Patent application number | Description | Published |
20120163964 | AXIAL RETENTION FEATURE FOR GAS TURBINE ENGINE VANES - A case assembly for a gas turbine engine is provided that includes an outer case with circumferentially spaced individual bosses that include a recess. A vane assembly is received in the outer case. An axial retention ring has uninstalled and installed conditions. The axial retention ring outside of the recess is in the uninstalled condition and received in the recess in the installed condition. An anti-rotation feature, such as a ring, is arranged between the bosses in a locking condition to prevent rotation of the axial retention ring between the installed and uninstalled conditions. | 06-28-2012 |
20130108430 | FEATHER SEAL SLOT | 05-02-2013 |
20130149159 | GAS TURBINE ENGINE PART RETENTION - A gas turbine engine includes an engine casing structure and a retention block assembly. The engine casing structure includes a pocket which receives the retention block assembly. The retention block assembly includes a stop block and a pin that retains the stop block within the pocket. The stop block is loose relative to the pin. | 06-13-2013 |
20130309078 | SHIELD SYSTEM FOR GAS TURBINE ENGINE - A shield system for a gas turbine engine extends between an inner case structure and a vane pack. | 11-21-2013 |
20130318978 | LINER ASSEMBLY - A liner assembly includes a plurality of flaps arranged about a central axis and operable to move relative to the central axis. Each of the plurality of flaps defines a forward end and an aft end, lateral sides, and an inner surface and an outer surface relative to the central axis. Each of the plurality of flaps has a thickness between the inner surface and the outer surface, and thickness varies in a lateral direction between the lateral sides. | 12-05-2013 |
20130323045 | SEAL LAND FOR STATIC STRUCTURE OF A GAS TURBINE ENGINE - A seal land for a gas turbine engine can include a seal body circumferentially extending about a longitudinal centerline axis. The seal body includes at least one sealing surface that extends in a plane that is transverse to the longitudinal centerline axis. | 12-05-2013 |
20130330196 | FAN BLADE PLATFORM - A fan assembly includes a first fan blade with a rib extending therealong and a first fairing platform mounted on and supported from the first fan blade. The first fairing platform has a flange with a groove that mates with the rib. | 12-12-2013 |
20140056685 | ANNULAR TURBOMACHINE SEAL AND HEAT SHIELD - An example annular turbomachine seal includes an attachment portion, a first leg radially inward of the attachment portion, and a second leg radially inward of the attachment portion and configured to block flow from directly contacting an attachment associated with a bearing compartment of a turbomachine. | 02-27-2014 |
20140093358 | PIN CONNECTOR FOR CERAMIC MATRIX COMPOSITE TURBINE FRAME - A connector between a first object having a first coefficient of thermal expansion and a second object having a second coefficient of thermal expansion has a slot attaching to the second object. The slot formed by an inner shell having a slot shape and a first portion that blends into an outer surface of the second object, the slot having an enclosed portion facing forward and an aft portion that is open. | 04-03-2014 |
20140093371 | MID-TURBINE FRAME HEAT SHIELD - A heat shield for a mid-turbine frame has a conical body, including at least one axial retention feature, at least one circumferential retention feature, and at least one radial retention feature. | 04-03-2014 |
20140248146 | ATTACHMENT APPARATUS FOR CERAMIC MATRIX COMPOSITE MATERIALS - A first ceramic matrix composite structure having a first flange with a first aperture, and a second structure having a second flange with a second aperture are clamped together by a fastener and spring assembly. The second flange is in contact with the first flange and the apertures of the first and second flanges align with each other. A threaded fastener having a thermal expansion rate that is different than the thermal expansion rate of at least one of the first ceramic matrix composite structure and second structure extends through the aligned apertures. The fastener includes a bolt, a nut, and a spring assembly that maintains a constant clamping pressure irrespective of the thermal expansion differences between the bolt and the first ceramic matrix composite structure and second structure. | 09-04-2014 |
20140255174 | MANUFACTURE OF FULL RING STRUT VANE PACK - A vane assembly for a gas turbine engine is disclosed and includes a plurality of individual vane segments forming an annular ring. Each of the plurality of vane segments is formed of a ceramic matrix composite including at least one airfoil extending between an inner platform and an outer platform. An outer wrap is disposed about an outer periphery of the annular ring and over an interface between outer platforms of adjacent ones of the plurality of vane segments. | 09-11-2014 |
20140314547 | ATTACHMENT APPARATUS FOR CERAMIC MATRIX COMPOSITE MATERIALS - A first ceramic matrix composite structure having a first flange with a first aperture, and a second structure having a second flange with a second aperture are clamped together by a fastener and spring assembly. The second flange is in contact with the first flange and the apertures of the first and second flanges align with each other. A threaded fastener having a thermal expansion rate that is different than the thermal expansion rate of at least one of the first ceramic matrix composite structure and second structure extends through the aligned apertures. The fastener includes a bolt, a nut, and a spring assembly that maintains a constant clamping pressure irrespective of the thermal expansion differences between the bolt and the first ceramic matrix composite structure and second structure. | 10-23-2014 |