Line replaceable fuel nozzle apparatus, system and method

A gas turbine engine comprising,

• a compressor;
• a combustor in fluid communication with the compressor;
• a turbine in fluid communication with the combustor;
• and
• a fuel injector that is removable and installable within the combustor and configured to conduct fuel to the combustor, the fuel injector comprising:
• a fuel nozzle, including a radially extending inlet stem, defining a main fuel channel, a secondary fuel channel, a simplex fuel channel and a heat shield area,
• wherein the heat shield area is disposed about and configured to surround the simplex fuel channel,
• wherein a portion of the simplex fuel channel located in the radially extending inlet stem is of circular cross section defining a circumference having a first half and a second half, wherein the secondary fuel channel surrounds the first half circumference of the simplex fuel channel and the main fuel channel surrounds the second half circumference of the simplex fuel channel, and
• wherein the simplex fuel channel is disposed in the center of the fuel nozzle and wherein the main fuel channel and the secondary fuel channel are disposed about the simplex fuel channel;
• a pilot stage operatively coupled to, and in fluid communication with, the fuel nozzle and configured to receive fuel from the secondary fuel channel and the simplex fuel channel;
• and
• a main stage in fluid communication with and configured to receive fuel from the main fuel channel.

A fuel injector, comprising:

• a fuel nozzle having a radially extending inlet stem and defining a main fuel channel, a secondary fuel channel, a simplex fuel channel and a heat shield area,
• wherein the inlet defines a main flow area in fluid communication with the main fuel channel, a secondary flow area in fluid communication with the secondary fuel channel, and a simplex flow area in fluid communication with the simplex fuel channel,
• wherein the simplex fuel channel is disposed in the center of the fuel nozzle and wherein the main fuel channel and the secondary fuel channel are disposed about the simplex fuel channel,
• wherein the heat shield area is configured to separate and protect the main fuel channel, the secondary fuel channel and the simplex fuel channel from a heat load to prevent fuel coking,
• wherein a portion of the simplex fuel channel located in the radially extending inlet stem is of circular cross section defining a circumference having a first half and a second half, wherein the secondary fuel channel surrounds the first half circumference of the simplex fuel channel and the main fuel channel surrounds the second half circumference of the simplex fuel channel;
• and
• wherein the fuel nozzle is formed as a single piece;
• a pilot stage operatively coupled to, and in fluid communication with, the fuel nozzle and configured to receive fuel from the secondary fuel channel and the simplex fuel channel;
• and
• a main stage in fluid communication with and configured to receive fuel from the main fuel channel.