Fluid additive system
AssigneeRaytheon Technologies Corporation
InventorsNigel David Sawyers-Abbott, Kenneth N. Baker
Life of this patent
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Abstract
A lubrication system for a gas turbine engine includes a primary fluid tank to receive a primary fluid, at least one secondary fluid tank to receive at least one fluid additive, and a mixer. The mixer has at least a first inlet in fluid communication with the primary fluid tank and a second inlet in fluid communication with the at least one secondary fluid tank. The mixer has at least one outlet that delivers a mixture of the primary fluid and the at least one fluid additive to a gas turbine engine component.
Claims24
A lubrication system for a gas turbine engine comprising:
- a primary fluid tank to receive a primary fluid;
- at least one secondary fluid tank to receive at least one fluid additive;
- and
- a mixer having at least a first inlet in fluid communication with the primary fluid tank and a second inlet in fluid communication with the at least one secondary fluid tank, and including at least one outlet that delivers a mixture of the primary fluid and the at least one fluid additive to a gas turbine engine compartment, and wherein the mixture of the primary fluid and the at least one fluid additive is directly fed from the at least one mixer outlet into an inlet to the gas turbine engine component.
A method comprising:
- providing a primary fluid tank to receive a primary fluid, at least one secondary fluid tank to receive at least one fluid additive, and a mixer having at least a first inlet in fluid communication with the primary fluid tank and a second inlet in fluid communication with the at least one secondary fluid tank;
- mixing the primary fluid and the at least one fluid additive in the mixer and delivering a mixture of the primary fluid and the at least one fluid additive to a gas turbine engine component via at least one mixer outlet;
- and
- directly feeding the mixture of the primary fluid and the at least one fluid additive from the at least one mixer outlet into an inlet to the gas turbine engine component.
Dependencies are inferred from the claim text.