US 12,405,007 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 10, 2024, as Appl. No. 18/660,463.
Application 18/660,463 is a continuation in part of application No. 17/457,559, filed on Dec. 3, 2021, granted, now 12,078,100.
Prior Publication US 2024/0288167 A1, Aug. 29, 2024
This patent is subject to a terminal disclaimer.
Int. Cl. F02C 3/30 (2006.01); F02C 3/20 (2006.01); F02C 3/22 (2006.01); F23R 3/28 (2006.01); F23R 3/42 (2006.01)
CPC F23R 3/28 (2013.01) [F02C 3/20 (2013.01); F02C 3/22 (2013.01); F23R 3/42 (2013.01)] 19 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 comprising:
at least one fuel-air mixing assembly comprising a center body, an outer wall spaced from and circumscribing the center body, an annular flow passage defined between the outer wall and the center body, and having an inlet and an outlet, and at least one fuel orifice having a fuel outlet opening into the annular flow passage, and
a combustor configured to operate without diluent, the combustor including 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 His 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