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5382135 |
Rotor blade with cooled integral platform
A rotor blade having a cooled integral platform is disclosed. Various construction details are developed which disclose a rotor blade platform having a first cooling hole for directing rotor blade...
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5378108 |
Cooled turbine blade
Turbine blade (10) has a plurality of trailing edge discharge openings (28) discharging cooling air. The blade trailing edge has an increasing thickness "E" toward the tip end (16). Discharge...
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5374162 |
Airfoil having coolable leading edge region
A coolable rotor blade 16 having an airfoil section 18 is disclosed. Various construction details are developed which increase the cooling effectiveness under the airfoil section 18 under a variety...
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5370499 |
Film cooling of turbine airfoil wall using mesh cooling hole arrangement
A turbine airfoil has a mesh cooling hole arrangement which includes first and second pluralities of cooling holes extending between internal and external surfaces of an airfoil side wall at least...
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5368441 |
Turbine airfoil including diffusing trailing edge pedestals
A turbine airfoil having a cut-back trailing edge and a plurality of diffusing flow dividers upstream of the cut-back trailing edge is disclosed. Various construction details are developed which...
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5356265 |
Chordally bifurcated turbine blade
A gas turbine engine turbine blade includes an airfoil having pressure and suction sides joined together at leading and trailing edges and extending from a root to a tip. The airfoil also includes...
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5352091 |
Gas turbine airfoil
Tube 16 within airfoil 10 carries cooling air. Flow openings 28 in the tubes direct cooling air 29 against the airfoil inner surface 14. Protrusions 30 form extended surface in the form of...
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5348446 |
Bimetallic turbine airfoil
An airfoil for a gas turbine engine is constructed from a core body formed of a conventional nickel-based superalloy and leading and trailing edge components and squealer tip formed of a nickel...
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5342172 |
Cooled turbo-machine vane
A turbo-machine vane having a plurality of internal cavities for the flow of a cooling fluid, and a plurality of openings through the outer wall of the vane for communicating the internal cavities...
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5340274 |
Integrated steam/air cooling system for gas turbines
A steam or air cooled combined cycle gas turbine includes first and second turbine stages and a second nozzle stage. During start-up, cooling air is supplied radially inwardly through the second...
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5340278 |
Rotor blade with integral platform and a fillet cooling passage
A rotor blade having an integral platform with a cooled fillet is disclosed. Various construction details are developed which provide a cooling hole extending in proximity of the fillet to...
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5328331 |
Turbine airfoil with double shell outer wall
A coolable airfoil for use in gas turbine engine component such as a turbine blade or vane is provided with an integrally formed double shell outer wall surrounding at least one radially extending...
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5326224 |
Cooling hole arrangements in jet engine components exposed to hot gas flow
A jet engine component includes a body having a wall portion with an external surface exposed to hot gas flow and an internal surface exposed to a cooling air flow. The engine component...
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5320485 |
Guide vane with a plurality of cooling circuits
A fluid cooled guide vane is disclosed for use in a gas turbine engine which defines a plurality of separate cooling circuits to guide a cooling fluid through the interior of the vane, while at the...
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5288207 |
Internally cooled turbine airfoil
A turbine airfoil having a baffleless cooling passage for directing cooling fluid toward a trailing edge is disclosed. Various construction details are developed which provide axially oriented,...
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5282721 |
Passive clearance system for turbine blades
Spent cooling air from the internal passage(s) in a turbine blade of a gas turbine engine are judiciously located to inject air at the pressure side of the blade in proximity to or in the gap...
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5269653 |
Aerofoil cooling
There is provided an aerofoil 11 having a passage 17 supplied with cooling fluid from passage 13. When the leading edge area 14 of the aerofoil 11 erodes/corrodes the passage 17 becomes exposed so...
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5263820 |
Cooled aerofoil blade for vane for a gas turbine engine
A cooled aerofoil blade for a gas turbine engine has a hollow trailing edge region in which bridging members interconnect the convex and concave flanks of the blade. The bridging members are each...
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5263821 |
Mid-beam jointed reconfigurable bearingless main rotor assembly
A mid-beam jointed reconfigurable bearingless main rotor (BMR) assembly that includes reconfiguration joints that facilitate BMR assembly reconfiguration by main rotor blade removal or folding to...
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5261789 |
Tip cooled blade
A gas turbine engine blade includes an airfoil having first and second sides and a dovetail extending from the airfoil root. The airfoil includes a tip having a tip floor with first and second tip...
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5259730 |
Impingement cooled airfoil with bonding foil insert
An impinqement cooled airfoil is fabricated by diffusion bonding a pair of airfoil half-sections together using an insert which is prefabricated from diffusion bonding foil. The insert is...
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5253976 |
Integrated steam and air cooling for combined cycle gas turbines
A steam or air-cooled combined cycle gas turbine includes first and second turbine stages and a second nozzle stage disposed about a spacer between the turbine stages. Cooling steam is passed...
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5246341 |
Turbine blade trailing edge cooling construction
Internal cooling of the trailing edge of the airfoil of the turbine blade for a gas turbine engine includes a cascade formed from juxtaposed rows of longitudinally extending spaced airfoil shaped...
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5246340 |
Internally cooled airfoil
A hollowed, internally cooled airfoil per gas turbine engines with an improved internal configuration for pronounced impingement cooling. Internal ribs extend across the hollowed interior and...
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5232343 |
Turbine blade
An exemplary preferred embodiment of the present invention includes a gas turbine blade having an internal coolant passage therein of width D and a plurality of longitudinally spaced substantially...
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5223320 |
Perforated two layered sheet for use in film cooling
A perforated sheet for the promotion of film cooling a gas turbine engine comprises two separate layers of laminate material which are placed in superposed abutting relationship. The first layer...
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5215431 |
Cooled turbine guide vane
A hollow turbine guide blade or vane is provided with three separate cooling circuits formed by virtue of two radial partitions extending the length of the blade within the cavity bounded by the...
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5203873 |
Turbine blade impingement baffle
An impingement-cooled gas turbine blade includes an impingement baffle which, during engine operation, is subject only to shear loading. A tubular baffle body is provided with a pair of mounting...
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5193975 |
Cooled gas turbine engine aerofoil
The present invention relates to cooled gas turbine engine aerofoils particularly for turbine stator vanes or tubine rotor blades. The leading edge region of a hollow aerofoil is provided with rows...
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5193980 |
Hollow turbine blade with internal cooling system
A hollow turbine blade equipped with a cooling system comprises a pair of internal partitions connected to the intrados and extrados walls of the blade and dividing the interior of the blade into...
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5192192 |
Turbine engine foil cap
In an axial flow turbo-machine such as a gas turbine engine, a foil cap for hollow blades or cantilevered vanes, aft of the combustion chamber thereof is provided, the cap having cooling apertures...
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5183385 |
Turbine blade squealer tip having air cooling holes contiguous with tip interior wall surface
A turbine blade squealer tip has a plurality of holes defined through the end cap of the blade tip portion and located contiguous with an interior surface of the squealer tip wall along at least...
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5176499 |
Photoetched cooling slots for diffusion bonded airfoils
Cooling passages are accurately formed along the faying surfaces of a pair of diffusion bonded members such as a pair of half sections used to fabricate an airfoil. A particularly advantageous...
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5165852 |
Rotation enhanced rotor blade cooling using a double row of coolant passageways
A rotor blade such as a turbine rotor blade for a jet engine. The airfoil blade portion of the rotor blade has a plurality of longitudinally extending coolant passageways preferably interconnected...
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5152667 |
Cooled wall structure especially for gas turbine engines
A cooled wall structure including a hot side, a cold side, a linear slot opening through the hot side, a plurality of diffusion chambers below the hot side separated therefrom by relatively thin...
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5125798 |
Method and apparatus for cooling air flow at gas turbine bucket trailing edge tip
An apparatus and method for varying the cooling air flow within a gas turbine bucket tip. Each turbomachinery blade contains at least one radial cooling passage located between a hollow interior...
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5102299 |
Airfoil trailing edge cooling configuration
An airfoil includes a plurality of interior cooling air paths arranged so as to provide crossover metering and pressure side bleed of cooling air at the trailing edge region of the airfoil.
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5096379 |
Film cooled components
A variety of configurations for convergent-divergent film cooling holes are disclosed, together with the hole drilling methods necessary to achieve the configurations.
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5090866 |
High temperature leading edge vane insert
A two part vane (38) comprises a metallic downstream portion (42) and a high temperature leading edge insert (40) disposed between two retaining buttons (46,48) loosely fit into recesses (50)...
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5073083 |
Turbine vane with internal cooling circuit
A vane for a turbojet engine, is disclosed having an airfoil-shaped body with a leading edge, a trailing edge, a generally concave sidewall and a generally convex sidewall defining a hollow vane...
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5073086 |
Cooled aerofoil blade
A gas turbine engine turbine aerofoil blade includes an aerofoil portion having pressure and suction flanks. The flanks are internally interconnected by wall member which cooperates with the flanks...
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5062768 |
Cooled turbomachinery components
An aerofoil for a gas turbine engine turbine rotor blade or stator vane is subject to film cooling by multiple rows of small cooling air exit apertures in the exterior surface of the blade or vane....
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5052889 |
Offset ribs for heat transfer surface
Augmenting ribs (40) of zig-zag configuration are provided on a heat transfer surface (38) for increasing local heat transfer in a selected zone (68,70) of the surface (38).
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5022817 |
Thermostatic control of turbine cooling air
A gas turbine engine is provided with hollow guide vanes having thermally responsive actuators mounted within each for individually controlling the cooling air flow therethrough in response to...
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4992026 |
Gas turbine blade
A blade of a gas turbine includes a main body having a dovetail portion and a blade portion extending from the dovetail portion. A cooling air passage for flowing a cooling air is formed in the...
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4962640 |
Apparatus and method for cooling a gas turbine vane
An apparatus and method are provided for preventing the plugging of cooling air distribution holes in a hollow gas turbine vane by particles entrained in the cooling air. The portion of the cooling...
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4946346 |
Gas turbine vane
A gas turbine vane has a vane airfoil defining a cavity extending along the longitudinal direction of the vane airfoil. A guide cylinder is disposed in the cavity to guide coolant fluid supplied...
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4940388 |
Cooling of turbine blades
In order to facilitate efficient use of high pressure cooling air in a turbine rotor blade its aerofoil has a triple-pass convoluted cooling air duct in its leading edge region, and a triple-pass...
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4923371 |
Wall having cooling passage
The invention comprises a wall having first and second spaced surfaces, and a first plane disposed therebetween which includes first and second coplanar and orthogonal axes. A passage extends...
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4893987 |
Diffusion-cooled blade tip cap
An improved turbine blade tip with diffusion cooling holes in the tip is disclosed. One particular embodiment of the invention provides an improved squealer blade tip with diffusion cooling holes...
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