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7621720 |
Cooling device
A cooling device for a wind turbine is provided, the cooling device including at lease one liquid-tight tube which is partially filled with a liquid coolant, wherein one end of the tube is located...
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7621718 |
Turbine vane with leading edge fillet region impingement cooling
A turbine vane for use in a gas turbine engine, the vane including an airfoil portion and a endwall in which fillets extend around the airfoil at the junction to the endwall. A leading edge outer...
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7607891 |
Turbine component with tip flagged pedestal cooling
A turbine blade for a gas turbine engine is provided with improved cooling at a radially outer portion of the trailing edge. A tip flag path is provided with a first pedestal array to increase the...
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7607890 |
Robust microcircuits for turbine airfoils
A cooling microcircuit for use in a turbine engine component, such as a turbine blade, having an airfoil portion is provided. The cooling microcircuit has at least one inlet slot for introducing a...
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7607889 |
Turbine blade and gas turbine equipped with a turbine blade
The invention relates to a turbine blade comprising a vane that runs along a blade axis and a platform region, which is located at the root of the vane having a platform that extends transversally...
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7607287 |
Airfoil acoustic impedance control
A noise control cassette for a gas turbine engine includes a perforated face sheet configured for exposure to an airflow, a non-perforated backing sheet, a core arranged between the face sheet and...
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7607286 |
Regenerative turbine blade and vane cooling for a tip turbine engine
A fan-turbine rotor assembly ( 24 ) includes a multitude of turbine blades ( 34 ) which each define a turbine blade passage which bleed air from a diffuser section ( 74 ) to provide for...
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7600967 |
Stator assembly, module and method for forming a rotary machine
A stator assembly for a rotary machine having an array of wall segments for bounding a working medium flow path is disclosed. Various construction details which provide a sealing structure for the...
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7600966 |
Turbine airfoil with improved cooling
A turbine airfoil includes an outer wall and a plurality of cooling passages or minicores formed in the outer wall. A web separates each adjacent pair of the minicores. In order to provide more...
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7597536 |
Turbine airfoil with de-coupled platform
An airfoil used in a gas turbine engine, such as a turbine blade, includes a thin slot formed between a platform section and an airfoil section of the blade, with a metering hole providing for a...
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7588413 |
Upstream plasma shielded film cooling
An upstream plasma boundary layer shielding system includes film cooling apertures disposed through a wall having cold and hot surfaces and angled in a downstream direction from a cold surface of...
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7585152 |
Cooling jets
Cooling jets 1 are provided with a longitudinal aspect 2 greater than width 3 . Thus, the coolant flow through the jet 1 is less susceptible to deflection by lateral or cross flows presented...
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7585148 |
Non-positive-displacement machine and rotor for a non-positive-displacement machine
The invention relates to a rotor for a non-positive-displacement machine provided with a hollow shaft, which is arranged coaxial to the rotation axis, is supported, on both sides and on the face,...
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7581928 |
Serpentine microcircuits for hot gas migration
A turbine engine component, such as a turbine blade, has an airfoil portion with a pressure side and a suction side. The turbine engine component also has a first cooling circuit within the...
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7581927 |
Serpentine microcircuit cooling with pressure side features
In accordance with the present invention, there is provided a turbine engine component having an airfoil portion with a pressure side and a suction side, a first microcircuit embedded in a wall...
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7581920 |
Method for air circulation in a turbomachine compressor, compressor arrangement using this method, compression stage and compressor incorporating such a arrangement, and aircraft engine equipped with such a compressor
An air circulation method in a turbomachine compressor includes minimizing an inner flowpath between two adjacent blades by providing labyrinths on an inner casing between the two adjacent blades,...
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7578653 |
Ovate band turbine stage
A turbine stage includes a stator nozzle having a row of vanes mounted between inner and outer bands. The inner band terminates in an ovate ledge converging aft from the vanes with radially outer...
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7578652 |
Hybrid vapor and film cooled turbine blade
An apparatus for a gas turbine engine includes an airfoil defining a leading edge and a trailing edge, a root located adjacent to the airfoil, a vapor cooling system, and a film cooling system for...
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7575414 |
Turbine nozzle with trailing edge convection and film cooling
A hollow cooled airfoil includes an array of radially-spaced apart, longitudinally-extending partitions defining a plurality of cooling channels therebetween. A plurality of aft pins are disposed...
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7572102 |
Large tapered air cooled turbine blade
A large tapered air cooled turbine blade having a serpentine flow cooling circuit with a first leg located adjacent to a leading edge of the blade and a third leg at the trailing edge, where the...
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7568882 |
Impingement cooled bucket shroud, turbine rotor incorporating the same, and cooling method
A localized directional impingement cooling is used to reduce the metal temperatures on highly stressed regions of the tip shroud.
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7563072 |
Turbine airfoil with near-wall spiral flow cooling circuit
A turbine blade with a plurality of spiral flow cooling channels spaced along the walls of the blade. Each spiral flow cooling circuit includes two adjacent channels that twist about each other in...
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7556476 |
Turbine airfoil with multiple near wall compartment cooling
The present invention is a turbine airfoil such as a rotor blade with a cooling circuit that provides convective cooling to the airfoil main body, and impingement cooling and film cooling to the...
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7556474 |
Turbomachine, for example a turbojet for an airplane
A turbomachine including a wheel with hollow blades that are cooled internally by a forced flow of cooling air. According to an important characteristic of the invention, a hook-annulus ( 70 ) is...
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7553534 |
Film cooled slotted wall and method of making the same
An article includes a substrate having a first surface and a second surface; a slot disposed in the second surface, the slot having a bottom surface substantially parallel to the second surface, a...
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7553131 |
Integrated platform, tip, and main body microcircuits for turbine blades
A turbine engine component has an airfoil portion with a pressure side and a suction side. The turbine engine component further has a first cooling microcircuit for cooling the suction side of the...
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7552590 |
Tube-type vortex reducer
A tube-type vortex reducer for the conduction of cooling air in a compressor ( 1 ) of a gas turbine, having radial secondary air tubes ( 2 ) arranged in a disk interspace ( 5 ) and attached to a...
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7549843 |
Turbine airfoil cooling system with axial flowing serpentine cooling chambers
A cooling system for a turbine airfoil of a turbine engine having suction and pressure side serpentine cooling channels formed between an internal support core and an outer wall of the turbine...
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7549840 |
Through thickness reinforcement of SiC/SiC CMC's through in-situ matrix plugs manufactured using fugitive fibers
A method of manufacturing a turbine engine component comprising the steps of providing and laying up a plurality of ceramic plies comprising woven ceramic fiber tows to form a turbine engine...
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7540707 |
Link device between an enclosure for passing cooling air and a stator nozzle in a turbomachine
A link device between an enclosure for passing cooling air and a stator nozzle in a turbomachine, the device comprising metal tubes having their ends mounted in leaktight manner in orifices in a...
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7537431 |
Turbine blade tip with mini-serpentine cooling circuit
A turbine blade having a cooling supply passage formed within the blade, and a blade tip with a squealer tip formed thereon. The blade tip includes a blade top or cap, and includes a plurality of...
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7534089 |
Turbine airfoil with near wall multi-serpentine cooling channels
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 outer wall of the turbine airfoil and be formed...
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7534088 |
Fluid injection system
In accordance with the present invention, there is provided a system for injecting a secondary fluid stream into a primary fluid stream with improved aerodynamic efficiency. The secondary fluid...
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7534087 |
Turbomachine, in particular a gas turbine
The invention relates to a turbo-machine, in particular to a gas turbine and to a method for accelerating a temperature modification of a rotor shaft rotationally mounted in said turbo-machine. The...
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7534085 |
Gas turbine engine with contoured air supply slot in turbine rotor
A gas turbine engine is provided with a turbine rotor disk having a plurality of disk slots which each receive a turbine blade. Cooling air is delivered into the disk slots, and flows into cooling...
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7533534 |
HPT aerodynamic trip to improve acoustic transmission loss and reduce noise level for auxiliary power unit
A method and device for decoupling combustor attenuation and pressure fluctuation from turbine attenuation and pressure fluctuation in a gas turbine engine. The engine has: a compressor; a...
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7530789 |
Turbine blade with a serpentine flow and impingement cooling circuit
A turbine blade with a film cooling holes arrangement to supply film cooling to hot sections on the pressure side and suction side of the blade. The cooling flow circuit for the blade uses a...
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7527470 |
Stator turbine vane with improved cooling
A turbomachine stator vane having a leading edge, a trailing edge, and pressure side and suction side faces, a first and a second series of a plurality of holes, calibrated emission holes, and a...
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7524163 |
Nozzle guide vanes
A turbine nozzle guide vane 10 with passages 28 leading from a hollow core 32 to respective seal strip slots 20 , to deliver cooling air to abutment faces 18 on each end of the vane 10.
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7520719 |
Method and apparatus for the cooling of the outer shrouds of the rotor blades of a gas turbine
Passive shroud cooling of rotor blades ( 5 ) is accomplished by a multitude of cooling-air flows introduced into the hot-gas flow upstream of the rotor blades on the outer circumference, these...
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7513739 |
Cooling circuits for a turbomachine moving blade
A moving blade for a turbomachine, the central portion of the blade including a pressure-side cooling circuit and a suction-side cooling circuit. The pressure-side circuit comprises at least first...
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7513738 |
Methods and apparatus for cooling gas turbine rotor blades
Methods and apparatus for cooling rotor blades of a gas turbine are provided. The turbine blade has an airfoil connected to the platform and a dovetail extending from the platform. A main cooling...
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7513737 |
Gas turbine blade cooling circuit having a cavity with a high aspect ratio
A blade for a turbomachine gas turbine, the blade having a cooling circuit comprising at least one cooling cavity with a high aspect ratio extending radially between a root and a tip of the blade,...
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7510376 |
Skewed tip hole turbine blade
A turbine blade includes a hollow airfoil having a plurality of bowed tip holes extending through a tip floor thereof and skewed toward a squealer rib extending outwardly from the floor.
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7510367 |
Turbine airfoil with endwall horseshoe cooling slot
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...
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7507071 |
Cooling arrangement
A cooling arrangement is provided in which an incident coolant flow is presented to a passage such that a proportion of that flow is diverted in order to create a standing relative overpressure in...
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7503749 |
Turbine nozzle with trailing edge convection and film cooling
An airfoil for a gas turbine engine has opposed pressure and suction sidewalls extending between a leading edge and a trailing edge. The airfoil includes an array of radially-spaced apart...
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7503748 |
Mounting arrangement for turbine blades
A mounting arrangement 31 incorporates a blade pocket cavity 35, 135, 235 between a blade platform 34, 134, 234 and a rotor disc post 53 . Coolant air is presented within the cavity 35,...
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7503179 |
System and method to exhaust spent cooling air of gas turbine engine active clearance control
An exemplary thermal air exhaust system includes circumferentially extending exhaust passages to exhaust thermal control air from an annular region between an outer casing and a distribution...
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7500823 |
Turbine blade
A turbine blade ( 2 ), with a root section ( 4 ), with a tip section ( 6 ) and with a blade leaf ( 12 ) which is provided with a number of coolant ducts ( 22 ) through which a coolant (K) is...
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