Surge protected gas turbine engine for providing variable bleed

Details Surge protected gas turbine engine for providing variable bleed Surge protected gas turbine engine for providing variable bleed

1988-05-23

1991-02-05

Casaregola, Louis J.

Power plants

Combustion products used as motive fluid

60 3929, F02C 7057

Patent

active

049894030

ABSTRACT:
Surge protection is achieved in a turbine engine intended to provide varying quantities of bleed air and having two compressor stages 48, 36 by providing the inlet 56 of the first stage 48 with variable inlet guide vanes 58, 60. The first stage compressor 48 is a high specific speed, single stage centrifugal compressor whose stable operating characteristics are highly sensitive to inlet guide vane geometry, thereby allowing variations in such geometry to be employed to prevent compressor surge.

REFERENCES:
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patent: 4428194 (1984-01-01), Stokes et al.
patent: 4550561 (1985-11-01), Coffinberry
Csanody, G. T. Turbomachines McGraw-Hill, 1964; pp. 15-17.
Treager, I. E. Aircraft Gas Turbine Engine Technology McGraw-Hill, 1970; p. 10.

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