A turboprop powered aircraft having a cowling or nacelle surrounding the engine, said cowling incorporates an air inlet and internal ducting to the engine wherein the inlet incorporated anti icing ducts, said inlet shape has a closed oval or other non-circular shape that is not coaxial to the engine propeller drive shaft. Inlet anti-icing heating duct means are provided for channeling a portion of the engines exhaust to the interior of the inlet rim. A further improvement in inlet efficiency can be achieved by reducing the thickness of the inlet cross-section, but this results in less space available for the hot exhaust connections. To provide for the inlet reduced section thickness, the exhaust flow connections also incorporate reduced thickness sections to facilitate cooling and insulation of the adjacent cowling and inlet duct surfaces from the excessive heat associated with the hot exhaust gas connection. Additional cooling means utilize air flow from openings in the engine cowling that are channeled to cool internal surfaces of the cowling that may be exposed to excessive heat.
Aircraft turboprop engine inlet compact profile configuration to improve air intake efficiency and without loss of anti-icing ability
2024-06-18
Patent
Electronic Resource
English
AIRCRAFT TURBOPROP ENGINE INLET COMPACT PROFILE CONFIGURATION
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