US 12,339,001 B2
System and method having flame stabilizers for isothermal expansion in turbine stage of gas turbine engine
Joel Meador Hall, Simpsonville, SC (US); and John Farrior Woodall, Greer, SC (US)
Assigned to GE Infrastructure Technology LLC, Greenville, SC (US)
Filed by GE Infrastructure Technology LLC, Greenville, SC (US)
Filed on Apr. 12, 2024, as Appl. No. 18/634,812.
Application 18/634,812 is a continuation of application No. 18/092,120, filed on Dec. 30, 2022, granted, now 11,971,170.
Prior Publication US 2024/0255148 A1, Aug. 1, 2024
This patent is subject to a terminal disclaimer.
Int. Cl. F23R 3/18 (2006.01); F23R 3/20 (2006.01); F23R 3/22 (2006.01)
CPC F23R 3/18 (2013.01) [F23R 3/20 (2013.01); F23R 3/22 (2013.01)] 27 Claims
OG exemplary drawing
 
1. A system, comprising:
a plurality of turbine blades configured to mount in a turbine stage of a gas turbine;
a plurality of flame stabilizers configured to stabilize flames relative to the plurality of turbine blades, wherein each turbine blade of the plurality of turbine blades comprises a set of flame stabilizers of the plurality of flame stabilizers at a plurality of different axial positions over a range of at least 10 percent of an axial length between leading and trailing edges of the respective turbine blade,
wherein the respective set of flame stabilizers of a first turbine blade of the plurality of turbine blades has a different arrangement than the respective set of flame stabilizers of a second turbine blade of the plurality of turbine blades.