Patent application number | Description | Published |
20120171004 | MATERIALS HANDLING VEHICLE HAVING A MANIFOLD LOCATED ON A POWER UNIT FOR MAINTAINING FLUID PRESSURE AT AN OUTPUT PORT AT A COMMANDED PRESSURE CORRESPONDING TO AN AUXILLARY DEVICE OPERATING PRESSURE - A materials handling vehicle is provided comprising: a power unit; a work assembly coupled to the power unit comprising a first auxiliary device; and a fluid supply system. The fluid supply system may comprise: pump structure for supplying a fluid; a first manifold apparatus located on the power unit; a second manifold apparatus located on the work assembly; and fluid supply line structure coupled between the first and second manifolds. The first manifold may receive fluid from the pump structure and comprise valve structure for maintaining fluid pressure at an output port of the first manifold apparatus at a commanded pressure substantially equal to or greater than an operating pressure of the first auxiliary device. | 07-05-2012 |
20120209478 | MATERIALS HANDLING VEHICLE ESTIMATING A SPEED OF A MOVABLE ASSEMBLY FROM A LIFT MOTOR SPEED - A materials handling vehicle is provided comprising: a support structure including a fixed member; a movable assembly coupled to the support structure; a hydraulic system; and a control system. The support structure further comprises lift apparatus to effect movement of the movable assembly relative to the support structure fixed member. The lift apparatus includes at least one ram/cylinder assembly. The hydraulic system includes a motor, a pump coupled to the motor to supply a pressurized fluid to the at least one ram/cylinder assembly, and at least one electronically controlled valve associated with the at least one ram/cylinder assembly. The control structure may estimate a speed of the movable assembly from a speed of the motor and control the operation of the at least one valve using the estimated movable assembly speed. | 08-16-2012 |
20130183127 | WARM UP CYCLE FOR A MATERIALS HANDLING VEHICLE - A method for operating a materials handling vehicle includes activating the materials handling vehicle and performing a warm up cycle. During the warm up cycle, energy is provided to at least one valve within the materials handling vehicle so as to energize the valve without providing a working fluid to the valve. Providing energy to the at least one valve effects a heating of oil located within the at least one valve. | 07-18-2013 |
20140326541 | MATERIALS HANDLING VEHICLE ESTIMATING A SPEED OF A MOVABLE ASSEMBLY FROM A LIFT MOTOR SPEED - A materials handling vehicle is provided including: a support structure including a fixed member; a movable assembly coupled to the support structure; a hydraulic system; and a control system. The support structure further includes lift apparatus to effect movement of the movable assembly relative to the support structure fixed member. The lift apparatus includes at least one ram/cylinder assembly. The hydraulic system includes a motor, a pump coupled to the motor to supply a pressurized fluid to the at least one ram/cylinder assembly, and at least one electronically controlled valve associated with the at least one ram/cylinder assembly. The control structure may estimate a speed of the movable assembly from a speed of the motor and calculate an updated pump volumetric efficiency using the estimated movable assembly speed and a determined movable assembly speed. | 11-06-2014 |
20140326542 | MATERIALS HANDLING VEHICLE MEASURING ELECTRIC CURRENT FLOW INTO/OUT OF A HYDRAULIC SYSTEM MOTOR - A materials handling vehicle is provided comprising: a support structure including a fixed member; a movable assembly coupled to the support structure; a hydraulic system; and a control system. The support structure further comprises lift apparatus to effect movement of the movable assembly relative to the support structure fixed member. The lift apparatus includes at least one ram/cylinder assembly. The hydraulic system includes a motor, a pump coupled to the motor to supply a pressurized fluid to the at least one ram/cylinder assembly, and at least one electronically controlled valve associated with the at least one ram/cylinder assembly. The control structure may measure an electric current flow into and/or out of the hydraulic system motor and reduce an operating speed of the hydraulic system motor if the electric current flow into and/or out of the hydraulic system motor is greater than or equal to a predetermined threshold value. | 11-06-2014 |
20140330488 | MATERIALS HANDLING VEHICLE MONITORING A PRESSURE OF HYDRAULIC FLUID WITHIN A HYDRAULIC STRUCTURE - A materials handling vehicle is provided comprising: a support structure including a fixed member; a movable assembly coupled to the support structure; a hydraulic system; and a control system. The support structure further comprises lift apparatus to effect movement of the movable assembly relative to the support structure fixed member. The lift apparatus includes at least one ram/cylinder assembly. The hydraulic system includes a motor, a pump coupled to the motor to supply a pressurized fluid to the at least one ram/cylinder assembly, and at least one electronically controlled valve associated with the at least one ram/cylinder assembly. The control structure may estimate a speed of the movable assembly from a speed of the motor and control the operation of the at least one valve using the estimated movable assembly speed. | 11-06-2014 |
Patent application number | Description | Published |
20120124964 | GAS TURBINE ENGINE WITH IMPROVED FUEL EFFICIENCY - A turbofan engine includes a fan driven by a low pressure turbine through a gear reduction. The gear reduction has a gear ratio of greater than or equal to about 2.4. The low pressure turbine has an expansion ratio greater than or equal to about 5. The fan has a bypass ratio greater than or equal to about 8. In other features, a turbofan engine includes a variable geometry fan exit guide vane (FEGV) system having a multiple of circumferentially spaced radially extending fan exit guide vanes. Rotation of the fan exit guide vanes between a nominal position and a rotated position selectively changes a fan bypass flow path to permit efficient operation at various flight conditions. | 05-24-2012 |
20120171018 | GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT - A gas turbine engine includes a fan section, a gear arrangement configured to drive the fan section, a compressor section and a turbine section. The compressor section includes a low pressure compressor section and a high pressure compressor section. The turbine section is configured to drive compressor section and the gear arrangement. An overall pressure ratio, which is provided by a combination of a pressure ratio across said low pressure compressor section and a pressure ratio across said high pressure compressor section, is greater than about 35. The pressure ratio across the low pressure compressor section is between about 3 and about 8 whereas the pressure ratio across the high pressure compressor section is between about 7 and about 15. | 07-05-2012 |
20120315130 | GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT - A gas turbine engine includes a fan section, a gear arrangement configured to drive the fan section, a compressor section and a turbine section. The compressor section includes a low pressure compressor section and a high pressure compressor section. The turbine section is configured to drive compressor section and the gear arrangement. An overall pressure ratio, which is provided by a combination of a pressure ratio across said low pressure compressor section and a pressure ratio across said high pressure compressor section, is greater than about 35. The pressure ratio across the high pressure compressor section is between about 7 and about 15, and a pressure ratio across the fan section is less than or equal to 1.45. | 12-13-2012 |
20130195645 | GEARED TURBOMACHINE ARCHITECTURE HAVING A LOW PROFILE CORE FLOW PATH CONTOUR - An exemplary geared turbomachine assembly includes a core inlet having a radially inner boundary that is spaced a first radial distance from a rotational axis of a turbomachine, and a compressor section inlet having a radially inner boundary that is spaced a second radial distance from the rotational axis. A ratio of the second radial distance to the first radial distance is of about 0.65 to about 0.9. | 08-01-2013 |
20140083107 | Method for Setting a Gear Ratio of a Fan Drive Gear System of a Gas Turbine Engine - A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan section including a fan rotatable about an axis and a speed reduction device in communication with the fan. The speed reduction device includes a star drive gear system with a star gear ratio of at least 1.5. A fan blade tip speed of the fan is less than 1400 fps. | 03-27-2014 |
20140090388 | OFF-TAKE POWER RATIO - An example method of allocating power within a gas turbine engine includes driving an off-take power delivery assembly using a first amount of power from a spool, the first amount of power corresponding to an off-take power requirement of a gas turbine engine; and driving the spool of the gas turbine engine using a second amount of power, wherein a ratio of the first amount of power to the second amount of power is greater than or equal to 0.009. | 04-03-2014 |
20140096509 | Geared Turbofan Engine With Increased Bypass Ratio and Compressor Ratio ... - A gas turbine engine is typically comprised of a fan stage, multiple compressor stages, and multiple turbine stages. These stages are made up of alternating rotating blade rows and static vane rows. The total number of blades and vanes is the airfoil count. An overall pressure ratio is greater than 30. A bypass ratio is greater than 8. A stage ratio is the product of the bypass ratio and the overall pressure ratio divided by the number of stages. An airfoil ratio is that product divided by the airfoil count. The stage ratio is greater than or equal to 22 and/or the airfoil ratio is greater than or equal to 0.12. | 04-10-2014 |
20140157752 | GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT - A method of designing a gas turbine engine includes providing a fan section including a fan; driving the fan section via a gear arrangement; providing a compressor section, including both a first compressor and a second compressor; and driving the compressor section and the gear arrangement via a turbine section. The pressure ratio across the first compressor is greater than or equal to about 7. | 06-12-2014 |
20140157753 | GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT - A method of designing a gas turbine engine includes providing a fan section including a fan; driving the fan section via a gear arrangement; providing a compressor section, including both a first compressor and a second compressor; and driving the compressor section and the gear arrangement via a turbine section. An overall pressure ratio, being provided by the combination of a pressure ratio across the first compressor and a pressure ratio across the second compressor, is greater than or equal to about 35. The pressure ratio across the first compressor is greater than or equal to about 7. | 06-12-2014 |
20140157754 | GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT - A gas turbine engine has a fan section, including a fan, a gear arrangement configured to drive the fan section, and a compressor section, including both a first compressor and a second compressor. A turbine section is configured to drive the compressor section and the gear arrangement. An overall pressure ratio is provided by the combination of the first compressor and the second compressor, with the overall pressure ratio being greater than or equal to about 35. A pressure ratio across the fan section is less than or equal to about 1.50. The fan is configured to deliver a portion of air into the compressor section, and a portion of air into a bypass duct. | 06-12-2014 |
20140157755 | GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT - A gas turbine engine has a fan section, including a fan, a gear arrangement configured to drive the fan section, and a compressor section, including both a first compressor and a second compressor. A turbine section is configured to drive the compressor section and the gear arrangement. An overall pressure ratio is provided by the combination of the first compressor and the second compressor. The fan is configured to deliver a portion of air into the compressor section, and a portion of air into a bypass duct. A bypass ratio which is defined as a volume of air passing to the bypass duct compared to a volume of air passing into the compressor section is greater than or equal to about 8. | 06-12-2014 |
20140157756 | GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT - A gas turbine engine has a fan section, including a fan, a gear arrangement configured to drive the fan section, the geared arrangement defining a gear reduction ratio greater than or equal to about 2.6. A compressor section includes both a first compressor and a second compressor. A turbine section is configured to drive the compressor section and the gear arrangement. An overall pressure ratio is provided by the combination of the first compressor and the second compressor. | 06-12-2014 |
20140157757 | GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT - A gas turbine engine has a fan section, including a fan, a gear arrangement configured to drive the fan section, and a compressor section, including both a first compressor and a second compressor. A turbine section is configured to drive the compressor section and the gear arrangement. The turbine section includes a fan drive turbine configured to drive the fan section, a pressure ratio across the fan drive turbine being greater than or equal to about 5. An overall pressure ratio is provided by the combination of the first compressor and the second compressor. | 06-12-2014 |
20140165534 | GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT - A gas turbine engine has a fan section, including a fan, a gear arrangement configured to drive the fan section, and a compressor section, including both a first compressor and a second compressor. A turbine section is configured to drive the compressor section and the gear arrangement. An overall pressure ratio is provided by the combination of the first compressor and the second compressor, with the overall pressure ratio being greater than or equal to about 35. The fan is configured to deliver a portion of air into the compressor section, and a portion of air into a bypass duct. A bypass ratio, which is defined as a volume of air passing to the bypass duct compared to a volume of air passing into the compressor section, is greater than or equal to about 8. | 06-19-2014 |
20140186158 | GAS TURBINE ENGINE SHAFT BEARING CONFIGURATION - A gas turbine engine includes a core housing that includes an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. A geared architecture is arranged within the inlet case. A shaft provides a rotational axis. A hub is operatively supported by the shaft. A rotor is connected to the hub and supports a compressor section. The compressor section is arranged axially between the inlet case flow path and the intermediate case flow path. A bearing is mounted to the hub and supports the shaft relative to one of the intermediate case and the inlet case. | 07-03-2014 |
20140193238 | METHOD FOR SETTING A GEAR RATIO OF A FAN DRIVE GEAR SYSTEM OF A GAS TURBINE ENGINE - A gas turbine engine includes a fan section including a fan that is rotatable about an axis. A speed reduction device is connected to the fan. The speed reduction device includes a star drive gear system with a star gear ratio of at least 1.5. A bypass ratio is greater than about 11.0. | 07-10-2014 |
20140205438 | RELATIONSHIP BETWEEN FAN AND PRIMARY EXHAUST STREAM VELOCITIES IN A GEARED GAS TURBINE ENGINE - Please replace the abstract with the following rewritten abstract. No new matter has been added. | 07-24-2014 |
20140205439 | GAS TURBINE ENGINE SHAFT BEARING CONFIGURATION - A gas turbine engine includes a housing including an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. A geared architecture is arranged within the inlet case. The geared architecture includes an epicyclic gear train. A fan is rotationally driven by the geared architecture. A shaft provides a rotational axis. A hub is operatively supported by the shaft. First and second bearings support the shaft relative to the intermediate case and the inlet case, respectively. | 07-24-2014 |
20140234078 | METHOD FOR SETTING A GEAR RATIO OF A FAN DRIVE GEAR SYSTEM OF A GAS TURBINE ENGINE - A gas turbine engine includes a fan section including a fan rotatable about an axis. A speed reduction device is connected to the fan. The speed reduction device includes a planetary fan drive gear system with a planet gear ratio of at least 2.5. A bypass ratio is greater than about 11.0. | 08-21-2014 |
20140260326 | GEARED TURBOFAN ENGINE WITH HIGH COMPRESSOR EXIT TEMPERATURE - A gas turbine engine includes a fan with a plurality of fan blades rotatable about an axis, and a compressor section that includes at least first and second compressor sections. An average exit temperature of the compressor section is between about 1000° F. and about 1500° F. The engine also includes a combustor that is in fluid communication with the compressor section, and a turbine section that is in fluid communication with the combustor. A geared architecture is driven by the turbine section for rotating the fan about the axis. | 09-18-2014 |
20140290211 | TURBINE ENGINE INCLUDING BALANCED LOW PRESSURE STAGE COUNT - A turbine engine includes at least a compressor section and a turbine section, each having at least a first and second portion. A ratio of turbine section second portion stages to compressor section second portion stages is less than or equal to 1. | 10-02-2014 |
20150013301 | TURBINE ENGINE INCLUDING BALANCED LOW PRESSURE STAGE COUNT - A turbine engine includes at least a compressor section and a turbine section, each having at least a first and second portion. A ratio of turbine section second portion stages to compressor section second portion stages is less than or equal to 1. | 01-15-2015 |
20150027101 | GEARED GAS TURBINE ENGINE ARCHITECTURE FOR ENHANCED EFFICIENCY - An example gas turbine engine includes, among other things, a geared architecture rotatably coupled to the fan drive shaft, and a high pressure compressor. The gas turbine engine is configured so that a core temperature at an exit of the high-pressure compressor is approximately in a range of about 1150 to about 1350 degrees Fahrenheit at take-off. The gas turbine engine is configured so that an Exhaust Velocity Ratio, defined by a ratio of a fan stream exhaust velocity to a primary stream exhaust velocity, is approximately in a range of about 0.75 to about 0.90. A Bypass Ratio of the engine is greater than about 8.0. | 01-29-2015 |