Bypass gas turbine fan employing a stub rotor stage and a main r

Details Bypass gas turbine fan employing a stub rotor stage and a main r Bypass gas turbine fan employing a stub rotor stage and a main r

1976-07-08

1977-10-25

Garrett, Robert E.

Power plants

Reaction motor

Interrelated reaction motors

415 77, F02K 306

Patent

active

040550427

ABSTRACT:
A gas turbine engine has a core engine which drives a fan, the fan comprising a main rotor stage and a stub rotor stage whose blades have a smaller radial extent than those of the main rotor stage. The main and stub stages of the fan both compress air to form a main fan airflow and a stub stage airflow respectively, the stub stage airflow being divided into two portions one of which rejoins the main fan airflow and one of which enters the core engine intake. In order to match the flow angles of the various flows, the stub stage has inner and outer outlet guide vanes which give different degrees of deflection to the two component portions of the stub stage airflow.

REFERENCES:
patent: 2923125 (1960-02-01), Rainbow
patent: 3494129 (1970-02-01), Krebs et al.
patent: 3546882 (1970-12-01), Berkey
patent: 3879941 (1975-04-01), Sargisson

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