Patent application number | Description | Published |
20130312425 | PASSIVE THERMOSTATIC VALVE - An airfoil includes an airfoil body having an internal cavity. A thermostatic valve is located at least partially within the internal cavity. The thermostatic valve is configured to passively control fluid flow into the internal cavity in response to a temperature within the internal cavity. | 11-28-2013 |
20130323079 | TURBOMACHINERY COMPONENT COOLING SCHEME - A turbomachinery component includes a surface exposed to hot working fluid flow. The surface has an undulating contour formed from a series of alternating protuberances and troughs. A set of three cooling outlets is associated with each trough. | 12-05-2013 |
20130323080 | VORTEX GENERATORS FOR IMPROVED FILM EFFECTIVENESS - An airfoil includes a suction surface, a pressure surface, a first showerhead cooling hole and a second showerhead cooling hole. The suction surface and the pressure surface both extend axially between a leading edge and a trailing edge, as well as radially from a root section to a tip section. The first showerhead cooling hole and the second showerhead cooling hole both extend into pressure surface near the leading edge. The first showerhead cooling hole and the second showerhead cooling hole are angled in opposing directions. | 12-05-2013 |
20140212298 | GAS TURBINE ENGINE 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 having an exterior surface that extends in a radial direction to a tip. A camber line at the tip extends from the leading edge to the trailing edge. Pressure and suction side shelves are arranged in the exterior surface on opposing sides of the camber line respectively in the pressure and suction side walls. A plateau is proud of and separates the pressure and suction side shelves. The plateau is arranged along the camber line and extends to the leading edge. | 07-31-2014 |
20140254631 | Actively Cooled Gas Turbine Sensor Probe Housing - An actively cooled turbine sensor assembly is designed to withstand post-combustion gas-path conditions of gas turbine engines. The housing forms part of a cooling system and includes an elongated tubular structure that may be inserted into the hot flow path. The distal end portion of the sensor assembly is contoured to minimize heat transfer. The housing also includes leading and trailing plenums for flowing cooling air through the housing and out through the distal end portion. Additional side cavities may also be provided for active cooling of the sensor and reducing possible heat conduction paths to the sensor. | 09-11-2014 |
20140271101 | MODULATED TURBINE VANE COOLING - A vane structure includes a baffle movably mounted within an aperture, the baffle movable to control a cooling flow between a first cooling cavity and a second cooling cavity. | 09-18-2014 |
20150307990 | METHOD AND SYSTEM FOR CONTROLLING COATING IN NON-LINE-OF-SIGHT LOCATIONS - A method for coating a turbine engine component, said method includes the steps of: placing the component into a chamber; injecting a non-reactive carrier gas containing a coating material into the chamber; and forming a coating on a desired portion of the component by locally heating the desired portion of the component by redirecting a directed energy beam onto the desired portion of the component. | 10-29-2015 |
20150322801 | AIRFOIL LEADING EDGE FILM ARRAY - An airfoil according to an exemplary aspect of the present disclosure includes, among other things, a first cooling hole with a first cooling passage arranged at a first angle relative to a chordwise axis and a second cooling hole with a second cooling passage arranged at a second different angle relative to the chordwise axis. A radial projection of the first cooling passage intersects a radial projection of the second cooling passage. | 11-12-2015 |