| Patent application number | Description | Published |
|---|
| 20090004012 | COVER PLATE FOR TURBINE ROTOR HAVING ENCLOSED PUMP FOR COOLING AIR - A cover plate for use with a rotor disk in a gas turbine engine includes an enclosed chamber associated with a web on the rotor disk. The enclosed chamber ensures that adequate cooling air is delivered by rotation of the cover plate. | 01-01-2009 |
| 20090074563 | SEAL FOR GAS TURBINE ENGINE COMPONENT - A gas turbine engine component includes a pressurized fluid source, an airfoil, and a seal member for selectively providing sealing at an end of the airfoil. The seal member includes a stowed position for non-sealing and a deployed position for sealing. The seal member is operatively connected with a pressurized fluid source for moving the seal member between the stowed position and the deployed position. | 03-19-2009 |
| 20090148282 | 3D CONTOURED VANE ENDWALL FOR VARIABLE AREA TURBINE VANE ARRANGEMENT - A turbine section of a gas turbine engine includes an arcuate vane platform segment having a substantially flat surface over which a rotational turbine vane may swing. | 06-11-2009 |
| 20090214329 | FILTER SYSTEM FOR BLADE OUTER AIR SEAL - A gas turbine engine component having a filter mounted adjacent an impingement cavity to filter particles out of a secondary cooling airflow outboard of a cooling channel in communication with the secondary cooling airflow. | 08-27-2009 |
| 20090257875 | PLATFORMLESS TURBINE BLADE - A turbine blade rotor assembly is disclosed for a gas turbine engine. The assembly includes a rotor having nickel alloy turbine blades secured thereto. Each of the blades includes a root and an airfoil. The roots are supported by the rotor. A ceramic matrix composite platform separate from the turbine blades is supported between each pair of the turbine blades adjacent to the airfoils. In another example, the airfoil includes a perimeter. A shroud having an aperture receives the airfoil with a single shroud substantially surrounding the airfoil at the perimeter. In one example, the turbine blade includes high and low pressure sides opposite one another that extend from a tip to a root. The airfoil is free from any protrusions extending from the high and low pressure sides on a portion of the blade axially outward from the root. | 10-15-2009 |
| 20090324425 | PARTICLE RESISTANT IN-WALL COOLING PASSAGE INLET - A cooling microcircuit for a turbine engine component has a first cooling passage which has at least one inlet oriented in a radially outward direction for preventing particles from entering the cooling passage and for dislodging particles which may become lodged in the at least one inlet. | 12-31-2009 |
| 20100116452 | Investment casting cores and methods - A method involves forming a core assembly. The forming includes molding a first ceramic core over a first refractory metal core to form a core subassembly. The subassembly is assembled to a second ceramic core. | 05-13-2010 |
| 20100196160 | COOLED TURBINE BLADE SHROUD - A turbine blade for use in high temperature applications includes an as-cast airfoil portion and an as-cast outer tip shroud portion and the outer tip shroud portion has at least one as-cast internal cooling circuit for cooling the outer tip shroud, and the at least one as-cast internal cooling circuit having a plurality of exits for discharging cooling air over exterior surfaces of the shroud. A process for forming a turbine blade comprises the steps of forming an as-cast turbine blade having an airfoil portion and a tip shroud and the forming step comprising forming at least one as-cast cooling circuit within the tip shroud. | 08-05-2010 |
| 20100247293 | VARIABLE AREA TURBINE VANE ARRANGEMENT - A ring vane nozzle for a gas turbine engine according to an exemplary aspect of the present disclosure includes a multiple of fixed turbine vanes between an inner vane ring and an outer vane ring and a multiple of rotational turbine vanes between the inner vane ring and the outer vane ring, each of the rotational turbine vanes rotatable about an axis of rotation. | 09-30-2010 |
| 20110020115 | REFRACTORY METAL CORE INTEGRALLY CAST EXIT TRENCH - A refractory metal core for use in casting a turbine engine part has a main portion and a plurality of tabs extending from the main portion. An end portion having a first edge which joins together the plurality of tabs and a second edge, opposed to the first edge, located internally of an exterior boundary of the cast part may be provided. | 01-27-2011 |
| 20110088865 | PROCESS TO CAST SEAL SLOTS IN TURBINE VANE SHROUDS - A process for casting a turbine engine component is provided. The process comprises the steps of placing a refractory core assembly comprising two intersecting plates in a die, encapsulating the refractory core assembly in a wax pattern having the form of the turbine engine component, forming a ceramic shell mold about the wax pattern, removing the wax pattern, and pouring molten material into the ceramic shell mold to form the turbine engine component. | 04-21-2011 |
| 20110139393 | PROCESS TO CAST SEAL SLOTS IN TURBINE VANE SHROUDS - A process for casting a turbine engine component is provided. The process comprises the steps of placing a refractory core assembly comprising two intersecting plates in a die, encapsulating the refractory core assembly in a wax pattern having the form of the turbine engine component, forming a ceramic shell mold about the wax pattern, removing the wax pattern, and pouring molten material into the ceramic shell mold to form the turbine engine component. | 06-16-2011 |
