Swirler arrangement for combustor of gas turbine engine

Details Swirler arrangement for combustor of gas turbine engine Swirler arrangement for combustor of gas turbine engine

1987-01-02

1988-08-16

Stout, Donald E.

Power plants

Combustion products used as motive fluid

Combustion products generator

60748, F02C 314, F23R 314

Patent

active

047634820

ABSTRACT:
A gas turbine engine has an annular combustor structure which includes a plurality of annularly displaced combustion zones. A fuel nozzle is positioned in each combustion zone for supplying fuel thereto. A swirler is supported on each of the fuel nozzles and includes a plurality of angularly-directed passages for causing a swirling action of the air entering the combustion chamber through the nozzles. The swirlers are associated in pairs, each of the swirlers of each pair including a tab extending radially outwardly. When air is supplied through the angularly-directed passages, the swirlers are urged in a direction which brings the tabs of each pair into engagement with each other and thereby limits further rotational movement of the swirlers.

REFERENCES:
patent: 2577918 (1951-12-01), Rowe
patent: 2813397 (1957-11-01), Fisher et al.
patent: 3000183 (1961-09-01), Hall
patent: 3273343 (1966-09-01), Cretella
patent: 3589127 (1971-06-01), Kenworthy et al.
patent: 3869246 (1975-03-01), Hammond, Jr. et al.
patent: 4525996 (1985-07-01), Wright et al.

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