Lubrication circuit, particularly in an aircraft engine
AssigneeSafran Aircraft Engines
InventorGabriel aloys Karcher
Life of this patent
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Abstract
A lubrication circuit comprising an oil tank (4) integrated into a first lubricated chamber (5) comprises an evacuation conduit (20) on a recovery conduit (10) from lubricated chambers of the circuit leading to the reservoir (4), opening up into an outlet (21) when an excessive pressure in the tank, that is a symptom of progressive filling, is reached. Application to aircraft engine lubrication circuits, particularly to guard against fuel leaks in the lubricant as a result of a defective heat exchanger.
Claims8
Lubrication circuit of a first chamber (5) and at least one second chamber (2) for an aircraft engine, the lubrication circuit comprising:
- a lubricant tank (4),
- a discharge conduit (6) from the lubricant tank (4) into the first chamber (5),
- a ventilation conduit (8) connecting the first chamber (5) to the second chamber (2),
- a lubricant recovery conduit (10) connecting the second chamber (2) to the lubricant tank (4) and equipped with a pump (11) forcing a flow towards the lubricant tank (4), and an outlet ventilation conduit (9) connecting the first chamber (5) to a medium external to the circuit, an evacuation conduit (20) connecting to the lubricant recovery conduit (10) between the pump (11) and the lubricant tank (4) and leading to an outlet (21), the evacuation conduit (20) being equipped with a discharge valve (22) preventing backflows to the lubricant recovery conduit and configured to open when the pressure in the lubricant recovery conduit exceeds a predetermined overpressure threshold,
- a control valve (23) on the ventilation conduit (8),
- a depressurization conduit (38) connected to the control valve (23) and leading to a depressurization outlet (24), and
- a valve control conduit (25) originating from the evacuation conduit (20) downstream from the discharge valve (22),
- wherein the control valve (23) is configured to bring the ventilation conduit (8) into communication with the depressurization conduit (38) when a pressure threshold is reached in the valve control conduit (25).
Aircraft engine comprising a shaft, a first chamber (5) that is a gearbox, a second chamber (2) that is a chamber containing shaft bearing support blocks, and a lubrication circuit for the first chamber and the second chamber, the lubrication circuit comprising:
- a lubricant tank (4),
- a discharge conduit (6) from the tank (4) into the first chamber (5),
- a ventilation conduit (8) connecting the first chamber (5) to the second chamber (2),
- a lubricant recovery conduit (10) connecting the second chamber (2) to the tank (4) and equipped with a pump (11) forcing a flow towards the tank (4), and an outlet ventilation conduit (9) connecting the first chamber (5) to a medium external to the circuit, an evacuation conduit (20) connecting to the recovery conduit (10;
- 37) between the pump (11) and the tank (4) and leading to an outlet (21), the evacuation conduit (20) being equipped with a discharge valve (22) preventing backflows to the recovery conduit and configured to open when the pressure in the recovery conduit exceeds a predetermined overpressure threshold,
- a control valve (23) on the ventilation conduit (8),
- a depressurisation conduit (38) connected to the control valve (23) and leading to a depressurisation outlet (24), and
- a valve control conduit (25) originating from the evacuation conduit downstream from the discharge valve (22),
- wherein the valve is configured to bring the ventilation conduit (8) into communication with the depressurisation conduit (38) when a pressure threshold is reached in the control conduit.
Dependencies are inferred from the claim text.