FIELD: engines and pumps.
SUBSTANCE: invention relates to a turbine engine and in particular to a system for improving the operational suitability of a fuel injector. Fuel injector comprises a central body configured to receive the first portion of the air and to deliver this air to the combustion zone. In addition, the fuel injector comprises a swirler configured to receive the second portion of the air and to deliver this air to the combustion zone. Swirler comprises an outer circumferential wall, an inner circumferential wall and a swirling blade. Swirling blade comprises a radial swirling profile located at its downstream edge. Radial swirling profile comprises one section extending from the outer circumferential wall to the first transition point and the second section extending from the transition point to the inner circumferential wall. At least one section, either the first or the second one, is substantially straight, and at least one section, either the first or the second one, is arcuated. Method of directing the air through the fuel injector, as well as the swirler of the fuel injector, are also presented.
EFFECT: invention allows improving operational suitability of the fuel injector.
23 cl, 11 dwg
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Authors
Dates
2018-02-06—Published
2013-04-29—Filed