US 12,228,284 B2
Nozzle tip with shielded core for a dual combustion systems
Oleg Morenko, Oakville (CA); and Sandeep Vishal Dhalla, Woodbridge (CA)
Assigned to PRATT & WHITNEY CANADA CORP., Longueuil (CA)
Filed by Pratt & Whitney Canada Corp., Longueuil (CA)
Filed on May 17, 2021, as Appl. No. 17/322,812.
Prior Publication US 2022/0364509 A1, Nov. 17, 2022
Int. Cl. F23R 3/28 (2006.01); F02C 7/22 (2006.01)
CPC F23R 3/283 (2013.01) [F02C 7/22 (2013.01); F05D 2220/323 (2013.01)] 13 Claims
OG exemplary drawing
 
1. A dual combustion system for an aircraft engine, comprising:
a liquid fuel source including a biofuel or kerosene;
a gaseous hydrogen fuel source; and
a fuel nozzle assembly including:
a first fuel conduit in fluid communication with the liquid fuel source, the first fuel conduit defined between a nozzle body and a fuel swirler, the first fuel conduit extending along a longitudinal axis from a first location to a first fuel outlet at an outlet end of the nozzle body;
a second fuel conduit in fluid communication with the gaseous hydrogen fuel source, the second fuel conduit defined between the fuel swirler and a heat shield radially inward of the first fuel conduit, the second fuel conduit extending along the longitudinal axis from a second location to a second fuel outlet at an outlet end of the fuel swirler, the first location of the first fuel conduit disposed axially between the second location of the second fuel conduit and the outlet end of the nozzle body, an axial length of the second fuel conduit greater than that of the first fuel conduit, a cross-section area of the second fuel conduit smaller than that of the first fuel conduit;
an air conduit radially inward of the second fuel conduit and extending through the heat shield along the longitudinal axis from an air inlet at an inlet end of the heat shield to an air outlet at an outlet end of the heat shield, the heat shield sealing the air conduit from the second fuel conduit between the air inlet and the air outlet, the air conduit having an axial length between the inlet end and the outlet end of the heat shield, the axial length of the air conduit greater than that of the second fuel conduit; and
a feed arm coupled to the nozzle body;
wherein the first fuel conduit is in fluid communication with a third fuel conduit extending through the feed arm, wherein the first fuel conduit passes through a first lateral port extending through the nozzle body in a first direction transverse to the longitudinal axis, and wherein the second fuel conduit is in fluid communication with a fourth fuel conduit extending through the feed arm, and wherein the second fuel conduit passes through a second lateral port extending through both the fuel swirler and the nozzle body in a second direction transverse to the longitudinal axis, and
wherein the nozzle body and the fuel swirler each extend along the longitudinal axis from a nozzle tip into a cavity in the feed arm to a position upstream of the fourth fuel conduit relative to a fuel flow through the first fuel conduit and the second fuel conduit.