PRATT & WHITNEY Patent applications |
Patent application number | Title | Published |
20140096537 | Thin Metal Duct Damper - A damper for damping vibration of a structural member of a gas turbine engine is disclosed. The damper may include a first metal mesh pad which abuts an outer circumferential surface of the structural member, and a garter spring which abuts the first metal mesh pad. Both the metal mesh pad and the garter spring may completely or partially encircle the structural member. Alternatively, the damper may include a damper cover which encloses the first metal mesh pad and the garter spring and which abuts the outer surface of the structural member. A second metal mesh pad may be inserted between the damper cover and the garter spring. A gas turbine engine which comprises such a damper is also disclosed. | 04-10-2014 |
20140037399 | No Flange Damage Wedge Lock Washers - No flange damage wedge lock washers are disclosed. The washers may comprise an upper washer and a lower washer. The lower washer may have a generally smooth bottom surface and at least one means for securement. The at least one means for securement may be arranged to keep together the lower washer and a flange without causing damage to the flange. A locking fastener assembly which comprises no flange damage wedge lock washers is also disclosed. The locking fastener assembly may include a lower washer having a generally smooth bottom surface and at least one means for securement. A method of manufacturing a locking fastener assembly which comprises no flange damage wedge lock washers is also disclosed. The locking fastener assembly of the method may include a lower washer having a generally smooth bottom surface and at least one means for securement. | 02-06-2014 |
20140017087 | Dynamic Stability and Mid Axial Preload Control for a Tie Shaft Coupled Axial High Pressure Rotor - A middle support member is used to provide axial support and control to the tie shaft. The middle support member includes a high pressure compressor coupling nut that applies a preload that allows the high pressure compressor stack to be installed separately from the high pressure turbine rotor through a kickstand. | 01-16-2014 |
20140013599 | Method of Manufacturing Fan Blade Shields - A method for manufacturing a fan blade shield having a sheath cavity made from a hard metal material is disclosed The method may comprise: performing a sheath cavity grinding step for the fan blade shield; and performing a sheath cavity bottom grinding step for the fan blade shield. A method for forming a fan blade is disclosed. The method may comprise: obtaining a fan blade body; obtaining a fan blade shield made from a hard metal material and having a sheath cavity match a leading edge of the fan blade body, the fan blade shield being obtained by a process comprising: performing a sheath cavity grinding step for the fan blade shield; and performing a sheath cavity bottom grinding step for the fan blade shield; and attaching the fan blade shield to the leading edge of the fan blade body to produce the fan blade. | 01-16-2014 |
20140000266 | Gas Turbine Fuel Nozzle End Cover Using Au-Ni Braze and Method Producing Same | 01-02-2014 |
20130340440 | Machined Aerodynamic Intercompressor Bleed Ports - An air bleed system for a jet engine is provided. The air bleed system is located in the low pressure compressor chamber and comprises a movable bleed valve and a stationary, annular bleed case having a forward section and an aft section and ligaments connecting the two sections and providing structural support to the bleed case. The ligaments are machined from the bleed case into an aerodynamic shape that maximizes the flow of air through the bleed ports. | 12-26-2013 |
20130330171 | Ring Seal Midplate - A seal assembly for a rotary machine which includes a rotor assembly having a rotatable rotor shaft is disclosed. The seal assembly may comprise a spacer, a seal plate, a ring seal, and a ring seal midplate. The spacer, the seal plate, and the ring seal midplate may be rotatable with the shaft and extend outwardly from the shaft. The ring seal is free and provides a seal for a bearing compartment of the rotary machine. The ring seal midplate is not attached to the spacer or the seal plate during a hardface process which is applied to any component of the seal assembly. The ring seal midplate may be longitudinally located between the spacer and the seal plate and be radially spaced between the ring seal and the shaft. | 12-12-2013 |
20130321824 | Optical Detection of Airfoil Axial Position with NSMS - A method for determining axial location of rotor blades is provided. The method may monitor an output signal of a sensor configured to detect the proximity of the rotor blades, wherein at least one of the rotor blades being marked with a position marker that is configured to cause a recognizable inconsistency in the output signal only when the rotor blades rotate at a known default axial position. The method may further determine the axial displacement of the rotor blades if the inconsistency is not detected in the output signal for at least one full revolution of the rotor blades. | 12-05-2013 |
20130306194 | Manufacturing Process for Aerospace Bearing Rolling Elements - A method of treating bearing rolling elements or bearing rings after a hardening and temper heat treatment is disclosed. The method may include treating the bearing rolling elements in a tumbling treatment and then in a duplex hardening treatment. The method may include treating the bearing rings in a peening treatment and then in a duplex hardening treatment. The duplex hardening treatment may also include at least one sequential process segment consisting of subjecting the bearing rolling element & rings to a nitriding process to increase the surface hardness and compressive residual stress. The combined two-step process produces a deep surface/sub-surface residual stress greater than the depth of the maximum operating von-Mises shear stress along with an ultra-hard surface with high magnitude of compressive residual stress. In so doing, the bearing ring and rolling elements will have significantly enhanced rolling contact fatigue resistance and resistance to surface imperfections and debris. | 11-21-2013 |
20130302151 | Stator Assembly - A stator assembly or a stator stage is disclosed. The stator assembly includes an endless case that is coupled to or includes at least one lug for engaging an anti-rotation stator segment. The anti-rotator segment includes one curved side edge and one straight or linear side edge. The case also accommodates a plurality of middle stator segments, each having curved side edges on both sides. Finally, a third type of stator segment is a “neighbor” stator segment with one curved side edge and one linear side edge that abuttingly engages the linear side edge of the anti-rotation stator segment. The straight or linear side edges of the anti-rotation stator segments and the neighbor stator segments enable an endless case to be loaded with stator segments from an axial direction. None of the stator segments need to be installed from a radial direction. | 11-14-2013 |
20130302141 | Convective Shielding Cooling Hole Pattern - The cooling system for a turbine may include a plurality of platform cooling openings positioned in a platform of the turbine airfoil. In particular, the first set of cooling openings may create a first cooling path and a second set of cooling openings may be placed in the path of the first cooling path where the first cooling flow will cool the second set of cooling openings. | 11-14-2013 |
20130291382 | Method for Working of Combustor Float Wall Panels - A method for working or repairing a combustor wall panel that may be damaged is disclosed. The method comprises providing a supplemental body to a combustor float wall panel, and attaching at least one cooling pin to the supplemental body. | 11-07-2013 |
20130287565 | TEC Mount Redundant Fastening - A mounting apparatus for a turbine exhaust case (TEC) is provided. The mounting apparatus may include a neck, support links and a plurality of fastening pins. The neck may include an upper portion that is receivable within a pylon associated with the TEC and at least one neck aperture extending therethrough. The support links may downwardly extend from a lower portion of the neck. The support links may be configured to at least partially receive a section of the TEC. Each support link may include at least one link aperture extending therethrough. The fastening pins may include at least one neck pin extending through the neck aperture and at least one link pin extending through the link aperture of each support link. | 10-31-2013 |
20130280043 | Electronic Means for Detecting Buffered Main Shaft Seal Wear or Failure in a Turbine Engine - In accordance with an embodiment, a gas turbine engine is provided having a bearing chamber leak detection system. The gas turbine engine includes a rotatable shaft, a bearing assembly supporting the rotatable shaft, and a plurality of bearing chamber seals surrounding the rotatable shaft creating an annular bearing chamber enclosing the bearing assembly. One or more walls substantially surrounding the bearing chamber create a plenum between the walls and the bearing chamber, and a pressurized air inlet to the plenum is provided. The pressurized air inlet includes an airflow sensor configured and positioned to sense a flow of pressurized air into the plenum, such that airflow at the sensor is indicative of airflow from the plenum into the bearing chamber via one or more of the plurality of bearing chamber seals. | 10-24-2013 |
20130270777 | Duplex Finger Seal for Joints with High Relative Displacement - The sealing apparatus and method of assembling the same is disclosed. The sealing apparatus may comprise a resilient member and a sealing member. The resilient member may define a cavity having a closed end and an open end. The resilient member may include a first wall having a first inner sealing surface and a second wall having a second inner sealing surface. The first and second walls may be joined at the closed end. The sealing member may be disposed at least partially in the cavity in sealing engagement with the first and second inner sealing surfaces. The sealing member may comprise an upper plurality of layered finger seals and a lower plurality of layered finger seals. | 10-17-2013 |
20130263635 | Liquid Drop Peening Method and Apparatus Therefor - A method for peening a surface of a material is disclosed. The method may include producing repeated, separated and high speed liquid drops and moving the liquid drops across the surface to be peened. The liquid drops are essentially free of air bubbles and the velocity of the liquid drops is at least 500 ft/sec. A peening apparatus to produce repeated, separated and high speed liquid drops is also disclosed. The apparatus may comprise a storage tank, a nozzle, a pump, an accumulator, a regulator and an actuator. The apparatus may control the volume and velocity of the produced liquid drops as well as the frequency of the liquid drop production. | 10-10-2013 |
20130259659 | Knife Edge Seal for Gas Turbine Engine - A seal for a gas turbine engine and a gas turbine engine employing such a seal are disclosed. More specifically, the engine includes a knife edge seal which is better able to withstand the extremely high temperatures and mechanical loads to which gas turbine engine components are increasingly subjected. By moving the knife edge seal to the aft hub and cantilevering its angle off of vertical, thermal and mechanical loads are balanced and thus thermal mechanical fatigue life is improved while low cycle fatigue is maintained. | 10-03-2013 |
20130259646 | Dual-Intent Locator Pin and Removable Plug for Gas Turbines - A borescope plug configuration is disclosed. The borescope plug configuration comprises an inspection path defined through a bore in a first engine structure, a second engine structure, and an opening into the gas path of an engine. The borescope plug configuration further comprises a removable plug for sealing the inspection path. The removable plug is adapted to couple the first engine structure to the second engine structure. | 10-03-2013 |
20130236296 | Low Pressure Compressor Variable Vane Control for Two-Spool Turbofan or Turboprop Engine - A system and a method for adjusting an angle of at least one stator vane of a low pressure compressor (LPC) of a two spool gas turbine engine is disclosed. Variable stator vanes are rotatably coupled to a stationary case in one of the stages of the LPC. An actuator is coupled to at least one of the variable stator vanes for imparting rotation of the stator vane about a radius of the case. Various coupling or linkage arrangements may be made so that rotation of one vane results in rotation of the other vanes disposed along the case. The controller includes the stored constraints, the ability to estimate operating condition, and the ability to estimate optimum targets. | 09-12-2013 |
20130232950 | Exit Manifold Flow Guide - An exit manifold is disclosed which includes a manifold body that includes a plurality of inlets. The manifold body provides communication between the inlets and a discharge port. At least one of the inlets directs flow in a first direction and at least one of the inlets directs flow in a second direction. The first and second directions are opposite and the material flowing in these opposite directions collides in front of the discharge outlet. The collision of these two oppositely-directed flows creates a high pressure stagnation region that may block or impede flow from one or more inlets that may be in alignment with the discharge port. | 09-12-2013 |
20130230386 | Diffuser Seal for Geared Turbofan or Turboprop Engines - A diffuser seal for an aft end of a high pressure compressor of a gas turbine engine is disclosed. The diffuser seal includes a flow guide carrier coupled to the diffuser case. The flow guide carrier is also coupled to a static seal. The static seal engages a rotary seal and permits air flow through the static and rotary seals in the aft direction. The flow guide carrier is also coupled to a fairing and a fairing/hub support. The flow guide carrier supports the fairing in a spaced-apart position with respect to the rear hub so that air flowing through the static and rotary seals passes between a forward surface of the fairing and the rear hub. The fairing/hub support extends forward from the flow guide support and engages an aft surface of the fairing thereby limiting movement of the rear hub and fairing in the aft direction. This design helps to prevent parts or debris from piercing the rear hub and entering the high pressure turbine in the even of a fan blade-out or fan blade-off event. | 09-05-2013 |
20130219855 | Method of Using an Afterburner to Reduce High Velocity Jet Engine Noise - A system and method of reducing noise caused by jet engines is provided. The method comprises the steps of using the afterburner to heat the exhaust gas flow while simultaneously reducing power to the core engine. Together these two operations reduce the pressure of the exhaust gas in the nozzle area while holding the exhaust gas velocity constant, which maintains engine thrust while decreasing engine noise. The method may be supplemented by altering the location of the afterburner flames to create an inverted exhaust velocity profile, thereby decreasing engine noise even further. | 08-29-2013 |
20130209248 | Anti-Rotation Stator Segments - A stator assembly for a turbofan gas turbine engine is disclosed. The stator assembly is coupled to a shroud of the engine. The stator assembly includes an endless case fixedly coupled to the engine shroud. The case includes a forward portion, an aft portion and a central portion disposed therebetween. The case extends about an axis of the engine. The forward and aft portions of the case include rails that extend towards each other and form forward and aft pockets with the central portion respectfully. The stator assembly also includes a locking stator segment. The locking stator segment includes a shroud that includes a forward hook and a pair of aft hooks with a platform disposed therebetween. The forward and aft hooks are retained in the forward and aft pockets of the case respectfully. | 08-15-2013 |
20130202780 | Integrated Multicoat Automatic Pause Resume Circuit - The present disclosure sets forth an automated apparatus and method for applying gas plasma coatings to aircraft engine parts. The process and apparatus employ a plurality of sensors which continually monitor various process parameters associated with the coating process. If any of the measured parameters fall out of tolerance, the coating process is interrupted to allow a user to fix the source of the problem, where upon the process is reengaged. Moreover, the process and apparatus employ a pause resume circuit which uses predetermined durations for pausing and resuming the coating process. | 08-08-2013 |
20130195652 | Modal Tuning for Vanes - A vane having a cambered airfoil body is frequency-tuned via a number of cavities formed in a surface of the vane. At least some of the cavities are filled with a nonmetallic filler material, and the remainder of the cavities are left unfilled. A cover is affixed to the vane so as to cover at least the unfilled cavities. In an embodiment, the filling and covering of cavities is performed in a manner that excludes the frequency modes of the guide vane from a precluded band, e.g., an engine excitation band. | 08-01-2013 |
20130177038 | Automated Dewpoint Oxygen Measurement System - An apparatus and method to automate the process of measuring and verifying trace gas levels such as oxygen and dewpoint inside a retort used to coat or heat treat substrates are provided. The apparatus may include an integrated measuring system, and an operator interface. The method may include coupling the apparatus to the retort in which the substrate is coated or heat treated, activating the integrated measuring system to measure and verify atmospheric conditions within the retort, and providing operator access to process parameters and status through the operator interface. The measurement and verification system may be completely autonomous. | 07-11-2013 |
20130158680 | Hybrid Control System - A hybrid control system and a method for predicting a behavior of a physical system using the hybrid control system is disclosed. The hybrid control system may include a model inverting control system capable of implementing a model inverting control law and determining an active set of goals and limits and a model predictive control system capable of implementing a model predictive control law and utilizing the active set of goals and limits to determine current effector requests, the current effector requests being used to control behavior of the physical system. | 06-20-2013 |
20130145769 | Gas Turbine Engine with Variable Overall Pressure Ratio - A gas turbine engine has a variable overall pressure rate (“OPR”). The engine includes a high pressure compressor having at least a primary stage having a set of primary rotors and a secondary stage having a set of secondary rotors. A clutch is provided to selectively engage the secondary rotors with the primary rotors. Engagement of the clutch may be controlled based on the vehicle travel mode, such as disengaging during a takeoff mode to reduce turbine entry temperature and engaging during a loiter mode to increase OPR. | 06-13-2013 |
20130114879 | Method and System for Automated Defect Detection - A computer program product and method for performing automated defect detection of blades within an engine is disclosed. The method may include providing a storage medium for storing data and programs used in processing video images, providing a processing unit for processing images, receiving from a borescope an initial set of images of a plurality of members inside of a device, and using the processing unit to apply Robust Principal Component Analysis to decompose the initial set of images into a first series of low rank component images and a second series of sparse component images, wherein there are at least two images in the initial series. | 05-09-2013 |
20130114878 | System and Method for Automated Defect Detection Utilizing Prior Data - A system and method for performing automated defect detection by utilizing data from prior inspections is disclosed. The system and method may include providing a image capture device for capturing and transmitting at least one current image of an object and providing a database for storing at least one prior image from prior inspections. The system and method may further include registering the at least one current image with the at least one prior image, comparing the registered at least one current image with the at least one prior image to determine a transformation therebetween and updating the database with the at least one current image. | 05-09-2013 |
20130113916 | System and Method for Multiple Simultaneous Automated Defect Detection - A system and method for performing automated defect detection using multiple image capture devices is disclosed. The system and method may include providing a plurality of image capture devices, the plurality of image capture devices capturing and transmitting a plurality of images of an object. The system and method may further include determining a feature correspondence between the plurality of images of the plurality of image capture devices, creating mosaiced images of the plurality of images if the feature correspondence is found or known and performing at least of an automated analysis and a manual inspection on the mosaiced images to find any defects in the object. | 05-09-2013 |
20130113915 | Method and System for Position Control Based on Automated Defect Detection Feedback - A computer program product and method for performing position control on device members that have been identified as defective. The method may include providing a storage medium that stores data and programs used in processing images and a processing unit that processes the images, receiving, by the processing unit from an image capture device coupled to the processing unit, a set of images of a plurality of members inside of a device, detecting, by the processing unit, a defect in a first member of the plurality of members, and providing instructions to move the first member to an inspection position in the device. The device may be an engine and the members may be blades within the engine. | 05-09-2013 |
20130113914 | System and Method for Automated Borescope Inspection User Interface - A system and method for improving human-machine interface while performing automated defect detection is disclosed. The system and method may include an image capture device for capturing and transmitting data of an object, performing automated analysis of the data and reviewing results of the automated analysis by a human inspector and providing feedback. The system and method may further include refining the automated analysis of the data based upon the feedback of the human inspector. | 05-09-2013 |
20130113913 | System and Method for Data-Driven Automated Borescope Inspection - A system and method for performing automated defect detection of blades within an engine is disclosed. The system and method may include an image capture device capable of capturing and transmitting images of a plurality of blades of an engine, creating a normal blade model of an undamaged one of the plurality of blades and determining defects within the plurality of blades by utilizing the normal blade model. | 05-09-2013 |
20130086922 | Combined Pump System for Engine TMS AOC Reduction and ECS Loss Elimination - A compression pump for an engine is provided. The pump may include a first impeller operatively coupled to a main shaft of the engine, a first inlet configured to at least partially receive bypass airflow, and a first outlet configured to direct compressed air to a thermal management system. | 04-11-2013 |
20120188380 | Machine Tool - Based, Optical Coordinate Measuring Machine Calibration Device - A calibration artifact for an inspection system is provided. The calibration artifact comprises a base adapted for placement within a holding fixture of an inspection system during calibration, a sphere operatively connected to the base, and a light source operatively connected to the base. The base, the sphere, and the light source are removable from the inspection system after calibration. | 07-26-2012 |
20110229305 | COVER PLATE FOR TURBINE VANE ASSEMBLY - Embodiments of a cover plate and material blank for forming the cover plate may include features and characteristics to accommodate tolerance issues in a turbine vane assembly. In one embodiment, the cover plate is formed from a material blank configured to provide the cover plate with a flexible flange area that can be secured to the turbine vane assembly. The flange area may have a range of motion that may be responsive to an installation force, which effectively modifies the configuration of the cover plate to such degree as to seal the cover plate to the turbine vane assembly. | 09-22-2011 |
20100030365 | COMBINED MATCHING AND INSPECTION PROCESS IN MACHINING OF FAN CASE RUB STRIPS - A workpiece is secured to a rotatable spindle with locking mechanisms and an image recording device takes an image of the workpiece secured to the spindle. The recorded image is compared to a database to select the appropriate program for the workpiece. A cutting tool is provided, and a rough material removal process is initiated on the workpiece. The surface of the workpiece where material has been removed is then inspected. | 02-04-2010 |
20090254286 | Systems and Methods for Modeling Surface Properties of a Mechanical Component - There is a method for modeling the surface fatigue life of a mechanical component. The method has the following steps: a) modeling the surface fatigue life of the mechanical component on an atomistic scale to form an atomistic model, b) modeling the surface fatigue life of the mechanical component on a mesoscale to form a mesoscale model, c) modeling the surface fatigue life of the mechanical component on a macroscale to form a macroscale model, and d) testing the surface fatigue life of the mechanical component. Feedback from the macroscale model is employed at least once to validate the atomistic model. Feedback from the macroscale model is employed at least once to validate the mesoscale model. Feedback from the testing is employed at least once to validate the macroscale model. There is also an interactive, multiscale model for prediction surface fatigue life or degradation rate for a mechanical component. | 10-08-2009 |