOPHER W KESTER
Application Number:
JP2021032674A
Publication Date:
October 11, 2021
Filing Date:
March 02, 2021
Export Citation:
Assignee:
GENERAL ELECTRIC CO GE
International Classes:
F01D5/28; F01D5/14; F01D9/02; F01D25/00; F04D29/24
Attorney, Agent or Firm:
Hirokazu Ogura