[특허]Turbocharger with turbine shroud

Turbocharger with turbine shroud 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F04D-029/42 F01D-009/04
출원번호	US-0642634 (2015-03-09)
등록번호	US-9810238 (2017-11-07)
발명자 / 주소	Annati, Richard E. McCormack, Jeffrey W. Frick, Matthew J.
출원인 / 주소	Caterpillar Inc.
대리인 / 주소	Finnegan, Henderson, Farabow, Garrett & Dunner LLP
인용정보	피인용 횟수 : 0 인용 특허 : 146

초록 ▼

A turbine assembly includes a turbine housing and a turbine wheel disposed within the turbine housing. The turbine wheel includes a rotational axis and a plurality of blades. The turbine assembly includes a turbine shroud disposed between the turbine housing and the turbine wheel along a radial direction. The turbine shroud is separate from the turbine housing. The turbine shroud includes an annular portion extending generally in an axial direction with respect to the rotational axis and a plate portion intersecting the annular portion to form a convex curved surface. At least a portion of the blades is disposed in at least a portion of the annular portion. Each blade includes a leading edge and a tip portion. Each leading edge is angled with respect to the rotational axis, and each tip portion forms a concave portion that curves around the curved surface of the turbine shroud.

대표청구항 ▼

1. A turbine assembly comprising: a turbine housing;a turbine wheel disposed within the turbine housing, the turbine wheel including a first end opposite a second end and a rotational axis extending between the first end and the second end, the turbine wheel including a plurality of blades;a turbine shroud disposed between the turbine housing and the turbine wheel along a radial direction, the turbine shroud being separate from the turbine housing, the turbine shroud including: an annular portion extending generally in an axial direction with respect to the rotational axis, at least a portion of the plurality of blades being disposed in at least a portion of the annular portion, anda plate portion intersecting the annular portion to form a convex curved surface;wherein each of the plurality of blades of the turbine wheel includes a leading edge and a tip portion, each leading edge being angled with respect to the rotational axis, each tip portion forming a concave portion that curves around the curved surface of the turbine shroud; anda heat shield disposed adjacent the second end of the turbine wheel, the turbine shroud being attached to the heat shield, wherein the heat shield further includes a plurality of bores extending along the radial direction for receiving a plurality of pins configured to radially attach the heat shield to a bearing housing, wherein the plurality of pins are press fit into respective bores in the heat shield and slidably received in respective bores in the bearing housing. 2. The turbine assembly of claim 1, wherein a gap is formed between at least a portion of the turbine shroud and the turbine housing. 3. The turbine assembly of claim 1, wherein the turbine shroud is symmetric with respect to the rotational axis, and the turbine housing is asymmetric with respect to the rotational axis. 4. The turbine assembly of claim 1, wherein each of the plurality of blades has a leading edge that forms an angle of about 10 to about 40 degrees with respect to the rotational axis. 5. The turbine assembly of claim 1, wherein the leading edge and the tip portion of each of the plurality of blades intersect to form a first corner. 6. The turbine assembly of claim 5, wherein the curved surface of the turbine shroud is disposed adjacent the first corner of each of the plurality of blades such that each first corner is aligned with the curved surface of the turbine shroud along the radial direction and along the axial direction. 7. The turbine assembly of claim 1, wherein a gap between a first point on the curved surface and the first corner is less than about 0.025 inches during operation of the turbine assembly. 8. The turbine assembly of claim 1, wherein: the concave portion is located between an intermediate point on the tip portion and the first corner; anda gap between a second point on the curved surface of the turbine shroud and the intermediate point on the tip portion is less than about 0.025 inches during the operation of the turbine assembly. 9. The turbine assembly of claim 1, wherein: each of the plurality of blades have a trailing edge intersecting the tip portion to form a second corner; anda gap between the second corner and a point on the annular portion of the turbine shroud is less than about 0.025 inches during the operation of the turbine assembly. 10. The turbine assembly of claim 1, wherein the turbine shroud further includes a nozzle portion, the nozzle portion including the plate portion and a plurality of nozzle vanes attached to the plate portion, the plurality of nozzle vanes being configured to receive a flow of exhaust from a turbine inlet in the turbine housing. 11. The turbine assembly of claim 1, further including a sealing element disposed around the annular portion and configured to limit a flow of exhaust between the turbine housing and the turbine shroud. 12. A turbocharger comprising: a compressor housing including a compressor wheel;a turbine housing including a turbine wheel, the turbine wheel including a first end opposite a second end and a rotational axis extending between the first end and the second end;a shaft attached at a first end to the compressor wheel and attached at a second end to the turbine wheel;a bearing housing connecting the compressor housing to the turbine housing;a turbine shroud disposed between the turbine housing and the turbine wheel along a radial direction, the turbine shroud being separate from the turbine housing; anda heat shield radially attached to the bearing housing by a plurality of pins extending along the radial direction, the heat shield being disposed between the bearing housing and the turbine wheel, wherein the plurality of pins are press fit into respective bores in the heat shield and slidably received in respective bores in the bearing housing. 13. The turbocharger of claim 12, wherein the turbine housing is rotatable around the rotational axis relative to the heat shield and the turbine shroud. 14. The turbocharger of claim 12, wherein the turbine shroud is attached to the heat shield by a plurality of fasteners.

이 특허에 인용된 특허 (146)

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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
구성항목	기본정보 상세정보 관리번호, 국가코드, 자료구분, 상태, 출원번호, 출원일자, 공개번호, 공개일자, 등록번호, 등록일자, 발명명칭(한글), 발명명칭(영문), 출원인(한글), 출원인(영문), 출원인코드, 대표IPC 관리번호, 국가코드, 자료구분, 상태, 출원번호, 출원일자, 공개번호, 공개일자, 공고번호, 공고일자, 등록번호, 등록일자, 발명명칭(한글), 발명명칭(영문), 출원인(한글), 출원인(영문), 출원인코드, 대표출원인, 출원인국적, 출원인주소, 발명자, 발명자E, 발명자코드, 발명자주소, 발명자 우편번호, 발명자국적, 대표IPC, IPC코드, 요약, 미국특허분류, 대리인주소, 대리인코드, 대리인(한글), 대리인(영문), 국제공개일자, 국제공개번호, 국제출원일자, 국제출원번호, 우선권, 우선권주장일, 우선권국가, 우선권출원번호, 원출원일자, 원출원번호, 지정국, Citing Patents, Cited Patents
저장형식	Text(ASCII format) Excel format PIAS분석(.xls)
메일정보	받는사람 (필수) @ 보내는사람 (선택) @ 제목 내용 KISTI 검색결과 이메일 서비스
안내	총 건의 자료가 검색되었습니다. 다운받으실 자료의 인덱스를 입력하세요. (1-10,000) 검색결과의 순서대로 최대 10,000건 까지 다운로드가 가능합니다. 데이타가 많을 경우 속도가 느려질 수 있습니다.(최대 2~3분 소요) 다운로드 파일은 UTF-8 형태로 저장됩니다. 파일의 내용이 제대로 보이지 않을실 때는 웹브라우저 상단의 보기 -> 인코딩 -> 자동선택 여부를 확인하십시오. ~ Text(ASCII format) Excel format

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Turbocharger with turbine shroud 원문보기

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Turbocharger with turbine shroud 원문보기

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