Patent application number | Description | Published |
20140214187 | RC/Autonomous Machine Mode Indication - A method and system for displaying machine mode information to a remote operator of a plurality of machines includes collecting video data from each of the machines, collecting machine sensor information from each of the machines, collecting machine alert information with respect to each of the machines, and collecting machine operating mode data with respect to each of the machines. A machine display is then provided at a remote control center including one or more screen regions corresponding to the video of one or more machines. The machine display further includes a machine mode and alert indicator including machine areas associated with each of the machines, wherein each machine area including a graphical mode indicator denoting an operating mode of the associated machine. | 07-31-2014 |
20140214240 | UNIVERSAL REMOTE OPERATOR STATION - A remote operator station for controlling an operation of a machine is disclosed. The remote operator station comprises a display device, a plurality of control devices, and a controller communicably coupled to the display device and the control devices. The controller is configured to display a list of types of machines capable of being operated remotely. The controller receives an input indicative of a machine selected from the list. The controller determines a plurality of functionalities associated with the operation of the selected machine. The controller maps the determined functionalities to the plurality of control devices and further displays the mapped functionalities associated with the control devices. | 07-31-2014 |
20140240506 | Display System Layout for Remote Monitoring of Machines - A display system for presenting information relating to the remote monitoring and operation of machines is provided. The display includes a display screen configured to include a main section adapted to display video image data relating to a selected monitored machine. A first side section is arranged along a first edge of the display screen and adapted to display respective video image data associated with each of a plurality of monitored machines. A second side section is arranged along a second edge of the display screen and adapted to display video image data relating to a worksite. | 08-28-2014 |
20140277957 | System and Method for Determining a Ripping Path - A system for determining a ripping path includes a position sensing system, a work implement, and a controller. The controller is configured to determine a plurality of positions of the machine as the machine moves along an operating path and the work implement moves a volume of material and sense the material characteristics of at each of the plurality of positions along the operating path. The controller is further configured to determine the ripping path based upon the material characteristics sensed at the plurality of positions and store the ripping path. | 09-18-2014 |
20150291180 | System for Remotely Controlling a Machine - A system for remotely controlling a machine includes a remote input device, a transmitter remote from the machine, and a receiver at the machine. A controller is configured to store a desired communications threshold, receive input commands from the remote input device, generate a plurality of remote control input signals based upon the input commands, and transmit the plurality of remote control input signals at a location remote from the machine. The controller is further configured to receive at least some of the plurality of remote control input signals at the machine, determine a communications parameter based upon at least one of the plurality of remote control input signals, compare the communications parameter to the desired communications threshold, and generate a command to stop the machine if the communications parameter is outside the desired communications threshold. | 10-15-2015 |
Patent application number | Description | Published |
20120237348 | DAMPER PIN - A damper pin for coupling platforms of adjacent turbine blades includes a first flat longitudinal end region, a second flat longitudinal end region and a reduced cross sectional area. The reduced cross sectional area is separated from the first flat longitudinal end region by a first main body region and the reduced cross sectional area is separated from the second flat longitudinal end region by a second main body region. The cross sectional area of the reduced cross sectional area is less than the cross sectional area of each of the first and second main body regions. | 09-20-2012 |
20120237350 | TURBINE BLADE WITH MATE FACE COOLING AIR FLOW - A gas turbine engine blade comprises a dovetail, a shank extending from the dovetail, an airfoil, and a platform between the shank and the airfoil. The platform comprises a side wall extending between an upstream side and a downstream side of the platform. A first pin channel extends from the upstream side of the sidewall and a second pin channel, co-axial with the first pin channel, extends from the downstream side of the sidewall. The first channel includes a radial notch at the upstream longitudinal end of the first pin channel. | 09-20-2012 |
20130318787 | MANUFACTURING A FAMILY OF AIRFOILS - A method of manufacturing a family of airfoils includes providing a plurality of airfoil blanks of identical geometry, selecting a first airfoil geometry from a family of airfoil geometries, selecting a second, different airfoil geometry from the family of airfoil geometries, machining a first one of the plurality of airfoil blanks to the first airfoil geometry to produce a first airfoil of the family of airfoil geometries, and machining a second, different one of the plurality of airfoil blanks to the second airfoil geometry to produce a second, different airfoil of the family of airfoil geometries | 12-05-2013 |
20140047842 | SUCTION SIDE TURBINE BLADE TIP COOLING - An airfoil for a gas turbine engine includes pressure and suction walls spaced apart from one another and joined at leading and trailing edges to provide an airfoil that extends in a radial direction. The airfoil has a cooling passage arranged between the pressure and suction walls that extend toward a tip of the airfoil. The tip includes a pocket that separates the pressure and suction walls. Scarfed cooling holes fluidly connect the cooling passage to the pocket. The scarfed cooling holes include a portion that is recessed into a face of the suction wall and exposed to the pocket. | 02-20-2014 |
20140072436 | TURBINE AIRFOIL PLATFORM RAIL WITH GUSSET - A blade for a gas turbine engine includes a shank interconnecting a root and a platform, and an airfoil extending radially from the shank. The shank includes a pocket with the platform overhanging the pocket. A rail extends axially along a lateral edge of the platform and extends radially inward from the platform in a direction opposite the airfoil. A gusset extends from an underside of the platform facing the pocket and in a circumferential direction between the rail and the shank. | 03-13-2014 |
20140112792 | DAMPER PIN - A damper pin for coupling platforms of adjacent turbine blades includes a first flat longitudinal end region, a second flat longitudinal end region and a reduced cross sectional area. The reduced cross sectional area is separated from the first flat longitudinal end region by a first main body region and the reduced cross sectional area is separated from the second flat longitudinal end region by a second main body region. The cross sectional area of the reduced cross sectional area is less than the cross sectional area of each of the first and second main body regions. | 04-24-2014 |
20140165591 | TURBINE UNDER PLATFORM AIR SEAL STRIP - A gas turbine engine stage includes a rotor having a slot. A blade has a root received in the slot, and a shank that extends radially outward from the root to a platform that supports an airfoil. A seal is supported on the shank and in engagement circumferentially between and with the shank and the rotor within the slot. A gas turbine engine includes compressor and turbine sections. The turbine section has a rotor with a slot. A combustor is provided axially between the compressor and turbine sections. A turbine blade in the turbine section includes a root received in the slot and a shank that extends radially outward from the root to a platform that supports an airfoil. | 06-19-2014 |
20150354369 | GAS TURBINE ENGINE AIRFOIL PLATFORM COOLING - An airfoil for a gas turbine engine includes an airfoil that extends from a platform that has first and second circumferential sides that respectively extend to first and second circumferential edges. The first circumferential side has a tapered surface at a first angle relative to a flow path surface. The second circumferential surface has a cooling hole that extends toward the second lateral edge at a second angle relative to the flow path surface. The tapered surface and the cooling hole are axially aligned with one another. | 12-10-2015 |
20150369055 | BELL MOUTH INLET FOR TURBINE BLADE - An airfoil assembly for a gas turbine engine is disclosed and includes a platform portion defining a portion of a gas flow path and a root portion for attachment of the turbine airfoil, the root portion including a bottom surface including a bottom area and a plurality of inlets that define a total inlet area as a ratio of the inlet area to the bottom area. An airfoil extends from the platform and including a plurality of cooling air passages in communication with the plurality of inlets. | 12-24-2015 |
20160003074 | GAS TURBINE ENGINE STATOR VANE PLATFORM COOLING - An airfoil component for a gas turbine engine includes a platform joined to an airfoil. The platform includes a flow path surface that extends between spaced apart lateral surfaces. The airfoil extends from the flow path surface. A contoured surface adjoins the flow path surface and one of the lateral surfaces. | 01-07-2016 |
20160032730 | OBTUSE ANGLE CHEVRON TRIP STRIP - An airfoil includes a cooling air passage for receiving a cooling air flow. A chevron including a first rib and a second rib extends from a common tip is disposed within the cooling passage for generating a turbulent flow to improve heat transfer. The chevron includes an angle between the first rib and the second rib that is greater than 90 degrees. | 02-04-2016 |
20160047271 | DUCTING PLATFORM COVER PLATE - The present disclosure relates to cooling systems for turbine stators. A stator may include a vane platform. A ducting plate may be coupled to the vane platform. The ducting plate and the vane platform may form a cooling chamber between the ducting plate and the vane platform. The ducting plate may include an inlet adjacent to a leading edge of the vane platform. The vane platform may include an outlet adjacent to a trailing edge of the vane platform. The ducting plate may be configured to channel cooling air through the cooling chamber from the leading edge to the trailing edge. | 02-18-2016 |