US 12,454,909 B2
Combustor size rating for a gas turbine engine using hydrogen fuel
Michael A. Benjamin, Cincinnati, OH (US); and Manampathy G. Giridharan, Mason, OH (US)
Assigned to General Electric Company, Evendale, OH (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on May 24, 2024, as Appl. No. 18/673,559.
Application 18/673,559 is a continuation in part of application No. 17/457,559, filed on Dec. 3, 2021, granted, now 12,078,100.
Prior Publication US 2024/0309804 A1, Sep. 19, 2024
This patent is subject to a terminal disclaimer.
Int. Cl. F02C 7/22 (2006.01); F02C 3/22 (2006.01); F23R 3/28 (2006.01)
CPC F02C 3/22 (2013.01) [F02C 7/22 (2013.01); F23R 3/28 (2013.01); F05D 2220/323 (2013.01); F05D 2240/35 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A gas turbine engine comprising:
a hydrogen fuel delivery assembly configured to deliver a hydrogen fuel flow;
a compressor section configured to compress air flowing therethrough to provide a compressed air flow; and
a combustion section having a combustor with a fuel mixer and the combustor configured to operate without diluent, the combustor having an inner liner, an outer liner, and a combustion chamber, the combustion chamber characterized by a combustor size rating between one inch and seven inches at a core air flow parameter between two and one half kN and sixty kN, wherein the combustor size rating is a function of the core air flow parameter, and wherein the combustor size rating is defined by:

OG Complex Work Unit Math
wherein H is a maximum height of the combustion chamber measured by a forward line extending from an inner surface of the outer liner to an inner surface of the inner liner and L is a length of the combustion chamber measured from a midpoint of the forward line to a midpoint of an aft line, the aft line extending from the inner surface of the inner liner to the inner surface of the outer liner at a leading edge of a turbine nozzle,
and, wherein the core air flow parameter is defined by:

OG Complex Work Unit Math
and, the fuel mixer comprising:
an outer wall defining a longitudinal direction and having a mixture outlet;
a first compressed air flow passage and a second compressed air flow passage forming an intersection;
a common flow passage fluidly coupled to the intersection and to the mixture outlet; and
a fuel supply passage having a fuel outlet fluidly coupled to at least one of the first compressed air flow passage, the second compressed air flow passage, or the intersection.