Surge protected gas turbine engine for providing variable bleed air flow

Claim 1

A surge protected gas turbine engine for providing a variable flow of bleed air without operation near full load condition, comprising: a radial inflow, axial outflow turbine wheel rotatable about an axis; an annular combustor located about said axis for producing hot gases of combustion; means, including an annular nozzle, connected to said combustor and disposed about said turbine wheel such that hot gases of combustion impinge upon the turbine wheel to drive the same about said axis; a pair of radial inflow, axial outflow, centrifugal compressors coupled to said turbine wheel to be driven thereby, said rotary compressors each having an inlet and an outlet being connected in series to thereby define a first stage compressor and a second stage compressor, said first stage compressor being a single stage, centrifugal compressor having a high specific speed (N s in excess of about 100) where ##EQU3## and N=rpm of the first stage compressor, CFS=first stage compressor inlet volumetric flow in ft 3 /sec, and H ad =adiabatic head in ft., said second stage compressor further being back to back with said turbine wheel; means connecting said second stage compressor outlet to said combustor to provide compressed air thereto; means associated with at least said first stage compressor outlet for obtaining bleed air therefrom; variable inlet guide vanes for said first stage inlet and selectively movable between open, closed and intermediate positions; a sensor in said bleed air obtaining means; and means responsive to said sensor for moving said guide vanes toward said closed position as bleed air flow decreases, and toward said open position as bleed air flow increases.