Patent ID: 7442006
Filing Date: 2008-10-28
Classification: F04D,Y10T

Abstract:
1. An integrated assembly for a centrifugal compressor on an engine body of a gas turbine engine with a central axis, the centrifugal compressor having an impeller disposed to receive an axially oriented airflow, accelerate the airflow, and expel the airflow radially, the centrifugal compressor further having a compressor body, the integrated assembly comprising: a shroud coaxial with the central axis, the shroud surrounding the impeller and providing an inlet for receiving the axially oriented airflow, the shroud having a plurality of diffuser vanes integral with the shroud and extending axially from a downstream surface of the shroud; a ring coaxial with the central axis, the ring having an upstream surface disposed for fixed attachment to the plurality of diffuser vanes, the ring with a rim extending axially from a perimeter of the ring and away from the downstream surface of the shroud; a band disposed coaxially with and surrounding the rim, the band having an upstream edge proximate to the downstream surface and a downstream edge distal to the downstream surface, the band having an outwardly-extending flange along the downstream edge; a plurality of deswirler vanes attached to both the rim and the band to hold the rim and the band in spaced relationship; wherein the radially oriented airflow expelled from the impeller flows through a diffuser passage formed between the shroud and the ring and flows thereafter through a deswirler passage formed between the rim and the band; and a compressor housing disposed to removably attach the shroud to the compressor body; wherein the compressor housing forms a redirection passage between the diffuser passage and the deswirler passage.