754results about "Power plant cooling arrangments" patented technology

An unmanned helicopter has a fuselage (1a) with a main body (4) and a tail body; a main rotor (6) provided above the main body (4) and driven by an engine in the fuselage (1a); a tail rotor placed at the rear of the tail body (5); a pair of left and right support legs (8,8) extended downward from lower left and lower right sections of the main body (4); a pair of left and right skids (9) provided at lower ends of the support legs (8,8) and positioned, in a front view, more on the outside in the width direction of the fuselage (1a) than the main body (4); and a radiator (71) positioned, in a side view, more on the front side than the front edges of the skids (8) and formed so as to extend downward from the vicinity of a bottom surface (83) of a main body front section so that an airflow receiving surface of the radiator is oriented in the front-rear direction of the fuselage (1a). Outer edges, in the width direction of the fuselage (1a), of the radiator (71) are projected outward, in the front view, from outer edges of a main body bottom surface (83) near the radiator (71). Also, outer edges (71a) of the radiator (71) are positioned more on the inside, in the width direction of the fuselage (1a), than the skids (9).

An improved passive cooling system for an aircraft APU compartment that includes a lightweight annular air-cooled oil cooler that is strategically oriented and shrouded to face its annular inlet away axially downstream from the exhaust of the APU to make it inherently fireproof to flames from the APU or any location within the APU compartment that fuel can accumulate.

A low drag ducted ram air turbine generator and cooling system is provided. The ducted ram air turbine generator and cooling system has reduced drag with respect to prior ram air turbine generator systems while extracting dynamic energy from the air stream during the complete range of intended flight operating regimes. A centerbody / valve tube having an aerodynamically shaped nose is slidably received in a fairing and primary structure to provide a variable inlet area. An internal nozzle control mechanism attached to the valve tube positions nozzle control doors to provide variable area nozzles directing air flow to the turbine stator and rotor blades to maintain optimum generator efficiency. An alternate embodiment includes an annular internal nozzle having interleaved panels to modulate the air flow to the turbine.

Provided is a method for providing fire shield protection to an aircraft auxiliary power unit, or portion thereof, or to other aircraft systems.

An aircraft engine includes a precooler disposed within a nacelle. The precooler defines an ambient air passage and a bleed air passage. Air passes through the precooler from an ambient air inlet to an ambient air outlet. Bleed air passes through the precooler from a bleed air inlet to a bleed air outlet. Heat is transferred between the air and the bleed air via heat exchange within the precooler. At least one pressure relief door disposed proximate to the air outlet of the engine. A controller is operatively connected to the pressure relief door. The controller at least opens the pressure relief door based on a demand for increased flow of air through the ambient air passage.