|
Match
|
Document |
Document Title |
|
|
8172514 |
Rim seal for a gas turbine engine
The rim seal is positioned in an annular space between blades and a non-rotating adjacent structure in a gas turbine engine. The rim seal is connectable to the non-rotating structure and is made of...
|
|
|
8167563 |
Blade arrangement
A blade arrangement, with a rotor and a plurality of blades which are arranged on the periphery of the rotor in a ring, and a plurality of damping elements are provided. Between two directly...
|
|
|
8152436 |
Blade under platform pocket cooling
Inlets are provided at a front end of inter-blade cavities for allowing coolant to flow therein to cool down the undersurface of the blade platforms as well as the rim of the disc of a rotor assembly.
|
|
|
8152469 |
Annular turbine ring rotor
A fan-turbine rotor assembly (24) includes one or more turbine ring rotors (32). Each turbine ring rotor is cast as a single integral annular ring. By forming the turbine as one or more rings,...
|
|
|
8137072 |
Turbine blade including a seal pocket
A turbine blade is disclosed. The turbine blade may have an airfoil extending from a first surface of a turbine platform. The turbine blade may further have a first side pocket of the turbine...
|
|
|
8137071 |
Damper for turbomachine vanes
A turbomachine vane damper constructed so as to be housed between the lower face of the platforms of two adjacent turbomachine vanes and the rim of the rotor disk on which the vanes are mounted is...
|
|
|
8137067 |
Turbine with interrupted purge flow
A blade attachment apparatus for a turbine is provided and includes a member, which rotates about an axis of the turbine, including fore and aft disk posts that retain corresponding fore and aft...
|
|
|
8128365 |
Turbine airfoil cooling system with rotor impingement cooling
A turbine airfoil cooling system of a turbine engine having a hollow, disc post body positioned between adjacent roots of turbine airfoils and aligned with the roots to cool inner aspects of the...
|
|
|
8113784 |
Coolable airfoil attachment section
A rotor blade suitable for use in a gas turbine engine includes an attachment section which defines at least one internal cooling passage along a passage axis through the attachment section.
|
|
|
8105037 |
Endwall with leading-edge hump
An example airfoil assembly includes a base having an airfoil projecting radially therefrom. The base extends laterally away from the airfoil. The airfoil extends axially from an airfoil leading...
|
|
|
8100655 |
Method of machining airfoil root fillets
An airfoil root fillet having a predetermined compound curve profile can be flank milled with a single flank milling cutter having a generally conical flank milling portion and a rounded tip...
|
|
|
8096772 |
Turbine vane for a gas turbine engine having serpentine cooling channels within the inner endwall
A turbine vane for a gas turbine engine having an internal cooling system in fluid communication with cooling channels positioned in the inner endwall is disclosed. The cooling system in the inner...
|
|
|
8096769 |
Damper
Dampers (56, 76, 96) are utilized with regard to mounting arrangements (50, 70, 90) in gas turbine engines (10) in order to facilitate cooling. It is known to provide slotted upper surface or...
|
|
|
8083475 |
Turbine bucket angel wing compression seal
The present application provides an angel wing seal for a turbine bucket. The angel wing seal may include a first wing with a sinusoidally-shaped outer edge and a number of wing teeth positioned...
|
|
|
8070421 |
Mechanically affixed turbine shroud plug
A sealing interface for a component in a turbine machine, wherein a plug is mechanically affixed within an entrance passage of an aperture. The plug is secured in place within the entrance passage...
|
|
|
8070438 |
Fan blade for a gas turbine engine
An injection-molded thermoplastic mini-platform is adhesively bonded, in use, to the aerofoil surfaces of a fan blade in a gas turbine engine. The mini-platform is divided into a number of leaves,...
|
|
|
8066489 |
Aerofoil assembly
An aerofoil assembly includes a plurality of rotatable blades. A damping member is disposed between at least two of the blades, each of the at least two blades having an aerofoil portion, a stem...
|
|
|
8066479 |
Non-integral platform and damper for an airfoil
A section of a gas turbine engine includes a damper which extends from a disk between a first blade and a second blade to provide a dissipating vibratory motion energy in the form of friction heating.
|
|
|
8061994 |
Rotorcraft blade, a rotorcraft rotor provided with said blade, and a method of fabricating said blade
A rotorcraft rotor blade (1) has a blade root (1′) and a free end opposite from the blade root (1′), the blade (1) being provided at least with a spar (2) laid flat on a suction-side face (3) and...
|
|
|
8052378 |
Film-cooling augmentation device and turbine airfoil incorporating the same
A turbine airfoil is disclosed. The airfoil includes one of a turbine shroud, liner, vane or blade, including an airfoil sidewall having a film-cooling hole that extends between an airfoil cooling...
|
|
|
8052382 |
Turbo machine and gas turbine
A gas turbine (1) includes a rotor (2) which has two rotor blade rows (5) with a plurality of rotor blades (6), and also a rotor heat shield (7), which is arranged between them, with a plurality of...
|
|
|
8021118 |
Turbine blade for a turbine with a cooling medium passage
A turbine blade for a turbine of a thermal power plant, with a platform for partial delimiting of a flow passage in the turbine, wherein the platform has at least one cooling medium passage, which...
|
|
|
8016546 |
Systems and methods for providing vane platform cooling
Systems and methods for cooling vane platforms are provided. In this regard, a representative method for cooling a vane platform includes: providing a cooling channel on a platform from which a...
|
|
|
8011892 |
Turbine blade nested seal and damper assembly
A turbine blade damper-seal assembly includes a seal nested within a damper such that both the seal and damper are disposed to provide sealing between adjacent blade platforms. The seal traverses...
|
|
|
7988418 |
Microcircuits for small engines
A turbine engine component for use in a small engine application has an airfoil portion having a root portion, a tip portion, a suction side wall, and a pressure side wall. The suction side wall...
|
|
|
7976281 |
Turbine rotor blade and method of assembling the same
A rotor blade assembly includes a shank, an airfoil that is formed integrally with the shank, and a removable platform coupled between said shank and said airfoil via a friction fit. A method of...
|
|
|
7950900 |
Aerofoil stage and seal for use therein
A stage for a gas turbine engine, having a plurality of circumferentially spaced apart radially extending aerofoils, includes a plurality of annulus fillers to bridge the spaces between adjacent...
|
|
|
7946808 |
Seal between rotor blade platforms and stator vane platforms, a rotor blade and a stator vane
A rotor and a stator assembly, wherein the rotor (30) comprises at least one stage of rotor blades (32) and the stator (34) comprises at least one stage of turbine stator vanes (36). The rotor...
|
|
|
7931442 |
Rotor blade assembly with de-coupled composite platform
A rotor disk assembly with a platform spacer secured to the rotor disk and un-coupled from the rotor blades. Adjacent rotor blades are secured to the rotor disk slots by conventional means. The...
|
|
|
7927073 |
Advanced cooling method for combustion turbine airfoil fillets
The present invention is directed to a hollow turbine airfoil having a cooling system designed to provide enhanced cooling to the fillet of a turbine airfoil. The turbine airfoil may include at...
|
|
|
7922453 |
Process for preparing turbine blades or vanes for a subsequent treatment, and associated turbine blade or vane
Process for preparing turbine blades or vanes for a subsequent treatment, for example the application of a coating and/or a material-removing operation, wherein the turbine blade or vane has an...
|
|
|
7887297 |
Airfoil array with an endwall protrusion and components of the array
An airfoil array includes a laterally extending endwall 56 with a series of airfoils such as 28, or 38 projecting from the endwall. The airfoils cooperate with the endwall to define a series of...
|
|
|
7878763 |
Turbine rotor blade assembly and method of assembling the same
A removable rotor blade platform includes a first platform leg, a second platform leg, and a platform portion coupled to the first and second platform legs. The first platform leg is configured to...
|
|
|
7874804 |
Turbine blade with detached platform
A turbine blade with a detached platform in which the platform has a central opening in which the blade is inserted and held in place. The blade includes a root portion with a fir tree...
|
|
|
7874803 |
Gas turbine rotor
On a gas turbine rotor with internally cooled airfoils (4) of the turbine rotor blades and a mechanical sealing and damping element arranged between opposite side faces (6) of adjacent blade...
|
|
|
7866950 |
Turbine blade with spar and shell
A turbine blade for use in a gas turbine engine, where the turbine blade is made from a spar and shell construction in which a thin walled shell is held in place between the blade tip and the...
|
|
|
7862300 |
Turbomachinery blade having a platform relief hole
A turbomachinery blade having a relief hole in its platform and a method of limiting the formation and/or propagation of cracks in the trailing edge of the blade are provided. The relief hole may...
|
|
|
7841828 |
Turbine airfoil with submerged endwall cooling channel
A turbine airfoil usable in a turbine engine and having at least one cooling system. At least a portion of the cooling system may be positioned in an endwall attached to the turbine airfoil. The...
|
|
|
7811053 |
Fan rotor design for coincidence avoidance
A fan rotor capable of avoiding coincidence will include a fan hub comprising one or more slots each designed to receive a fan blade; and one or more fan blades disposed within the slots. One or...
|
|
|
7811058 |
Cooling arrangement
Cooling with regard to high-pressure turbine platforms is important in order to maintain gas turbine engine efficiency. Cottage Roof dampers located below junction gaps between adjacent platforms...
|
|
|
7766621 |
Split shank rotor blade
A shroudless turbine rotor blade of the type having a platform damper interface, is provided with at least one slot which extends from the aerofoil side of a platform flow boundary to a point in...
|
|
|
7766606 |
Turbine airfoil cooling system with platform cooling channels with diffusion slots
A cooling system for a turbine airfoil of a turbine engine having suction side platform cooling channels and pressure side platform cooling channels for cooling hot spots in a platform attached to...
|
|
|
7762781 |
Composite blade and platform assembly
A turbine blade and platform assembly in which the platform is a separate piece that is secured to the blade through shear pins that extend along slots formed between opposed abutting parts of the...
|
|
|
7762780 |
Blade assembly in a combustion turbo-machine providing reduced concentration of mechanical stress and a seal between adjacent assemblies
A blade assembly 100 (FIG. 5) configuration that includes a means for distributing mechanical stress (e.g., a stress dissipater 54) is provided. The stress dissipater is configured to reduce the...
|
|
|
7758309 |
Vane wheel of turbine comprising a vane and at least one cooling channel
There is described a vane wheel of a turbine comprising at least one vane, the footing thereof being held on a wheel disk. At least one cooling channel is arranged between the wheel disk and the...
|
|
|
7753651 |
Balancing flyweight, rotor disk equipped therewith, rotor and aircraft engine comprising them
The balancing flyweight of a turbomachine rotor includes two pyramid shaped end parts each one having a base and an apex, and an intermediate part which connects the two bases of the end parts...
|
|
|
7731482 |
Bucket vibration damper system
A damping system for a turbine bucket. The damping system includes a damper pocket with a variable tangential depth and a damper pin positional within the damper pocket.
|
|
|
7708528 |
Platform mate face contours for turbine airfoils
Gas turbine engine components having an airfoil extending outwardly of a platform are mounted in adjacent relationship, and such that cooling air flows outwardly of a gap between mating faces of...
|
|
|
7708525 |
Industrial gas turbine blade assembly
A gas turbine blade assembly includes a neck defining a neck cavity, and has a first end and a second end at an opposite side relative to the first end. A platform has first and second sides. The...
|
|
|
7695247 |
Turbine blade platform with near-wall cooling
A turbine blade having a platform and an airfoil extending from the platform. The platform includes a plurality of pressure side cooling channels formed within the platform and extending from a...
|