IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0154258
(2005-06-15)
|
등록번호 |
US-7390163
(2008-06-24)
|
발명자
/ 주소 |
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
9 인용 특허 :
1 |
초록
▼
A multi-stage radial flow compressor and turbine includes a rotor having a first plurality of blades and a second plurality of blades radially outward from the first plurality. A stator has a plurality of blades radially positioned between the two sets of rotor blades. The stator also includes a plu
A multi-stage radial flow compressor and turbine includes a rotor having a first plurality of blades and a second plurality of blades radially outward from the first plurality. A stator has a plurality of blades radially positioned between the two sets of rotor blades. The stator also includes a plurality of combustors positioned radially outward from the stators. The rotor also has turbine blades radially outward from the combustors which are driven by the combusted gas.
대표청구항
▼
The invention claimed is: 1. A multi-stage compressor and turbine, comprising: a housing; a gas inlet coupled to the housing; a gas outlet coupled to the housing; a rotor having a first plurality of rotor blades and a second plurality of rotor blades both being positioned radially outward from the
The invention claimed is: 1. A multi-stage compressor and turbine, comprising: a housing; a gas inlet coupled to the housing; a gas outlet coupled to the housing; a rotor having a first plurality of rotor blades and a second plurality of rotor blades both being positioned radially outward from the gas inlet, the rotor being rotatable about an axis of rotation relative to the housing, the axis of rotation defining radial directions perpendicular to the axis of rotation; a stator having a first plurality of stator blades positioned radially outward from the first plurality of rotor blades and radially inward from the second plurality of rotor blades, the stator also having a plurality of combustors positioned radially outward from the second plurality of rotor blades; the rotor also having a plurality of rotor turbine blades positioned radially outward from the plurality of combustors. 2. The multi-stage compressor of claim 1, wherein: the stator has a second plurality of stator blades positioned radially outward from the second plurality of rotor blades, the plurality of combustors being positioned radially outward from the second plurality of stator blades. 3. The multi-stage compressor of claim 1, wherein: the stator has a plurality of stator turbine blades positioned radially outward from the plurality of rotor turbine blades. 4. The multi-stage compressor of claim 1, wherein: the stator has a plurality of fluid injection ports positioned radially inward of the plurality of rotor turbine blades and radially outward from the first plurality of stator blades. 5. The multi-stage compressor of claim 1, wherein: the plurality of fluid injection ports are configured to inject water. 6. The multi-stage compressor of claim 1, further comprising: a rotor blade ring attached to each of the first plurality of rotor blades, the rotor blade ring being positioned in a recess in the stator. 7. The multi-stage compressor of claim 6, further comprising: a stator blade ring attached to each of the first plurality of stator blades, the stator blade ring being positioned within a recess in the rotor. 8. A compressor and turbine, comprising: a housing; a gas inlet coupled to the housing; a gas outlet coupled to the housing; a rotor having a first plurality of rotor blades positioned radially outward from the gas inlet, the rotor being rotatable about an axis of rotation relative to the housing, the axis of rotation defining radial directions which are perpendicular to the axis of rotation; and a stator having a first plurality of stator blades positioned radially outward from the first plurality of rotor blades, the stator also having a plurality of combustors positioned radially outward from the first plurality of rotor blades; the rotor also having a plurality of rotor turbine blades positioned radially outward from the plurality of combustors, the rotor having a radius defined by a radial distance from the axis of rotation to a radially outermost part of the rotor turbine blades, the first plurality of rotor blades having a radially outermost part which extends radially outward to a position no more than one half the radius of the rotor. 9. The compressor and turbine of claim 8, wherein: the rotor includes a second plurality of rotor blades positioned radially outward from the first plurality of stator blades. 10. The compressor and turbine of claim 9, wherein; the stator includes has a second plurality of stator blades positioned radially outward from the second plurality of rotor blades, the plurality of combustors being positioned radially outward from the second plurality of stator blades. 11. The compressor and turbine of claim 9, wherein: the stator has a plurality of stator turbine blades positioned radially outward from the plurality of rotor turbine blades. 12. The compressor and turbine of claim 9, wherein: the stator has plurality of fluid injection ports positioned radially inward of the plurality of rotor turbine blades and radially outward from the first plurality of stator blades. 13. The compressor and turbine of claim 11, wherein: the plurality of fluid injection ports are configured to inject water adjacent to the plurality of combustors. 14. The compressor and turbine of claim 11, further comprising: a rotor blade ring attached to each of the first plurality of rotor blades. 15. The compressor and turbine of claim 11, further comprising: a stator blade ring attached to each of the first plurality of stator blades, the stator blade ring being recessed relative to the rotor. 16. A compressor and turbine, comprising: a housing; a gas inlet coupled to the housing; a gas outlet coupled to the housing; a rotor having a first plurality of rotor blades positioned radially outward from the gas inlet, the rotor being rotatable about an axis of rotation relative to the housing, the axis or rotation defining radial directions perpendicular to the axis of rotation; and a stator having a first plurality of stator blades positioned radially outward from the first plurality of rotor blades, the stator also having a plurality of combustors positioned radially outward from the second plurality of rotor blades; the rotor also having a plurality of rotor turbine blades positioned radially outward from the plurality of combustors, the rotor having a radius defined by a distance from the axis of rotation to a radially outermost part of the rotor turbine blades, the first plurality of rotor blades having a radial length defined by a radial distance from a radially innermost part to a radially outermost part which is less than one third the radius of the rotor. 17. The compressor and turbine of claim 16, wherein: the rotor includes a second plurality of rotor blades, the first plurality of stator blades being radially inward from the second plurality of rotor blades. 18. The compressor and turbine of claim 16, wherein: the stator has a second plurality of stator blades positioned radially outward from the second plurality of rotor blades, the plurality of combustors being positioned radially outward from the second plurality of stator blades. 19. The compressor and turbine of claim 16, wherein: the stator has a plurality of stator turbine blades positioned radially outward from the plurality of rotor turbine blades. 20. The compressor and turbine of claim 16, wherein: the stator has plurality of fluid injection ports positioned radially inward of the plurality of rotor turbine blades and radially outward from the first plurality of stator blades. 21. The compressor and turbine of claim 16, wherein: the plurality of fluid injection ports are configured to inject water adjacent to the plurality of combustors. 22. The compressor and turbine of claim 16, further comprising: a rotor blade ring attached to each of the first plurality of rotor blades. 23. The compressor and turbine of claim 16, further comprising: a stator blade ring attached to each of the first plurality of stator blades, the stator blade ring being recessed relative to the rotor.
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