[특허]Gas turbine engine duct having a coupled fluid volume

Roll-Royce Corporation

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특허 상세정보

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Gas turbine engine duct having a coupled fluid volume

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02C-007/141
미국특허분류(USC)	060/772; 060/039.08; 060/267
출원번호	US-0715961 (2010-03-02)
등록번호	US-8627667 (2014-01-14)
발명자 / 주소	Lozier, Thomas S. Bowman, Mark E. Cathcart, Gregory D. Porter, Ronald P.
출원인 / 주소	Roll-Royce Corporation
대리인 / 주소	Krieg DeVault LLP
인용정보	피인용 횟수 : 1 인용 특허 : 22

초록

A fluid tank structure is disclosed that is integrated within a bypass duct of a turbofan gas turbine engine. The fluid tank structure includes a hollow interior that is closed off when the fluid tank structure is coupled with an inner wall of the bypass duct. The inner wall forms one wall of a fluid tank volume enclosed by the fluid tank structure.

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1. A gas turbine engine apparatus comprising: a radially inner fan bypass duct wall having a bypass duct wall first side operable to direct a flow of air in an annular bypass passage of a turbofan engine, the radially inner fan bypass duct wall also having a bypass duct wall second side;a fluid oil tank bowl having a bottom and at least two sides that extend from the bottom to the fan bypass duct wall second side to create a hollow interior, the sides of the bowl having a portion that is coupled to the fan bypass duct wall second side; anda fluid tank volume formed between the bypass duct wall second side and the fluid oil tank bowl and confined within a half cylinder of the radially inner fan bypass duct wall, the bypass duct wall second side of the radially inner fan bypass duct wall defining a fluid boundary of the fluid tank volume;wherein the radially inner fan bypass duct wall is disposed radially external to the flow of air of the annular bypass passage of the turbofan engine. 2. The apparatus of claim 1, wherein the fluid tank volume is operable to receive a quantity of oil. 3. The apparatus of claim 1, which further includes a radially outer bypass duct wall disposed at the side of the bypass duct wall second side. 4. The apparatus of claim 3, wherein the fluid oil tank bowl is disposed between the radially inner fan bypass duct wall and the radially outer bypass duct wall. 5. The apparatus of claim 3, which further includes a structured core disposed between the radially inner fan bypass duct wall and the radially outer bypass duct wall. 6. The apparatus of claim 5, wherein the structured core is a honeycomb shaped construction. 7. The apparatus of claim 1, wherein the fluid oil tank further includes a feed line traversing through the radially inner fan bypass duct wall and useful to provide a conduit through which a fluid may be received within the fluid oil tank bowl. 8. The apparatus of claim 1, wherein the fluid oil tank bowl has sides coupled to the bypass duct wall second side. 9. An apparatus comprising: a turbofan bypass duct portion having a fluid oil tank bowl disposed between a radially inner wall and a radially outer wall and a structural core configured to provide strength to the turbofan bypass duct portion substantially across a radial space between the radially inner wall and radially outer wall of the turbofan bypass duct portion, wherein the radially inner wall has an inner side and an outer side, the inner side forming a flow path boundary for passage of bypass air, and wherein the fluid oil tank bowl has a bottom and at least two sides that extend from the bottom to the outer side of the radially inner wall, and wherein the fluid oil tank bowl is engaged to the outer side of the radially inner wall and is structured to form a space bounded by the fluid oil tank bowl and the outer side of the radially inner wall, the space operable to receive a fluid that contacts the fluid oil tank bowl and the outer side of the radially inner wall. 10. The apparatus of claim 9, wherein the radially inner wall is a radially inner wall of an annular turbofan bypass passage formed by the turbofan bypass duct portion. 11. The apparatus of claim 9, wherein the fluid oil tank bowl has one or more of the at least two sides engaged to the outer side of the radially inner wall. 12. The apparatus of claim 9, wherein the fluid oil tank bowl is bonded to the radially inner wall. 13. The apparatus of claim 9, wherein a fluid operable to be contained in the fluid oil tank bowl is oil. 14. The apparatus of claim 9, wherein the structural core is a honeycomb configured structure. 15. The apparatus of claim 9, which further includes a sight gauge useful for determining a status of a fluid contained within the fluid oil tank bowl, the radially outer wall including an aperture through which the sight gauge can be viewed. 16. The apparatus of claim 9, which further includes an air/oil separator. 17. An apparatus comprising: a gas turbine engine bypass duct having a first wall offset from a second wall, wherein a radially inward facing side of the first wall is operable to direct a flow of air in an annular bypass passage of a turbofan engine; andmeans for containing oil within the gas turbine engine bypass duct, the means located between the first wall and second wall, wherein the means for containing oil has a bottom and at least two sides that extend from the bottom to a radially outward facing side of the first wall to define a fluid tank volume, the radially outward facing side of the first wall defining a fluid boundary of the fluid tank volume;wherein the gas turbine engine duct, and the means located between the first wall and second wall, are disposed radially external to the flow of air in the annular bypass passage of the turbofan engine. 18. A method comprising: providing a gas turbine engine bypass duct wall having a radially inward side and a radially outward side opposite that of the radially inward side, and configuring the radially inward side to be operable to direct a flow of air in an annular bypass passage of a turbofan engine;forming a fluid tank volume by engaging a fluid oil tank structure with a portion of the radially outward side of the gas turbine engine bypass duct wall, wherein the fluid oil tank structure has a bottom and at least two sides that extend from the bottom to the radially outward side of the fluid oil tank structure;fastening the fluid oil tank structure to the portion of the radially outward side of the gas turbine engine bypass duct wall to secure the fluid oil tank structure to the radially outward side of the gas turbine engine bypass duct wall, the radially outward side defining a fluid boundary of the fluid tank volume;enclosing the fluid oil tank structure between the gas turbine engine bypass duct wall and a second gas turbine engine bypass duct wall; andsupporting the gas turbine engine bypass duct wall with a core structure that provides a load path that directly connects the gas turbine engine bypass duct wall and the second gas turbine engine bypass duct wall. 19. The method of claim 18, wherein the fastening includes bonding the fluid oil tank structure to the radially outward side. 20. The method of claim 18, which further includes inserting a fluid fill tube through the gas turbine engine bypass duct wall.

이 특허에 인용된 특허 (22)

이 특허를 인용한 특허 피인용횟수: 1

Kupiszewski, Thomas. Method and system for radial tubular duct heat exchangers. USP20180610006369.

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특허 상세정보

Gas turbine engine duct having a coupled fluid volume

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Gas turbine engine duct having a coupled fluid volume

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