Patent application number | Description | Published |
20090126337 | RETROFIT DIRT SEPARATOR FOR GAS TURBINE ENGINE - A dirt separator may be retrofit into existing gas turbine engines since it is formed of circumferentially separate pieces which may be assembled together in the gas turbine engine. | 05-21-2009 |
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 |
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 |
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 |
20110243749 | GAS TURBINE ENGINE WITH NON-AXISYMMETRIC SURFACE CONTOURED ROTOR BLADE PLATFORM - A rotor blade for a gas turbine engine includes a platform section between a root section and an airfoil section, the platform section having a non-axisymmetric surface contour. | 10-06-2011 |
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 |
20130294897 | SHAPED RIM CAVITY WING SURFACE - A shaped rim cavity wing includes an upper surface and a lower surface. The lower surface has a geometric shape to control the separation of airflow as it passes around the lower surface to the top surface. A point of maximum extent defines the boundary between the upper surface and the lower surface, wherein the point of maximum extent defines a corner that that separates airflow from the shaped rim cavity rim and creates a flow re-circulation adjacent to the top surface of the shaped rim cavity wing. | 11-07-2013 |
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 |
20140037459 | AIRFOIL DESIGN HAVING LOCALIZED SUCTION SIDE CURVATURES - An airfoil for a gas turbine engine comprises a radially extending body having a transverse cross-section. The transverse cross-section comprises a leading edge, a trailing edge, a pressure side and a suction side. The pressure side extends between the leading edge and the trailing edge with a predominantly concave curvature. The suction side extends between the leading edge and the trailing edge with a predominantly convex curvature. The suction side includes an approximately flat portion flanked by forward and aft convex portions. In another embodiment, the suction side includes a series of local curvature changes that produce inflection points in the convex curvature of the suction side spaced from the trailing edge. | 02-06-2014 |
20140090380 | 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 airfoils may be circumferentially spaced apart on the endwall thereby defining a plurality of flow passages between adjacent airfoils. The airfoil array may further include a convex profiled region extending from the endwall near the leading edge of at least one of said plurality of airfoils, and a concave profiled region in the endwall near a middle of at least one of said plurality of flow passages. | 04-03-2014 |
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 |
20140154068 | 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 airfoils may be circumferentially spaced apart on the endwall thereby defining a plurality of flow passages between adjacent airfoils. The airfoil array may further include a convex profiled region extending from the endwall adjacent to the first side of at least one of said plurality of airfoils near the leading edge of the at least one of said plurality of airfoils, and a concave profiled region in the endwall and extending across said at least one of said plurality of flow passages. | 06-05-2014 |