Patent application number | Description | Published |
20090317227 | AIRFOIL EMBODYING MIXED LOADING CONVENTIONS - A high-lift airfoil embodying a combination of loading conventions in a single design specifically to reduce and control total pressure losses that occur in the flow channels between airfoils employed in turbomachinery applications is disclosed herein. The mixed-loading high-lift airfoil designs embody and exhibit the best total profile and secondary loss characteristics possessed by both aft-loaded airfoil and front-loaded airfoil conventions through controlling the development and interaction of boundary layers forming along the surfaces of the airfoils and the endwalls in such applications. The mixed-loading high-lift airfoil may be utilized in both rotating and non-rotating turbomachinery applications. | 12-24-2009 |
20100040462 | Separation-resistant inlet duct for mid-turbine frames - A transition duct assembly for a gas turbine engine includes an outer diameter surface and an inner diameter surface. A substantially annular flowpath having a radial offset is defined between the inner diameter surface and the outer diameter surface. A curvature distribution of the inner diameter surface includes a first region of increasing slope in a radial direction and a second region of decreasing slope in the radial direction adjacent to and downstream of the first region. The first and second regions are configured to reduce flow separation along the outer diameter surface of fluid traveling along the substantially annular flowpath. | 02-18-2010 |
20100209238 | TURBINE VANE AIRFOIL WITH TURNING FLOW AND AXIAL/CIRCUMFERENTIAL TRAILING EDGE CONFIGURATION - An airfoil with turning flow comprises a first surface, a second surface, a leading edge and a trailing edge. The first and second surfaces extend from the leading edge to a trailing edge. A chord extends from a midpoint of the leading edge to a midpoint of the trailing edge, defining a duct angle of at least fifteen degrees with respect to a turbine axis. An axial length of the chord defines an aspect ratio of at most one with respect to an average radial span of the leading and trailing edges. In a region of the trailing edge, an axial angle is at most four degrees and a circumferential angle is at most ten degrees, where the circumferential angle is defined in a direction opposite the turning flow. | 08-19-2010 |
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 area forward the airfoil leading edge portion. | 10-07-2010 |
20100266385 | Separation resistant aerodynamic article - An airfoil disclosed herein comprises a pressure surface | 10-21-2010 |
20110123322 | FLOW PASSAGE FOR GAS TURBINE ENGINE - Inefficiencies associated with the formation of horseshoe vortices in a gas turbine engine having a row of radially extending airfoils, are mitigated with an improved flow passage defined by the suction and pressure surface of two adjacent airfoils and endwalls (disposed proximal to the radially inner and outer ends of the airfoils). The flow passage includes a ridge disposed in one of the endwalls adjacent a suction surface of one of the airfoils, the ridge extending longitudinally from a location at or near the maximum circumferential extent of the airfoil suction side to a downstream location proximal to the trailing edge of the suction surface. | 05-26-2011 |
20110236200 | GAS TURBINE ENGINE WITH NON-AXISYMMETRIC SURFACE CONTOURED VANE PLATFORM - A vane segment for a gas turbine engine according to an exemplary aspect of the present disclosure includes an inner vane platform relative an axis, the inner vane platform having a non-axisymmetric surface contour. | 09-29-2011 |
20110268578 | HIGH PITCH-TO-CHORD TURBINE AIRFOILS - A low pressure turbine engine component for use in an engine, for propelling a vehicle such as an aircraft is formed by a disk portion and a plurality of low pressure turbine blades extending outwardly from the disk portion. Each of the low pressure turbine blades has an airfoil portion with an axial chord length and a trailing edge. The low pressure turbine blades are spaced apart so that there is a pitch-to-chord ratio greater than 1.4, wherein the pitch is a distance between the trailing edges of adjacent ones of the low pressure turbine blades and the chord is the axial chord length of the blades. | 11-03-2011 |
20120201663 | TURBOMACHINE FLOW PATH HAVING CIRCUMFERENTIALLY VARYING OUTER PERIPHERY - A turbomachine includes an annular flow path section between a plurality of radially extending stator blades and a plurality of radially extending rotor blades. At least a portion of the flow path section has a circumferentially varying outer periphery. | 08-09-2012 |
20120275922 | HIGH AREA RATIO TURBINE VANE - A vane for a turbine engine comprises an airfoil section, an inner platform and an outer platform. The airfoil section comprises pressure and suction surfaces extending from a leading edge to a trailing edge. The inner platform is attached to the airfoil section along an inner flow boundary, where the inner flow boundary extends from an upstream inlet region of the vane to a downstream outlet region of the vane. The outer platform is attached to the airfoil section along an outer flow boundary, where the outer flow boundary extends from the inlet region to the outlet region. An area ratio of the outlet region to the inlet region is greater than 2.4. | 11-01-2012 |
20130224014 | LOW LOSS AIRFOIL PLATFORM TRAILING EDGE - An airfoil platform comprises a leading edge portion and a trailing edge portion. The trailing edge portion comprises a first region having a convex flowpath contour, a second region having an intermediate flowpath contour extending downstream from the convex flowpath contour, and a third region having a concave or linear flowpath contour extending downstream from the intermediate flowpath contour to a downstream end of the trailing edge portion of the platform. | 08-29-2013 |
20130283819 | GEARED TURBOFAN WITH THREE TURBINES ALL CO-ROTATING - A gas turbine engine has a fan rotor, a first compressor rotor and a second compressor rotor. The second compressor rotor compresses air to a higher pressure than the first compressor rotor. A first turbine rotor drives the second compressor rotor and a second turbine rotor. The second turbine drives the compressor rotor. A fan drive turbine is positioned downstream of the second turbine rotor. The fan drive turbine drives the fan through a gear reduction. The first compressor rotor and second turbine rotor rotate as an intermediate speed spool. The second compressor rotor and first turbine rotor together as a high speed spool. The high speed spool, the intermediate speed spool, and the fan drive turbine configured to rotate in the same first direction. | 10-31-2013 |
20130302136 | NON-AXISYMMETRIC RIM CAVITY FEATURES TO IMPROVE SEALING EFFICIENCIES - Turbomachinery, such as a gas turbine engine, has parts with opposed first and second surfaces and with a cavity between the surfaces and with the first surface moving relative to the second surface. The turbomachinery further has at least one feature for creating pressure variations incorporated into the first and second surfaces. | 11-14-2013 |
20140003925 | AIRFOIL FOR IMPROVED FLOW DISTRIBUTION WITH HIGH RADIAL OFFSET | 01-02-2014 |
20140064951 | ROOT BOW GEOMETRY FOR AIRFOIL SHAPED VANE - A vane assembly used for controlling a turning gas flow includes multiple vanes, each of which is bowed toward a pressure side of the vane at the root of the vane. | 03-06-2014 |
20140090401 | Endwall Controuring - An airfoil array is disclosed. The airfoil array may include an endwall, and a plurality of airfoils radially projecting from the endwall. Each airfoil may have a first side and an opposite second side extending axially in chord between a leading edge and a trailing edge. The airfoil array may further include a convex profiled region extending from the endwall adjacent the first side of at least one of said plurality of airfoils and near the leading edge of the at least one of said plurality of airfoils. The airfoil array may further include a concave profiled region in the endwall adjacent the first side of said at least one of said plurality of airfoils and aft of the convex profiled region. | 04-03-2014 |
20140202133 | GAS TURBINE ENGINE MID TURBINE FRAME WITH FLOW TURNING FEATURES - A gas turbine engine includes first and second stages having a rotational axis. A circumferential array of airfoils is arranged axially between the first stage and the second stage. At least one of the airfoils have a curvature provided equidistantly between pressure and suction sides. The airfoils extend from a leading edge to a trailing edge at a midspan plane along the airfoil. An angle is defined between first and second lines respectively tangent to the intersection of the midspan plane and the curvature at airfoil leading and trailing edges. The angle is equal to or greater than about 10°. | 07-24-2014 |