Anti-icing system and aircraft
An anti-icing system according to the present invention includes: a piccolo tube that includes a flow path through which heated gas flows in the longitudinal direction from a rear end to a front end, and a plurality of ejection holes provided along the longitudinal direction to make the flow path communicate with an outside; and an engine serving as a supply source that supplies the heated gas toward the piccolo tube. The piccolo tube is decreased in an area of the flow path in a stepwise manner or in a continuous manner in the longitudinal direction, and has a continuous side surface provided with the ejection holes.
1. An anti-icing system, comprising:
a piccolo tube that includes a flow path through which heated gas flows in a longitudinal direction from a rear end to a front end, and a plurality of ejection holes provided along the longitudinal direction to make the flow path communicate with an outside; and
a supply source that supplies the heated gas toward the piccolo tube, wherein
the piccolo tube is decreased in an area of the flow path in a stepwise manner or in a continuous manner in the longitudinal direction, and has a continuous side surface provided with the ejection holes being spaced apart along the continuous side surface from one another and from a surface subjected to ejection of the heated gas, and
the piccolo tube is disposed such that a distance from each of the ejection holes to the surface subjected to ejection of the heated gas is constant along the longitudinal direction of the piccolo tube,
wherein the piccolo tube is configured of a plurality of pipes that are connected with one another in the longitudinal direction while central axes of the respective pipes are eccentric to one another, the pipes having different inner diameters and different outer diameters from one another.
2. The anti-icing system according to claim 1 , wherein the piccolo tube is configured of a plurality of pipes that are connected with one another in the longitudinal direction while central axes of the respective pipes are aligned, the pipes having different inner diameters from one another and a same outer diameter.
3. The anti-icing system according to claim 1 , wherein the piccolo tube has an inner diameter and an outer diameter that decrease in a continuous manner from the rear end to the front end.
4. The anti-icing system according to claim 1 , wherein the piccolo tube has a fixed inner diameter and a fixed outer diameter from the rear end to the front end, and a spacer is inserted into the flow path to cause the diameter of the flow path to taper off.
5. The anti-icing system according to claim 1 , wherein H/d 0 is within a range of 7 to 12, where d 0 is a diameter of each of the ejection holes, and H is a distance from each of the ejection holes to a surface subjected to ejection of the heated gas.
6. The anti-icing system according to claim 1 , wherein H/d 0 is within a range of 8 to 11, where d 0 is a diameter of each of the ejection holes, and H is a distance from each of the ejection holes to a surface subjected to ejection of the heated gas.
7. The anti-icing system according to claim 1 , wherein the plurality of ejection holes are arranged in a plurality of lines.
8. The anti-icing system according to claim 1 , wherein the piccolo tube is disposed along a wing length direction of a main wing of an aircraft at a position separated from an inner surface of a leading edge of the main wing by a predetermined distance, wherein the surface subjected to ejection of the heated gas is located on the inner surface.
9. The anti-icing system according to claim 1 , wherein the system is configured to allow, at respective distances from the continuous side surface being constant along the longitudinal direction of the piccolo tube, flow of the gases radially outwardly along the continuous side surface beyond the circumferences of the respective ejection holes upon exiting through the ejection holes.
10. The anti-icing system according to claim 1 , wherein the continuous side surface fully circumferentially encloses the flow path of the gases along extents of the piccolo tube having the continuous side surface, the extents being disposed longitudinally between adjacent ejection holes along the longitudinal direction of the piccolo tube.
11. An aircraft comprising the anti-icing system according to claim 1 .
12. The aircraft according to claim 11 , wherein the anti-icing system is provided in a main wing.
13. An anti-icing system, comprising:
a piccolo tube that includes a flow path through which heated gas flows in a longitudinal direction from a rear end to a front end, and a plurality of ejection holes provided along the longitudinal direction to make the flow path communicate with an outside; and
a supply source that supplies the heated gas toward the piccolo tube, wherein
the piccolo tube is decreased in an area of the flow path in a stepwise manner or in a continuous manner in the longitudinal direction, and has a continuous side surface provided with the ejection holes being spaced apart along the continuous side surface from one another and from a surface subjected to ejection of the heated gas, and
the piccolo tube is disposed such that a distance from each of the ejection holes to the surface subjected to ejection of the heated gas is constant along the longitudinal direction of the piccolo tube,
wherein the piccolo tube is configured of a plurality of pipes that are connected with one another in the longitudinal direction while central axes of the respective pipes are aligned, the pipes having different inner diameters from one another and a same outer diameter.