| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 415193000 | Plural, axially spaced vane sets | 18 |
| 20090068001 | STEAM TURBINE - A steam turbine has a stationary section, a turbine rotor, nozzle diaphragms, and a nozzle box. The stationary section includes a casing. The turbine rotor includes moving blade stages arranged in an axial direction. Each of the moving blade stages is provided with moving blades arranged in a circumferential direction, and rotatably provided in the casing. Each of the nozzle diaphragms has turbine nozzles arranged in the circumferential direction provided substantially coaxially with the turbine rotor by being secured to the stationary section. The nozzle box is supported on the stationary section and arranged at an upstream part of the moving blade stages substantially coaxially with the turbine rotor so as to lead steam flowing toward the turbine moving blades. The nozzle box holds at least two stages of the nozzle diaphragms. | 03-12-2009 |
| 20090123276 | STEAM TURBINE - A steam turbine is provided having a rotor which rotates around a machine axis, and a stator which concentrically encompasses the rotor with clearance, between which an annular passage is formed which is exposed to throughflow by steam in the axial direction and in which a multiplicity of rotor blades, which are fastened on the rotor, and fixed stator blades are arranged in a plurality of stages, wherein the stator blades of the last stage have a sweep with a sweep angle which changes in sign over the relative blade height. | 05-14-2009 |
| 20090169371 | STATOR CASCADE OF TURBO TYPE FLUID MACHINE - In the invention, stator blades are arranged in such a manner that respective intervals between the adjacent stator blades (SV) become unequal at least partly. If the stator blades are arranged as mentioned above, there are formed wave fronts having different moving directions and phases, and these wave fronts are interfered with each other so as to be attenuated. Accordingly, an interference noise is reduced. Therefore, in accordance with the invention, it is possible to reduce an interference noise without enlarging a rotor stator blade interval as well as reducing a used amount of a sound absorption material. | 07-02-2009 |
| 20100111684 | TURBINE AIRFOIL CLOCKING - An assembly of airfoils in a turbine engine, the assembly comprising: at least three successive axially stacked rows of airfoils in one of a compressor and a turbine: a first airfoil row, a second airfoil row, and a third airfoil row; wherein the first airfoil row and the third airfoil row each comprise one of a row of rotor blades and a row of stator blades, and the second airfoil row comprises the other; and wherein at least a majority of the mid-channel points of the airfoils in the third airfoil row are positioned circumferentially within +/−25% pitch of the third airfoil row with respect to the location at which a wake flow during a selected operating condition from the first airfoil row is determined to enter the third airfoil row. | 05-06-2010 |
| 20100158678 | AIRFOIL SHAPE FOR A TURBINE NOZZLE - An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a table. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches, the profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape. | 06-24-2010 |
| 20100172749 | WALL OF TURBO MACHINE AND TURBO MACHINE - The invention relates to wall of a turbo machine having a cascade of blades. The wall includes: a first platform facing a first passage between blades in the cascade of blades; and a second platform facing a second passage between adjacent cascade of blades on an upstream side and cascade of blades on a downstream side, and having a circumferential outline having a distribution of radial positions. According to the invention, loss due to disturbance of flow through the gap of axially adjacent walls can be reduced. | 07-08-2010 |
| 20110318174 | Compressor Rectifier Architecture - The present invention relates to a turbomachine rectifier comprising a plurality of stator vanes ( | 12-29-2011 |
| 20130089415 | GAS TURBINE WITH OPTIMIZED AIRFOIL ELEMENT ANGLES - A turbine airfoil assembly for installation in a gas turbine engine. The airfoil assembly includes an endwall and an airfoil extending radially outwardly from the endwall. The airfoil includes pressure and suction sidewalls defining chordally spaced apart leading and trailing edges of the airfoil. An airfoil mean line is defined located centrally between the pressure and suction sidewalls. An angle between the mean line and a line parallel to the engine axis at the leading and trailing edges defines gas flow entry angles, α, and exit angles, β. Airfoil inlet and exit angles are substantially in accordance with pairs of inlet angle values, α, and exit angle values, β, set forth in one of Tables 1, 3, 5 and 7. | 04-11-2013 |
| 20140271158 | COMPRESSOR STATOR - Compressor stators ( | 09-18-2014 |
| 20140356149 | FAN - A fan includes an impeller and a frame. The frame is used for accommodating the impeller. The frame includes a plurality of static blade groups. Each of the static blade groups has a plurality of static blades. Moreover, at least one first static blade of a first static blade group and at least one first static blade of a second static blade group are symmetric with respect to a central axis of the frame. | 12-04-2014 |
| 20150050135 | STATOR BLADE DIAPHRAGM RING, STEAM TURBINE AND METHOD - A stator blade diaphragm ring includes a plurality of stator blades each having a root and a radial pin receiver. The diaphragm ring further includes a first ring having a plurality of slots, wherein each slot is engaged by the root of one of the plurality of stator blades and a second ring having a plurality of radial through passageways, wherein each radial through passageway is aligned with the radial pin receiver of one of the plurality of stator blades. The diaphragm also includes a plurality of pins, wherein each pin extends from one of the radial through passageways into the radial pin receiver of one of the plurality of stator blades. | 02-19-2015 |
| 20160097281 | GAS TURBINE ENGINE AIRFOIL MISTUNING - A circumferential airfoil array that provides a total airfoil count for the stage and that includes first and second sets of airfoils with different vibrational frequencies. First and second arcuate regions are arranged opposite one another and third and fourth arcuate regions are arranged opposite one another. The first set of airfoils has first primary, first secondary and first tertiary airfoil groups. The second set of airfoils has second primary, second secondary and second tertiary airfoil groups. The first primary airfoil group and second primary airfoil group are respectively arranged in the first and second arcuate regions. The first secondary airfoil group and second secondary airfoil group are arranged in the third arcuate region. The first tertiary airfoil group and the second tertiary airfoil group are arranged in the fourth arcuate region. The first and second arcuate regions provide greater than 50% of the total airfoil count. | 04-07-2016 |
| 20160146013 | TURBINE ARRANGEMENT - The invention relates to a turbine for generating work by a stagewise expansion of a gas, such as steam wherein a downstream stage guide average height is less than an adjacent upstream stage runner average height. | 05-26-2016 |
| 20160377091 | Axial Turbomachine Compressor Casing - The present application relates to an axial turbomachine low-pressure compressor stator. The stator includes an outer annular casing made of organic matrix composite materials. The stator also has groups of vanes having an outer shroud, several rows of stator vanes spaced axially from one another, and segments of inner shrouds at the inner ends of the vanes. The rows of stator vanes are aligned along the circumference of the casing. Each outer shroud is pressed against the inside of the casing so it can be fastened by means of attachment pins. The outer shroud, and the rows of vanes of said group forming a one-piece assembly. The device of the present application reduces the number of vane attachment elements to a few attachment portions distributed on the shroud. | 12-29-2016 |
| 415194000 | Diverse size or spacing in different spaced vane sets | 4 |
| 20080286095 | Centrifugal Compressor Return Passages Using Splitter Vanes - A return section in a multistage centrifugal compressor includes a plurality of circumferentially positioned flow vanes, and a plurality of splitter vanes disposed between the flow vanes. The splitter vanes serve to minimize or eliminate regions of reverse or separated flow, resulting in improved compressor performance. | 11-20-2008 |
| 20090155062 | METHOD OF DESIGNING A MULTISTAGE TURBINE FOR A TURBOMACHINE - A method of designing a multistage turbine for a turbomachine in which each turbine stage comprises a stator row and a rotor row each made up of an annular row of airfoils, wherein, for all of the stator or rotor rows, it consists in simultaneously modifying the shapes of the airfoils of said rows to straighten out the wakes from the trailing edges of said airfoils, then in angularly positioning the rows in such a manner that the wakes from the airfoils of the stator (or rotor) airfoils impact against the leading edges of the stator (or rotor, respectively) airfoils of the rows situated downstream, in order to achieve multistage aerodynamic coupling simultaneously over the turbine as a whole. | 06-18-2009 |
| 20140322001 | TURBOMACHINERY STATIONARY VANE ARRANGEMENT FOR DISK AND BLADE EXCITATION REDUCTION AND PHASE CANCELLATION - A turbomachine includes a plurality of rotating blades adjacent to a plurality of stationary vanes attached to a stationary casing. Stationary vanes are spaced apart circumferentially with equal spacing around an inner perimeter of the casing. Optionally, stationary vanes are offset radially and/or circumferentially. Stationary vanes may alternate with leading and/or trailing edges at different distances from the rotating blades. In one embodiment, stationary vanes have tapered leading and/or trailing edge angles to homogenize flow and reduce stator wake excitation, flow excitation, and acoustic excitation due to interaction with spinning modes of acoustic pressure pulsations at rotating blade passing frequency. Tapered trailing edges are arranged such that they are inclined at mutually opposing angles to reduce rotor blade and/or disk excitation by: a) homogenizing the successive wakes within the flow stream, and b) reducing the effect of vortices shed-off the stationary vanes on acoustic modes of the gas within the casing. | 10-30-2014 |
| 20140328675 | Axial Turbomachine Stator with Ailerons at the Blade Roots - The present application relates to the compressor stator of an axial turbomachine. The stator comprises an annular row of main stator blades and auxiliary blades each of which are associated with a main blade. The auxiliary blades are located at the trailing edges of the main blades and are in the vicinity of the pressure faces of the main blades. The auxiliary blades are aligned to generate a low-pressure area at the trailing edges of the main blades. Thus, a flow bypassing a main blade by its suction face is sucked in by the low-pressure area when it approaches the trailing edge of the main blade. Stalling is thus avoided and the efficiency of the machine is improved. | 11-06-2014 |
