Hybrid worm gas turbine engine

Details Hybrid worm gas turbine engine Hybrid worm gas turbine engine

2007-05-01

2009-12-01

Cuff, Michael (Department: 3741)

Power plants

Combustion products used as motive fluid

With gear, pressure exchanger, or screw-type compressor

C060S726000

Reexamination Certificate

active

07624565

ABSTRACT:
A gas turbine engine has components including a compressor, a combustor, and a turbine. At least one component is radially bladed having at least one row of radially extending rotatable blades and at least another is a worm component having an inner body disposed within an outer body. The inner and outer bodies have offset inner and outer axes, intermeshed inner and outer helical blades wound about the inner and outer axes respectively, and at least one of the inner and outer bodies being rotatable about a corresponding one of the inner and outer axes. An aircraft gas turbine engine has components in serial downstream flow relationship including a fan, a low pressure compressor, a high pressure compressor, a combustor, a high pressure turbine, and a low pressure turbine. At least one of the components is radially bladed and at least one of the components is a worm component.

REFERENCES:
patent: 1892217 (1932-12-01), Moineau et al.
patent: 2553548 (1951-05-01), Pawl et al.
patent: 4144001 (1979-03-01), Streicher
patent: RE30400 (1980-09-01), Zimmern
patent: 4482305 (1984-11-01), Natkai et al.
patent: 5605124 (1997-02-01), Morgan
patent: 7530217 (2009-05-01), Murrow et al.

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