Turbine engine fuel injector with permanent leakage flow
AssigneeSnecma
InventorsEmilie Charlotte Pousseo, Jose Roland Rodrigues
Life of this patent
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Abstract
A fuel injector for a turbine engine, the injector including a body including a mechanism for admitting fuel under pressure, a stop valve for feeding a primary fuel circuit, and a metering valve mounted downstream from the stop valve for feeding a secondary fuel circuit. The injector further includes at least one leakage channel, that can be formed by a thread, that extends from a zone situated downstream from the stop valve and upstream from the metering valve to a zone situated downstream from the metering valve to generate a permanent leakage flow in the secondary circuit.
Claims8
A fuel injector for a turbine engine or an airplane turboprop or turbojet, the fuel injector comprising:
- a body including an admission orifice for admitting fuel under pressure;
- a stop valve mounted in the body downstream from the admission orifice and configured to open at a first determined fuel pressure and to remain open beyond the first determined fuel pressure to feed a primary fuel circuit;
- a metering valve mounted in the body downstream from the stop valve and configured to open beyond a second determined fuel pressure greater than the first determined fuel pressure, and to remain open beyond the second determined fuel pressure to feed a secondary fuel circuit;
- a tubular support radially surrounding the metering valve, the metering valve configured to slide within the tubular support;
- and
- at least one leakage channel extending in the tubular support from a zone situated downstream from the stop valve and upstream from the metering valve to a zone situated downstream from the metering valve to generate a permanent leakage flow in the secondary fuel circuit.
Dependencies are inferred from the claim text.