Inertial particle separator for aircraft engine
An inertial particle separator, having: an inlet duct defining an intake; an intermediate duct extending from the inlet duct to an engine inlet; a bypass duct in fluid communication with and extending downstream from the inlet duct, the bypass duct defining an outlet communicating with the environment of the aircraft engine, a splitter defined at an intersection of a wall of the bypass duct and a wall of the intermediate duct; a splitter vane within the intermediate duct and having a leading edge located upstream of the splitter relative to a flow circulating through the separator, the splitter vane and the wall of the intermediate duct defining a channel therebetween; and a porous plate extending across the channel and defining openings sized so as to aggregate ice and be blocked by ice under icing conditions.
1. An inertial particle, separator (IPS) communicating with an engine inlet of an aircraft engine, comprising:
an inlet duct defining an intake communicating with an environment outside of the aircraft engine;
an intermediate duct extending from the inlet duct to the engine inlet;
a bypass duct in fluid communication with and extending from the inlet duct in a downstream direction relative to a flow circulating through the IPS, the bypass duct defining an outlet communicating with the environment outside of the aircraft engine;
a splitter defined at an intersection of a wall of the bypass duct and a wall of the intermediate duct;
a splitter vane within the intermediate duct and having a leading edge located upstream of the splitter relative to the flow circulating through the IPS, the splitter vane and the wall of the intermediate duct defining a channel therebetween; and
a porous plate extending across the channel and defining openings sized so as to aggregate ice such that the channel is blocked by ice under icing conditions.
2. The IPS of claim 1 , wherein the splitter vane has an airfoil-shaped cross-section.
3. The IPS of claim 1 , wherein an extrapolation of the wall of the bypass duct connects to the leading edge of the splitter vane and wherein an extrapolation of a suction side of the splitter vane tangentially merges with the wall of the intermediate duct.
4. The IPS of claim 1 , wherein the leading edge of the splitter vane is located radially outwardly of the splitter relative to a central axis of the aircraft engine.
5. The IPS of claim 1 , wherein the inlet duct curves radially away from a central axis of the aircraft engine from the intake to a mid-section of the inlet duct and curves radially toward the central axis of the aircraft engine rotation from the mid-section to the splitter.
6. The IPS of claim 1 , wherein the bypass duct extends radially away from a central axis of the aircraft engine downstream of the splitter.
7. The IPS of claim 1 , wherein the splitter vane has a chord length extending from the leading edge of the splitter vane to a trailing edge of the splitter vane, the porous plate located at mid-chord between the leading edge and the trailing edge.
8. The IPS of claim 1 , wherein the porous plate perpendicularly intersects the splitter vane and/or the wall of the intermediate duct.
9. The IPS of claim 1 , wherein the porous plate is a screen made with wires, each having a diameter ranging from 0.15 to 3.5 millimeters and spaced apart from one another by a distance ranging from 0.5 to 12 millimeters to form the openings.
10. An inertial particle separator (IPS) communicating with an engine inlet of an aircraft engine, comprising:
an inlet duct defining an intake communicating with an environment outside the aircraft engine;
an intermediate duct extending from the inlet duct to the engine inlet;
a bypass duct in fluid communication with and extending downstream from the inlet duct, the bypass duct defining an outlet communicating with the environment outside of the aircraft engine;
a splitter defined at an intersection of a wall of the bypass duct and a wall of the intermediate duct;
a channel defined through the splitter and extending from the wall of the bypass duct to the wall of the intermediate duct; and
a porous plate extending across the channel and defining openings sized so as to aggregate icing droplets and be blocked by an ice coating under icing conditions.
11. The IPS of claim 10 , wherein the channel has opposed side walls each extending from the wall of the bypass duct to the wall of the intermediate duct, a splitter vane defined by one of the opposed side walls of the channel and a first portion of the wall of the intermediate duct extending from the intersection to the channel.
12. The IPS of claim 11 , wherein the intersection is defined by a leading edge of the splitter vane.
13. The IPS of claim 10 , wherein the channel is defined through a portion of the wall of the bypass duct where the wall of the bypass duct extends radially toward a central axis of the aircraft engine in a downstream direction relative to a flow circulating through the bypass duct.
14. The IPS of claim 10 , wherein the inlet duct curves radially away from an axis of rotation of the aircraft engine from the intake to a mid-section of the inlet duct and curves radially toward the axis of rotation from the mid-section to the splitter.
15. The IPS of claim 10 , wherein the bypass duct extends radially away from an axis of rotation of the aircraft engine downstream of the splitter.
16. The IPS of claim 10 , wherein the porous plate is located at a mid-length of the channel.
17. The IPS of claim 10 , wherein the porous plate is normal relative to a flaw direction of an airflow circulating therethrough.
18. The IPS of claim 10 , wherein a cross-sectional area of the channel is less than that of the intermediate duct.