US 11,674,400 B2
Gas turbine engine nozzles
Matteo Renato Usseglio, Turin (IT); Enrico Ganzitti, Avigliana (IT); Gianfranco Brandino, Chieri (IT); Rafal Robak, Pszczyna (PL); and Tomasz Mucha, Meszna (PL)
Assigned to GE AVIO S.R.L., Rivalta di Torino (IT); and AVIO POLSKA SP. Z O.O, Biata-Bielsko (PL)
Filed by GE Avio S.r.l., Rivalta di Turin (IT); and Avio Polska Sp. z o.o., Biata-Bielsko (PL)
Filed on Aug. 4, 2021, as Appl. No. 17/393,743.
Claims priority of application No. 437289 (PL), filed on Mar. 12, 2021.
Prior Publication US 2022/0290571 A1, Sep. 15, 2022
Int. Cl. F01D 9/04 (2006.01); F01D 9/02 (2006.01); F01D 25/24 (2006.01); F01D 11/00 (2006.01)
CPC F01D 9/02 (2013.01) [F01D 9/041 (2013.01); F01D 11/005 (2013.01); F01D 25/243 (2013.01); F01D 25/246 (2013.01); F05D 2220/32 (2013.01); F05D 2240/128 (2013.01)] 17 Claims
OG exemplary drawing
 
1. A gas turbine engine comprising:
a frame assembly;
a turbine assembly; and
a nozzle disposed in the turbine assembly, wherein the nozzle defines an inner end along a radial direction and an outer end along the radial direction, wherein the outer end of the nozzle is supported by the frame assembly, wherein the inner end of the nozzle is supported by the frame assembly, and wherein the inner end of the nozzle is displaceable relative to the frame assembly in at least the radial direction; and
wherein the outer end of the nozzle is coupled to the frame assembly at a plurality of interfaces spaced apart from one another around a circumference of the gas turbine engine, wherein the plurality of interfaces includes a first interface and a second interface, wherein the first interface defines a first geometry, and wherein the second interface defines a second geometry different than the first geometry;
wherein the first interface comprises a first pin and defines a first slot, wherein the second interface comprises a second pin and defines a second slot, wherein the second slot defines a different geometry than the first slot.