Rocket engine thrust chamber, injector, and turbopump

A method comprising:

• using one or more additive manufacturing processes to form a thrust chamber and an injector for a rocket engine, wherein:
• the thrust chamber includes:
• an exterior skin,
• an interior skin offset from the exterior skin so as to form a first gap between the exterior skin and the interior skin,
• a plurality of walls bridging between the exterior skin and the interior skin and located within the first gap, wherein the walls define a plurality of coolant flow passages within the first gap and extend from a first end of the thrust chamber to a second end of the thrust chamber;
• and
• the injector includes:
• a plate with a plurality of first propellant ports fluidically connecting one side of the plate with an opposing side of the plate,
• a propellant distribution plenum,
• a plurality of annular plenums including a first annular plenum and a second annular plenum,
• a plurality of radial passages, and
• a plurality of support columns, wherein:
• the propellant distribution plenum is annular and has an outer diameter and an inner diameter,
• each annular plenum of the plurality of annular plenums has an outer diameter and an inner diameter,
• the inner diameter of the first annular plenum is larger than the outer diameter of the second annular plenum,
• the plurality of radial passages includes first radial passages and second radial passages, wherein the first radial passages fluidically connect the propellant distribution plenum with the first annular plenum and are equidistantly spaced about the outer diameter of the first annular plenum and the second radial passages fluidically connect the first annular plenum with the second annular plenum and are equidistantly spaced about the outer diameter of the second annular plenum,
• the first annular plenum and the second annular plenum are both offset from the plate to form a gap,
• the injector is connected to the first end of the thrust chamber,
• the thrust chamber and the injector are configured so that fluid flowed through the first end of the thrust chamber via the coolant flow passages enters the propellant distribution plenum of the injector via the first propellant ports, and
• each support column of the plurality of support columns:
• spans the gap between the plate and one of the annular plenums, and
• includes a column base adjacent to the plate, a base plenum within the column base, a riser passage that fluidically connects the base plenum with the respective annular plenum of the plurality of annular plenums to which the support column spans, and at least one second propellant port, and
• the at least one second propellant port of that support column is not collocated with the first propellant ports of the plurality of first propellant ports.