US 11,753,952 B2
Support structure for a turbine vane of a gas turbine engine
Lawrence A. Binek, Glastonbury, CT (US); and David W. Morganson, Marlborough, CT (US)
Assigned to Raytheon Technologies Corporation, Farmington, CT (US)
Filed by United Technologies Corporation, Farmington, CT (US)
Filed on Oct. 4, 2019, as Appl. No. 16/593,638.
Prior Publication US 2021/0102704 A1, Apr. 8, 2021
Int. Cl. F01D 9/02 (2006.01); F01D 9/04 (2006.01); F23R 3/00 (2006.01); F23R 3/50 (2006.01); B22F 10/40 (2021.01); B22F 10/64 (2021.01); B33Y 10/00 (2015.01); B33Y 80/00 (2015.01)
CPC F01D 9/044 (2013.01) [B22F 10/40 (2021.01); B22F 10/64 (2021.01); F01D 9/023 (2013.01); F01D 9/041 (2013.01); F23R 3/002 (2013.01); F23R 3/50 (2013.01); B33Y 10/00 (2014.12); B33Y 80/00 (2014.12); F05D 2230/30 (2013.01); F05D 2240/12 (2013.01); F05D 2240/35 (2013.01); F05D 2300/1723 (2013.01); F23R 2900/00018 (2013.01)] 12 Claims
OG exemplary drawing
 
8. A gas turbine engine comprising:
a diffuser wall;
a combustor liner;
a support structure integrally attached to the combustor liner at a radially distal position; and
a turbine vane integrally attached to the support structure at an inwardly adjacent position to the radially distal position, wherein the turbine vane is attached to the diffuser wall at a radially proximal position and the support structure is formed of a repeating network of spar assemblies;
wherein the combustor liner and turbine vane are formed of a metal or alloy that can tolerate the high temperature and pressure environment of the gas turbine engine and the support structure formed of the same metal or alloy as the turbine vane and combustor liner is less dense than the turbine vane and combustor liner such that the support structure is configured to be removed without damaging the turbine vane and combustor liner such that when the support structure is removed the turbine vane remains attached to the diffuser wall and a thermal expansion gap is formed between the turbine vane and the combustor liner.