[특허]Centrifugal impeller and turbomachine

Centrifugal impeller and turbomachine 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F04D-029/02 F04D-029/28 F04D-029/22
출원번호	US-0511621 (2010-11-22)
등록번호	US-9816518 (2017-11-14)
우선권정보	IT-CO2009A0049 (2009-11-23)
국제출원번호	PCT/US2010/057623 (2010-11-22)
§371/§102 date	20121008 (20121008)
국제공개번호	WO2011/063333 (2011-05-26)
발명자 / 주소	Giannozzi, Massimo Giovannetti, Iacopo Massini, Andrea Aksel, Bulent Lanaud, Christophe O'Flynn, Julian Finn, Scott
출원인 / 주소	Giannozzi, Massimo
대리인 / 주소	GE Global Patent Operation
인용정보	피인용 횟수 : 0 인용 특허 : 39

초록

A centrifugal impeller for a turbomachine is provided. The centrifugal impeller comprises a plurality of aerodynamic vanes, each of the aerodynamic vanes having internal walls on which is associated a fabric element.

대표청구항 ▼

1. A centrifugal impeller for a turbomachine comprising: a plurality of aerodynamic veins, each of the aerodynamic veins having internal walls on which is associated a first fabric element, wherein a second fabric element is alternately associated on an upper wall of a vein and a lower wall of an adjacent vein as a continuous fabric element passing along a respective impeller blade therebetween. 2. The impeller of claim 1, wherein the first fabric element of each of the plurality of aerodynamic veins is configured to surround each of the aerodynamic veins. 3. The impeller of claim 1, wherein a third fabric element has a conical surface with fabric blades stretching out from the conical surface. 4. The impeller of claim 1, comprising: a fourth fabric element associated over the aerodynamic veins; the fourth element having substantially a centrifugal shroud shape and function. 5. The impeller of claim 1, wherein an inner core element is associated under the aerodynamic veins in order to facilitate a manufacturing process of the impeller. 6. The impeller of claim 5, wherein the inner core element is surrounded by at least one of a fourth fabric element, a fifth fabric element, a sixth fabric element, and a seventh fabric element. 7. The impeller of claim 1, wherein the fabric elements of each of the plurality of aerodynamic veins are made by a plurality of unidirectional or multidirectional fibers, comprising anisotropy along at least a preferential direction. 8. The impeller of claim 1, wherein the first fabric element of each of the plurality of aerodynamic veins is impregnated with a filling material. 9. The impeller of claim 1, wherein a fifth fabric element comprises a rear-plate for a finished impeller; the fifth fabric element having substantially an annular planar shape. 10. The impeller of claim 1, wherein a sixth fabric element associated under the aerodynamic veins; the sixth fabric element having substantially an annular shape able to be matched with an external inferior surface of the aerodynamic veins. 11. The impeller of claim 1, wherein a seventh fabric element associated around the interior surface of an axial hole is used to associate a rotor for the turbomachine. 12. The impeller of claim 1, wherein a segmented fabric element able is fitted inside a space at a corner of shaped slots-of the aerodynamic veins to increase a rigidity of a whole assembly of a finished impeller, eliminate preferential flowpaths for a filling material, and avoid regions containing only filling material with no fiber where cracking might initiate during cure. 13. The impeller of claim 1, wherein a shaped component associated inside each of the aerodynamic veins acts against erosion of a working fluid. 14. The impeller of claim 6, wherein the inner core element is comprised of a material different from a material of the at least one of a fourth fabric element, a fifth fabric element, a sixth fabric element, and a seventh fabric element. 15. A turbomachine comprising a plurality of aerodynamic veins, each of them having internal walls on which is associated a first fabric element, wherein a second fabric element is alternately associated on an upper wall of a vein and a lower wall of an adjacent vein as a continuous fabric element passing along a respective impeller blade therebetween. 16. The turbomachine of claim 15, wherein the fabric elements of each of the plurality of aerodynamic veins are configured to surround each of the aerodynamic veins. 17. The turbomachine of claim 15, wherein a third fabric element has a conical surface with fabric blades stretching out from the conical surface. 18. The turbomachine of claim 15, wherein the first fabric element of each of the plurality of aerodynamic veins is impregnated with a filling material. 19. The turbomachine of claim 15, wherein an inner core element is associated under the aerodynamic veins in order to facilitate a manufacturing process of the impeller.

이 특허에 인용된 특허 (39)

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IPC	Description
A	생활필수품
A62	인명구조; 소방(사다리 E06C)
A62B	인명구조용의 기구, 장치 또는 방법(특히 의료용에 사용되는 밸브 A61M 39/00; 특히 물에서 쓰이는 인명구조 장치 또는 방법 B63C 9/00; 잠수장비 B63C 11/00; 특히 항공기에 쓰는 것, 예. 낙하산, 투출좌석 B64D; 특히 광산에서 쓰이는 구조장치 E21F 11/00)
A62B-1/08	.. 윈치 또는 풀리에 제동기구가 있는 것

내보내기 구분	파일저장 인쇄 메일전송
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연합인증

Centrifugal impeller and turbomachine 원문보기

초록

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Centrifugal impeller and turbomachine 원문보기

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