Patent ID: 8596076
Filing Date: 2013-12-03
Classification: F02C

Abstract:
1. A variable pressure ratio gas turbine engine, comprising: a high pressure spool having a high pressure turbine and a high pressure compressor mechanically driven by said high pressure turbine; a lower pressure spool having a lower pressure turbine and a lower pressure compressor mechanically driven by said lower pressure turbine; a combustor; and a flow control system structured to selectively provide flow to said combustor from said high pressure compressor and said lower pressure compressor, wherein an inlet of said high pressure compressor is in fluid communication with a discharge of said lower pressure compressor, further comprising a compressor bypass flowpath in parallel fluid communication with the discharge of said lower pressure compressor with respect to the inlet of said high pressure compressor; and wherein said high pressure compressor employs a plurality of shrouded compressor blades, and wherein said compressor bypass flowpath has an inner flowpath wall formed in part by shrouds of said shrouded compressor blades.