US 12,078,100 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, Cincinnati, OH (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Dec. 3, 2021, as Appl. No. 17/457,559.
Prior Publication US 2023/0175435 A1, Jun. 8, 2023
Int. Cl. F02C 3/22 (2006.01); B64D 27/10 (2006.01); B64D 37/04 (2006.01); B64D 37/30 (2006.01); F02C 6/20 (2006.01)
CPC F02C 3/22 (2013.01) [B64D 27/10 (2013.01); B64D 37/04 (2013.01); B64D 37/30 (2013.01); F02C 6/20 (2013.01); F05D 2240/35 (2013.01)] 6 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 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 the combustor size rating is defined by:
L2/H,
where 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:
Thrust/Bypass Ratio.