| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 415209100 | Plural, axially spaced vane sets acting successively or having specific spacing means | 11 |
| 20100266399 | Gas turbine engine - A gas turbine engine is provided comprising an outer casing and a plurality of circumferentially positioned vane segments. The outer casing is provided with a circumferential casing slot. The plurality of circumferentially positioned vane segments are coupled to the outer casing. Each vane segment comprises at least one vane airfoil, a radially inner shroud coupled to a first end of the airfoil, a radially outer shroud coupled to a second end of the airfoil, and a strongback fixedly coupled to axially spaced-apart portions of the outer shroud such that a gap is provided between the strongback and the outer shroud. The strongback may comprise axially spaced-apart first and second end portions received in the casing slot. | 10-21-2010 |
| 20110014040 | FLUID FLOW MACHINE WITH BLADE ROW GROUP - A fluid flow machine has a main flow path in at least one stage, with a rotor arrangement and a stator arrangement, resulting in an increased rotor-stator constriction ratio QRS, which satisfies the following equation: | 01-20-2011 |
| 20120020780 | AXIAL FLOW FUN - The invention is directed to dual purposes of increasing air volume and reducing noises of an inline axial flow fan. In the inline axial flow fan including a first axial flow fan unit | 01-26-2012 |
| 20120201669 | ROTATING COMPONENT OF A TURBINE ENGINE - A rotating component of a turbine engine is provided and includes a wheel having a face to which fluid flow is provided and a plurality of impeller vanes forming a plurality of grooves along which the fluid flow is directed from an outer to an inner diameter of the wheel face, at least one of the plurality of the impeller vanes including a radially inwardly facing vane surface formed to define a cutaway portion. | 08-09-2012 |
| 20130058776 | AERODYNAMIC COUPLING BETWEEN TWO ANNULAR ROWS OF STATIONARY VANES IN A TURBINE ENGINE - A turbine engine has at least two successive annular rows of stationary vanes, e.g. formed by the vanes of a nozzle and by an annular row of casing arms arranged downstream from the nozzle Each casing arm extends substantially in a radial plane passing between the trailing edges of two adjacent stationary vanes of the nozzle, and the pitch between these two stationary vanes is greater than the pitch between the other stationary vanes of the nozzle, in such a manner that the wakes formed at the trailing edges of these two stationary vanes pass respectively on either side of the corresponding casing arm. | 03-07-2013 |
| 20140186172 | COOLING FAN MODULE - The invention relates to a cooling fan module for a motor vehicle, having a fan impeller which has a multiplicity of fan impeller blades which are connected to one another via a fan impeller outer ring, having a frame, on which the fan impeller is mounted, having an annular reverse flow guide device, which has an inner ring and an outer ring and which is designed to de-spin a reverse flow between the inner ring and the outer ring and to mix said reverse flow with the slot flow between inner ring and fan impeller outer ring. | 07-03-2014 |
| 20150125288 | BAYONET SPACER RETENTION SYSTEM FOR VARIABLE TURBINE GEOMETRY VANE PACKS - A variable geometry turbocharger includes a vane pack having rotatable vanes constrained by a pair of vane rings connected by a plurality of spacer connectors. The spacer connectors can include a spacer body for maintaining a minimum spacing between the vane rings. The spacer connectors are configured for bayonet mounting to at least one of the vane rings. To that end, the spacer connectors can include shaft portions extending from opposing sides of the spacer body. A plurality of transverse protrusions can extend outwardly from each shaft portion. Each shaft portion can be received in a respective in a vane ring. The spacer connectors can be rotated such that the transverse protrusions are offset from aperture portions that allow passage of the transverse portions, thereby retaining the vane rings in place in spaced relation. Such a system avoids close tolerances, press fits, expensive bolted joints or weld processes. | 05-07-2015 |
| 20150292343 | TURBINE ENGINE VANE ARRANGEMENT HAVING A PLURALITY OF INTERCONNECTED VANE ARRANGEMENT SEGMENTS - A turbine engine vane arrangement and a method for manufacturing a turbine engine vane arrangement are provided. The vane arrangement includes a plurality of vane arrangement segments arranged circumferentially around an axial centerline. Each of the vane arrangement segments includes an airfoil that extends radially between a first platform segment and a second platform segment. The first platform segment extends circumferentially between a first mate face and a second mate face. The first mate face of a first of the vane arrangement segments is bonded to the second mate face of a second of the vane arrangement segments. | 10-15-2015 |
| 20150377251 | APPARATUS FOR TRANSFERRING ENERGY BETWEEN A ROTATING ELEMENT AND FLUID - In some embodiments, a plenum of an apparatus for transferring energy between a rotating element and a fluid may include a through hole disposed through the plenum; a plurality of inlet guide vanes disposed proximate a peripheral edge of the through hole, the plurality of inlet guide vanes comprising a first group of inlet guide vanes having a symmetrical profile, a second group of inlet guide vanes, and a third group of inlet guide vanes, wherein each inlet guide vane of the second group and third group have a cambered profile, and wherein each inlet guide vane of the third group has a different cambered profile from each other inlet guide vane of the third group. | 12-31-2015 |
| 20160017739 | SEAL ASSEMBLY FOR A GUIDE VANE ASSEMBLY - The present disclosure relates generally to a guide vane assembly including a first airfoil, including a first airfoil trailing edge, a second airfoil, including a second airfoil leading edge, positioned aft the first airfoil to create a gap therebetween, and a seal assembly disposed within the gap to engage the first airfoil trailing edge and the second airfoil leading edge. | 01-21-2016 |
| 20160024928 | BLADE CASCADE FOR A TURBOMACHINE - The present invention relates to a blade cascade for a gas turbine, which has a first group with at least two, in particular at least three, first blade arrangements of the same type to one another (A | 01-28-2016 |
