Oil system for aircraft engine having features to prevent drainage of component
An aircraft engine having a centerline, has: an oil system including: a component located above the centerline and having an inlet and an outlet; an oil circuit interconnecting the components and including an input line connected to the inlet and an output line connected to the outlet, the input line defining an input U-shaped section, the output line defining an output U-shaped section; a valve connected on the input line or the output line and located between the component and a respective one of the input U-shaped section and the output U-shaped section; and an anti-siphon line connecting the input line to the output line and defining a flow path of a lesser flow circulating area of the input line and the output line, the input U-shaped section, the output U-shaped section, and the component located between connection points defined between the anti-siphon line and the input and output lines.
1 . An aircraft engine having a centerline, comprising:
an oil system including:
a component located above the centerline and having an inlet and an outlet;
an oil circuit fluidly connected to the component, the oil circuit including an input line fluidly connected to the inlet and an output line fluidly connected to the outlet, the input line defining an input U-shaped section, the output line defining an output U-shaped section;
a valve fluidly connected on the input line or the output line, the valve located between the component and a respective one of the input U-shaped section and the output U-shaped section; and
an anti-siphon line fluidly connecting the input line to the output line, the anti-siphon line defining a flow path of a lesser flow circulating area of the input line and the output line, the input U-shaped section, the output U-shaped section, and the component located between connection points defined between the anti-siphon line and the input and output lines.
2 . The aircraft engine of claim 1 , wherein the valve is located on the output line.
3 . The aircraft engine of claim 1 , wherein the valve is one of two valves, each of the two valves fluidly connected to a respective one of the input line and the output line.
4 . The aircraft engine of claim 3 , wherein each of the two valves is located between the component and a respective one of the input U-shaped section and the output U-shaped section.
5 . The aircraft engine of claim 3 , wherein the two valves are located closer to the component than the connection points of the anti-siphon line.
6 . The aircraft engine of claim 1 , wherein the component is an air-cooled oil cooler.
7 . The aircraft engine of claim 1 , wherein the flow circulating area of the anti-siphon line is selected such that a pressure drop of an oil flow through the anti-siphon line while the aircraft engine is running is greater than a pressure drop through the component.
8 . The aircraft engine of claim 7 , wherein the flow circulating area of the anti-siphon line is at most 5% of that of the input and output lines.
9 . The aircraft engine of claim 1 , wherein the anti-siphon line is connected to both of the input line and the output line at respective input and output connection points, a distance along a direction perpendicular to a ground between each of the input and output connection points and a respective one of lowest points of the input and output U-shaped sections being at least three times a diameter of a respective one of the input and output lines.
10 . An oil system for an aircraft engine, comprising:
a component located above a central axis of the aircraft engine, the component containing a volume of oil during operation of the aircraft engine, the component having an inlet and an outlet;
an oil circuit fluidly connected to the component, the oil circuit including an input line fluidly connected to the inlet and an output line fluidly connected to the outlet, the input line defining an input U-shaped section, the output line defining an output U-shaped section;
a valve fluidly connected on the input line or the output line, the valve located between the component and a respective one of the input U-shaped section and the output U-shaped section; and
an anti-siphon line fluidly connecting the input line to the output line while bypassing the input U-shaped section and the output U-shaped section, a flow circulating area of the anti-siphon line being less than that of the input line and of the output line.
11 . The oil system of claim 10 , wherein the valve is located on the output line.
12 . The oil system of claim 10 , wherein the valve is one of two valves, each of the two valves being fluidly connected to a respective one of the input line and the output line.
13 . The oil system of claim 12 , wherein each of the two valves is located between the component and a respective one of the input U-shaped section and the output U-shaped section.
14 . The oil system of claim 12 , wherein the two valves are located closer to the component than the connection points of the anti-siphon line.
15 . The oil system of claim 10 , wherein the component is an air-cooled oil cooler.
16 . The oil system of claim 10 , wherein the flow circulating area of the anti-siphon line is selected such that a pressure drop of an oil flow through the anti-siphon line while the aircraft engine is running is greater than a pressure drop through the component.
17 . The oil system of claim 16 , wherein the flow circulating area of the anti-siphon line is at most 5% of that of the input and output lines.
18 . The oil system of claim 10 , wherein the anti-siphon line is connected to both of the input line and the output line at respective input and output connection points, a distance along a direction perpendicular to the central axis between each of the input and output connection points and a respective one of lowest points of the input and output U-shaped sections being at least three times a diameter of a respective one of the input and output lines.