US 12,320,301 B2
Combustion chamber module having an annular combustion chamber
Gregor Christoffer Gebel, Ludwigsfelde (DE); and Carsten Clemen, Mittenwalde (DE)
Assigned to ROLLS-ROYCE DEUTSCHLAND LTD & CO KG, Blankenfelde-Mahlow (DE)
Filed by Rolls-Royce Deutschland Ltd & Co KG, Blankenfelde-Mahlow (DE)
Filed on Jul. 24, 2024, as Appl. No. 18/782,262.
Claims priority of application No. 10 2023 207 553.9 (DE), filed on Aug. 7, 2023.
Prior Publication US 2025/0052198 A1, Feb. 13, 2025
Int. Cl. F02C 7/22 (2006.01); F02C 9/40 (2006.01)
CPC F02C 7/222 (2013.01) [F02C 9/40 (2013.01); F05D 2240/60 (2013.01)] 13 Claims
OG exemplary drawing
 
1. A fluid supply assembly comprising:
a line assembly for supplying a fluid mass flow of fuel in a variable supply quantity from a fuel reservoir to a combustion chamber of an engine, the fluid mass flow including a primary mass flow supplied via a primary line and a secondary mass flow supplied via a secondary line,
a restrictor disposed in the primary line and having an inner diameter less than that of the primary line, the restrictor being is a passively operating and having an invariable geometry without moving parts, by which a mass flow ratio of the primary mass flow to the secondary mass flow is altered as a function of the fluid mass flow supplied via the line assembly;
the fluid mass flow being supplied as more than 50% via the primary line and a remaining proportion of the fluid mass flow via the secondary line, as a result of which a minimum mass flow ratio is given;
wherein the restrictor is configured as a long orifice having a length that is a multiple of greater than 1 of the inner diameter and a Reynolds number of not more than 1000 is obtained at a predetermined minimum fluid mass flow at the inner diameter, such that the mass flow ratio increases steadily with increasing fluid mass flow until a certain maximum mass flow is reached;
wherein the primary line is a main line and the secondary line is a pilot line of the fuel supply assembly;
wherein the minimum mass flow ratio, where a relatively high proportion of the secondary mass flow flows through the pilot line, occurs at low engine operating conditions for stabilizing a flame in the combustion chamber, while a higher mass flow ratio, where a lower proportion of the secondary mass flow flows through the pilot line, occurs at higher engine operating conditions.