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| Number | Title | Issue Date |
| 7959409 | Repaired vane assemblies and methods of repairing vane assemblies Methods are provided for repairing a vane assembly, where the vane assembly includes an inner annular housing, an outer annular housing, and a vane extending therebetween. In one embodiment, the method includes removing an identified section of the vane to thereby f... | 06/14/2011 |
| 7434313 | Method for repairing a turbine engine vane assembly and repaired assembly A repaired turbine engine stationary vane assembly, including at least one airfoil bonded between inner and outer bands, is provided by a method of providing first and second vane assembly members bonded at respective circumferential edges, for example by brazing or... | 10/14/2008 |
| 7431558 | Air intake An air intake with at least one inlet port area and one outlet port area, in which there is arranged at least one structure which may be flowed through and around, comprises an opening and modifies the clear cross-section only slightly, in particular serving as a fr... | 10/07/2008 |
| 7427187 | Welded nozzle assembly for a steam turbine and methods of assembly A steam turbine nozzle singlet having a blade or airfoil between inner and outer sidewalls is provided. The sidewalls include steps or flanges which are received in complementary recesses in the rings enabling axially short low heat input welds e.g., e-beam welds. T... | 09/23/2008 |
| 7410342 | Airfoil support A blade or a vane preferably used in a gas turbine engine, the blade or vane being formed of a metallic core or insert with a ceramic airfoil surface bonded to the metallic insert. The insert includes a series of concave and convex portions arranged along the outer ... | 08/12/2008 |
| 7374398 | Automotive compressor An automotive compressor is provided having a casing defining an intake section for fluid for compression, and a delivery section for delivering the compressed fluid. An impeller is movable angularly inside the casing to increase the pressure of the fluid. A distrib... | 05/20/2008 |
| 7351039 | Compressor rotor blade A compressor rotor blade (1) includes a rotor blade (2), a platform (3) that adjoins the rotor blade (2) and blade footing (4) that adjoins the platform (3). The rotor blade (4) is embodied so as to be massive, withou... | 04/01/2008 |
| 7334800 | Seal for a gas turbine engine having improved flexibility A seal extending between adjacent slots of a gas turbine engine is disclosed. The seal comprises a plurality of generally planar members fixed together along a central axis. The outer member further comprises rounded ends that encompass the second and plurality of t... | 02/26/2008 |
| 7329087 | Seal-less CMC vane to platform interfaces A stator vane assembly for a gas turbine includes a ceramic matrix composite airfoil held between radially inner and outer metal platforms wherein an interface between the airfoil and at least one of the radially inner and outer platforms is shaped to create a circu... | 02/12/2008 |
| 7326030 | Support system for a composite airfoil in a turbine engine A turbine airfoil support system for coupling together a turbine airfoil formed from two or more components, wherein the support system is particularly suited for use with a composite airfoil. In at least one embodiment, the turbine airfoil support system may be con... | 02/05/2008 |
| 7311495 | Vane support in a gas turbine engine A fluid flow machine comprises an array of vanes (2) which are supported at their ends by inner and outer support structures 4, 6. The ends of the vanes are received in slots 8, 10, with resilient material 12 disposed between the vane ... | 12/25/2007 |
| 7306429 | Axial-flow heat-dissipating fan An axial-flow heat-dissipating fan includes an impeller and a casing. The impeller includes a hub and a plurality of blades formed on the hub. The casing includes an air inlet, an air outlet, a base in the air outlet, and guiding ribs mounted between the casing and ... | 12/11/2007 |
| 7222422 | Method for refurbishing surfaces subjected to high compression contact A process for refurbishing a worn surface of a shroud support component of a turbomachine, as well as a shroud support component refurbished with the process. The process generally entails removing a surface region of the worn surface so as to define a repair surfac... | 05/29/2007 |
| 7220102 | Guide blade of axial-flow fan shroud Guide blades of an axial flow fan shroud for guiding the air blown by an axial flow fan in an axial direction. A guide blade of an axial flow fan shroud has a leading edge for introducing the air blown by an axial flow fan including a plurality of blades; a trailing... | 05/22/2007 |
| 7185433 | Turbine nozzle segment and method of repairing same A method for repairing a stationary turbine nozzle segment having at least one vane disposed between outer and inner structural bands includes providing an engine-run turbine nozzle segment having at least one vane disposed between outer and inner bands, wherein the... | 03/06/2007 |
| 7186092 | Airfoil having improved impact and erosion resistance and method for preparing same A turbine airfoil having an improved impact and erosion resistance. The airfoil comprises: (a) a base segment having an impact resistant leading edge section proximate to the leading edge comprising a material having having a yield strength of least about 250 ksi an... | 03/06/2007 |
| 7181914 | Diffuser for gas turbine engine A gas turbine engine pre-diffuser 40 is generally annular, including radially inner and radially outer walls 40 and 42 and a generally cylindrical midline 48 defined between the walls. The pre-diffuser 40 includes a central member ... | 02/27/2007 |
| 7172389 | Method for making a repaired turbine engine stationary vane assembly and repaired assembly A method is provided for making a repaired turbine engine stationary vane assembly including at least one airfoil bonded between spaced apart first and second platforms. The method comprises providing a first vane assembly member including at least a portion of the ... | 02/06/2007 |
| 7172388 | Multi-point seal A spring seal for sealing a gap defined between first and second gas turbine engine components. The spring seal has a grasping portion for graspingly receiving a portion of the first component, and a spring loading portion adapted to extend between the first and sec... | 02/06/2007 |
| 7152864 | Seal assembly It is disclosed a seal assembly (5) which comprises a layered structure. It consists of a first layer (9, 12) of a base material, a second layer (10) of thermal insulating material on top of the base material and a third layer (11, 12) of... | 12/26/2006 |
| 7147434 | Nozzle ring with adhesive bonded blading for aircraft engine compressor Blades (3) extending radially from the inner shroud (1) to the outer shroud (2) are attached to the inner shroud by means of a sealing cement containing an organic polyimide-based polymer adhesive. ... | 12/12/2006 |
| 7146990 | Process for repairing sulfidation damaged turbine components A process is provided for cleaning a surface of an internal cavity of a gas turbine component having sulfidation or sulfur bearing deposits comprising: inserting into the internal cavity a fluoride salt; and heating the fluoride salt and the component in an inert at... | 12/12/2006 |
| 7121793 | Undercut flange turbine nozzle A turbine nozzle includes a vane joined to opposite inner and outer bands. The inner band includes a pocket adjoining a flange which recesses in part the inner surface of the band. The pocket undercuts the flange to form a notch at the base thereof. ... | 10/17/2006 |
| 7118332 | Heat dissipating fan with air-guiding structure A heat dissipating fan includes a casing having an outlet, a base mounted in the outlet of the casing, and a plurality of air guiding members mounted in the outlet and connected between the base and the casing. Each air guiding member defines at least one air concen... | 10/10/2006 |
| 7097420 | Methods and apparatus for assembling gas turbine engines A method of assembling a gas turbine engine includes providing a plurality of stator vane sectors that each include an equal number of stator vanes that are circumferentially-spaced such that a first circumferential spacing is defined between each pair of adjacent s... | 08/29/2006 |
| 7083381 | Hydrokinetic torque converter stator blade construction A stator blade for a hydrokinetic torque converter, the blade profile having geometric characteristics that improve torque flow efficiency in the converter torque flow circuit, whereby the torque converter efficiency at high speed ratios is improved without signific... | 08/01/2006 |
| 7066799 | Protection mask for surface treatment of turbomachine blades A protection mask used during surface treatment for a turbomachine blade, including for example a sand blasting step and/or a metal coating step, includes at least one part matching the shape of a portion of the blade. The mask is designed to resist surface treatmen... | 06/27/2006 |
| 7052234 | Turbine vane collar seal A collar seal is configured for a turbine nozzle vane. The seal includes a retainer having a circumferential airfoil contour conforming with the airfoil contour of the vane. A flexible leaf is surrounded by the retainer and fixedly joined thereto. A woven sheath enc... | 05/30/2006 |
| 7040862 | Axial flow fan A fan wherein an airflow adjustment device is used to make fine adjustments to the air discharged by the blower and a method of adjusting a fan's airflow by attaching a flow adjustment device. ... | 05/09/2006 |
| 7021890 | Turbo pump In order to provide a high-head, large-delivery turbopump adapted for excellent suction performance and foreign matter passability by having characteristics of an inducer, axial flow vanes, and mixed flow vanes imparted together to centrifugal vanes, a progressively... | 04/04/2006 |
| 7001147 | Airfoil shape and sidewall flowpath surfaces for a turbine nozzle A turbine nozzle includes airfoil and sidewall surfaces. The airfoil and sidewall surfaces have profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Tables I–IV for the pressure and suction sides of the airfoil, and the ... | 02/21/2006 |
| 6994520 | Internal core profile for a turbine nozzle airfoil First stage nozzle airfoils have internal core profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein X, Y and Z values are in inches. The X and Y values are distances which, when connected by smooth continui... | 02/07/2006 |
| 6994518 | Pre-whirl generator for radial compressor A pre-whirl generating apparatus (26) is provided that employs deformable air deflecting vanes (46) adjacent the inlet (18) of a radial air compressor (12-22), which vanes (46) can be mechanically deformed to generate positi... | 02/07/2006 |
| 6979173 | Turbine blade or vane A turbine blade or vane includes an inner contour profile which is matched to the contour profile of the outer transition region, so that a substantially uniform blade or vane wall thickness is achieved. ... | 12/27/2005 |
| 6969232 | Flow directing device A flow directing device of a gas turbine engine, comprising: an airfoil having a leading edge, trailing edge, suction side and pressure side; a wall abutting the airfoil; and a fillet between the airfoil and wall. The fillet has an enlarged section at the leading ed... | 11/29/2005 |
| 6962479 | Compound centrifugal and screw compressor A compound centrifugal and screw compressor comprising two separate sections. The first section is a conventional centrifugal compressor body 2 with a plurality of radial vanes 3 and 4 on the front face. The second section of the compressor is a... | 11/08/2005 |
| 6921246 | Methods and apparatus for assembling gas turbine nozzles A method facilitates assembling a turbine nozzle for a gas turbine engine. The method includes providing a turbine nozzle including a plurality of airfoil vanes that extend between an inner band and an outer band, and forming a compound radii fillet that extends bet... | 07/26/2005 |
| 6913442 | Apparatus for retaining an internal coating during article repair An internal coating on an internal passage wall exposed at a passage opening through an article external surface is protected from removal during repair of the article, including removal of at least a portion of an external coating, by a masking assembly disposed ab... | 07/05/2005 |
| 6910854 | Leak resistant vane cluster A vane cluster for a turbine engine compressor or turbine includes a shroud 12 with a nonlinear slot 26 extending therethrough to divide the shroud into thermally independent shroud segments 24. The slot is bordered by matching nonlinear surface... | 06/28/2005 |
| 6905308 | Turbine nozzle segment and method of repairing same A method is provided for repairing a turbine nozzle segment having at least one vane disposed between outer and inner bands. The method includes separating the inner band from the nozzle segment, and joining the inner band to a newly manufactured replacement casting... | 06/14/2005 |
