A fuel injector (18) for a hydrogen combusting aircraft gas turbine engine has at least one air through-passage (44, 52) extending axially from a front face (40) to a rear face (54). The injector further comprises a fuel manifold (42) in communication with a hydrogen fuel feed line (38). A plurality of fuel outlets (64) is provided surrounding the or each air passage (44, 52) and an annular fuel gallery (76) is provided around each air through passage (44, 52) configured to supply the fuel outlets (64), the annular fuel gallery (76) communicating with the fuel manifold (42).
Fuel injector
2023-05-24
Patent
Electronic Resource
English