|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||60/3907 ; 60/3929|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 5 인용 특허 : 4|
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.
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 coup...