US20140090930A1 - Multiple reservoir lubrication system - Google Patents
Multiple reservoir lubrication system Download PDFInfo
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- US20140090930A1 US20140090930A1 US13/630,205 US201213630205A US2014090930A1 US 20140090930 A1 US20140090930 A1 US 20140090930A1 US 201213630205 A US201213630205 A US 201213630205A US 2014090930 A1 US2014090930 A1 US 2014090930A1
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- Prior art keywords
- reservoir
- lubricant
- lubrication system
- valve
- manifold
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Classifications
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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
- 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
- F01M11/00—Component parts, details or accessories, not provided for in, or of interest apart from, groups F01M1/00 - F01M9/00
- F01M11/06—Means for keeping lubricant level constant or for accommodating movement or position of machines or engines
- F01M11/062—Accommodating movement or position of machines or engines, e.g. dry sumps
- F01M11/065—Position
- F01M11/067—Position inverted, e.g. for inverted flight
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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
Definitions
- Example areas of a gas turbine engine require uninterrupted lubrication during engine operation.
- Example areas are bearings, such as rolling element bearings or journal bearings, or gears used throughout the engine and engine accessories.
- Lubricant is stored in a reservoir.
- a sudden change in attitude of the engine could move the lubricant in the reservoir, moving the lubricant away from a discharge passage. If this occurs, there could be an interruption in the supply of lubricant to the lubricated components.
- a lubrication system for use with a gas turbine engine includes, a first reservoir for containing a lubricant.
- the first reservoir includes a first discharge passage through which the lubricant is flowable in a first direction.
- a second reservoir contains the lubricant.
- the second reservoir includes a second discharge passage through which the lubricant is flowable in a second direction.
- the first direction is generally opposite to the second direction.
- a first pump pumps the lubricant from the first reservoir.
- a second pump pumps the lubricant from the second reservoir.
- a manifold distributes the lubricant to a component. The lubricant from the first pump and the second pump flows into the manifold and exits the manifold through a manifold discharge.
- the component is a bearing.
- the component is a fan journal bearing of a gas turbine engine.
- the first direction is substantially upwardly and the second direction is substantially downwardly.
- an output of each of the first pump and the second pump is greater than a lubrication requirement of the component.
- the lubricant flows directly from the manifold discharge of the manifold to the component.
- a valve in a further embodiment of any of the foregoing lubrication systems, includes a valve.
- the lubricant flows from the manifold discharge of the manifold to the valve.
- valve is a relief valve.
- valve directs a portion of the lubricant to the component and a remainder of the lubricant to at least one of the first reservoir and the second reservoir.
- valve closes if one of the first reservoir or the second reservoir is empty.
- the valve is a control valve.
- the lubrication system includes a sensor associated with each of the first reservoir and the second reservoir that detects an amount of the lubricant in each of the first reservoir and the second reservoir.
- the control valve directs the lubricant to the one of the first reservoir and the second reservoir if one of the sensors detects that the one of the first reservoir and the second reservoir is depleted of the lubricant.
- a lubrication system for use with a gas turbine engine includes, a first reservoir for containing a lubricant.
- the first reservoir includes a first discharge passage through which the lubricant is flowable in a first direction.
- a second reservoir containing a lubricant.
- the second reservoir includes a second discharge passage through which the lubricant is flowable in a second direction.
- the first direction is opposite to the second direction.
- a first pump pumps the lubricant from the first reservoir.
- a second pump pumps the lubricant from the second reservoir.
- a manifold distributes the lubricant to a bearing.
- the lubricant from the first pump and the second pump flows into the manifold and exits the manifold through a manifold discharge, and a valve.
- the lubricant flows from the manifold discharge of the manifold to the valve.
- the component is a fan journal bearing of a gas turbine engine.
- the first direction is substantially upwardly and the second direction is substantially downwardly.
- an output of each of the first pump and the second pump is greater than a lubrication requirement of the component.
- valve is a relief valve.
- valve directs a portion of the lubricant to the component and a remainder of the lubricant to at least one of the first reservoir and the second reservoir.
- valve closes if one of the first reservoir or the second reservoir is empty.
- the valve is a control valve.
- the lubrication system includes a sensor associated with each of the first reservoir and the second reservoir that detects an amount of the lubricant in each of the first reservoir and the second reservoir.
- the control valve directs the lubricant to the one of the first reservoir and the second reservoir if one of the sensors detects that the one of the first reservoir and the second reservoir is depleted of the lubricant.
- FIG. 1 illustrates a schematic view of an embodiment of a gas turbine engine
- FIG. 2 illustrates a lubrication system
- FIG. 1 schematically illustrates a gas turbine engine 20 .
- the gas turbine engine 20 is disclosed herein as a two-spool turbofan that generally incorporates a fan section 22 , a compressor section 24 , a combustor section 26 and a turbine section 28 .
- Alternative engines might include an augmentor section (not shown) among other systems or features.
- 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 turbofans as the teachings may be applied to other types of turbine engines including three-spool or geared turbofan architectures.
- the fan section 22 drives air along a bypass flowpath B while the compressor section 24 drives air along a core flowpath C for compression and communication into the combustor section 26 then expansion through the turbine section 28 .
- the gas turbine engine 20 generally includes a low speed spool 30 and a high speed spool 32 mounted for rotation about an engine central longitudinal axis A relative to an engine static structure 36 via several bearing systems 38 . It should be understood that various bearing systems 38 at various locations may alternatively or additionally be provided. For example, the bearing system 38 also includes fan journal bearings 38 a.
- the low speed spool 30 generally includes an inner shaft 40 that interconnects a fan 42 , a low pressure compressor 44 and a low pressure turbine 46 .
- the inner shaft 40 is connected to the fan 42 through a geared architecture 48 to drive the fan 42 at a lower speed than the low speed spool 30 .
- the high speed spool 32 includes an outer shaft 50 that interconnects a high pressure compressor 52 and a high pressure turbine 54 .
- a combustor 56 is arranged between the high pressure compressor 52 and the high pressure turbine 54 .
- a mid-turbine frame 58 of the engine static structure 36 is arranged generally between the high pressure turbine 54 and the low pressure turbine 46 .
- the mid-turbine frame 58 further supports bearing systems 38 in the turbine section 28 .
- the inner shaft 40 and the outer shaft 50 are concentric and rotate via bearing systems 38 about the engine central longitudinal axis A, which is collinear with their longitudinal axes.
- the core airflow C is compressed by the low pressure compressor 44 , then the high pressure compressor 52 , mixed and burned with fuel in the combustor 56 , then expanded over the high pressure turbine 54 and low pressure turbine 46 .
- the mid-turbine frame 58 includes airfoils 60 which are in the core airflow path.
- the turbines 46 , 54 rotationally drive the respective low speed spool 30 and high speed spool 32 in response to the expansion.
- the gas turbine engine 20 is in one example a high-bypass geared aircraft engine.
- the gas turbine engine 20 bypass ratio is greater than about six (6:1) with an example embodiment being greater than ten (10:1).
- the geared architecture 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 (2.3:1).
- the low pressure turbine 46 has a pressure ratio that is greater than about five (5:1).
- the low pressure turbine 46 pressure ratio is pressure measured prior to inlet of low pressure turbine 46 as related to the pressure at the outlet of the low pressure turbine 46 prior to an exhaust nozzle.
- the gas turbine engine 20 bypass ratio is greater than about ten (10:1), and the fan diameter is significantly larger than that of the low pressure compressor 44 .
- the low pressure turbine 46 has a pressure ratio that is greater than about five (5:1).
- the geared architecture 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 2.5 (2.5:1). 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.
- the fan section 22 of the gas turbine engine 20 is designed for a particular flight condition—typically cruise at about 0.8 Mach and about 35,000 feet.
- TSFC is the industry standard parameter of 1 bm of fuel being burned divided by 1 bf 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 feet per second divided by an industry standard temperature correction of [(Tram ° R)/518.7) 0. 5 ].
- the “Low corrected fan tip speed” as disclosed herein according to one non-limiting embodiment is less than about 1150 feet per second (351 meters per second).
- the gas turbine engine 20 includes a lubrication system 62 that lubricates the bearing system 38 .
- the lubrication system 62 lubricates the fan journal bearings 38 a.
- the lubrication system 62 provides a constant and uninterrupted supply of lubricant.
- the lubricant is oil.
- the lubrication system 62 does not depend on gravity or valves for operation.
- the lubrication system 62 is also tolerant of debris and can operate autonomously.
- the lubrication system 62 includes a first reservoir 64 and a second reservoir 66 that each contain the lubricant. At least one of the reservoirs 64 and 66 continuously supplies the lubricant to the bearing system 38 under any operating condition.
- the first reservoir 64 includes a first discharge passage 68 that directs the lubricant to flow from the first reservoir 64 in a first direction X.
- the direction X is generally downwardly.
- the second reservoir 66 includes a second discharge passage 70 that directs the lubricant to flow from the second reservoir 66 in a second direction Y.
- the direction Y is generally upwardly.
- the direction X is opposite to the direction Y.
- the lubricant in the discharge passage 68 flows to a first pump 72
- the lubricant in the second discharge passage 70 flows to a second pump 74 .
- the pumps 72 and 74 are each sized so that the individual output of each of the pumps 72 and 74 or the combined output of the pumps 72 and 74 exceed the lubrication or cooling requirements of the bearing system 38 .
- two reservoirs 64 and 66 and two pumps 72 and 84 are illustrated and described, any number of reservoirs and pumps can be employed in the lubrication system 62 .
- the first pump 72 and the second pump 74 supply the lubricant to a common manifold 76 through the discharge passages 68 and 70 , respectively.
- the lubricant is discharged from the common manifold 76 through a common discharge 78 and ultimately to the bearing system 62 .
- the lubricant in the reservoirs 64 and 66 moves towards the upper portion of the reservoirs 64 and 66 . This could interrupt the flow of lubricant through the discharge passage 68 that directs the lubricant downwardly. However, as the discharge passage 70 directs the lubricant upwardly, the lubricant can continue to flow in an uninterrupted manner through the discharge passage 70 .
- the lubricant in the reservoirs 64 and 66 moves towards the lower portion of the reservoirs 64 and 66 . This could interrupt the flow of lubricant through the discharge passage 70 that directs the lubricant upwardly. However, as the discharge passage 68 directs the lubricant downwardly, the lubricant can continue to flow in an uninterrupted manner through the discharge passage 68 .
- the lubricant flows directly from the common discharge 78 of the common manifold 76 to the bearing system 38 .
- the lubricant flows from the common discharge 78 of the common manifold 76 to a valve 80 .
- the valve 80 directs the flow of the lubricant to the bearing system 38 and the reservoirs 64 and 66 as needed.
- the valve 80 is a relief valve, which is passive valve.
- the valve 80 directs the lubricant to the bearing system 38 and returns any excess lubricant to replenish the first reservoir 64 and the second reservoir 66 .
- the discharge pressure of the lubricant system 62 drops, closing the valve 80 .
- the pumps 72 and 74 continue to operate, and the pump 72 and 74 associated with the depleted reservoir 64 and 66 pumps air because the lubricant is depleted (for example, because of altitude or gravity vector location, etc.).
- the flow of the lubricant from the full reservoir 64 and 66 creates a seal at the valve 80 that blocks the flow of air from the empty reservoir 64 and 66 into the valve 80 .
- the lubricant from the reservoir 64 and 66 is pumped to the valve 80 , which directs the lubricant to the reservoir 64 and 66 that is empty.
- the lubrication system 62 returns to its initial state.
- the valve 80 can then be opened by pressure.
- the valve 80 is a control valve, which is an active valve.
- Each of the reservoirs 64 and 66 includes a sensor 82 that detects an amount of the lubricant in each of the reservoirs 64 and 66 . This information is provided to the valve 80 . Based on the information obtained by the sensors 82 , the valve 80 can be opened to return the excess lubricant to the reservoir 64 and 66 with the depleted lubricant.
- the reservoirs 64 and 66 are in direct communication with each other.
- the reservoirs 64 and 66 can supply lubricant to each other when needed to prevent depletion of the lubricant in either of the reservoirs 64 and 66 .
- the lubrication system 62 can be employed in a gas turbine engine without geared architecture.
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Abstract
A lubrication system for use with a gas turbine engine includes a first reservoir for containing a lubricant. The first reservoir includes a first discharge passage through which the lubricant is flowable in a first direction. A second reservoir contains the lubricant. The second reservoir includes a second discharge passage through which the lubricant is flowable in a second direction. The first direction is generally opposite to the second direction. A first pump pumps the lubricant from the first reservoir. A second pump pumps the lubricant from the second reservoir. A manifold distributes the lubricant to a component. The lubricant from the first pump and the second pump flows into the manifold and exits the manifold through a manifold discharge.
Description
- Some areas of a gas turbine engine require uninterrupted lubrication during engine operation. Example areas are bearings, such as rolling element bearings or journal bearings, or gears used throughout the engine and engine accessories. Lubricant is stored in a reservoir.
- A sudden change in attitude of the engine could move the lubricant in the reservoir, moving the lubricant away from a discharge passage. If this occurs, there could be an interruption in the supply of lubricant to the lubricated components.
- A lubrication system for use with a gas turbine engine according to an exemplary embodiment of this disclosure, among other possible things includes, a first reservoir for containing a lubricant. The first reservoir includes a first discharge passage through which the lubricant is flowable in a first direction. A second reservoir contains the lubricant. The second reservoir includes a second discharge passage through which the lubricant is flowable in a second direction. The first direction is generally opposite to the second direction. A first pump pumps the lubricant from the first reservoir. A second pump pumps the lubricant from the second reservoir. A manifold distributes the lubricant to a component. The lubricant from the first pump and the second pump flows into the manifold and exits the manifold through a manifold discharge.
- In a further embodiment of any of the foregoing lubrication systems, the component is a bearing.
- In a further embodiment of any of the foregoing lubrication systems, the component is a fan journal bearing of a gas turbine engine.
- In a further embodiment of any of the foregoing lubrication systems, the first direction is substantially upwardly and the second direction is substantially downwardly.
- In a further embodiment of any of the foregoing lubrication systems, an output of each of the first pump and the second pump is greater than a lubrication requirement of the component.
- In a further embodiment of any of the foregoing lubrication systems, the lubricant flows directly from the manifold discharge of the manifold to the component.
- In a further embodiment of any of the foregoing lubrication systems, includes a valve. The lubricant flows from the manifold discharge of the manifold to the valve.
- In a further embodiment of any of the foregoing lubrication systems, the valve is a relief valve.
- In a further embodiment of any of the foregoing lubrication systems, the valve directs a portion of the lubricant to the component and a remainder of the lubricant to at least one of the first reservoir and the second reservoir.
- In a further embodiment of any of the foregoing lubrication systems, the valve closes if one of the first reservoir or the second reservoir is empty.
- In a further embodiment of any of the foregoing lubrication systems, the valve is a control valve. The lubrication system includes a sensor associated with each of the first reservoir and the second reservoir that detects an amount of the lubricant in each of the first reservoir and the second reservoir. The control valve directs the lubricant to the one of the first reservoir and the second reservoir if one of the sensors detects that the one of the first reservoir and the second reservoir is depleted of the lubricant.
- A lubrication system for use with a gas turbine engine according to an exemplary embodiment of this disclosure, among other possible things includes, a first reservoir for containing a lubricant. The first reservoir includes a first discharge passage through which the lubricant is flowable in a first direction. A second reservoir containing a lubricant. The second reservoir includes a second discharge passage through which the lubricant is flowable in a second direction. The first direction is opposite to the second direction. A first pump pumps the lubricant from the first reservoir. A second pump pumps the lubricant from the second reservoir. A manifold distributes the lubricant to a bearing. The lubricant from the first pump and the second pump flows into the manifold and exits the manifold through a manifold discharge, and a valve. The lubricant flows from the manifold discharge of the manifold to the valve.
- In a further embodiment of any of the foregoing lubrication system, the component is a fan journal bearing of a gas turbine engine.
- In a further embodiment of any of the foregoing lubrication systems, the first direction is substantially upwardly and the second direction is substantially downwardly.
- In a further embodiment of any of the foregoing lubrication systems, an output of each of the first pump and the second pump is greater than a lubrication requirement of the component.
- In a further embodiment of any of the foregoing lubrication systems, the valve is a relief valve.
- In a further embodiment of any of the foregoing lubrication systems, the valve directs a portion of the lubricant to the component and a remainder of the lubricant to at least one of the first reservoir and the second reservoir.
- In a further embodiment of any of the foregoing lubrication systems, the valve closes if one of the first reservoir or the second reservoir is empty.
- In a further embodiment of any of the foregoing lubrication systems, the valve is a control valve. The lubrication system includes a sensor associated with each of the first reservoir and the second reservoir that detects an amount of the lubricant in each of the first reservoir and the second reservoir. The control valve directs the lubricant to the one of the first reservoir and the second reservoir if one of the sensors detects that the one of the first reservoir and the second reservoir is depleted of the lubricant.
- These and other features of the present invention can be best understood from the following specification and drawings, the following of which is a brief description.
-
FIG. 1 illustrates a schematic view of an embodiment of a gas turbine engine; and -
FIG. 2 illustrates a lubrication system. -
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. - Although depicted as a 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 turbofans as the teachings may be applied to other types of turbine engines including three-spool or geared turbofan architectures.
- The
fan section 22 drives air along a bypass flowpath B while thecompressor section 24 drives air along a core flowpath C for compression and communication into thecombustor section 26 then expansion through theturbine section 28. - The
gas turbine 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 thatvarious bearing systems 38 at various locations may alternatively or additionally be provided. For example, thebearing system 38 also includesfan journal bearings 38 a. - The
low speed spool 30 generally includes aninner shaft 40 that interconnects afan 42, a low pressure compressor 44 and alow pressure turbine 46. Theinner shaft 40 is connected to thefan 42 through 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 ahigh pressure compressor 52 and ahigh pressure turbine 54. - A
combustor 56 is arranged between thehigh pressure compressor 52 and thehigh pressure turbine 54. - A mid-turbine frame 58 of the engine
static structure 36 is arranged generally between thehigh pressure turbine 54 and thelow pressure turbine 46. The mid-turbine frame 58 furthersupports bearing systems 38 in theturbine section 28. - The
inner 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 C is compressed by the low pressure compressor 44, then the
high pressure compressor 52, mixed and burned with fuel in thecombustor 56, then expanded over thehigh pressure turbine 54 andlow pressure turbine 46. The mid-turbine frame 58 includesairfoils 60 which are in the core airflow path. Theturbines low speed spool 30 andhigh speed spool 32 in response to the expansion. - The
gas turbine engine 20 is in one example a high-bypass geared aircraft engine. In a further example, thegas turbine engine 20 bypass ratio is greater than about six (6:1) with an example embodiment being greater than ten (10:1). 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 (2.3:1). Thelow pressure turbine 46 has a pressure ratio that is greater than about five (5:1). Thelow 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. - In one disclosed embodiment, the
gas turbine engine 20 bypass ratio is greater than about ten (10:1), and the fan diameter is significantly larger than that of the low pressure compressor 44. Thelow pressure turbine 46 has a pressure ratio that is greater than about five (5:1). 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 2.5 (2.5:1). 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 thegas turbine engine 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 feet, with the engine at its best fuel consumption, also known as bucket cruise Thrust Specific Fuel Consumption (“TSFC”). TSFC is the industry standard parameter of 1 bm of fuel being burned divided by 1 bf 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 feet per second divided by an industry standard temperature correction of [(Tram ° R)/518.7)0. 5]. The “Low corrected fan tip speed” as disclosed herein according to one non-limiting embodiment is less than about 1150 feet per second (351 meters per second).
- As shown in
FIG. 2 , thegas turbine engine 20 includes alubrication system 62 that lubricates the bearingsystem 38. In one example, thelubrication system 62 lubricates thefan journal bearings 38 a. Thelubrication system 62 provides a constant and uninterrupted supply of lubricant. In one example, the lubricant is oil. Thelubrication system 62 does not depend on gravity or valves for operation. Thelubrication system 62 is also tolerant of debris and can operate autonomously. - The
lubrication system 62 includes afirst reservoir 64 and asecond reservoir 66 that each contain the lubricant. At least one of thereservoirs bearing system 38 under any operating condition. - The
first reservoir 64 includes afirst discharge passage 68 that directs the lubricant to flow from thefirst reservoir 64 in a first direction X. In this example, the direction X is generally downwardly. Thesecond reservoir 66 includes asecond discharge passage 70 that directs the lubricant to flow from thesecond reservoir 66 in a second direction Y. In this example, the direction Y is generally upwardly. In this example, the direction X is opposite to the direction Y. - The lubricant in the
discharge passage 68 flows to afirst pump 72, and the lubricant in thesecond discharge passage 70 flows to asecond pump 74. Thepumps pumps pumps system 38. Although tworeservoirs pumps 72 and 84 are illustrated and described, any number of reservoirs and pumps can be employed in thelubrication system 62. - The
first pump 72 and thesecond pump 74 supply the lubricant to acommon manifold 76 through thedischarge passages common manifold 76 through acommon discharge 78 and ultimately to thebearing system 62. As the flow of the lubricant through thedischarge passages - For example, if the aircraft suddenly drops, the lubricant in the
reservoirs reservoirs discharge passage 68 that directs the lubricant downwardly. However, as thedischarge passage 70 directs the lubricant upwardly, the lubricant can continue to flow in an uninterrupted manner through thedischarge passage 70. - In another example, if the aircraft suddenly rises, the lubricant in the
reservoirs reservoirs discharge passage 70 that directs the lubricant upwardly. However, as thedischarge passage 68 directs the lubricant downwardly, the lubricant can continue to flow in an uninterrupted manner through thedischarge passage 68. - In one example, the lubricant flows directly from the
common discharge 78 of thecommon manifold 76 to thebearing system 38. - In another example, the lubricant flows from the
common discharge 78 of thecommon manifold 76 to avalve 80. Thevalve 80 directs the flow of the lubricant to thebearing system 38 and thereservoirs - In one example, the
valve 80 is a relief valve, which is passive valve. Thevalve 80 directs the lubricant to thebearing system 38 and returns any excess lubricant to replenish thefirst reservoir 64 and thesecond reservoir 66. - If one of the
reservoirs lubricant system 62 drops, closing thevalve 80. Thepumps pump reservoir full reservoir valve 80 that blocks the flow of air from theempty reservoir valve 80. The lubricant from thereservoir valve 80, which directs the lubricant to thereservoir reservoirs lubrication system 62 returns to its initial state. Thevalve 80 can then be opened by pressure. - In another example, the
valve 80 is a control valve, which is an active valve. Each of thereservoirs sensor 82 that detects an amount of the lubricant in each of thereservoirs valve 80. Based on the information obtained by thesensors 82, thevalve 80 can be opened to return the excess lubricant to thereservoir - In another example, the
reservoirs reservoirs reservoirs - Although a
gas turbine engine 20 with gearedarchitecture 48 is described, thelubrication system 62 can be employed in a gas turbine engine without geared architecture. - The foregoing description is only exemplary of the principles of the invention. Many modifications and variations are possible in light of the above teachings. It is, therefore, to be understood that within the scope of the appended claims, the invention may be practiced otherwise than using the example embodiments which have been specifically described. For that reason the following claims should be studied to determine the true scope and content of this invention.
Claims (19)
1. A lubrication system for use with a gas turbine engine comprising:
a first reservoir for containing a lubricant, wherein the first reservoir includes a first discharge passage through which the lubricant is flowable in a first direction;
a second reservoir for containing the lubricant, wherein the second reservoir includes a second discharge passage through which the lubricant is flowable in a second direction, wherein the first direction is generally opposite to the second direction;
a first pump that pumps the lubricant from the first reservoir;
a second pump that pumps the lubricant from the second reservoir; and
a manifold to distribute the lubricant to a component, wherein the lubricant from the first pump and the second pump flows into the manifold and exits the manifold through a manifold discharge.
2. The lubrication system as recited in claim 1 wherein the component is a bearing.
3. The lubrication system as recited in claim 1 wherein the component is a fan journal bearing of a gas turbine engine.
4. The lubrication system as recited in claim 1 wherein the first direction is substantially upwardly and the second direction is substantially downwardly.
5. The lubrication system as recited in claim 1 wherein an output of each of the first pump and the second pump is greater than a lubrication requirement of the component.
6. The lubrication system as recited in claim 1 wherein the lubricant flows directly from the manifold discharge of the manifold to the component.
7. The lubrication system as recited in claim 1 including a valve, wherein the lubricant flows from the manifold discharge of the manifold to the valve.
8. The lubrication system as recited in claim 7 wherein the valve is a relief valve.
9. The lubrication system as recited in claim 8 wherein the valve directs a portion of the lubricant to the component and a remainder of the lubricant to at least one of the first reservoir and the second reservoir.
10. The lubrication system as recited in claim 8 wherein the valve closes if one of the first reservoir or the second reservoir is empty.
11. The lubrication system as recited in claim 7 wherein the valve is a control valve, and the lubrication system includes a sensor associated with each of the first reservoir and the second reservoir that detects an amount of the lubricant in each of the first reservoir and the second reservoir, and the control valve directs the lubricant to the one of the first reservoir and the second reservoir if one of the sensors detects that the one of the first reservoir and the second reservoir is depleted of the lubricant.
12. A lubrication system for use with a gas turbine engine comprising:
a first reservoir for containing a lubricant, wherein the first reservoir includes a first discharge passage through which the lubricant is flowable in a first direction;
a second reservoir for containing a lubricant, wherein the second reservoir includes a second discharge passage through which the lubricant is flowable in a second direction, wherein the first direction is opposite to the second direction;
a first pump that pumps the lubricant from the first reservoir;
a second pump that pumps the lubricant from the second reservoir;
a manifold to distribute the lubricant to a bearing, wherein the lubricant from the first pump and the second pump flows into the manifold and exits the manifold through a manifold discharge; and
a valve, wherein the lubricant flows from the manifold discharge of the manifold to the valve.
13. The lubrication system as recited in claim 12 wherein the component is a fan journal bearing of a gas turbine engine.
14. The lubrication system as recited in claim 12 wherein the first direction is substantially upwardly and the second direction is substantially downwardly.
15. The lubrication system as recited in claim 12 wherein an output of each of the first pump and the second pump is greater than a lubrication requirement of the component.
16. The lubrication system as recited in claim 12 wherein the valve is a relief valve.
17. The lubrication system as recited in claim 16 wherein the valve directs a portion of the lubricant to the component and a remainder of the lubricant to at least one of the first reservoir and the second reservoir.
18. The lubrication system as recited in claim 16 wherein the valve closes if one of the first reservoir or the second reservoir is empty.
19. The lubrication system as recited in claim 16 wherein the valve is a control valve, and the lubrication system includes a sensor associated with each of the first reservoir and the second reservoir that detects an amount of the lubricant in each of the first reservoir and the second reservoir, and the control valve directs the lubricant to the one of the first reservoir and the second reservoir if one of the sensors detects that the one of the first reservoir and the second reservoir is depleted of the lubricant.
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/630,205 US20140090930A1 (en) | 2012-09-28 | 2012-09-28 | Multiple reservoir lubrication system |
PCT/US2013/061096 WO2014052207A1 (en) | 2012-09-28 | 2013-09-22 | Multiple reservoir lubrication system |
US15/709,663 US10711645B2 (en) | 2012-09-28 | 2017-09-20 | Multiple reservoir lubrication system |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/630,205 US20140090930A1 (en) | 2012-09-28 | 2012-09-28 | Multiple reservoir lubrication system |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US15/709,663 Continuation US10711645B2 (en) | 2012-09-28 | 2017-09-20 | Multiple reservoir lubrication system |
Publications (1)
Publication Number | Publication Date |
---|---|
US20140090930A1 true US20140090930A1 (en) | 2014-04-03 |
Family
ID=50384173
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US13/630,205 Abandoned US20140090930A1 (en) | 2012-09-28 | 2012-09-28 | Multiple reservoir lubrication system |
US15/709,663 Active 2033-04-28 US10711645B2 (en) | 2012-09-28 | 2017-09-20 | Multiple reservoir lubrication system |
Family Applications After (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US15/709,663 Active 2033-04-28 US10711645B2 (en) | 2012-09-28 | 2017-09-20 | Multiple reservoir lubrication system |
Country Status (2)
Country | Link |
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US (2) | US20140090930A1 (en) |
WO (1) | WO2014052207A1 (en) |
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US20180003082A1 (en) * | 2012-09-28 | 2018-01-04 | United Technologies Corporation | Multiple reservoir lubrication system |
US20180283211A1 (en) * | 2017-03-31 | 2018-10-04 | United Technologies Corporation | Gas turbine engine lubrication system and apparatus with boost pump system |
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Also Published As
Publication number | Publication date |
---|---|
US20180003082A1 (en) | 2018-01-04 |
WO2014052207A1 (en) | 2014-04-03 |
US10711645B2 (en) | 2020-07-14 |
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Owner name: UNITED TECHNOLOGIES CORPORATION, CONNECTICUT Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:JAMES, DENMAN H.;REEL/FRAME:029044/0801 Effective date: 20120928 |
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