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| Application No. | Application Title | Issue Date |
| 20110044795 | TURBINE VANE PLATFORM LEADING EDGE COOLING HOLES A vane for use in a gas turbine engine has a platform connected to an airfoil. There is a cooling passage for supplying cooling air to the platform. A cooling chamber supplies cooling air to a plurality of cooling slots at the platform. The cooling slots have a non-unif... | 02/24/2011 |
| 20110040719 | FAILURE DETECTION SYSTEM RISK REDUCTION ASSESSMENT A process includes determining a probability of a failure mode of a system being analyzed reaching a failure limit as a function of time to failure limit, determining a probability of a mitigation of the failure mode as a function of a time to failure limit, and quantif... | 02/17/2011 |
| 20110030456 | NON-DESTRUCTIVE INSPECTION METHOD FOR METALLIC ALLOYS A non-destructive inspection method for detecting the presence of a contaminant that has alloyed with a metallic alloy of a part includes exposing the metallic alloy of the part to an extraction solution. The extraction solution extracts at least a portion of any of the... | 02/10/2011 |
| 20110020105 | NACELLE FLOW ASSEMBLY A nacelle assembly for a turbine engine has a cowl for a turbine engine. The cowl has a first surface spaced from a second surface. The second surface defines defining a bypass flow passage. A flow volume is spaced between the first surface and the second surface. A plu... | 01/27/2011 |
| 20110016880 | RETAINER FOR SUSPENDED THERMAL PROTECTION ELEMENTS IN A GAS TURBINE ENGINE A hanger system includes a pin with a head section which defines a pin axis. A clip assembly captures the head section to permit movement of the pin within a hanger in a direction traverse to the pin axis. A fastener which retains the clip assembly to the hanger.... | 01/27/2011 |
| 20110016879 | LOW PROFILE ATTACHMENT HANGER SYSTEM FOR A COOLING LINER WITHIN A GAS TURBINE ENGINE SWIVEL EXHAUST DUCT An exhaust duct assembly includes a cooling liner spaced apart from an exhaust duct case that articulate for use in a short take off vertical landing (STOVL) type of aircraft. The cooling liner assembly is attached to the exhaust duct case through a foldable attachment ... | 01/27/2011 |
| 20110014045 | FAN EXHAUST NOZZLE FOR TURBOFAN ENGINE The cross sectional flow area of a fan discharge nozzle on one side of a central plane of an associated gas turbine engine power plant is greater than the corresponding flow area of the fan discharge nozzle on an opposite side of the central plane to compensate for the ... | 01/20/2011 |
| 20110000217 | MANAGING SPOOL BEARING LOAD USING VARIABLE AREA FLOW NOZZLE A turbine engine provides a spool supporting a turbine. The spool is arranged in a core nacelle and includes a thrust bearing. A fan is arranged upstream from the core nacelle and is coupled to the spool. A fan nacelle surrounds the fan and core nacelle and provides a b... | 01/06/2011 |
| 20100326046 | VALVE SYSTEM FOR A GAS TURBINE ENGINE A valve system intermediate a secondary flow path and a primary flow path to selectively communicate secondary airflow into the primary gas flow path and control airflow injected from a higher pressure plenum into a lower pressure flowpath.... | 12/30/2010 |
| 20100325887 | REPAIR METHOD FOR GAS TURBINE ENGINE COMPONENTS A method for repairing a gas turbine engine component includes applying a braze slurry to a first portion of the component, applying a pre-sintered preform to a second portion of the component that is different than the first portion, and brazing the component.... | 12/30/2010 |
| 20100323596 | NOTCHED GRIND WHEEL AND METHOD TO MANUFACTURE A ROTOR BLADE RETENTION SLOT A grind wheel includes a rim having at least one notch formed in the rim to grind a slot base of a blade retention slot within a rotor disk.... | 12/23/2010 |
| 20100320061 | TRACK WITH OVERLAPPING LINKS FOR DRY COAL EXTRUSION PUMPS A chain for a particulate material extrusion pump includes a plurality of links, each of the plurality of links having a link body and a link ledge, wherein each link ledge of the plurality of links at least partially overlaps the link body of an adjacent one of the plu... | 12/23/2010 |
| 20100313639 | GAS TURBINE ENGINE DEBRIS MONITORING ARRANGEMENT An example method of controlling gas turbine engine debris monitoring sensors includes detecting debris carried by air moving through an engine using at least first and second debris sensors, and processing signals from both the first and second debris sensors using a c... | 12/16/2010 |
| 20100310358 | INNER DIAMETER SHROUD ASSEMBLY FOR VARIABLE INLET GUIDE VANE STRUCTURE IN A GAS TURBINE ENGINE An inner shroud assembly includes an aft core segment mountable to a forward core segment to support a multiple of vanes for rotational movement relative thereto. A shroud backing plate segment engageable with the aft core segment and at least one fastener which passes ... | 12/09/2010 |
| 20100307389 | REACTOR SYSTEM AND SOLID FUEL COMPOSITE THEREFOR A reactor system includes a fluidized-bed. A fuel and a sulfur absorbent material are eluted through the fluidized-bed. The reactor system may include a heat exchanger having a heat-exchanging portion within a heating zone of the reactor that is hermetically sealed from... | 12/09/2010 |
| 20100307367 | GUIDED PROJECTILE A non-propulsive projectile and method of maneuvering the non-propulsive projectile. The non-propulsive projectile includes a divert system with a multiple of valves to maneuver the projectile in response to a control system.... | 12/09/2010 |
| 20100301062 | SINGLE BI-TEMPERATURE THERMAL STORAGE TANK FOR APPLICATION IN SOLAR THERMAL PLANT Thermocline storage tanks for solar power systems are disclosed. A thermocline region is provided between hot and cold storage regions of a fluid within the storage tank cavity. One example storage tank includes spaced apart baffles fixed relative to the tank and arrang... | 12/02/2010 |
| 20100294128 | FUEL DEOXYGENATOR WITH POROUS SUPPORT PLATE A device for use in a fluid system includes a fuel channel for receiving fuel having dissolved gas therein. A gas permeable membrane supported by a porous support, the gas permeable membrane in communication with the fuel channel. A gas-removal channel adjacent the gas ... | 11/25/2010 |
| 20100292905 | SYSTEM AND METHOD OF ESTIMATING GAS TURBINE ENGINE PERFORMANCE An example method of estimating gas turbine engine performance deterioration includes monitoring debris in at least a portion of an engine and estimating performance deterioration of at least one component of the engine using information from the monitoring. The method ... | 11/18/2010 |
| 20100288874 | ENGINE MOUNT BEARING SLEEVE REPAIR Bearing bores for engine mount components must be periodically repaired. A component is disassembled and a bearing is removed from the bearing bore. An inner surface of the bearing bore is machined to remove any damage. A sizing sleeve is selected to have a press fit wi... | 11/18/2010 |
| 20100288034 | SYSTEM AND METHOD OF ASSESSING THERMAL ENERGY LEVELS OF A GAS TURBINE ENGINE COMPONENT An example method of assessing a component of a gas turbine engine includes monitoring debris in at least a portion of an engine and establishing an estimated thermal energy level for a component of the engine based on the monitoring. The method may use gas path paramet... | 11/18/2010 |
| 20100287907 | SYSTEM AND METHOD OF ESTIMATING A GAS TURBINE ENGINE SURGE MARGIN An example method of estimating a gas turbine engine surge margin and surge margin deterioration includes monitoring debris in at least a portion of an engine and establishing an estimated surge margin for the engine using information from the monitoring The method may ... | 11/18/2010 |
| 20100286959 | DEGRADED ACTUATOR DETECTION An actuator control system is disclosed that includes an actuator continuously movable between multiple positions. The controller is configured to command the actuator to a desired actuator position and to apply the command to an actuator model. The controller is config... | 11/11/2010 |
| 20100284816 | AIRFOIL ATTACHMENT A rotor blade for a gas turbine engine includes an airfoil that extends in span between a tip and a root opposite from the tip. The root includes a plug, a looped portion that surrounds the plug and a clamp. The clamp contacts only a portion of the looped portion on an ... | 11/11/2010 |
| 20100284793 | METHOD OF ELECTRICAL DISCHARGE SURFACE REPAIR OF A VARIABLE VANE TRUNNION A method of repairing a variable vane for a gas turbine engine includes the steps of positioning a trunnion of a variable vane within an electrical discharge machine environment, and connecting the trunnion as a first electrode through an electrical discharge machine po... | 11/11/2010 |
| 20100269512 | GAS TURBINE ENGINE HAVING SLIM-LINE NACELLE A gas turbine engine system includes nacelle, a first boundary layer control device, a second boundary layer control device, at least one sensor, and a controller. The nacelle is defined about an axis and includes an inlet lip section, an inlet internal diffuser section... | 10/28/2010 |
| 20100269486 | GAS TURBINE ENGINE HAVING SLIM-LINE NACELLE A method of providing a slim-line nacelle for a gas turbine engine includes the steps of detecting a windmilling condition and increasing a discharge airflow area of a variable area fan nozzle in response to the detection of the windmilling condition.... | 10/28/2010 |
| 20100269485 | INTEGRATED VARIABLE AREA NOZZLE AND THRUST REVERSING MECHANISM A variable area fan nozzle for use with a gas turbine engine system includes a nozzle having a cross-sectional area associated with a discharge air flow from a fan bypass passage. The nozzle is selectively moveable between multiple static positions for varying the cross... | 10/28/2010 |
| 20100266442 | BURN-RESISTANT AND HIGH TENSILE STRENGTH METAL ALLOYS Burn-resistant metal alloys that also have a high tensile strength are described. The alloys generally include about 55 to about 75 weight percent nickel, about 12 to about 17 weight percent cobalt, about 4 to about 16 weight percent chromium, about 1 to about 4 weight ... | 10/21/2010 |
| 20100266401 | TURBINE ENGINE ROTATING CAVITY ANTI-VORTEX CASCADE A gas turbine engine rotor drum includes spaced apart discs providing a cavity between the discs. The discs are configured to rotate in a rotational direction about an axis. An annular support is mounted on at least one of the discs and within the cavity. A cascade of r... | 10/21/2010 |
| 20100266391 | MECHANICAL ATTACHMENT OF CERAMIC OR METALLIC FOAM MATERIALS A thermal barrier includes a thermal barrier member having at least one material selected from a metal foam or a ceramic foam. The thermal barrier member includes an attachment section for securing the thermal barrier member with a corresponding attachment section of a ... | 10/21/2010 |
| 20100266387 | TURBINE ENGINE ROTATING CAVITY ANTI-VORTEX CASCADE A gas turbine engine rotor drum includes spaced apart discs providing a cavity between the discs. The discs are configured to rotate in a rotational direction about an axis. An annular support is mounted on at least one of the discs and within the cavity. A cascade of r... | 10/21/2010 |
| 20100266385 | Separation resistant aerodynamic article An airfoil disclosed herein comprises a pressure surface 42 exposed to a stream of fluid, a suction surface 40 exposed to the stream of fluid and a passage 56 extending from a passage intake end 60 to a passage discharge end 66. The in... | 10/21/2010 |
| 20100265026 | PASSIVE ELECTRICAL COMPONENTS WITH INORGANIC DIELECTRIC COATING LAYER A passive electrical component includes an inorganic dielectric coating layer laser applied to a conductor layer.... | 10/21/2010 |
| 20100264601 | SHROUDED FACE SEAL AND COMPONENTS THEREOF One embodiment of the face seal described herein includes a seal seat and a seal element carried by a seal housing. The seal element cooperates with the seal seat to establish a seal. The housing includes a seal element support and a shroud. The seal housing is made of ... | 10/21/2010 |
| 20100263497 | BOLT HOLDER TOOL A tool includes a base ring which defines a multiple of bores, each of the multiple of bores sized to receive one of a multiple of socket assemblies. A slide ring mountable to the base ring to rotate the multiple of socket assemblies.... | 10/21/2010 |
| 20100257841 | VARIABLE AREA FAN NOZZLE AND THRUST REVERSER A nozzle for use in a gas turbine engine includes a nozzle door having a first end, a second end opposed from the first end, and a pivot between the first end and the second end. A linkage connects to the nozzle door and to an actuator. The actuator is selectively opera... | 10/14/2010 |
| 20100257839 | Hydrocarbon-fueled rocket engine with endothermic fuel cooling A rocket engine utilizes a kerosene-based fuel in a supercritical state which is catalytically converted to lighter hydrocarbons with heat from a thrust chamber assembly which operates as a heat exchanger. This process is facilitated by a fuel stabilization deoxygenator... | 10/14/2010 |
| 20100254821 | INTERMEDIATE-MANUFACTURED COMPOSITE AIRFOIL AND METHODS FOR MANUFACTURING An intermediate-manufactured composite airfoil includes first and second composite skins each having a plurality of fibers in a polymer matrix. A composite core is removably located between the first and second composite skins. The composite core includes a dry, three-d... | 10/07/2010 |
| 20100254797 | ENDWALL WITH LEADING-EDGE HUMP An example airfoil assembly includes a base having an airfoil projecting radially therefrom. The base extends laterally away from the airfoil. The airfoil extends axially from an airfoil leading edge portion to an airfoil trailing edge portion. The base has a humped are... | 10/07/2010 |
