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US20130177397 SLOTTED TURBINE AIRFOIL  
A slotted turbine static nozzle airfoil. In one embodiment, the turbine static nozzle airfoil includes a concave pressure wall having a slot extending therethrough; a convex suction wall adjoined...
US20120134780 AXIAL FLOW GAS TURBINE  
In an axial flow gas turbine efficient cooling and a long life-time can be achieved by providing the outer blade platforms (45)with a plurality of outer teeth (46a-c) running parallel to each...
US20110188993 RING SECTOR OF TURBOMACHINE TURBINE  
A turbine ring sector comprising: a wall presenting an inside face and an outside face, the inside face defining an axially oriented airflow passage through which gas flows; anda...
US20110038710 Application of Dense Vertically Cracked and Porous Thermal Barrier Coating to a Gas Turbine Component  
A configuration for coating a turbine component such as a blade or vane with various forms of thermal barrier coating to provide enhanced temperature capability and increased strain tolerance is...
US20150063982 MULTI-STAGE INFLOW TURBINE PUMP FOR PARTICLE COUNTERS  
An airborne, gas particle counter, includes an inflow multiple stage turbine pump inducing flow through a particle counter. The turbine pump includes a rotor and stator assemblies and establishes...
US20140301823 HYDRAULIC MACHINE HAVING AN INTAKE MANIFOLD LOCATED AT THE TOP  
The invention relates to a hydraulic machine having turbines or a pump turbine, comprising an impeller that is mounted such as to be rotatable about a vertical axis of rotation and has a plurality...
US20120213626 EXPLOSION-WELDED GAS TURBINE SHROUD AND A PROCESS OF FORMING AN EXPLOSION-WELDED GAS TURBINE  
An explosion-welded turbine shroud and a process of forming an explosion-welded gas turbine shroud are disclosed. The explosion-welded gas turbine shroud includes a first alloy explosion welded to...
US20140047844 GAS TURBINE ENGINE COMPONENT HAVING PLATFORM TRENCH  
A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform that axially extends between a leading edge and a trailing...
US20150082808 GAS TURBINE ENGINES WITH TURBINE AIRFOIL COOLING  
An airfoil for a gas turbine engine is provided. The airfoil includes a body with a leading edge, a trailing edge, a first side wall extending between the leading edge and the trailing edge, and a...
US20110052373 HIGH-TURNING DIFFUSER STRUT WITH FLOW CROSS-OVER SLOTS  
A turning strut for use in a diffuser of a turbine engine has a leading edge with first and second opposing surfaces depending therefrom that terminate at a trailing edge. Slots extend through the...
US20110044798 TURBINE NOZZLE FOR A TURBOMACHINE  
A turbine nozzle for a turbomachine, the nozzle including two coaxial platforms interconnected by radial vanes, an inner platform being connected to an annular partition that is festooned or...
US20100322760 Interlocked CMC Airfoil  
A ceramic matrix composite (CMC) airfoil assembled from a pressure side wall (42) and a suction side wall (52) joined by interlocking joints (18, 19) at the leading and trailing edges (22, 24) of...
US20140017066 DEVICE FOR SEPARATING WATER DROPLETS FROM A GAS OR VAPOR FLOW  
A moisture separator for a steam turbine power plant for separating moisture from a flow of vapor or gas that includes a bundle of vanes having a corrugated portion and a trailing edge. The...
US20120134781 AXIAL FLOW GAS TURBINE  
In an axial flow gas turbine (30), a substantial reduction of the consumption of cooling air can be achieved by providing, within a turbine stage (TS), structure (39-44) to reuse the cooling air...
US20130336767 COOLING FOR A TURBINE AIRFOIL TRAILING EDGE  
An assembly for a gas turbine engine includes a first platform and an airfoil extending from the first platform. The airfoil includes a first fillet, pressure side biased discharge openings, and a...
US20110135447 SYSTEM FOR REDUCING THE LEVEL OF EROSION AFFECTING A COMPONENT  
A system for removing moisture from a steam/water mixture engaging a stationary component of a steam turbine. The system includes an airfoil located within a flow path of a steam turbine. The...
US20140093355 EXTENDED INDENTATION FOR A FASTENER WITHIN AN AIR FLOW  
A vane includes a surface with an aperture having an extended indentation at least partially therearound.
US20140321962 Turbine Nozzle for Air Cycle Machine  
A nozzle for use in an air cycle machine has a plate. A plurality of vanes extend away from the plate. The plurality of vanes extend for a height away from the plate. A width is defined as the...
US20140041623 FLOW-CONTROL ASSEMBLY COMPRISING A TURBINE-GENERATOR CARTRIDGE  
A flow-control assembly may include a fluid conduit and a flow-control valve in the fluid conduit. The flow-control assembly may further include a fluid expansion conduit with an inlet defined at...
US20140010633 NOZZLE PARTICLE DEFLECTOR FOR A GAS TURBINE ENGINE  
A particle deflector for a gas turbine engine deters accumulation of particles in cooling passages of nozzle vanes of the engine. The particle deflector is arranged to be disposed around a turbine...
US20110081228 INTERTURBINE VANE WITH MULTIPLE AIR CHAMBERS  
A gas turbine engine has a mid turbine frame disposed between turbine rotor assemblies. The mid turbine frame includes hollow airfoils radially extending through an annular gas path duct. The...
US20100329846 TURBINE ENGINE COMPONENTS  
A turbine engine component includes a wall, a main opening, and two clusters of two or more auxiliary openings. The wall includes cool and hot air sides. The main opening extends between the cool...
US20150044028 LOW PRESSURE RATIO FAN ENGINE HAVING A DIMENSIONAL RELATIONSHIP BETWEEN INLET AND FAN SIZE  
According to an example embodiment, a gas turbine engine assembly includes, among other things, a fan that has a plurality of fan blades. A diameter of the fan has a dimension D that is based on a...
US20150110601 COOLANT BRIDGING LINE FOR A GAS TURBINE, WHICH COOLANT BRIDGING LINE CAN BE INSERTED INTO A HOLLOW, COOLED TURBINE BLADE  
A coolant bridging line for a gas turbine having inner and outer sides which are separated by a wall, wherein the coolant bridging line extends from a first component of the gas turbine to a...
US20100129198 HYDRAULIC MACHINE INCLUDING MEANS FOR INJECTING A FLOW DRAWN FROM A MAIN FLOW  
The invention relates to a hydraulic machine through which a main flow (E) of water passes, including at least one turbine blade profile (1) having an upstream end (8) and a downstream end (10),...
US20140255145 Systems and Methods for Providing a Flow of Purge Air and an Adjustable Flow of Cooling Air in a Gas Turbine Application  
Embodiments of the disclosure include systems and methods for providing a flow of purge air and an adjustable flow of cooling air to a wheel space cavity or a stator cavity. According to one...
US20060285968 Turbine rotor cooling flow system  
Disclosed herein is an apparatus comprising a disk coverplate for a turbine rotor, the disk coverplate comprising a plurality of cooling holes, wherein the distance between the centers of any two...
US20140321965 TURBINE NOZZLES AND METHODS OF MANUFACTURING THE SAME  
A turbine nozzle assembly includes an inner circumferential support platform, an outer circumferential support platform, and a plurality of airfoil vanes disposed between the inner circumferential...
US20150226072 WELDED DUAL CHAMBER IMPINGEMENT TUBE  
A tube for being installed into a guide vane of a turbine is provided herein. The tube includes a tube wall for forming a fluid channel and a dividing wall which is arranged inside the fluid...
US20130323019 APPARATUS FOR MINIMIZING SOLID PARTICLE EROSION IN STEAM TURBINES  
Solid particle erosion in a steam turbine is minimized by diverting through angled slots formed in appendages of outer rings of the diaphragms, a portion of the steam from the steam flow path...
US20140023483 AIRFOIL ASSEMBLY INCLUDING VORTEX REDUCING AT AN AIRFOIL LEADING EDGE  
An airfoil assembly including an endwall and an airfoil extending from the into a gas flow path. The endwall includes upstream and downstream edges, and is defined on a platform structure having a...
US20110217158 COOLED TURBINE RIM SEAL  
A rim seal assembly includes an annular seal element circumscribing an engine centerline or axis and mounted on an annular platform including a radially inwardly extending annular platform flange...
US20140352313 DIFFUSER STRUT FAIRING  
A diffuser strut fairing includes a top portion, a bottom portion, a pressure side portion, a suction side portion, an inner surface and an outer surface. The pressure side portion and the suction...
US20140212270 GAS TURBINE ENGINE COMPONENT HAVING SUCTION SIDE CUTBACK OPENING  
An airfoil for a gas turbine engine, according to an exemplary aspect of the present disclosure includes, among other things, a pressure side wall and a suction side wall spaced apart from the...
US20140056690 GAS TURBINE  
A gas turbine includes a turbine blade, a turbine vane, a ring segment circumferentially surrounding the turbine blade, an outer shroud circumferentially surrounding the turbine vane, and a...
US20110164960 HEAT TRANSFER ENHANCEMENT IN INTERNAL CAVITIES OF TURBINE ENGINE AIRFOILS  
An airfoil includes a leading edge, a trailing edge, a suction side and a pressure side; a plurality of internal cooling cavities extending radially within the airfoil, one of the plurality of...
US20130017064 GAS TURBINE AIRFOIL WITH SHAPED TRAILING EDGE COOLANT EJECTION HOLES  
A turbine blade or vane includes at least one internal radial channel for the circulation of cooling medium bordered on a pressure side by a pressure side wall and on a suction side by a suction...
US20110262265 INSTALLATION HAVING A THERMAL TRANSFER ARRANGEMENT  
A gas turbine engine 2 is installed in a nacelle 4 to define a bay 16 which is ventilated by air entering the bay 16 through an intake 27. A partition 28 in the bay 16 includes a permeable wall 34...
US20140321964 Turbine Nozzle and Shroud for Air Cycle Machine  
A nozzle and shroud for use in an air cycle machine has a plate and a shroud curving in a first axial direction about a center axis of the shroud relative to the plate. A plurality of vanes...
US20140321963 Turbine Nozzle and Shroud for Air Cycle Machine  
A nozzle and shroud for use in an air cycle machine has a plate and a shroud curving in a first axial direction about a center axis of the shroud relative to the plate. A plurality of vanes...
US20130177396 Impingement Cooling System for Use with Contoured Surfaces  
The present application provides an impingement cooling system for use with a contoured surface. The impingement cooling system may include an impingement plenum and an impingement plate with a...
US20140083113 FLOW CONTROL TAB FOR TURBINE SECTION FLOW CAVITY  
Flow control tabs for turbine sections are provided. The turbine section includes a stator assembly and a rotor assembly. The rotor assembly includes a bucket, the bucket having a shank. The rotor...
US20130051979 TURBINE SHROUD SEGMENT WITH INTEGRATED IMPINGEMENT PLATE  
A turbine shroud segment is metal injection molded (MIM) about an insert having a cooling air cavity covered by an impingement plate. The insert is held in position in an injection mold and then...
US20130259645 TURBINE AIRFOIL TRAILING EDGE COOLING SLOTS  
A turbine airfoil includes pressure and suction sidewalls extending along a span from a base to a tip. Spanwise spaced apart trailing edge cooling holes in the pressure sidewall end at...
US20100232931 HEAT DISSIPATION FAN  
A heat dissipation fan includes a base with a plurality of holes defined therein, a stator mounted on the base and being placed around the holes of the base, and an impeller rotatably attached to...
US20090016871 Systems and Methods Involving Variable Vanes  
Systems and methods involving vanes are provided. In this regard, a representative method for modifying the throat area between vanes of a gas turbine engine includes: directing a gas flow path of...
US20140119888 IMPINGEMENT COOLING OF TURBINE BLADES OR VANES  
A turbine assembly includes a basically hollow aerofoil. A wall segment may be arranged at a side of the aerofoil. An insertion aperture in the wall segment provides access to the aerofoil and an...
US20140000287 GAS TURBINE ENGINE TURBINE VANE AIRFOIL PROFILE  
A turbine vane for a gas turbine engine includes inner and outer platforms joined by a radially extending airfoil. The airfoil includes leading and trailing edges joined by spaced apart pressure...
US20130343873 TURBINE ENGINE VARIABLE AREA VANE  
A turbine engine stator vane is provided that rotates about an axis, and includes an airfoil, a flange and a shaft. The airfoil extends axially between a first airfoil end and a second airfoil...
US20130177384 TURBINE NOZZLE COMPARTMENTALIZED COOLING SYSTEM  
The present application provides a compartmentalized cooling system for providing a cooling flow in a turbine with a flow of combustion gases therein. The compartmentalized cooling system may...