Aircraft incorporating a low-temperature bleed system
An aircraft incorporating a bleed system for extracting compressed air from the aircraft main engines to be used as a source of pressurized air for the aircraft. The bleed air system includes a first pre-cooler installed at one of the main engines nacelle and coupled with the bleed duct, and adapted for cooling down the bleed air extracted from the main engine, and a second pre-cooler installed at the pylon and coupled with bleed duct and downstream the first pre-cooler. The working temperature of the aircraft bleed system is reduced, down to max 200° C., so that the dimensions of an Over Heat Detection System (OHDS) is reduced.
1. An aircraft incorporating a bleed air system for extracting compressed air from aircraft main engines to be used as a source of pressurized air for the aircraft, the bleed air system comprising a bleed air duct running from the aircraft main engines and passing through an aircraft pylon and wings;
wherein the bleed air system comprises:
a first pre-cooler installed at one of a main engine nacelle and coupled with the bleed air duct, and adapted for cooling down bleed air extracted from the main engine; and
a second pre-cooler installed at the pylon and coupled with the bleed air duct and downstream the first pre-cooler; and
wherein a wing anti-ice protection system is coupled with the bleed air duct upstream the second pre-cooler, so that pressurized air for wing anti-ice protection system can be supplied by the first pre-cooler.
2. The aircraft according to claim 1 , wherein the second pre-cooler comprises an ozone converter.
3. The aircraft according to claim 1 , further comprising an Over Heat Detection System for the bleed air duct, and wherein the Over Heat Detection System extends exclusively between the first and second pre-coolers.
4. The aircraft according to claim 1 , further comprising air-conditioning packs coupled with the bleed air system downstream the second pre-cooler.