This present invention in aerospace engineering correlation to an aircraft system which provides anti-icing, and which also can be ordered to control in an alternative mode to provide anti-icing or boundary layer rule.
Hot compressed flow is discharged from a cavity to other side of the leading edge, which through a multitude of small holes in the leading edge skin surface into the air-flow injecting on the leading edge. At first embodiment the anti-icing system utilizes part of air control system in existence for a laminar flow control process. Instead of sucking air into the wing, it is done in the laminar flow control mode, this flow is reversed in the anti-icing level, blowing hot compressed air out of the wing surface. In a second incorporation, the anti-icing system is used solely in the anti-icing method.
It is in the history of aerospace engineering, Most widely used wing anti-icing system in commercial turbo-fan aircraft is the bleed air method. In this system, high pressure, high temperature air is fed through the compressor of the engine which again discharged through a perforated tube which positioned within a leading edge chamber of the wings (or other aircraft structure) and as a spray against the inner surface of the wing leading edge outer surface. Bleed air anti-icing system is generally an “on-off” type system without any modulating capability. But the sizing criteria for the system is a maximum anti-icing efforts during idle gradient. Since bleed air temperature and pressure are very low at this power setting system, the mass flow must be high enough.
The anti-icing air, which after heating up the inside of the leading edge skin, will pass overboard at a fairly high temperatures. This dump loss can exceed 50% of the energy supplied in system.
Other thought is that, as turbo-fan engines are meant for higher propulsion efficiency, but the gas generators become smaller and the penalties from bleed air flow becomes larger. Modern turbo-prop engine gas generators are becoming small, so that the amount of bleed air flow required for the anti-icing and cabin pressurization can become more disallow.
There are a many number of other deicing and anti-icing systems in use other than the engine bleed air system described above. Such system is to utilize inflatable rubber boots at the aircraft leading edge portions, which is being widely used for deicing on slower propeller airplanes. Nevertheless, the boot does not provide a smooth enough surface for high performance aircraft.
Glycol anti-icing is another system in aerospace engineering, In that glycol is discharged over the surface areas where anti-icing is desired. But, this leaves a sticky residue on the wing which helps collect dust, and so that frequent wing cleaning is required. Yet, the cost and trouble of refueling glycol tanks are undesirable features.
Further another method is to utilize in aerospace engineering is electric resistance heaters which attached to the both sides of the leading edge skin surface. This can be a very energy efficient system. But the drawback is that in the case of a defect, the field repair can be difficult and there can be a lay up of an aircraft for an undesirably long period of time.
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