Gas turbine engine with geared turbofan and oil thermal management system
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F01D-025/18
F01D-025/20
F02K-009/64
F02C-007/06
F02C-007/14
출원번호
US-0245317
(2014-04-04)
등록번호
US-9341080
(2016-05-17)
발명자
/ 주소
Phillips, Kathleen R.
Phillips, Thomas G.
Stearns, Ethan K.
Papa, Federico
출원인 / 주소
United Technologies Corporation
대리인 / 주소
Carlson, Gaskey & Olds, P.C.
인용정보
피인용 횟수 :
0인용 특허 :
11
초록▼
A gas turbine engine includes a fan, a compressor section, a combustion section, and a turbine section. A fan drive gear system is configured for driving the fan at a speed different than the turbine section. A lubricant system includes a lubricant pump delivering lubricant to an outlet line. The ou
A gas turbine engine includes a fan, a compressor section, a combustion section, and a turbine section. A fan drive gear system is configured for driving the fan at a speed different than the turbine section. A lubricant system includes a lubricant pump delivering lubricant to an outlet line. The outlet line splits into at least a hot line and into a cool line. The hot line is directed primarily to locations in the gas turbine engine that are not intended to receive cooler lubricant. The cool line is directed through one or more heat exchangers at which the lubricant is cooled, and the cool line then is routed to the fan drive gear system. At least one of the one or more heat exchangers is a fuel/oil cooler at which lubricant will be cooled by fuel leading to the combustion section. The fuel/oil cooler is downstream of a point where the outlet line splits into the at least the hot line and the cool line, such that the hot line is not directed through the fuel/oil cooler. A method is also disclosed.
대표청구항▼
1. A gas turbine engine comprising: a fan;a compressor section;a combustion section;a turbine section;a fan drive gear system configured for driving the fan at a speed different than the turbine section;a lubricant system including a lubricant pump delivering lubricant to an outlet line, said outlet
1. A gas turbine engine comprising: a fan;a compressor section;a combustion section;a turbine section;a fan drive gear system configured for driving the fan at a speed different than the turbine section;a lubricant system including a lubricant pump delivering lubricant to an outlet line, said outlet line splitting into at least a hot line and into a cool line, said hot line being directed primarily to locations in the gas turbine engine that are not intended to receive cooler lubricant, and said cool line being directed through one or more heat exchangers at which the lubricant is cooled, and said cool line splitting into a first line and a second line, said first line then being routed to said fan drive gear system;at least one of said one or more heat exchangers is a fuel/oil cooler at which lubricant will be cooled by fuel leading to the combustion section, and said fuel/oil cooler being downstream of a point where said outlet line splits into said at least said hot line and said cool line, such that said hot line is not directed through said fuel/oil cooler; anda valve located downstream from where the second line combines with said hot line after all of said one or more heat exchangers, the valve selectively supplying the lubricant to the fan drive gear system by routing the lubricant from said hot line to the first line without routing through an additional heat exchanger when additional lubricant is necessary for the fan drive gear system. 2. The gas turbine engine as set forth in claim 1, wherein said locations in the engine that are not intended to receive cooler lubricant include bearings associated with at least the turbine section. 3. The gas turbine engine as set forth in claim 2, wherein said cool line supplies lubricant to a bearing in said fan drive gear system. 4. The gas turbine engine as set forth in claim 3, wherein the bearing in said fan drive gear system comprises a journal bearing. 5. The gas turbine engine as set forth in claim 1, wherein the lubricant in said hot line does not intermix back into said cool line until a point after said cool line has been routed to the bearing for said fan drive gear system. 6. The gas turbine engine as set forth in claim 1, wherein the lubricant in the hot line is intermixed with a portion of the lubricant from the cool line prior to being delivered to said locations in the gas turbine engine that are not intended to receive cooler lubricant. 7. The gas turbine engine as set forth in claim 6, wherein the compressor section includes a first compressor section axially forward of a second compressor section. 8. The gas turbine engine as set forth in claim 7, wherein the turbine section includes a fan drive turbine and a second turbine, and said fan drive turbine configured for driving said first compressor section, and the fan drive gear system such that said fan and said first compressor are driven at different speeds. 9. The gas turbine engine as set forth in claim 8, wherein the second turbine section operates at a higher pressure than the fan drive turbine and is configured to drive the second compressor section. 10. The gas turbine engine as recited in claim 1, including a second valve located downstream of a point where said hot line splits from said cool line, said second valve selectively directing the lubricant between the fuel/oil cooler and at least one other of said one or more heat exchangers. 11. A method of designing a gas turbine engine comprising: defining a fan configured for rotation about an axis;configuring a compressor section, a combustor section, and a turbine section to define a core flow path;configuring a fan drive gear system for driving the fan at a speed different than the turbine section;defining a lubricant system to include a lubricant pump for delivering lubricant to an outlet line, said outlet defined to split into at least a hot line and into a cool line, said hot line being configured for directing lubricant primarily to locations in the gas turbine engine that are not intended to receive cooler lubricant, and said cool line configured for directing lubricant through one or more heat exchangers for cooling lubricant, and splitting said cool line into a first line and a second line, wherein the first line is configured for routing to the fan drive gear system;at least one of said one or more heat exchangers is configured as a fuel/oil cooler at which lubricant will be cooled by fuel leading to the combustion section, and said fuel/oil cooler being downstream of a point where said outlet line splits into said at least said hot line and said cool line, such that said hot line is not directed through said fuel/oil cooler; andlocating a valve downstream from where said second line combines with said hot line after all of said one or more heat exchangers, configuring the valve to selectively supply the lubricant to the fan drive gear system by routing the lubricant from said hot line to the first line without routing through an additional heat exchanger when additional lubricant is necessary for the fan drive gear system. 12. The method as set forth in claim 11, including configuring said locations in the engine that are not intended to receive cooler lubricant to include bearings associated with at least the turbine section. 13. The method as set forth in claim 12, wherein said cool line is configured to supply the lubricant to a journal bearing in said fan drive gear system. 14. The method as set forth in claim 11, including defining the system such that the lubricant in said hot line does not intermix back into said cool line until a point after said cool line has been routed to a bearing for said fan drive gear system. 15. The method as set forth in claim 11, including defining the system such that the lubricant in the hot line is intermixed with a portion of the lubricant from the cool line prior to being delivered to said locations in the gas turbine engine that are not intended to receive cooler lubricant. 16. The method as set forth in claim 11, including configuring a second valve located downstream of a point where said hot line splits from said cool line such that said second valve selectively directs the lubricant between the fuel/oil cooler and at least one other of said one or more heat exchangers.
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이 특허에 인용된 특허 (11)
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Burr Donald N. (Glastonbury CT) Danilowicz Paul S. (Manchester CT) Franz Thomas C. (Bolton CT) Mortimer Thomas P. (Bolton CT) Pero Edward B. (Somers CT), Fuel and oil heat management system for a gas turbine engine.
Stearns, Ethan K.; Glahn, Jorn A.; McKaveney, Daniel J., Gas turbine engine with geared turbofan and oil thermal management system with unique heat exchanger structure.
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