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Patent # Description
2016/0177793 METHOD FOR REGENERATING AN EXHAUST GAS AFTERTREATMENT DEVICE
The invention provides a method for regenerating an exhaust gas aftertreatment device of a vehicle having an internal combustion engine selectively operable to...
2016/0177792 BLOW-BY GAS INLET STRUCTURE OF OIL SEPARATOR FOR INTERNAL COMBUSTION ENGINE
A blow-by gas inlet structure of an oil separator adapted to be placed above a cam chamber of an internal combustion engine, comprises a plate that forms a...
2016/0177791 OIL MIST SEPARATOR
An oil mist separator that is provided at a portion further up than a cylinder head in an internal combustion engine body, includes: an oil mist separating...
2016/0177790 LASH ADJUSTER AND METHOD OF MAKING SAME
A method of manufacturing a lash adjuster body for use in a lash adjuster assembly can include forming a lash adjuster body to an as-formed condition including...
2016/0177789 TURBOSHAFT ENGINE EXHAUST NOZZLE HAVING ITS OUTLET PERPENDICULAR TO THE AXIS OF ROTATION OF THE ENGINE
A gas exhaust nozzle for a gas turbine, the exhaust nozzle having an annular inlet section centered on the axis of the gas turbine, a diffuser, a plenum...
2016/0177788 INTERGRATED SEAL SUPPORTS
An inner case for a gas turbine engine includes a case body defining a centerline axis. The case body includes a turbine seal support, and an I-rod support...
2016/0177787 JOINT ASSEMBLY AND A METHOD OF USING THE SAME
A joint assembly has first to third end portions of first to third components and an elongate resilient connection member. The first end portion interconnects...
2016/0177786 TURBINE SHROUD
A turbine shroud for a gas turbine engine includes an annular metallic carrier and a ceramic-containing blade track. A connection is formed between the annular...
2016/0177785 JOINT ASSEMBLY AND A METHOD OF USING THE SAME
A joint assembly includes a first end portion of a first hollow component, a second end portion of a second hollow component, and a first and second resilient...
2016/0177784 TURBOMACHINE WITH AXIAL STOP MEMBER
A turbomachine having an axial stop member arranged to restrain axial movement of a bearing assembly of the turbomachine, the axial stop member having a bore...
2016/0177783 HOUSING SUPPORT NUT CONNECTION
A housing connection includes a first housing defining a first housing compartment with a first set of threads defined circumferentially around the first...
2016/0177782 ENGINE COMPONENT HAVING PLATFORM WITH PASSAGEWAY
One exemplary embodiment of this disclosure relates to a gas turbine engine including a component. The component includes a platform having a mateface on a...
2016/0177781 SYSTEM AND METHOD FOR CONTROLLING AN ENVIRONMENTAL CONDITION OF AN ENGINE ELECTRONIC COMPONENT
The present disclosure relates generally to a gas turbine engine that includes a fan configured to generate a fanstream and a fanstream duct configured to...
2016/0177780 BLADE ARRANGEMENT OF A JET ENGINE OR AN AIRCRAFT PROPELLER
A blade arrangement of a jet engine or an aircraft propeller including a blade with a root portion and an aerofoil portion, wherein the aerofoil portion...
2016/0177779 BLADE
A turbomachine blade comprising a metallic leading edge having a weakened region extending in a spanwise direction; and a crack initiator for selectively...
2016/0177778 WAVEGUIDE
A waveguide for a sensor system for mounting in a casing structure to measure the clearance between the casing structure and a rotary blade. The casing...
2016/0177777 OVER TIP LEAKAGE MEASUREMENT
A rotor arrangement including: a rotor stage having an annular array of rotor blades each blade having a tip; a casing that surrounds the rotor stage and...
2016/0177776 OPTICAL MEASUREMENT SYSTEM FOR DETECTING TURBINE BLADE LOCKUP
An optical measurement system for detecting at least one locked blade assembly in a gas turbine. The system includes at least one light source for emitting...
2016/0177775 MECHANISM FOR DRIVING BLADE ORIENTATION ADJUSTING MEMBERS
A drive mechanism for driving at least two adjusting members, each adjusting member being used to adjust the orientation of the blades of a turbomachine...
2016/0177774 LOW NOISE TURBINE FOR GEARED GAS TURBINE ENGINE
A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a turbine section including a fan drive turbine,...
2016/0177773 Apparatus for Extending the Flow Range of Turbines
An apparatus for extending the operational flow rate range of a turbine is described herein. Two or more removable sleeves may be used to change the...
2016/0177772 THERMAL INSPECTION SYSTEM
A thermal inspection system is provided for a gas turbine engine hot section component with a cooling passage. This thermal inspection system includes a fluid...
2016/0177771 LASER MEASUREMENT SYSTEM FOR DETECTING TURBINE BLADE LOCKUP
A laser measurement system for detecting at least one locked blade assembly in a gas turbine. The system includes at least one laser device for emitting a...
2016/0177770 ELECTRICAL MACHINES
An arrangement of electrical machines including: a variable reluctance rotor. The arrangement also including an annular array of stators; each stator...
2016/0177769 GAS TURBINE ENGINE WITH ROTOR BLADE TIP CLEARANCE FLOW CONTROL
A gas turbine engine system includes a drive shaft and a compressor located in a compressor case. The compressor has a number of rotors. Each rotor includes a...
2016/0177768 BLADE TIP CLEARANCE SYSTEMS
A rotating blade tip clearance system includes a control ring carrier defining a centerline axis. The control ring carrier has a connecting portion, a...
2016/0177767 TROUGH SEAL FOR GAS TURBINE ENGINE
This disclosure relates to a gas turbine engine including a first engine component and a second engine component. The first engine component has a mate face...
2016/0177766 MINI BLIND STATOR LEAKAGE REDUCTION
What is described is a partial platform. The partial platform includes a leading edge, a trailing edge, a first circumferential edge and a second ...
2016/0177765 PINNED SEAL
An assembly includes a case structure, a seal interfacing with the case structure, a first pin, and a main pin hole on one of the seal and the case structure....
2016/0177764 COMPLIANT SEAL ASSEMBLY AND METHOD OF OPERATING
A compliant seal assembly that may be for an MTF of a gas turbine engine includes a housing orientated about an axis with a circumferentially extending groove...
2016/0177763 GAS TURBINE ENGINE SEALING ARRANGEMENT
A sealing arrangement for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a groove that extends...
2016/0177762 System and Method Including a Circumferential Seal Assembly to Facilitate Sealing in a Turbine
A method and system including a circumferential seal assembly for sealing between components within a turbine is provided. A circumferential seal assembly is...
2016/0177761 Ceramic Matrix Composite Nozzle Mounted With a Strut and Concepts Thereof
A nozzle assembly is provided which is, in part, formed of a low coefficient of thermal expansion material. The assembly includes a nozzle fairing formed of...
2016/0177760 GAS TURBINE VANE
The present invention generally relates to a vane for a gas turbine, and more in particular it provides an innovative vane with improved flexibility leading to...
2016/0177759 MOUNTING APPARATUS FOR LOW-DUCTILITY TURBINE NOZZLE
A turbine nozzle includes an arcuate inner band having opposed flowpath and back sides, and an aft flange extending outward from the back side; an arcuate...
2016/0177758 ANGLED RAIL HOLES
A gas turbine engine combustor configured to cool a first vane platform by directing airflow through an aft combustor rail is disclosed. In various...
2016/0177757 AIRFOIL PROFILE-SHAPED SEALS AND TURBINE COMPONENTS EMPLOYING SAME
An airfoil profile-shaped seal is disposable between an inside surface of a hollow airfoil body and a seal support. The seal includes an elongated member...
2016/0177756 AIRFOIL FILLET
The present disclosure includes airfoils for use in gas turbine engines. The airfoils comprise a fillet having a height of greater than 20% of the airfoil body...
2016/0177755 HARDWARE GEOMETRY FOR INCREASING PART OVERLAP AND MAINTAINING CLEARANCE
A gas-turbine engine is provided. The gas-turbine engine comprises a high pressure turbine with an aft blade platform. A static structure may be disposed aft...
2016/0177754 BONDED FAN PLATFORM
A fan is provided. The fan may comprise a fan blade and a blade platform coupled to the fan blade. The blade platform may be a thermoplastic. A fan blade...
2016/0177753 FULL HOOP BLADE TRACK WITH AXIALLY KEYED FEATURES
A turbine shroud for a gas turbine engine includes an annular metallic carrier, a blade track, and a cross-key connection formed between the annular metallic...
2016/0177752 BLADING MEMBER FOR A FLUID FLOW MACHINE
A blading member for fluid flow machines, for example, gas turbine engines. The blading member includes a platform member, at least one airfoil member, and at...
2016/0177751 BLADE AND GAS TURBINE PROVIDED WITH THE SAME
A blade is formed with blade air passages connecting the inside of a blade body of the blade and the inside of a platform of the blade. The platform is formed...
2016/0177750 ARRANGEMENT OF A ROTOR AND AT LEAST A BLADE
It is disclosed an arrangement of a rotor and at least a blade. The blade includes a root, a platform and an airfoil. The rotor includes a seat for the root....
2016/0177749 BLADING MEMBER FOR A FLUID FLOW MACHINE
A blading member for a fluid flow machine, for example, for use in gas turbine engines. The blading member includes a platform member and an airfoil member....
2016/0177748 TURBINE WHEEL WITH COMPOSITE BLADED RING
A turbine wheel for use in a gas turbine engine having a bladed ring attached to a rotor disk. The bladed ring includes features to fit within slots of the...
2016/0177747 CHANNEL MARKER AND RELATED METHODS
Various embodiments of the disclosure include a component, methods of forming components, and methods of cooling components. In some embodiments, a method...
2016/0177746 ARTICLES FOR HIGH TEMPERATURE SERVICE AND METHOD FOR MAKING
Articles, such as components for high temperature turbomachinery components, include one or more coatings bearing certain perovskite compositions resistant to...
2016/0177745 ABRASIVE TIPS FOR CERAMIC MATRIX COMPOSITE BLADES AND METHODS FOR MAKING THE SAME
A blade and method for producing the blade for a gas turbine engine are described herein. The blade may include a composite airfoil. The airfoil may comprise a...
2016/0177744 BLADE
A turbomachine blade comprising a metallic leading edge having a region having varying fracture resistance in a spanwise direction so as to increase energy...
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