Patent ID: 8336288

Claim:
A gas-turbine engine, comprising: a fan; a fan casing; an engine casing; a fan duct positioned between the fan casing and the engine casing; high-pressure and low-pressure turbines arranged behind each other in a flow direction in the engine casing; and a bleeding mechanism positioned on an upstream side of the low-pressure turbine for bleeding at least part of an airflow leaving the high-pressure turbine radially into the fan duct; wherein the bleeding mechanism includes a plurality of air openings leading into the fan duct and a plurality of valve flaps for opening and closing the air openings; wherein the valve flaps are moveable directly into the airflow between the high-pressure turbine and the low-pressure turbine when the air openings are open to at least partially block the airflow between the high-pressure turbine and the low-pressure turbine and divert that airflow into the fan duct; wherein, when the valve flaps are moved directly into the airflow to at least partially block the airflow, portions of the valve flaps that block the airflow do so to an extent that they extend radially inward of the engine casing.