GAS TURBINE COMPRESSOR

A compressor for a gas turbine, in particular of an aircraft engine, having a plurality of arrays (10-25) of flow-directing elements that are serially disposed in a through flow direction from a compressor inlet to a compressor outlet (1, 2); at least one upstream, mistuned array (20) of flow-direct...

Ausführliche Beschreibung

Gespeichert in:

Bibliographische Detailangaben
1. Verfasser:	SCHÖNENBORN, Harald
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 NON-POSITIVE DISPLACEMENT PUMPS POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS PUMPS FOR LIQUIDS OR ELASTIC FLUIDS STEAM ENGINES WEAPONS
Online-Zugang:	Volltext bestellen
Tags:	Tag hinzufügen Keine Tags, Fügen Sie den ersten Tag hinzu!

Beschreibung
Zusammenfassung:	A compressor for a gas turbine, in particular of an aircraft engine, having a plurality of arrays (10-25) of flow-directing elements that are serially disposed in a through flow direction from a compressor inlet to a compressor outlet (1, 2); at least one upstream, mistuned array (20) of flow-directing elements and at least one downstream, mistuned array (22) of flow-directing elements each having at least two types of flow-directing elements that differ structurally from one another; and at least 80%, in particular at least 95% of the rotor blades (45) of a furthest downstream rotor blade array (25) that, in the through flow direction, is configured downstream of the downstream, mistuned array (22) of flow-directing elements, being mutually identically constructed.