IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
UP-0611558
(2006-12-15)
|
등록번호 |
US-7798777
(2010-10-11)
|
발명자
/ 주소 |
- Moussa, Zaher Milad
- Granda, Caroline Curtis
- Walter, Robert Albert
|
출원인 / 주소 |
|
대리인 / 주소 |
Andes, Esq., William Scott
|
인용정보 |
피인용 횟수 :
2 인용 특허 :
5 |
초록
▼
A compressor assembly for a gas turbine engine is provided. The compressor assembly includes a rotating impeller including an inlet, an outlet, and a body extending therebetween. The compressor assembly further includes a non-rotating impeller shroud. The body and the shroud define an impeller chamb
A compressor assembly for a gas turbine engine is provided. The compressor assembly includes a rotating impeller including an inlet, an outlet, and a body extending therebetween. The compressor assembly further includes a non-rotating impeller shroud. The body and the shroud define an impeller chamber including a radially inner surface and a radially outer surface. The radially inner surface includes an arcuate flow surface. The flow surface includes a first portion and a second portion extending downstream from the first portion. The impeller chamber includes a variable area wherein a first cross-sectional area is defined between the radially outer surface and the first portion, and a second cross-sectional area is defined downstream from the first cross-sectional area. The first cross-sectional area is greater than the second cross-sectional area. A method of operating the compressor assembly is also included.
대표청구항
▼
What is claimed is: 1. A method of operating a gas turbine engine, said method comprising: channeling airflow towards an impeller of a centrifugal compressor that includes an axially oriented inlet, a radially oriented outlet, and a chamber extending therebetween, wherein the direction of airflow i
What is claimed is: 1. A method of operating a gas turbine engine, said method comprising: channeling airflow towards an impeller of a centrifugal compressor that includes an axially oriented inlet, a radially oriented outlet, and a chamber extending therebetween, wherein the direction of airflow in the chamber changes from an axial flow at the inlet to a radially outward flow at the outlet; channeling airflow through the impeller inlet into a convergent-divergent flow path defined within the impeller chamber downstream from the inlet; channeling airflow from a third cross-sectional area defined upstream from a first cross-sectional area, said third cross-sectional area is larger than said first cross-sectional area; and channeling airflow from said first cross-sectional area of the flow path into a second cross-sectional area of the flow path defined downstream from the first cross-sectional area, wherein the second cross-sectional area is smaller than the first cross-sectional area. 2. A method in accordance with claim 1 further comprising channeling airflow through the inlet at a first velocity. 3. A method in accordance with claim 2 wherein said method further comprises channeling airflow through the outlet at a second absolute velocity that is of greater magnitude than the first absolute velocity. 4. A centrifugal compressor assembly for a gas turbine engine, said centrifugal compressor assembly comprising: a rotating centrifugal impeller comprising an axially-oriented inlet, a radially-oriented outlet, and a body extending therebetween; and a non-rotating impeller shroud, said body and said shroud define an impeller chamber comprising a radially inner surface and a radially outer surface, said radially inner surface comprises an arcuate, convergent-divergent flow surface, said flow surface comprises a first portion and a second portion extending downstream from said first portion, said impeller chamber comprising a variable area wherein a first cross-sectional area is defined between said radially outer surface and said first portion, and a second cross-sectional area is defined downstream from said first cross-sectional area, said first cross-sectional area is greater than said second cross-sectional area, said impeller chamber further comprises a third cross-sectional area defined upstream from said first cross-sectional area, said third cross-sectional area is larger than said first cross-sectional area, wherein the direction of airflow in said impeller chamber changes from an axial flow at the inlet to a radially outward flow at the outlet. 5. A compressor assembly in accordance with claim 4 wherein said second cross-sectional area is defined between said radially outer surface and said second portion. 6. A compressor assembly in accordance with claim 4 wherein said first portion is formed integrally with said second portion. 7. A compressor assembly in accordance with claim 4 wherein said first portion is formed integrally with said second portion and said impeller body. 8. A compressor assembly in accordance with claim 4 wherein said flow path further comprises an apex defined between said first portion and said second portion. 9. A compressor assembly in accordance with claim 4 wherein a leading edge of a splitter is defined between said first portion and said second portion. 10. A gas turbine engine comprising: a rotor shaft; and a centrifugal compressor assembly coupled to said rotor shaft, said centrifugal compressor assembly comprising a rotating impeller comprising an axially-oriented inlet, radially-oriented outlet, and a body extending therebetween, and a non-rotating impeller shroud, said body and said shroud define an impeller chamber comprising a radially inner surface and a radially outer surface, said radially inner surface comprises an arcuate, convergent-divergent flow surface, said flow surface comprises a first portion and a second portion extending downstream from said first portion, said impeller chamber comprising a variable area wherein a first cross-sectional area is defined between said radially outer surface and said first portion, and a second cross-sectional area is defined downstream from said first cross-sectional area, said first cross-sectional area is greater than said second cross-sectional area, said impeller chamber further comprises a third cross-sectional area defined upstream from said first cross-sectional area, said third cross-sectional area is larger than said first cross-sectional area wherein the direction of airflow in said impeller chamber changes from an axial flow at the inlet to a radially outward flow at the outlet. 11. A gas turbine engine in accordance with claim 10 wherein said second cross-sectional area is defined between said radially outer surface and said second portion. 12. A gas turbine engine in accordance with claim 10 wherein said first portion is formed integrally with said second portion. 13. A gas turbine engine in accordance with claim 10 wherein said first portion is formed integrally with said second portion and said impeller body. 14. A gas turbine engine in accordance with claim 10 wherein said flow path further comprises an apex defined within said first portion. 15. A gas turbine engine in accordance with claim 10 wherein a leading edge of a splitter is defined between said first portion and said second portion.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.