Patent application number | Description | Published |
20090148299 | AIRFOIL LEADING EDGE SHAPE TAILORING TO REDUCE HEAT LOAD - An airfoil includes a leading edge surface that includes a non-continuous curvature distribution. A stagnation region of the airfoil includes a curvature larger than adjacent segments to reduce heat transfer into the airfoil. The reduced curvature in the stagnation region is surrounded by the adjacent segments with larger curvatures to tailor the airfoil surface to provide a desired balance between heat transfer properties and aerodynamic performance. | 06-11-2009 |
20110135482 | TIP VORTEX CONTROL - A rotor blade for a gas turbine engine includes an attachment and an airfoil. The airfoil has a stagger angle, a base region, a transition region and a tip region. The stagger angle changes as the airfoil extends between the attachment and a tip. The base region is disposed adjacent to the attachment. The transition region is located between the base and the tip regions. A rate of the change of the stagger angle in the transition region is greater than a rate of the change of the stagger angle in the base region. The rate of the change of the stagger angle in the transition region is greater than a rate of change of the stagger angle in the tip region. | 06-09-2011 |
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 |
20130302162 | BLADE TIP HAVING A RECESSED AREA - An example blade assembly includes, among other things a blade tip having a pressure side and a suction side, and a plurality of grooves within the blade tip. At least one of the grooves has a contour that is different than both a contour of the pressure side and a contour of the suction side. | 11-14-2013 |
20130315745 | AIRFOIL MATEFACE SEALING - An airfoil includes an airfoil working portion and an adjoining endwall. The endwall has a leading edge, a trailing edge, a first mateface, and a second mateface that collectively define a perimeter of the endwall, with the first and second matefaces arranged opposite one another. A forward zone is defined by the endwall that extends to the leading edge. The first and second matefaces are each oriented at an angle α | 11-28-2013 |
20140010650 | TIP LEAKAGE FLOW DIRECTIONALITY CONTROL - A turbine airfoil comprises a suction sidewall, a pressure sidewall, a tip wall, and a tip leakage control channel. Each sidewall extends spanwise from an airfoil base and chordwise between a leading edge and a trailing edge. The tip wall extends chordwise from the leading edge to the trailing edge and joins respective outer spanwise ends of the suction and pressure sidewalls. The tip leakage control channel has an inlet and an outlet recessed into an outer surface of the tip wall. An inlet of the channel begins proximate a junction of the airfoil pressure sidewall and the tip wall. An outlet of the channel terminates at a recessed portion of the junction of the tip wall and the suction sidewall. | 01-09-2014 |
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 |
20140186190 | TIP LEAKAGE FLOW DIRECTIONALITY CONTROL - An airfoil according to an exemplary aspect of the present disclosure includes, among other things, a suction sidewall and a pressure sidewall, each sidewall extending spanwise from an airfoil base and extending chordwise between a leading edge and a trailing edge. A tip wall extends chordwise from the leading edge to the trailing edge and joining respective outer spanwise ends of the suction and pressure sidewalls. A tip leakage control channel is recessed into the tip wall, the tip leakage control channel including a control channel floor that extends between a first control channel vane sidewall and a second control channel vane sidewall established by a corresponding tip leakage control vane. An internal cooling cavity is disposed between the suction sidewall and the pressure sidewall and a channel cooling aperture feeds airflow from the internal cooling cavity to the tip leakage control channel. | 07-03-2014 |
20150285157 | VARIABLE VANE AND SEAL ARRANGEMENT - One exemplary embodiment of this disclosure relates to a system including an airfoil having a static portion, a moveable portion, and a seal between the static portion and the moveable portion. The seal is moveable separate from the static portion and the moveable portion. | 10-08-2015 |
20150330229 | TIP LEAKAGE FLOW DIRECTIONALITY CONTROL - A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an airfoil having a tip wall that joins outer spanwise ends of a suction sidewall and a pressure sidewall, a tip leakage control channel recessed into an outer surface of the tip wall, a tip leakage control vane integrally formed on the tip wall adjacent to the tip leakage control channel and an air seal radially outward of the tip wall and positioned to minimize leakage at the tip wall. | 11-19-2015 |
20150330230 | TIP LEAKAGE FLOW DIRECTIONALITY CONTROL - An airfoil according to an exemplary aspect of the present disclosure includes, among other things, a suction sidewall and a pressure sidewall, each sidewall extending spanwise from an airfoil base and extending chordwise between a leading edge and a trailing edge. A tip wall extends chordwise from the leading edge to the trailing edge and joining respective outer spanwise ends of the suction and pressure sidewalls. A tip leakage control vane is formed with an outer surface of the tip wall and a winglet is formed at a junction between the suction sidewall and the tip leakage control vane. | 11-19-2015 |