Mixed flow compressor for gas turbine engine

A compressor 10 for a gas turbine engine comprises a casing 16, a mixed flow stage 12 and a further mixed, or a centrifugal, flow stage 14. The stages 12, 14 are axially spaced apart, and a bearing arrangement 20 is located between the stages 12, 14 to provide means for rotatably mounting rotors 26,...

Ausführliche Beschreibung

Gespeichert in:

Bibliographische Detailangaben
1. Verfasser:	ROBERT CHARLES TONKS
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT PUMPS POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS PUMPS FOR LIQUIDS OR ELASTIC FLUIDS WEAPONS
Online-Zugang:	Volltext bestellen
Tags:	Tag hinzufügen Keine Tags, Fügen Sie den ersten Tag hinzu!

Beschreibung
Zusammenfassung:	A compressor 10 for a gas turbine engine comprises a casing 16, a mixed flow stage 12 and a further mixed, or a centrifugal, flow stage 14. The stages 12, 14 are axially spaced apart, and a bearing arrangement 20 is located between the stages 12, 14 to provide means for rotatably mounting rotors 26, 44 in the casing 16. The rotors 26, 44 may be carried on a common shaft 18 which is rotatably mounted in the casing 16 by a bearing support assembly 56. The bearing support assembly 56 may include a frusto-conical section 58, a cylindrical section 60 and radial sections 62, 64. The bearing means 20 may comprise journal bearings and thrust bearings, and a diffuser 28 may be located between the stages 12, 14.