IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0774179
(2007-07-06)
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등록번호 |
US-8763363
(2014-07-01)
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발명자
/ 주소 |
|
출원인 / 주소 |
|
대리인 / 주소 |
Andes, Esq., William Scott
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인용정보 |
피인용 횟수 :
3 인용 특허 :
14 |
초록
▼
A method of assembling a turbine engine is provided. The method includes providing a heat exchanger having a curvilinear body. The method also includes coupling the heat exchanger to at least one of a fan casing and an engine casing of the turbine engine. The curvilinear body facilitates reducing pr
A method of assembling a turbine engine is provided. The method includes providing a heat exchanger having a curvilinear body. The method also includes coupling the heat exchanger to at least one of a fan casing and an engine casing of the turbine engine. The curvilinear body facilitates reducing pressure losses in airflow channeled into the heat exchanger.
대표청구항
▼
1. A method of manufacturing a turbine engine, said method comprising: providing a heat exchanger having a curvilinear body, an inlet, and an outlet;extending a plurality of heat exchanger elements through the curvilinear body such that a curvilinear airflow passageway is defined between adjacent he
1. A method of manufacturing a turbine engine, said method comprising: providing a heat exchanger having a curvilinear body, an inlet, and an outlet;extending a plurality of heat exchanger elements through the curvilinear body such that a curvilinear airflow passageway is defined between adjacent heat exchanger elements, wherein each passageway is substantially parallel to the plurality heat exchanger elements, and wherein each heat exchanger element includes an inlet coupled to the heat exchanger inlet and an outlet coupled to the heat exchanger outlet such that each heat exchanger element extends from the heat exchanger inlet to the heat exchanger outlet and includes at least one curved portion; andcoupling the heat exchanger to at least one of a fan casing and an engine casing of the turbine engine, wherein each of at least one of the fan casing and the engine casing include a curvilinear passage substantially similar in shape to the curvilinear body, the curvilinear body extending through at least one of the curvilinear passages, wherein the curvilinear body facilitates reducing pressure losses in airflow channeled into the heat exchanger. 2. A method in accordance with claim 1, wherein said coupling the heat exchanger comprises coupling the heat exchanger to at least one of the fan casing and the engine casing without an outlet plenum, such that the airflow is discharged directly from the heat exchanger without passing through an outlet plenum. 3. A method in accordance with claim 1, further comprising coupling the heat exchanger to at least one of a fan casing and an engine casing of the turbine engine without an inlet plenum, such that airflow is channeled directly into the heat exchanger without passing through an inlet plenum. 4. A method in accordance with claim 1, further comprising varying at least one of a size, orientation, and relative location of each heat exchanger element. 5. A method in accordance with claim 4, wherein varying at least one of a size, orientation, and relative location of each heat exchanger element facilitates increasing an amount of contact between the airflow and the heat exchanger elements. 6. A method in accordance with claim 4, wherein providing a heat exchanger having a curvilinear body facilitates reducing a volume of air required to cool oil flowing through the heat exchanger elements. 7. A method in accordance with claim 1, further comprising coupling the heat exchanger to at least one of a fan casing and an engine casing of the turbine engine without a diffuser, such that the airflow is channeled into the heat exchanger without passing through a diffuser. 8. A heat exchanger for a turbine engine, said heat exchanger comprising: an inlet and an outlet;a curvilinear body extending between said inlet and said outlet, said curvilinear body configured to reduce pressure losses in airflow channeled into said heat exchanger, wherein said curvilinear body extends through a curvilinear passage defined in at least one of a fan casing and an engine casing, said curvilinear body being substantially similar in shape to said curvilinear passage; anda plurality of heat exchanger elements extending through said curvilinear body such that a curvilinear airflow passageway is defined between adjacent said heat exchanger elements, wherein said passageway is substantially parallel to said heat exchanger elements, and wherein each said heat exchanger element includes an inlet coupled to said heat exchanger inlet and an outlet coupled to said heat exchanger outlet such that each heat exchanger element extends from said heat exchanger inlet to said heat exchanger outlet and comprises at least one curved portion. 9. A heat exchanger in accordance with claim 8, wherein said heat exchanger outlet is configured to couple to at least one of said fan casing and said engine casing of the turbine engine without an outlet plenum, such that the airflow is discharged directly from said heat exchanger without passing through an outlet plenum. 10. A heat exchanger in accordance with claim 8, wherein said heat exchanger inlet is configured to couple to at least one of said fan casing and said engine casing of the turbine engine without an inlet plenum, such that the airflow is channeled directly into said heat exchanger without passing through an inlet plenum. 11. A heat exchanger in accordance with claim 8, wherein at least one of a size, orientation, and relative location of each said heat exchanger element is variable. 12. A heat exchanger in accordance with claim 11, wherein each said heat exchanger element is configured to vary in size, orientation, and relative location to increase an amount of contact between the airflow and said heat exchanger elements. 13. A heat exchanger in accordance with claim 11, wherein said curvilinear body is configured to reduce a volume of air required to cool oil flowing through said heat exchanger elements. 14. A heat exchanger in accordance with claim 8, wherein said heat exchanger is configured to couple to at least one of said fan casing and said engine casing of the turbine engine without a diffuser such that the airflow is channeled into said heat exchanger without passing through a diffuser. 15. A turbine engine comprising: an engine casing;a fan casing coupled to and positioned radially outward from said engine casing, wherein each of said engine casing and said fan casing include a curvilinear passage defined therein; anda heat exchanger configured to couple to at least one of said fan casing and said engine casing, said heat exchanger comprising:an inlet and an outlet;a curvilinear body extending between said inlet and said outlet and through at least one of said curvilinear passages, said curvilinear body being substantially similar in shape to at least one of said curvilinear passages, said curvilinear body configured to reduce pressure losses in airflow channeled into said heat exchanger; anda plurality of heat exchanger elements extending through said curvilinear body such that a curvilinear airflow passageway is defined between adjacent said heat exchanger elements, wherein said passageway is substantially parallel to said heat exchanger elements, and wherein each said heat exchanger element includes an inlet coupled to said heat exchanger inlet and an outlet coupled to said heat exchanger outlet such that each heat exchanger element extends from said heat exchanger inlet to said heat exchanger outlet and comprises at least one curved portion. 16. A turbine engine in accordance with claim 15, wherein said heat exchanger outlet is configured to couple to at least one of said fan casing and said engine casing without an outlet plenum, such that the airflow is discharged directly from said heat exchanger without passing through an outlet plenum. 17. A turbine engine in accordance with claim 15, wherein said heat exchanger inlet is configured to couple to at least one of said fan casing and said engine casing without an inlet plenum, such that the airflow is channeled directly into said heat exchanger without passing through an inlet plenum. 18. A turbine engine in accordance with claim 15, wherein at least one of a size, orientation, and relative location of each said heat exchanger element is variable. 19. A turbine engine in accordance with claim 18 wherein said curvilinear body is configured to reduce a volume of air required to cool oil flowing through said heat exchanger elements. 20. A turbine engine in accordance with claim 15, wherein said heat exchanger is configured to couple to at least one of said fan casing and said engine casing without a diffuser such that the airflow is channeled into said heat exchanger without passing through a diffuser.
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