US 12,152,502 B2
Selectively coated gas path surfaces within a hot section of a gas turbine engine
Eric Durocher, Boucherville (CA); Ian MacFarlane, Boucherville (CA); and Guy Lefebvre, St. Bruno de Montarville (CA)
Assigned to PRATT & WHITNEY CANADA CORP., Longueuil (CA)
Filed by Pratt & Whitney Canada Corp., Longueuil (CA)
Filed on Oct. 29, 2021, as Appl. No. 17/514,602.
Prior Publication US 2023/0138749 A1, May 4, 2023
Int. Cl. F01D 5/28 (2006.01); F01D 9/04 (2006.01)
CPC F01D 5/288 (2013.01) [F01D 9/041 (2013.01); F05D 2240/12 (2013.01); F05D 2240/80 (2013.01); F05D 2260/231 (2013.01); F05D 2300/611 (2013.01)] 15 Claims
OG exemplary drawing
 
1. An apparatus for a gas turbine engine, comprising:
a hot section structure of the gas turbine engine;
the hot section structure configured with a plurality of surfaces respectively forming boundaries of a gas path through the hot section structure, the plurality of surfaces including an uncoated first surface and a second surface; and
the hot section structure including metal and thermal barrier material, the uncoated first surface formed by the metal, and the second surface formed by the thermal barrier material;
wherein the uncoated first surface is formed by the metal such that the metal forming the uncoated first surface is configured to be directly exposed to hot gas flowing through the gas path; and
wherein the hot section structure comprises a vane, and the thermal barrier material forms at least a portion of a trailing edge of the vane.