Integral gas turbine compressor and rotary fuel injector

Fluid reaction surfaces (i.e. – impellers) – Specific blade structure – Apertured or permeable

Reexamination Certificate

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Details

C416S181000, C060S744000, C060S776000

Reexamination Certificate

active

07896620

ABSTRACT:
An integral impeller and fuel pump for a small gas turbine engine, the impeller being a centrifugal impeller to supply compressed air to the combustor, the rotor disk of the centrifugal compressor having at least one radial fuel passage connecting a central bore of the rotor disk to a fuel nozzle located on the rear face of the rotor disk. A low pressure fuel supplied by a small pump delivers the fuel to the central bore where the fuel is collected within helical grooves and channeled into the radial fuel passages where the fuel is pressurized to a relatively high pressure due to the high rotational speed of the centrifugal compressor. Highly compressed fuel is injected into the combustor through fuel nozzles in an axial direction as the rotor disk rotates. Helical grooves in the central bore each connected to a radial fuel passage move the fuel to an opposite side of the central bore to counteract rotor imbalance. In another embodiment, a primary annular groove collects fuel and, at a low speed, passes all of the fuel to a first radial fuel passage into a first fuel nozzle such that only some of the fuel nozzles inject fuel into the combustor. At a higher speed, some of the fuel collected in the primary annular groove is spilled over into a secondary annular groove that passes the spilled-over fuel into a second radial passage and second fuel nozzle such that all of the fuel nozzles inject fuel into the combustor.

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