Gas turbine engine with geared turbofan and oil thermal management system
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-007/06
F02C-001/00
F02K-099/00
F01D-025/18
F02K-009/64
출원번호
US-0361997
(2012-01-31)
등록번호
US-8443582
(2013-05-21)
발명자
/ 주소
Phillips, Kathleen R.
Phillips, Thomas G.
Stearns, Ethan K.
Papa, Federico
출원인 / 주소
United Technologies Corporation
대리인 / 주소
Carlson, Gaskey & Olds, PC
인용정보
피인용 횟수 :
3인용 특허 :
3
초록▼
A lubricant supply system for a gas turbine engine has a lubricant lube pump delivering lubricant to an outlet line. The outlet line is split into at least a hot line and into a cool line, with the hot line directed primarily to locations associated with an engine that are not intended to receive co
A lubricant supply system for a gas turbine engine has a lubricant lube pump delivering lubricant to an outlet line. The outlet line is split into at least a hot line and into a cool line, with the hot line directed primarily to locations associated with an engine that are not intended to receive cooler lubricant, and the cool line directed through one or more heat exchangers at which lubricant is cooled. The cool line then is routed to a fan drive gear for an associated gas turbine engine. A method and apparatus are disclosed.
대표청구항▼
1. A lubricant supply system for a gas turbine engine comprising: 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 associated with the engine that are not intended to
1. A lubricant supply system for a gas turbine engine comprising: 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 associated with the engine that are not intended to receive cooler lubricant, and said cool line being directed through one or more heat exchangers at which lubricant is cooled, and said cool line then being routed to a fan drive gear for the associated gas turbine engine;at least one of said one or more heat exchangers is a fuel/oil cooler at which the lubricant will be cooled by fuel leading to a combustion section for the gas turbine engine, 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; andwherein a valve is positioned on said cool line and splits said cool line into two lines, with a first line being directed through said fuel/oil cooler and the lubricant in said cool line not being directed to the fuel/oil cooler being directed to at least one other cooler through a second line. 2. The system as set forth in claim 1, wherein said at least one other cooler includes an air-to-oil cooler. 3. The system as set forth in claim 2, wherein said at least one other cooler also includes an oil-to-oil cooler at which oil from a generator exchanges heat with the oil in said second line. 4. The system as set forth in claim 1, wherein said cool line supplies lubricant to a journal bearing in a fan drive gear. 5. The system as set forth in claim 1, wherein a valve selectively supplies lubricant from said hot line to the fan drive gear when additional lubricant is necessary. 6. The system as set forth in claim 1, wherein said hot line intermixes with a portion of the lubricant in the cool line prior to being directed to the locations associated with an engine that are not intended to receive cooler lubricant. 7. A gas turbine engine comprising: a fan, a compressor section, including a low pressure compressor section and a high pressure compressor section;a combustor;a turbine section including both a low pressure turbine and a high pressure turbine section, and said low pressure turbine section driving said low pressure compressor section, and a fan drive gear provided such that said low pressure turbine further driving said fan, with said fan and said low pressure compressor being driven at different rates;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 then being routed to said fan drive gear;at least one of said one or more heat exchangers is a fuel/oil cooler at which the lubricant will be cooled by fuel leading to a combustion section for the gas turbine engine, 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; andwherein a valve is positioned on said cool line and splits said cool line into two lines, with a first line being directed through said fuel/oil cooler and the lubricant in said cool line not being directed to the fuel/oil cooler being directed to at least one other cooler through a second line. 8. The gas turbine engine as set forth in claim 7, wherein said locations in the engine that are not intended to receive cooler lubricant include bearings associated with at least the turbine section. 9. The gas turbine engine as set forth in claim 7, wherein said at least one other cooler include an air-to-oil cooler. 10. The gas turbine engine as set forth in claim 9, wherein said at least one other cooler also includes an oil-to-oil cooler at which oil from a generator exchanges heat with the oil in said second line. 11. The gas turbine engine as set forth in claim 7, wherein said cool line supplies lubricant to a journal bearing in said fan drive gear. 12. The gas turbine engine as set forth in claim 7, wherein a valve selectively supplies lubricant from said hot line to the fan drive gear when additional lubricant is necessary. 13. The gas turbine engine as set forth in claim 7, wherein said low pressure turbine having a pressure ratio greater than about 5:1. 14. The gas turbine engine as set forth in claim 7, wherein a gear reduction ratio of said fan drive gear is greater than about 2.3. 15. The gas turbine engine as set forth in claim 7, wherein a diameter of said fan is significantly larger than a diameter of said low pressure compressor. 16. The gas turbine engine as set forth in claim 7, 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. 17. A method of managing lubricant supply for a gas turbine engine comprising: moving a lubricant from a lubricant pump into an outlet line, and splitting the outlet lines into a cool line which is delivered into at least one heat exchanger to cool the lubricant, and the cooled lubricant then being delivered to a gear reduction that drives a fan associated with the gas turbine engine; andsupplying lubricant from a hot line which is not passed through said at least one heat exchanger to bearings associated with at least a turbine section in the gas turbine engine;at least one of said one or more heat exchangers is a fuel/oil cooler and lubricant is cooled by fuel leading to a combustion section for the gas turbine engine in said fuel/oil cooler, 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;positioning a valve in said cool line; andsplitting said cool line into two lines, with directing a first line through said fuel/oil cooler and directing the lubricant in said cool line not being directed to the fuel/oil cooler to at least one other cooler through a second line. 18. The method as set forth in claim 17, wherein lubricant in the hot line being intermixed with a portion of the lubricant in the cool line prior to being delivered to said bearings.
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이 특허에 인용된 특허 (3)
Reuter, Charles; Dyer, Gerald P.; Haugsjaahabink, Todd; Shah, Satish, Fluid flow system for a gas turbine engine.
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.
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