Airbus Helicopters Deutschland Gmbh

Ralf Braeutigam

Sebastian Mores

Christian Wehle

Frank Loeser

Johannes Frese

Michael Stadler

An aircraft with a fuselage that defines at least an interior region and a drive system accommodating region, the drive system accommodating region being arranged inside the fuselage and comprising at least one fire protection zone that is defined by at least one associated firewall arrangement, the at least one fire protection zone accommodating at least one engine within the at least one associated firewall arrangement such that the associated firewall arrangement defines a fire-resistant separation between the at least one engine and the interior region of the fuselage, wherein the at least one associated firewall arrangement comprises at least one air duct for ducting a hot air flow that is generated in operation of the aircraft independent from heat generation of the at least one engine.

Aircraft with a fuselage that defines at least an interior region and a drive system accommodating region

An aircraft having at least one first and one second engine, each engine comprising a main air inlet opening, a by-pass air inlet opening and a bleed air outlet, said main air inlet opening being provided with an inlet barrier filter for filtering a main air stream through said main air inlet opening into the engine, said by-pass air inlet opening being provided with a by-pass door that is operable by an associated operating element to enable a by-pass air stream through said by-pass air inlet opening into the engine, and said bleed air outlet being provided for creating an outgoing bleed air stream going out of the engine in operation, at least one associated operating element being controllable by an outgoing bleed air stream.

Aircraft with an engine having a by-pass air inlet opening and a bleed air outlet

A helicopter with a fuselage, at least two engines substantially inside said fuselage, an air intake for each of said two engines and at least two separate lateral air inlet ports for said at least two engines in said fuselage. Said separate lateral air inlet ports being arranged on sides opposed to each other relative to an essentially vertical midplane of said fuselage and oriented with their respective cross section substantially parallel to a forward flight direction of the helicopter. At least one frontal air inlet port with a forward portion is provided separate from said lateral air inlet ports, said frontal air inlet port being located on a gear cowling of the fuselage oriented with its cross section substantially perpendicular to the forward flight direction of the helicopter.

Helicopter with engine air intakes

An air inlet () for an engine () of an aircraft (), the air inlet () having a duct () feeding outside air to said engine () together with a filter system combining at least one filter () and at least one bypass device (). Said filter () and said bypass device () are fastened on a common support () situated at one end of said duct () and on a flank of a fuselage () of said aircraft (). Said bypass device () comprises a cover () and an actuator () controlling opening of said cover (). Thus, when said filter () no longer allows outside air to pass therethrough, said cover () is opened, and outside air passes via the bypass device () in order to feed said engine () with outside air.

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Tapfheim, Germany

Ralf Braeutigam