GUIDE VANE RING AND ROTOR BLADE RING FOR A TURBOFAN ENGINE

A guide vane ring and/or a rotor blade ring for a low-pressure turbine of an aircraft gas turbine of a turbofan engine includes a plurality of airfoils disposed consecutively in a direction of rotation. The plurality of airfoils includes a first airfoil and a second airfoil adjacent to the first air...

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Bibliographische Detailangaben
Hauptverfasser:	Mueller-Schindewolffs, Christoph, Ramm, Guenter, Brettschneider, Markus, Malzacher, Franz
Format:	Patent
Sprache:	eng
Schlagworte:	BLASTING COMBUSTION ENGINES ENGINE PLANTS IN GENERAL HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION 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 guide vane ring and/or a rotor blade ring for a low-pressure turbine of an aircraft gas turbine of a turbofan engine includes a plurality of airfoils disposed consecutively in a direction of rotation. The plurality of airfoils includes a first airfoil and a second airfoil adjacent to the first airfoil in the direction of rotation. The first and second airfoils are disposed relative to each other such that a ratio e/t, viewed in a conical section, results froma smallest free flow cross-section e taken on the pressure side of the first airfoil from its trailing edge to a suction side of the second airfoil, anda pitch t of the airfoils, such that e/t is less than 0.31, (e/t