US 11,988,104 B1
Removable layer to adjust mount structure of a turbine vane for re-stagger
Robert A. White, III, Meriden, CT (US); Raymond Surace, Newington, CT (US); Howard J. Liles, Newington, CT (US); and Bryan P. Dube, Chepachet, RI (US)
Assigned to RTX Corporation, Farmington, CT (US)
Filed by Raytheon Technologies Corporation, Farmington, CT (US)
Filed on Nov. 29, 2022, as Appl. No. 18/070,978.
Int. Cl. F01D 25/00 (2006.01); F01D 9/04 (2006.01)
CPC F01D 25/005 (2013.01) [F01D 9/041 (2013.01); F05D 2220/323 (2013.01); F05D 2230/10 (2013.01); F05D 2240/12 (2013.01); F05D 2300/6033 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A turbine section in a gas turbine engine comprising:
a plurality of rotating turbine blades in a row;
a plurality of static stator vane circumferentially spaced in a row axially intermediate the rows of turbine blades, and each said stator vane in the stator vane row having at least an outer platform with mount structure at at least one of a trailing edge and a leading edge and an airfoil, each of said stator vanes formed of composite materials;
said mount structure being provided with sacrificial material, at least a first of said stator vanes being circumferentially adjacent to a second of said stator vanes, and an orientation of said first of said stator vanes being re-staggered relative to the second of said stator vanes, and such that an original formed mount structure of the first stator vane is not axially aligned with the mount structure of the second of the stator vane, and the sacrificial material of the first of the stator vanes being machined away such that a final trailing edge of the first of the stator vanes mount structure is now better axially aligned with the trailing edge of the second of the stator vanes mount structure trailing edge.