US 12,331,927 B2
Positional control of fuel injection into gas turbine combustors
Jason A. Ryon, Carlisle, IA (US); Philip E. O. Buelow, West Des Moines, IA (US); and Brandon P. Williams, Johnston, IA (US)
Assigned to Collins Engine Nozzles, Inc., Des Moines, IA (US)
Filed by Collins Engine Nozzles, Inc., Des Moines, IA (US)
Filed on Nov. 22, 2023, as Appl. No. 18/517,712.
Prior Publication US 2025/0164103 A1, May 22, 2025
Int. Cl. F23C 5/06 (2006.01); F23R 3/28 (2006.01); F02C 9/28 (2006.01); F02D 7/00 (2006.01); F23R 3/34 (2006.01)
CPC F23C 5/06 (2013.01) [F23R 3/283 (2013.01); F02C 9/28 (2013.01); F02D 7/00 (2013.01); F05D 2260/96 (2013.01); F05D 2270/14 (2013.01); F05D 2270/20 (2013.01); F23R 3/286 (2013.01); F23R 3/34 (2013.01)] 16 Claims
OG exemplary drawing
 
1. A system comprising:
a combustor for a gas turbine defining a main axis extending in an upstream-downstream direction, the combustor including a combustor dome bounding an upstream portion of the combustor, wherein a plurality of injector openings are defined through the combustor dome;
an injector defining a spray axis aligned with one of the plurality of injector openings for issuing a spray into the combustor along the spray axis;
an actuator operatively connected to the injector for movement of the injector relative combustor dome to adjust a relative position of the spray axis relative to the main axis; and
a high pressure case of a gas turbine engine outboard of the combustor, wherein the actuator is positioned outside the high pressure case.