TURBINE COMPRESSOR VANE

A compressor vane (62) can comprise at least one of four leakage control structures comprising a leading edge axial stack (160) near the root (128) of the vane (62), a portion (150) ofthe inner platform (132) of an inner band (86) extending forward and having a radiused geometry, a negative dihedral...

Ausführliche Beschreibung

Gespeichert in:

Bibliographische Detailangaben
Hauptverfasser:	FALK, Eric Andrew, WOOD, Peter John, TARNOWSKI, Andrzej Tomasz, BRZOZOWSKI, Jacek Michal, MOECKEL, Curtis William
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	BLASTING CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TOTRANSPORTATION ENGINE PLANTS IN GENERAL GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS HEATING LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINSTCLIMATE CHANGE WEAPONS
Online-Zugang:	Volltext bestellen
Tags:	Tag hinzufügen Keine Tags, Fügen Sie den ersten Tag hinzu!

Beschreibung
Zusammenfassung:	A compressor vane (62) can comprise at least one of four leakage control structures comprising a leading edge axial stack (160) near the root (128) of the vane (62), a portion (150) ofthe inner platform (132) of an inner band (86) extending forward and having a radiused geometry, a negative dihedral (210) shape to the airfoil body along the leading edge (120) and adjacent the root (128), and a trailing edge axial stack (170) for at least a portion of the trailing edge (122) ofthe vane (62) near the root (128). These leakage control structures increase operating efficiency ofthe turbine (10) where the efficiency is normally decreased due to leakage flow (96) from higher pressure stages of the compressor (22) to lower pressure stages.