Patent ID: 7624565

Claim:
A gas turbine engine comprising: at least three gas turbine engine components including in downstream flow relationship a compressor, a combustor, and a turbine; at least a first one of the gas turbine engine components being a radially bladed component having at least one row of radially extending rotatable blades; at least a second one of the gas turbine engine components being a worm component; the worm component including an inlet axially spaced apart and upstream from an outlet, an inner body disposed within an outer body, and the inner and outer bodies extending from the inlet to the outlet; the inner and outer bodies having offset inner and outer axes respectively; at least one of the inner and outer bodies being rotatable about a corresponding one of the inner and outer axes; the inner and outer bodies having intermeshed inner and outer helical blades wound about the inner and outer axes respectively; and the inner and outer helical blades extending radially outwardly and inwardly respectively.