GAS TURBINE ENGINE FOR AN AIRCRAFT

A gas turbine engine (1) for an aircraft comprising a compressor (3), a combustion chamber (7), and a turbine (5) having at least one stator (8, 10), and at least one rotor (9, 11). Each stator and rotor formed by a plurality of blades, a fluid channel formed between two consecutive blades, and each...

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Bibliographische Detailangaben
1. Verfasser:	GARDE LA CASA, Alexandre
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	A gas turbine engine (1) for an aircraft comprising a compressor (3), a combustion chamber (7), and a turbine (5) having at least one stator (8, 10), and at least one rotor (9, 11). Each stator and rotor formed by a plurality of blades, a fluid channel formed between two consecutive blades, and each blade having two opposing surfaces. The compressor (3) is in fluid communication with a first group of stator channels (28), and the combustion chamber (7) is in fluid communication with a second group of stator channels (29), such that heat exchange can be performed through two opposing surfaces of at least one stator blade. The outer and the inner walls (2, 4) defining a duct for the passage of the heated fluid through the rotor blades, and the outer wall (4) being also arranged for directing the compressed air towards the combustion chamber (7).