OPTIMAL LIFT DESIGNS FOR GAS TURBINE ENGINES

Turbine assemblies for gas turbine engines are provided. In one embodiment, a turbine assembly 75 includes a row 84 of circumferentially adjacent turbine rotor blades 74, each blade 74 in the row 84 of blades 74 including an airfoil 86 defining a chord ( c ) extending axially between opposite leadin...

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Bibliographische Detailangaben
Hauptverfasser:	DAILEY, Lyle Douglas, WADIA, Aspi Rustom, JOHNSON, Christopher Ryan, MOLLMANN, Daniel Edward
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	BLASTING ENGINE PLANTS IN GENERAL HEATING 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:	Turbine assemblies for gas turbine engines are provided. In one embodiment, a turbine assembly 75 includes a row 84 of circumferentially adjacent turbine rotor blades 74, each blade 74 in the row 84 of blades 74 including an airfoil 86 defining a chord ( c ) extending axially between opposite leading 96 and trailing edges 98 of the airfoil 86. The chords ( c ) in a mid-span region ( s mid ) of each blade are shorter than the chords ( c ) in span regions adjacent to the blade root 92 and the blade tip (94). In another exemplary embodiment, a turbine assembly 75 includes a row of circumferentially adjacent turbine stator vanes 72, each vane 72 in the row of vanes 72 including an airfoil 100 defining a chord ( c ) extending axially between opposite leading and trailing edges of the airfoil 100. The chords ( c ) in a mid-span region of each vane 72 are shorter than the chords ( c ) in span regions adjacent to the vane root 102 and the vane tip 104. A turbine rotor blade for a gas turbine engine also is provided.