Fuel injector
A fuel injector for a hydrogen combusting aircraft gas turbine engine has at least one air through-passage extending axially from a front face to a rear face. The injector further comprises a fuel manifold in communication with a hydrogen fuel feed line. A plurality of fuel outlets is provided surrounding the or each air passage and an annular fuel gallery is provided around each air through passage configured to supply the fuel outlets, the annular fuel gallery communicating with the fuel manifold.
1 . A fuel injector for a hydrogen combusting aircraft gas turbine engine comprising:
at least one air through-passage extending axially from a front face to a rear face;
a fuel manifold in communication with a hydrogen fuel feed line;
a plurality of fuel outlets surrounding a plurality of air through-passages;
an annular fuel gallery provided around each of the plurality of air through-passages configured to supply the fuel outlets, each of the annular fuel galleries communicating with the fuel manifold;
an injector front plate which forms the front face of the injector;
an injector rear plate which forms the rear face of the injector;
wherein the injector front plate and injector rear plate are coupled together;
a feed plate located between the injector front plate and the injector rear plate comprising a plurality of air through-holes;
wherein the injector rear plate comprises one or more fuel distribution channels which communicate between two or more of the annular fuel galleries; and
wherein the annular fuel galleries communicate with axially extending fuel through holes in the injector feed plate via the fuel distribution channels.
2 . A fuel injector according to claim 1 , wherein each fuel outlet of the plurality of fuel outlets is arranged to direct fuel towards air exiting a respective air through-passage.
3 . A fuel injector according to claim 1 , wherein the injector front plate, rear plate and feed plate are coupled by diffusion bonding or brazing.
4 . A fuel injector according to claim 1 , wherein, when assembled, the axially extending air through-holes of the injector rear plate, injector feed plate and injector front plate align to form a plurality of the plurality of air through-passages.
5 . A fuel injector according to claim 1 , wherein the injector front plate comprises the fuel manifold and comprises a plurality of axially extending air through-holes.
6 . A fuel injector according to claim 1 , wherein the injector rear plate comprises a plurality of axially extending air through-holes.
7 . A combustor for a gas turbine engine comprising a combustion chamber and a plurality of fuel injectors according to claim 1 .
8 . A gas turbine engine comprising a combustor according to claim 7 .