Patent application number | Description | Published |
20090180861 | COOLING ARRANGEMENT FOR TURBINE COMPONENTS - A turbine component includes an aft cooling circuit that extends between a turbine midsection and a turbine trailing end. The aft cooling circuit includes a trailing end section proximate the trailing end, a first interior section proximate the turbine midsection, and a first intermediate section fluidly connected between the trailing end section and the first interior section. A forward cooling circuit of the turbine component extends between the turbine midsection and a turbine leading end. The forward cooling circuit includes a leading end section proximate the leading end, a second interior section proximate the turbine midsection, and a plurality of second intermediate sections fluidly connected between the leading end section and the second interior section. The leading end section, the second intermediate section, the first intermediate section, and the trailing end section each include a plurality of coolant discharge openings for facilitating cooling of the turbine component. | 07-16-2009 |
20100206512 | Process and Refractory Metal Core For Creating Varying Thickness Microcircuits For Turbine Engine Components - The present disclosure is directed to a refractory metal core for use in forming varying thickness microcircuits in turbine engine components, a process for forming the refractory metal core, and a process for forming the turbine engine components. The refractory metal core is used in the casting of a turbine engine component. The core is formed by a sheet of refractory metal material having a curved trailing edge portion integrally formed with a leading edge portion. | 08-19-2010 |
20110135446 | Castings, Casting Cores, and Methods - If a refractory metal core (RMC) is punched, the punching asymmetry may be reflected in an asymmetry of the cast article features cast by the punched features. The punched features may have a shear zone and a fracture zone. The shear zone of the RMC will cast a relatively narrow portion of the post near one end; whereas the fracture zone will cast a relatively broader portion near the other end. The broader portion will also have a relatively shallow transition to the adjacent face of the slot-like passageway cast by the RMC. Where there is a stress asymmetry in the cast article in-use, the punching direction may be chosen so that the relatively broad portions of the post fall along the relatively higher stress face of the passageway. | 06-09-2011 |
20130092340 | Process and Refractory Metal Core for Creating Varying Thickness Microcircuits for Turbine Engine Components - The present disclosure is directed to a refractory metal core for use in forming varying thickness microcircuits in turbine engine components, a process for forming the refractory metal core, and a process for forming the turbine engine components. The refractory metal core is used in the casting of a turbine engine component. The core is formed by a sheet of refractory metal material having a curved trailing edge portion integrally formed with a leading edge portion. | 04-18-2013 |
20160069201 | Attachment Faces for Clamped Turbine Stator of a Gas Turbine Engine - An airfoil fairing shell for a gas turbine engine includes an airfoil section between an outer vane endwall and an inner vane endwall, at least one of the outer vane endwall and the inner vane endwall including a radial attachment face, a suction side tangential attachment face, a pressure side tangential attachment face, and an axial attachment face. | 03-10-2016 |
20160076383 | FILM COOLED ARTICLE - A film cooled component includes multiple film cooling holes. At least one of the film cooling holes has an elliptical cross sectional opening along the exterior surface of the film cooled component. | 03-17-2016 |
20160084096 | CLAMPED VANE ARC SEGMENT HAVING LOAD-TRANSMITTING FEATURES - A vane arc segment includes a radially inner and outer platforms and an airfoil mechanically clamped between the platforms. The airfoil has an airfoil section that extends radially between radially inner and outer fairing platforms. At least one of the fairing platforms includes forward and aft sides, circumferential sides, and a gas path side and an opposed radial side. The radial side includes a plurality of protrusions that have faces that are oriented substantially normal to, respectively, radial, tangential, and axial load transmission directions of the airfoil such that the faces, respectively, primarily bear radial, tangential, and axial load transmissions of the airfoil. | 03-24-2016 |
20160090851 | AIRFOIL ASSEMBLY WITH SPACER AND TIE-SPAR - An airfoil assembly includes at least one airfoil that has a hollow interior. First and second platforms are disposed between the airfoil. At least one tie-spar extends along an axis through the first platform, the hollow interior of the airfoil, and the second platform. There is a thermal expansion difference between a thermal expansion of the tie-spar in the axial direction and the combined thermal expansion of the airfoil and the first and second platform in the axial direction. At least one spacer portion is arranged on the tie-spar. The spacer portion has a thermal expansion in the axial direction that is greater than the thermal expansion difference such that the spacer portion maintains the tie-spar under tension and clamps the first and second platforms on the airfoil. | 03-31-2016 |