US20190063330A1 - Geared gas turbine engine with oil deaerator - Google Patents
Geared gas turbine engine with oil deaerator Download PDFInfo
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- US20190063330A1 US20190063330A1 US16/100,930 US201816100930A US2019063330A1 US 20190063330 A1 US20190063330 A1 US 20190063330A1 US 201816100930 A US201816100930 A US 201816100930A US 2019063330 A1 US2019063330 A1 US 2019063330A1
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- oil
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- deaerator
- gas turbine
- turbine engine
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/18—Lubricating arrangements
- F01D25/20—Lubricating arrangements using lubrication pumps
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/06—Arrangements of bearings; Lubricating
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16N—LUBRICATING
- F16N39/00—Arrangements for conditioning of lubricants in the lubricating system
- F16N39/002—Arrangements for conditioning of lubricants in the lubricating system by deaeration
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01M—LUBRICATING OF MACHINES OR ENGINES IN GENERAL; LUBRICATING INTERNAL COMBUSTION ENGINES; CRANKCASE VENTILATING
- F01M13/00—Crankcase ventilating or breathing
- F01M13/04—Crankcase ventilating or breathing having means for purifying air before leaving crankcase, e.g. removing oil
- F01M2013/0422—Separating oil and gas with a centrifuge device
- F01M2013/0427—Separating oil and gas with a centrifuge device the centrifuge device having no rotating part, e.g. cyclone
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/40—Transmission of power
- F05D2260/403—Transmission of power through the shape of the drive components
- F05D2260/4031—Transmission of power through the shape of the drive components as in toothed gearing
- F05D2260/40311—Transmission of power through the shape of the drive components as in toothed gearing of the epicyclical, planetary or differential type
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/60—Fluid transfer
- F05D2260/608—Aeration, ventilation, dehumidification or moisture removal of closed spaces
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/98—Lubrication
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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- Y02T50/671—
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Retarders (AREA)
- General Details Of Gearings (AREA)
Abstract
A gas turbine engine includes a fan section including a fan rotor, a compressor section, a turbine section including a fan drive turbine that drives the fan rotor through a gear reduction, and a lubrication system that supplies oil to the gear reduction and includes a lubricant pump that supplies a mixed air and oil to an inlet of a deaerator during operation. The deaerator includes a shell defining a cavity and a separator that separates the mixed air and oil in the cavity, delivers separated air to an air outlet of the deaerator and delivers separated oil back into an oil tank during operation. A method of designing a gas turbine engine is also disclosed.
Description
- This application is a continuation of U.S. patent application Ser. No. 15/873,961, filed Jan. 18, 2018, which is a continuation of U.S. patent application Ser. No. 14/737,670, filed Jun. 12, 2015. U.S. patent application Ser. No. 14/737,670 claims priority to U.S. Provisional Patent Application No. 62/019,452, filed Jul. 1, 2014.
- This application relates to a gas turbine engine having a gear reduction driving a fan wherein an oil tank has an improved deaerator.
- Gas turbine engines are known and, typically, include a fan delivering air into a bypass duct as propulsion air. The fan also delivers air into a core engine where it passes to a compressor. The air is compressed in the compressor and delivered downstream into a combustion section where it is mixed with fuel and ignited. Products of this combustion pass downstream over turbine rotors driving them to rotate.
- Historically, the fan rotor and a fan drive turbine rotor have been driven at the same speed. This placed a restriction on the desirable speed of both the fan and the fan drive turbine.
- More recently, it has been proposed to provide a gear reduction between the fan drive turbine and the fan rotor.
- The gear reduction is a source of increased heat loss. As an example, a geared turbofan engine creates about twice as much heat loss as a non-geared turbofan engine. In addition, the weight of the engine increases due to the weight of the gear reduction.
- It has typically been the case that a designer of a gas turbine engine sizes an oil tank such that the oil can sit in the oil tank long enough to de-aerate. On a normal turbofan engine, this had been approximately at least ten seconds.
- In a featured embodiment, a gas turbine engine comprises a fan drive turbine for driving a gear reduction. The gear reduction drives a fan rotor. A lubrication system supplies oil to the gear reduction. The lubrication system includes a lubricant pump supplying a mixed air and oil to a deaerator inlet. The deaerator includes a separator that for separating oil, and delivering separated air to an air outlet, and for delivering separated oil back into an oil tank. The separator includes a member having lubricant flow paths on both of two opposed sides.
- In another embodiment according to the previous embodiment, the separator has a splitter at an intermediate position in the inlet.
- In another embodiment according to any of the previous embodiments, the air outlet has a tube extending downwardly into a deaerator shell.
- In another embodiment according to any of the previous embodiments, an inlet velocity to the deaerator is less than or equal to 14 feet/second, and an exit velocity from the deaerator of the separated air is less than or equal to 14 feet/second.
- In another embodiment according to any of the previous embodiments, a deaerator exit delivers oil into the oil tank at least 2 inches (5.08 centimeters) between a freestanding oil level within the tank.
- In another embodiment according to any of the previous embodiments, a dwell time of oil in the tank as removed by the oil pump, on average, is five seconds or less.
- In another embodiment according to any of the previous embodiments, the oil tank may hold greater than or equal to 25 and less than or equal to 35 quarts of oil.
- In another embodiment according to any of the previous embodiments, the engine is rated greater than or equal to 15,000 and less than or equal to 35,000 lbs in rated thrust at take-off.
- In another embodiment according to any of the previous embodiments, the oil tank holds greater than or equal to 35 and less than or equal to 50 quarts of oil.
- In another embodiment according to any of the previous embodiments, the oil tank is associated with an engine having greater than or equal to 35,000 and less than or equal to 100,000 lbs in rated thrust at take-off.
- In another embodiment according to any of the previous embodiments, the gear reduction includes a sun gear for driving intermediate gears. Oil baffles are located circumferentially between the intermediate gears.
- In another embodiment according to any of the previous embodiments, an oil capture gutter surrounds the gear reduction.
- In another embodiment according to any of the previous embodiments, an oil capture gutter surrounds the gear reduction.
- In another embodiment according to any of the previous embodiments, the separator includes a scroll spiraling from the inlet to a deaerator exit.
- In another embodiment according to any of the previous embodiments, the exit includes a plurality of holes in a shell.
- In another featured embodiment, method of designing a gas turbine engine includes providing a fan drive turbine for driving a gear reduction. The gear reduction drives a fan rotor. A lubrication system is provided to supply oil to the gear reduction, with an oil tank, the lubrication system including a lubricant pump. Mixed air and oil are delivered to a deaerator inlet, the deaerator including a separator for separating oil, and delivering separated air to an air outlet, and delivering separated oil back into an oil tank. The lubricant separator includes a member having lubricant flow paths on both of two opposed sides.
- In another embodiment according to the previous embodiment, the separator is at an intermediate position in the inlet.
- In another embodiment according to any of the previous embodiments, the air outlet has a tube extending downwardly into a deaerator shell.
- In another embodiment according to any of the previous embodiments, the flow separator includes a scroll spiraling from the inlet to a deaerator exit.
- In another embodiment according to any of the previous embodiments, the separator is at an intermediate position in the inlet.
- These and other features may be best understood from the following drawings and specification.
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FIG. 1 is a schematic view of a gas turbine engine. -
FIG. 2 shows a portion of a cross-section of a gear reduction. -
FIG. 3 shows another portion of a gear reduction. -
FIG. 4 shows a lubrication system. -
FIG. 5 shows a deaerator. -
FIG. 6 shows internal structure of the deaerator. -
FIG. 7 shows additional internal structure of the deaerator. -
FIG. 1 schematically illustrates agas turbine engine 20. Thegas turbine engine 20 is disclosed herein as a two-spool turbofan that generally incorporates afan section 22, acompressor section 24, acombustor section 26 and aturbine section 28. Alternative engines might include an augmentor section (not shown) among other systems or features. Thefan section 22 drives air along a bypass flow path B in a bypass duct defined within anacelle 15, while thecompressor section 24 drives air along a core flow path C for compression and communication into thecombustor section 26 then expansion through theturbine section 28. Although depicted as a two-spool turbofan gas turbine engine in the disclosed non-limiting embodiment, it should be understood that the concepts described herein are not limited to use with two-spool turbofans as the teachings may be applied to other types of turbine engines including three-spool architectures. - The
exemplary engine 20 generally includes alow speed spool 30 and ahigh speed spool 32 mounted for rotation about an engine central longitudinal axis A relative to an enginestatic structure 36 viaseveral bearing systems 38. It should be understood that various bearingsystems 38 at various locations may alternatively or additionally be provided, and the location of bearingsystems 38 may be varied as appropriate to the application. - The
low speed spool 30 generally includes aninner shaft 40 that interconnects afan 42, a first (or low)pressure compressor 44 and a first (or low)pressure turbine 46. Theinner shaft 40 is connected to thefan 42 through a speed change mechanism, which in exemplarygas turbine engine 20 is illustrated as a gearedarchitecture 48 to drive thefan 42 at a lower speed than thelow speed spool 30. Thehigh speed spool 32 includes anouter shaft 50 that interconnects a second (or high)pressure compressor 52 and a second (or high)pressure turbine 54. Acombustor 56 is arranged inexemplary gas turbine 20 between thehigh pressure compressor 52 and thehigh pressure turbine 54. Amid-turbine frame 57 of the enginestatic structure 36 is arranged generally between thehigh pressure turbine 54 and thelow pressure turbine 46. Themid-turbine frame 57 furthersupports bearing systems 38 in theturbine section 28. Theinner shaft 40 and theouter shaft 50 are concentric and rotate via bearingsystems 38 about the engine central longitudinal axis A which is collinear with their longitudinal axes. - The core airflow is compressed by the
low pressure compressor 44 then thehigh pressure compressor 52, mixed and burned with fuel in thecombustor 56, then expanded over thehigh pressure turbine 54 andlow pressure turbine 46. Themid-turbine frame 57 includesairfoils 59 which are in the core airflow path C. Theturbines low speed spool 30 andhigh speed spool 32 in response to the expansion. It will be appreciated that each of the positions of thefan section 22,compressor section 24,combustor section 26,turbine section 28, and fandrive gear system 48 may be varied. For example,gear system 48 may be located aft ofcombustor section 26 or even aft ofturbine section 28, andfan section 22 may be positioned forward or aft of the location ofgear system 48. - The
engine 20 in one example is a high-bypass geared aircraft engine. In a further example, theengine 20 bypass ratio is greater than or equal to about six (6), with an example embodiment being greater than about ten (10), the gearedarchitecture 48 is an epicyclic gear train, such as a planetary gear system or other gear system, with a gear reduction ratio of greater than about 2.3 and thelow pressure turbine 46 has a pressure ratio that is greater than about five. In one disclosed embodiment, theengine 20 bypass ratio is greater than or equal to about ten (10:1), the fan diameter is significantly larger than that of thelow pressure compressor 44, and thelow pressure turbine 46 has a pressure ratio that is greater than about five 5:1.Low pressure turbine 46 pressure ratio is pressure measured prior to inlet oflow pressure turbine 46 as related to the pressure at the outlet of thelow pressure turbine 46 prior to an exhaust nozzle. The gearedarchitecture 48 may be an epicycle gear train, such as a planetary gear system or other gear system, with a gear reduction ratio of greater than about 2.3:1. It should be understood, however, that the above parameters are only exemplary of one embodiment of a geared architecture engine and that the present invention is applicable to other gas turbine engines including direct drive turbofans. - A significant amount of thrust is provided by the bypass flow B due to the high bypass ratio. The
fan section 22 of theengine 20 is designed for a particular flight condition—typically cruise at about 0.8 Mach and about 35,000 feet. The flight condition of 0.8 Mach and 35,000 ft, with the engine at its best fuel consumption—also known as “bucket cruise Thrust Specific Fuel Consumption (‘TSFC’)”—is the industry standard parameter of lbm of fuel being burned divided by lbf of thrust the engine produces at that minimum point. “Low fan pressure ratio” is the pressure ratio across the fan blade alone, without a Fan Exit Guide Vane (“FEGV”) system. The low fan pressure ratio as disclosed herein according to one non-limiting embodiment is less than about 1.45. “Low corrected fan tip speed” is the actual fan tip speed in ft/sec divided by an industry standard temperature correction of └(Tram ° R)/(518.7° R)┘0.5. The “Low corrected fan tip speed” as disclosed herein according to one non-limiting embodiment is less than about 1150 ft/second. - As shown in
FIG. 2 , aflexible shaft 99, which is driven by theturbine 46, drives asun gear 101 which, in turn, engages and drivesintermediate gears 102. In some embodiments, theintermediate gears 102 may be planet gears of a planetary epicyclic gear system. In other embodiments, theintermediate gears 102 may be star gears of a star epicyclic gear system. Theintermediate gears 102 engage and drive aring gear 103 to, in turn, drive anoutput shaft 106, which then drives thefan rotor 42. In other embodiments, a planetary gear carrier (not shown) driven by planetary gears may drive the fan shaft. Lubricant is supplied to ajournal pin 108, to theintermediate gears 102 and to other locations within thegear reduction 48. -
FIG. 3 shows baffles 100 which are placed circumferentially between adjacent planet gears 102. - A
gutter 104 surrounds thegear reduction 48 and captures oil that has left the gear reduction. Oil from thegear reduction 48 is returned to a pump 72 (SeeFIG. 4 ) or atank 90 as shown schematically inFIG. 4 . As shown, alubricant system 70 includes thegear reduction 48 which may be structured as shown inFIGS. 2 and 3 . Notably, complete details of the operation of the baffle, the gutter and the other portions of the gear reduction may be as disclosed in U.S. Pat. No. 6,223,616, the disclosure of which with regard to the operation of the gear reduction is incorporated by reference. - Oil flows from an
oil pump 72 to afilter 74 through apressure relief valve 76 to an air/oil cooler 78 and then to a fuel/oil cooler 80. The oil may pass through an oilpressure trim orifice 82 and back to thetank 90. Alternatively, the oil may pass through astrainer 84 and then to thegear reduction 48. Oil returning from the gear reduction and, in particular, from the gutter, may pass back directly to thepump 72 or to thetank 90. This is a simplification of the overall lubricant system and, as appreciated, there may be other components. - Applicant has recognized that by utilizing
baffles 100 and agutter 104 on thegear reduction 48, which may be generally as disclosed in the above-mentioned U.S. patent, the oil need not sit in the oil tank for ten seconds in order to de-aerate. Thus, the size of thetank 90 may be made much smaller. - Conventional turbofans allow the oil to dwell in an oil tank for approximately seven to ten seconds. The dwell time allows air bubbles to separate from the oil to prevent foaming. With the move to a geared gas turbine engine, the oil flow volumes may effectively double. This would require a much larger oil tank, and as much as twice as large if the same dwell time is allowed. Thus, it becomes important to reduce dwell time.
- Applicant has discovered that oil is de-aerated by the
baffles 100 and gutter system and that a dwell time in the oil tank to remove air bubbles may be less than five seconds. More preferably, it may be less than or equal to about 3.0 seconds. This allows the use ofoil tank 90 to be of a size roughly equivalent to the size utilized in prior non-geared gas turbine engines. Adeaerator 88 is shown incorporated into theoil tank 90. - The better the deaeration before the oil reaches the tank, the shorter the dwell time that can be achieved. The disclosed deaerator achieves these very low dwell times.
- As an example, an oil tank that holds 25 to 35 quarts of oil may be utilized on a geared gas turbine engine with 15,000 to 35,000 lbs in rated thrust at take-off. Further, an oil tank may be 35 quarts to 50 quarts of oil for an engine with 35,000 to 100,000 lbs in rated thrust at take-off.
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FIG. 5 shows adeaerator embodiment 188. Aline 190 receives an air/oil mixture such as from thepump 72. Air leaves through anair outlet 192, as shown inFIG. 4 . - A plurality of
oil outlets 194 are shown in anouter shell 195 of the deaerator. Anoil level 196 is shown schematically, and would be the oil level within theoil tank 90 ofFIG. 4 . - As shown in
FIG. 6 , a flow splitter orseparator 200 is provided inline to theinlet 190 and serves to split the air/oil flow into two paths, and at an intermediate location ininlet 190. This will hasten the deaeration of the mixed oil and air from theinlet 190. The air will be at the radially outer locations, and will pass through atube 193 into theair outlet 192. As shown,air outlet 192 has anend 300 extending into ashell 302 ofdeaerator 188. - As shown in
FIG. 7 , the oil will flow downwardly along anupper path 202 of a scroll or spiral, and along alower path 204. Although shown as vertically upper and lower sides, other opposed side orientations may be used. The inventive deaerator more quickly removes the oil, and thus facilitates the dwell times as mentioned above. - A
deaerator exit 194 delivers oil into theoil tank 90 at least 2 inches (5.08 centimeters) between afreestanding oil level 196 within thetank 90. An inlet velocity to thedeaerator 188 may be less than or equal to 14 feet/second. An exit velocity from thedeaerator 188 into theair outlet 192 may be less than or equal to 14 feet/second. - Applicant has found that introducing the oil and air mixture into an oil tank is much “quieter,” resulting in less re-aeration when it is delivered at least two inches below a free surface. As an example, if the oil were sprayed into the free surface, this could cause splashing and foaming.
- As to the velocity, high velocity oil and air mixtures entering the tank may cause re-aeration. The 14 feet/second is a very good goal to reduce the chances of re-aeration.
- Although an embodiment of this invention has been disclosed, a worker of ordinary skill in this art would recognize that certain modifications would come within the scope of this invention. For that reason, the following claims should be studied to determine the true scope and content of this invention.
Claims (30)
1. A gas turbine engine comprising:
a fan section including a fan rotor;
a compressor section;
a turbine section including a fan drive turbine that drives said fan rotor through a gear reduction;
a lubrication system that supplies oil to said gear reduction and includes a lubricant pump that supplies a mixed air and oil to an inlet of a deaerator during operation;
wherein said deaerator includes a shell defining a cavity and a separator that separates the mixed air and oil in said cavity, delivers separated air to an air outlet of said deaerator and delivers separated oil back into an oil tank during operation.
2. The gas turbine engine as set forth in claim 1 , wherein said separator includes a member that splits the mixed air and oil into lubricant flow paths on both of two opposed sides, said separator includes a scroll spiraling from said inlet to an exit of said deaerator, and said gear reduction includes a sun gear that drives intermediate gears, and a ring gear.
3. The gas turbine engine as set forth in claim 2 , wherein a gear reduction ratio of said gear reduction is greater than 2.3:1.
4. The gas turbine engine as set forth in claim 3 , wherein a dwell time of oil in said oil tank as removed by said lubricant pump, on average, is five seconds or less during operation.
5. The gas turbine engine as set forth in claim 4 , wherein said engine is rated greater than or equal to 15,000 and less than or equal to 100,000 lbs in rated thrust at take-off.
6. The gas turbine engine as set forth in claim 4 , wherein said member of said separator is at an intermediate position in said inlet.
7. The gas turbine engine as set forth in claim 6 , wherein said gear reduction includes oil baffles circumferentially between said adjacent intermediate gears.
8. The gas turbine engine as set forth in claim 7 , further comprising:
a bypass ratio of greater than or equal to 10;
wherein said fan section has a low fan pressure ratio of less than 1.45; and
wherein said fan drive turbine includes an inlet, an outlet and a pressure ratio of greater than 5, the pressure ratio being pressure measured prior to said inlet as related to pressure at said outlet prior to an exhaust nozzle.
9. The gas turbine engine as set forth in claim 8 , wherein said deaerator is incorporated into said oil tank, and said exit includes a plurality of oil outlets in a shell of said deaerator.
10. The gas turbine engine as set forth in claim 9 , wherein said exit delivers oil into said oil tank at least 2 inches (5.08 centimeters) beneath a freestanding oil level within said tank during operation.
11. The gas turbine engine as set forth in claim 9 , further comprising a gutter that surrounds said gear reduction such that said gutter captures oil from said gear reduction during operation.
12. The gas turbine engine as set forth in claim 11 , wherein said lubricant system includes a filter, an air/oil cooler and a fuel/oil cooler arranged such that oil flows from said lubricant pump to said filter, then flows to said air/oil cooler, and then flows to said fuel/oil cooler, and then passes back to said oil tank or said gear reduction during operation.
13. The gas turbine engine as set forth in claim 12 , wherein oil returning from said gutter passes back directly to said pump or said oil tank during operation.
14. The gas turbine engine as set forth in claim 11 , wherein an inlet velocity to said deaerator is less than or equal to 14 feet/second, and an exit velocity from said deaerator of the separated air is less than or equal to 14 feet/second during operation.
15. The gas turbine engine as set forth in claim 14 , wherein said fan drive turbine drives a compressor rotor of said compressor section, along with said fan rotor through said gear reduction, and a low corrected fan tip speed of less than 1150 feet/second.
16. The gas turbine engine as set forth in claim 15 , wherein a dwell time of oil in said oil tank as removed by said lubricant pump, on average, is three seconds or less during operation.
17. The gas turbine engine as set forth in claim 16 , wherein said intermediate gears engage and drive said ring gear to drive an output shaft that drives said fan rotor.
18. The gas turbine engine as set forth in claim 17 , wherein:
said oil tank may hold greater than or equal to 25 and less than or equal to 35 quarts of oil; and
wherein said oil tank is associated with an engine having greater than or equal to 15,000 and less than or equal to 35,000 lbs in rated thrust at take-off.
19. The gas turbine engine as set forth in claim 17 , wherein:
said oil tank holds greater than or equal to 35 and less than or equal to 50 quarts of oil; and
wherein said oil tank is associated with an engine having greater than or equal to 35,000 and less than or equal to 100,000 lbs in rated thrust at take-off.
20. A method of designing a gas turbine engine comprising:
providing a fan drive turbine that drives a fan rotor through a gear reduction; and
providing a lubrication system that supplies oil to said gear reduction, with an oil tank, said lubrication system including a lubricant pump, said lubrication system including a deaerator;
supplying a mixed air and oil to an inlet of said deaerator, said deaerator including a shell defining a cavity;
separating with said separator the mixed air and oil in said cavity, delivering separated air to an air outlet of said deaerator, and delivering separated oil from said deaerator back into said oil tank.
21. The method as set forth in claim 20 , wherein said step of separating includes a member of said separator splitting the mixed air and oil into lubricant flow paths on both of two opposed sides.
22. The method as set forth in claim 21 , wherein said separator includes a scroll spiraling from said inlet to an exit of said deaerator, and said step of separating includes causing oil to flow downwardly along upper and lower paths of said scroll.
23. The method as set forth in claim 22 , wherein:
said gear reduction includes a sun gear that drives intermediate gears, and a ring gear;
a dwell time of oil in said oil tank as removed by said lubricant pump, on average, is five seconds or less; and
said deaerator is incorporated into said oil tank.
24. The method as set forth in claim 23 , further comprising:
a bypass ratio of greater than or equal to 10;
wherein a gear reduction ratio of said gear reduction is greater than 2.3:1; and
wherein said fan drive turbine includes an inlet, an outlet and a pressure ratio of greater than 5, the pressure ratio being pressure measured prior to said inlet as related to pressure at said outlet prior to an exhaust nozzle.
25. The method as set forth in claim 24 , wherein said gear reduction includes oil baffles circumferentially between said adjacent intermediate gears.
26. The method as set forth in claim 25 , wherein:
an inlet velocity to said deaerator is less than or equal to 14 feet/second; and
an exit velocity from said deaerator of the separated air into said air outlet is less than or equal to 14 feet/second.
27. The method as set forth in claim 26 , wherein:
said oil tank may hold greater than or equal to 25 and less than or equal to 50 quarts of oil; and
wherein said oil tank is associated with an engine having rated greater than or equal to 15,000 and less than or equal to 100,000 lbs in rated thrust at take-off.
28. The method as set forth in claim 27 , further comprising capturing oil from said gear reduction in a gutter that surrounds said gear reduction.
29. The method as set forth in claim 28 , wherein said member of said separator is at an intermediate position in said inlet, and said air outlet has a tube extending downwardly into a shell of said deaerator.
30. The method as set forth in claim 29 , further comprising:
supplying oil from said lubricant pump to a filter, then to an air/oil cooler, and then to a fuel/oil cooler, and then passing the oil back to said oil tank or said gear reduction; and
delivering oil from said exit into said oil tank at least 2 inches (5.08 centimeters) beneath a freestanding oil level within said oil tank.
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US16/100,930 US20190063330A1 (en) | 2014-07-01 | 2018-08-10 | Geared gas turbine engine with oil deaerator |
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US201462019452P | 2014-07-01 | 2014-07-01 | |
US14/737,670 US9976490B2 (en) | 2014-07-01 | 2015-06-12 | Geared gas turbine engine with oil deaerator |
US15/873,961 US20180238242A1 (en) | 2014-07-01 | 2018-01-18 | Geared gas turbine engine with oil deaerator |
US16/100,930 US20190063330A1 (en) | 2014-07-01 | 2018-08-10 | Geared gas turbine engine with oil deaerator |
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US15/873,961 Continuation US20180238242A1 (en) | 2014-07-01 | 2018-01-18 | Geared gas turbine engine with oil deaerator |
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US15/873,961 Abandoned US20180238242A1 (en) | 2014-07-01 | 2018-01-18 | Geared gas turbine engine with oil deaerator |
US16/100,930 Abandoned US20190063330A1 (en) | 2014-07-01 | 2018-08-10 | Geared gas turbine engine with oil deaerator |
US17/085,616 Active 2036-01-09 US11725589B2 (en) | 2014-07-01 | 2020-10-30 | Geared gas turbine engine with oil deaerator |
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US15/873,961 Abandoned US20180238242A1 (en) | 2014-07-01 | 2018-01-18 | Geared gas turbine engine with oil deaerator |
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2018
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Also Published As
Publication number | Publication date |
---|---|
EP2963249B1 (en) | 2020-05-13 |
EP3693564A1 (en) | 2020-08-12 |
US20160017812A1 (en) | 2016-01-21 |
EP2963249A1 (en) | 2016-01-06 |
US11725589B2 (en) | 2023-08-15 |
US9976490B2 (en) | 2018-05-22 |
US20210231059A1 (en) | 2021-07-29 |
US20180238242A1 (en) | 2018-08-23 |
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