Ducted impeller

An engine assembly comprising:

• a casing mechanically coupled to a jet engine casing wherein the jet engine casing is further attached to a plurality of ducting panels including:
• forward ducting panels,
• a forward central ducting panel,
• a rear central ducting panel, and
• rear ducting panels,
• wherein each of the plurality of ducting panels extends radially outward from a root of each of the plurality of ducting panels to a tip of each of the plurality of ducting panels;
• wherein the root of each of the plurality of ducting panels is attached to the jet engine casing and the tip of each of the plurality of ducting panels terminates at a free end of each of the plurality of ducting panels,
• wherein the free end of each forward ducting panel is located within a flowpath between the jet engine casing and the casing and the root of each forward ducting panel is located forward of a combustion stage with respect to a longitudinal axis of the engine assembly,
• wherein the engine assembly further comprises:
• a low-pressure compression stage configured to compress gasses;
• a high-pressure compression stage, connected to the low-pressure compression stage and configured to further compress the gasses;
• a turbine stage connected to the combustion stage and configured to utilize energy in the gasses;
• a shaft, connected to the turbine stage, and configured to turn as a result of the turbine stage;
• and
• a ducted impeller comprising blades that are widest at a blade tip, narrowing down to a hub, while not over lapping and beginning with a rotation of 45 degrees measured from an axis of the shaft to a blade chord and of a smaller angle going toward the hub to create an even air pressure along an entire length of each blade,
• wherein the combustion stage is connected to the high-pressure compression stage and configured to heat the gases to three thousand degrees Fahrenheit by back pressure.