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5413458 |
Turbine vane with a platform cavity having a double feed for cooling fluid
A turbine vane for a gas turbine engine includes a platform with a cavity along the trailing edge having a double feed arrangement for injecting cooling fluid into the cavity. Various construction...
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5407320 |
Turbine cowling having cooling air gap
A turbine casing having temperature requirements that vary along the casing and which is at least partially enclosed by a cowling so that a gap is defined between the casing and cowling through...
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5399065 |
Improvements in cooling and sealing for a gas turbine cascade device
In a cascade device for a gas turbine, cooling air which has passed through a trailing air cooling chamber of each stationary blade is discharged from a tip of the stationary blade toward a side...
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5399066 |
Integral clearance control impingement manifold and environmental shield
Clearance control is provided by a shaped, integral environmental shield and circumferentially segmented cooling manifold. Each manifold has impingement rails located radially outside selected...
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5392515 |
Method of manufacturing an air cooled vane with film cooling pocket construction
An air cooled stator vane for a gas turbine engine is fabricated by casting the suction side wall and pressure side wall of the airfoil into separate halves and joining both halves at complementary...
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5391052 |
Impingement cooling and cooling medium retrieval system for turbine shrouds and methods of operation
The steam impingement cooling and retrieval system for turbine shrouds includes a plurality of circumferentially spaced housings about a turbine shroud, each housing being divided by an impingement...
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5385013 |
Aircraft gas turbine engine backbone deflection thermal control
A gas turbine engine thermal backbone deflection control apparatus to counter the effects of backbone bending due to nacelle aerodynamic, thrust, and maneuver loads by introducing a controlled...
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5382141 |
Compressor system and method of operation
In the operation of a compressor system in a subsea station for transporting a well stream, separated well stream gas is supplied to a compressor (12, 13) which is arranged with its motor (8) in a...
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5382133 |
High coverage shaped diffuser film hole for thin walls
A film cooling passage through the external wall of a hollow airfoil having in serial flow relation a metering section and a diffusing section, the diffusing section characterized in that it has...
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5380150 |
Turbine shroud segment
A turbine shroud segment includes a center hook along one edge which retains the segment to the turbine structure while permitting thermal distortion of the segment. In a particular embodiment, a...
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5374161 |
Blade outer air seal cooling enhanced with inter-segment film slot
A cooling enhancement for a gas turbine engine blade outer air seal is made up of a plurality of arcuate seal segments, and each one has one or more internal cooling passages. Each segment has a...
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5358374 |
Turbine nozzle backflow inhibitor
A turbine nozzle includes a vane integrally joined between outer and inner bands, with the inner band having a purge hole for discharging a portion of cooling air channeled through the vane. A...
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5352087 |
Cooling fluid ejector
A turbine section having a seal cavity with effectively continuous flow surfaces is disclosed. Various construction details are developed which disclose a fluid cooled stator assembly having a...
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5340271 |
Flow control method and means
The method controls gas flow in an axial flow compressor in which the flow at one or more chosen station in the direction of flow through the compressor is sensed at a series of circumferentially...
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5332357 |
Stator vane assembly for controlling air flow in a gas turbine engien
In an annular array of stator aerofoil vanes (25 ) each of the vanes (25 ) has a flank portion (35 ) which is pivotally attached to the remainder of its associated vane (25). Actuation means (60)...
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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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5327719 |
Circuit for ventilating compressor and turbine disks
A turbo-engine includes a compressor connected by a shaft to a turbine and includes a plurality of disk stages subjected to a thermal gradient, a gas vein in which the gas circulates from upstream...
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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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5320483 |
Steam and air cooling for stator stage of a turbine
The second-stage nozzles include a plurality of stator vanes 10 having first, second, third, fourth and fifth passages 40, 42, 44, 46 and 48, respectively, for cooling the vanes. The first and...
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5313797 |
Exhaust gas turbine powered system for transforming pressure into rotative motion
A rotary power transformer employing the exhaust gases of an internal combustion engine as the fluid medium for transforming pressure into a rotative motion. It includes a circular housing and a...
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5282726 |
Compressor supercharger with evaporative cooler
Apparatus and method for increasing the capacity of a gas compressor. The apparatus comprises a supercharger for compressing a gas flow and an evaporative cooler for cooling and ducting the...
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5281097 |
Thermal control damper for turbine rotors
Sheet Metal thermal control dampers are disposed in the cavities between turbine blades to bear against the undersides of opposed blade platforms portions of angularly adjacent blades under...
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5281085 |
Clearance control system for separately expanding or contracting individual portions of an annular shroud
Improved operation can be achieved from an enhanced gas turbine engine having a segmented annular shroud which radially expands and contracts to match the expansion and contraction of engine rotor...
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5273397 |
Turbine casing and radiation shield
A thermal radiation shield is joined to an annular casing through which combustion gases are axially flowable. The shield is spaced at least in part radially inwardly from the casing inner surface...
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5271711 |
Compressor bore cooling manifold
To control disc temperature, provide blade tip clearance control, and purge the rotor bore of a high pressure compressor in a gas turbine engine, an axially elongated manifold is disposed coaxially...
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5252026 |
Gas turbine engine nozzle
A gas turbine engine nozzle includes outer and inner bands and a plurality of spaced apart vanes extending therebetween. The inner band includes an outer surface facing the outer band over which is...
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5252025 |
Drainage pump
A drainage pump (10) in which the portion near the entrance of the impeller (12) in the suction tube (11) is open to the set lowest suction water level (L.W.L.) through an air intake pipe (15), so...
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5245821 |
Stator to rotor flow inducer
An aerodynamically efficient flow transfer device having a means to transfer flow from a static element to a rotor element such that the end of the exit flow is substantially parallel to an exit...
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5240372 |
Centrifugal pumps and systems utilizing same
A centrifugal pump for a first fluid has a housing with an inlet and includes a rotatable impeller which is adjacent to a stationary plate. The inlet communicates with a space defied between the...
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5236301 |
Centrifugal compressor
An improved centrifugal compressor for use in gas turbine engines includes a secondary air flow inlet in the compressor shroud at a location downstream of the inducer, with passive elements in the...
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5232335 |
Interstage thermal shield retention system
An interstage thermal shield assembly for a gas turbine engine. The assembly includes an axially-extending thermal shield positioned between first and second stage disks to form a seal...
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5232338 |
Blade array for turbomachines comprising suction ports in the inner and/or outer wall and turbomachines comprising same
A blade array for turbomachines comprises blades disposed between an inner wall and an outer wall. The inner wall and/or the outer wall is provided with a suction port near at least some blades....
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5224819 |
Cooling air pick up
A cooling air pick up for use in a gas turbine engine includes a cooling air duct incorporating a diffuser to maximize the cooling air pressure. The entry orifice of the pick up duct is formed in...
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5224818 |
Air transfer bushing
An air transfer assembly for a gas turbine engine is provided. The assembly transfers temperature control air from an annular plenum to an annular manifold through an air transfer tube interposed...
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5218822 |
Air start/assist for turbochargers
The compressor for a turbocharger includes an assist system to provide a power stream of a driving fluid such as air to act on the impeller of the compressor until the driving power of the exhaust...
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5217348 |
Turbine vane assembly with integrally cast cooling fluid nozzle
A gas turbine engine having a turbine vane assembly including an integrally cast cooling fluid nozzle is disclosed. Various construction details are developed which disclose a cooling fluid nozzle...
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5207556 |
Airfoil having multi-passage baffle
A hollow impingement baffle includes a septum extending between its bottom and top and spaced between its forward and aft edges to define a forward manifold and an aft manifold. The baffle includes...
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5205708 |
High pressure turbine component interference fit up
An interference fit up for an HPT hanger is accomplished by machining and casting features into the hanger which create a spring effect when the hanger is assembled into the support. The spring...
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5193976 |
Injection device for the ON-LINE wet cleaning of compressors
In an injection device for the ON-LINE wet cleaning of compressor, the liquid cleaning agent is injected via a nozzle into the flow passage upstream of the compressor. The nozzle is a molecular...
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5167486 |
Turbo-machine stage having reduced secondary losses
A turbine stage comprising a set of fixed vanes (1) fixed to the stator (3) of the turbine and supporting a diaphragm, followed by a set of moving vanes (8) mounted on a disk (9) which is fixed to...
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5165847 |
Tapered enlargement metering inlet channel for a shroud cooling assembly of gas turbine engines
To cool the shroud in the high pressure turbine section of a gas turbine engine, high pressure cooling air is directed in metered flow through channels, which include tapered enlargement...
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5160241 |
Multi-port air channeling assembly
An air channeling assembly includes an outer casing having a series of spaced apart air ports spaced radially outwardly from an inner casing to define a plenum therebetween. A series of baffles are...
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5154578 |
Compressor casing for a gas turbine engine
The present invention relates to a compressor casing for a gas turbine engine in which an inner casing is radially adjustable so as to maintain a radial clearance between the casing and a rotor as...
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5152666 |
Stator assembly for a rotary machine
A stator assembly 46 for an axial flow rotary machine 10 is disclosed. Various construction details which increase the efficiency of the machine are developed. In one embodiment, the machine...
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5149247 |
Single HP-MP internal stator for a steam turbine with controlled steam conditioning
The HP-MP steam turbine body has a single internal stator surrounding both the HP and the MP portions of the rotor. The internal stator co-operates with the external stator to define axial...
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5145315 |
Gas turbine vane cooling air insert
A gas turbine stationary vane is provided having cooling air inserts and an inpingement plate attached to the outer shroud of the vane. The inserts extend only a short distance above their mounting...
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5134844 |
Aft entry cooling system and method for an aircraft engine
An aft entry system in a gas turbine engine is provided for cooling selected one or more of aft high and low pressure turbine stages of the engine. The aft entry system includes an air flow circuit...
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5135354 |
Gas turbine blade and disk
Each of a pair of axially spaced turbine disks (12,14) has a plurality of blade retention fingers (20) at the periphery. Each blade has a pair of chevrons (64,66), one engaging a contiguous chevron...
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5129795 |
Motor driven pump
A motor driven pump of the canned or isolated stator type wherein pressure regulation of fluid control for motor cooling and magnetic thrust balancing of the motor rotor are independent of each other.
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5125794 |
Impulse turbine stage with reduced secondary losses
An impulse turbine stage comprising a set (1) of fixed vanes (2) fixed to the stator (3) of the turbine and supporting a diaphragm (4), followed by a set (7) of moving vanes (8) mounted on a disc...
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