Patent ID: 7628018
Filing Date: 2009-12-08
Classification: F01D,F02C,F04D,F05D,Y02T

Abstract:
1. A high performance gas turbine gas generator comprising: a rotatable shaft defining an axial direction and a radial direction; a single compressor stage comprising a dual-entry high pressure ratio centrifugal compressor having a housing and a bladed impeller mounted on the shaft and defining with the housing a pair of opposed axially directed inlets and a single radially directed outlet; a combustor assembly operatively connected to receive compressed air from the centrifugal compressor outlet and configured for combusting fuel with the compressed air to produce combustion gases; a radial inflow turbine mounted on the shaft and operatively connected to receive combustion gases from the combustor assembly through a radially directed inlet and configured to partially expand the received combustion gases to drive the centrifugal compressor, the radial inflow turbine also configured to direct the partially expanded combustion gases through a generally axially directed turbine outlet, wherein the shaft is rotatably supported by a pair of bearing assemblies positioned at opposed axial ends of the centrifugal compressor, wherein the radial inflow turbine is mounted on a cantilevered portion of the shaft extending axially outboard of one of the bearing assemblies, wherein the centrifugal compressor inlets are further configured to provide, at a rated mass flow and speed (RPM), a maximum compressor inlet Mach Number of about 1.4 or less, and wherein the centrifugal compressor is further configured to provide at the rated speed and mass flow, a pressure ratio of about 12:1 or greater.