[특허]Supersonic compressor rotor

General Electric Company

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특허 상세정보

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Supersonic compressor rotor

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F04D-019/02 F04D-021/00 F04D-029/38 F04D-017/12
출원번호	US-0639036 (2009-12-16)
등록번호	US-9103345 (2015-08-11)
발명자 / 주소	Nagel, Zachary William Hofer, Douglas Carl
출원인 / 주소	General Electric Company
대리인 / 주소	Caruso, Andrew J.
인용정보	피인용 횟수 : 1 인용 특허 : 8

초록
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Provided is a supersonic compressor having a supersonic compressor rotor including a clockable rotor disk allowing restriction or opening of portions of a fluid flow channel of the rotor in order to enhance performance of the rotor during different operational stages, for example rotor start-up or steady state. The supersonic compressor has a first rotor disk, a second rotor disk and a third rotor disk which share a common axis of rotation. The first and second rotor disks are rotatably coupled, and the third rotor disk is disposed between them. The third rotor disk is independently rotatable relative to the first and second disks, and has a raised surface structure for restricting or opening a portion of the flow channel defined by the three rotor disks and at least two vanes. The flow channel contains a supersonic compression ramp and encompasses the raised surface structure.

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청구항
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1. A supersonic compressor rotor comprising: (a) a first rotor disk;(b) a second rotor disk; and(c) a third rotor disk;said first, second, and third rotor disks sharing a common axis of rotation;said first and second rotor disks being rotatably coupled and together defining a rotor surface of the supersonic compressor rotor;said third rotor disk being disposed between said first and second rotor disks, said third rotor disk being independently rotatable relative to said first and second rotor disks, said third rotor disk comprising a raised surface structure;said first, second and third rotor disks together with at least two vanes defining a flow channel encompassing the raised surface structure of the third rotor disk;said flow channel comprising a supersonic compression ramp;wherein the at least two vanes are disposed in a screw-like fashion across the rotor surface defined by the first and second rotor disks and rotatably couple the first and second rotor disks,and wherein the raised surface structure is of dimensions such that it may not pass under a vane. 2. The supersonic compressor rotor according to claim 1, wherein said flow channel is an axial flow channel. 3. The supersonic compressor rotor according to claim 1, wherein the first rotor disk and the second rotor disk are rotatably coupled via a drive shaft. 4. The supersonic compressor rotor according to claim 1, wherein the raised surface structure is a ramp. 5. The supersonic compressor rotor according to claim 1, wherein said flow channel comprises a plurality of supersonic compression ramps. 6. The supersonic compressor rotor according to claim 1, wherein said flow channel defines a subsonic diffusion zone. 7. A supersonic compressor rotor comprising: (a) a first rotor disk having an outer surface;(b) a second rotor disk having an outer surface; and(c) a third rotor disk;said first, second, and third rotor disks defining an outer surface of the supersonic compressor rotor;said first, second, and third rotor disks sharing a common axis of rotation;said first and second rotor disks being rotatably coupled;said third rotor disk being disposed between said first and second rotor disks, said third rotor disk being independently rotatable relative to said first and second rotor disks, said third rotor disk comprising a raised surface structure;said first, second and third rotor disks together with at least two vanes defining an axial flow channel encompassing the raised surface structure of the third rotor disk;said axial flow channel comprising a supersonic compression ramp;said axial flow channel allowing fluid communication axially along the outer surface the supersonic compressor rotor;wherein the at least two vanes are disposed in a screw-like fashion across and joined to the outer surfaces of the first and second rotor disks;and wherein the raised surface structure is of dimensions such that it may not pass under a vane. 8. A supersonic compressor comprising: (a) a fluid inlet;(b) a fluid outlet; and(c) at least one supersonic compressor rotor, said supersonic compressor rotor comprising: (i) a first rotor disk;(ii) a second rotor disk; and(iii) a third rotor disk;said first, second, and third rotor disks sharing a common axis of rotation;said first and second rotor disks being rotatably coupled and together defining a rotor surface of the supersonic compressor rotor;said third rotor disk being disposed between said first and second rotor disks, said third rotor disk being independently rotatable relative to said first and second rotor disks, said third rotor disk comprising a raised surface structure;said first, second and third rotor disks together with at least two vanes defining a flow channel encompassing the raised surface structure of the third rotor disk;said flow channel comprising a supersonic compression ramp;wherein the at least two vanes are disposed in a screw-like fashion across the rotor surface defined by the first and second rotor disks and rotatably couple the first and second rotor disks,and wherein the raised surface structure is of dimensions such that it may not pass under a vane. 9. The supersonic compressor according to claim 8, which is comprised within a gas turbine. 10. A method of compressing a fluid, said method comprising: (a) introducing a fluid through a low pressure gas inlet into a gas conduit comprised within a supersonic compressor; and(b) removing a gas through a high pressure gas outlet of said supersonic compressor;said supersonic compressor comprising a supersonic compressor rotor disposed between said low pressure gas inlet and said high pressure gas outlet, said supersonic compressor rotor comprising: (i) a first rotor disk;(ii) a second rotor disk; and(iii) a third rotor disk;said first, second, and third rotor disks sharing a common axis of rotation;said first and second rotor disks being rotatably coupled and together defining a rotor surface of the supersonic compressor rotor;said third rotor disk being disposed between said first and second rotor disks, said third rotor disk being independently rotatable relative to said first and second rotor disks, said third rotor disk comprising a raised surface structure;said first, second and third rotor disks together with at least two vanes defining a flow channel encompassing the raised surface structure of the third rotor disk;said flow channel comprising a supersonic compression ramp;wherein the at least two vanes are disposed in a screw-like fashion across the rotor surface defined by the first and second rotor disks and rotatably couple the first and second rotor disks,and wherein the raised surface structure is of dimensions such that it may not pass under a vane. 11. The method according to claim 10, wherein said fluid comprises carbon dioxide. 12. The method according to claim 10, wherein said fluid comprises natural gas. 13. The method according to claim 10, wherein said supersonic compressor rotor comprises at least three flow channels. 14. A method for starting a supersonic compressor, said method comprising: (a) providing a supersonic compressor comprising a supersonic compressor rotor disposed within a fluid conduit of the supersonic compressor;said supersonic compressor rotor comprising: (i) a first rotor disk;(ii) a second rotor disk; and(iii) a third rotor disk;said first, second, and third rotor disks sharing a common axis of rotation;said first and second rotor disks being rotatably coupled and together defining a rotor surface of the supersonic compressor rotor;said third rotor disk being disposed between said first and second rotor disks, said third rotor disk being independently rotatable relative to said first and second rotor disks, said third rotor disk comprising a raised surface structure;said first, second and third rotor disks together with at least two vanes defining a flow channel encompassing the raised surface structure of the third rotor disk;said flow channel comprising a supersonic compression ramp;wherein the at least two vanes are disposed in a screw-like fashion across the rotor surface defined by the first and second rotor disks and rotatably couple the first and second rotor disks,and wherein the raised surface structure is of dimensions such that it may not pass under a vane;(b) positioning the raised surface structure of the third rotor disk within the flow channel downstream of a throat area of the flow channel during rotor start up; and(c) repositioning the raised surface structure of the third rotor disk within the throat area of the flow channel during steady state operation of the rotor.

이 특허에 인용된 특허 (8)

이 특허를 인용한 특허 피인용횟수: 1

Dickson, Bradford W.; Kidd, Harry Allan. Supersonic compressor with separator. USP2018039909597.

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Supersonic compressor rotor

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이 특허에 인용된 특허 (8)

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Supersonic compressor rotor

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이 특허에 인용된 특허 (8)

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