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| Number | Title | Issue Date |
| 7871240 | Helical spring damper A damped spring assembly includes a helical spring. The helical spring is movable along an axis and has a winding direction. A damper is movable along the axis and includes a helical shape. The damper is wound in a direction opposite the winding direction. The dampe... | 01/18/2011 |
| 7648335 | Method and an injection nozzle for interspersing a gas flow with liquid droplets In the method for interspersing a gas flow with liquid droplets, the liquid droplets are injected in a liquid injection plane into the gas flow, characterized in that an auxiliary gas is simultaneously injected with the liquid droplets into the gas flow. The injecti... | 01/19/2010 |
| 7428906 | Method for cleaning a stationary gas turbine unit during operation A method for cleaning a stationary gas turbine unit during operation, wherein the unit comprises a turbine, a compressor driven by the turbine, the compressor having an inlet, an air inlet duct arranged upstream of the air inlet of the compressor, the inlet duct hav... | 09/30/2008 |
| 7334412 | Cooling air and injected liquid system for gas turbine blades The invention relates to a turbine 1, in particular a gas turbine, which along a swivel-mounted rotationally symmetrical rotor 2 has a compressor 3, a combustion chamber 5 and a turbine section 7 formed of a plurality of turbine st... | 02/26/2008 |
| 7322793 | Turbine motor of a rotary atomizer A turbine, e.g., with a blade arrangement, which receives an air flow in the radial direction and which is located on a carrier surface of the turbine wheel, is used as a drive motor for a rotary atomizer. The drive channel, which contains the turbine blades and whi... | 01/29/2008 |
| 7291946 | Damper for stator assembly A damper for a stator assembly, the stator assembly comprising a stator segment and a seal mounted to the stator segment. The damper locates between the stator segment and the seal, and comprises: a medial section; and opposed arms extending from the medial section.... | 11/06/2007 |
| 7246993 | Coolable segment for a turbomachine and combustion turbine A coolable segment for a turbomachine such as a combustion turbine, which turbomachine is operated with a hot fluid. The segment comprises a cooling wall extending in an axial direction and in a circumferential direction orthogonal to the axial direction; a hot flui... | 07/24/2007 |
| 7240682 | Washing fluid pump The invention concerns a washing fluid pump (1) for windows and/or headlamp cleaning installations on motor vehicles including at least one motor, at least one pump housing (2) with at least one impeller (11) arranged therein, at least one intak... | 07/10/2007 |
| 7114910 | Method and injection nozzle for interspersing a gas flow with liquid droplets In the method for interspersing a gas flow (8) with fluid droplets (5), the fluid droplets (5) are injected in a fluid injection plane into the gas flow (8), characterised in that an auxiliary gas (6.1, 6.2) is simultaneously injec... | 10/03/2006 |
| 7104750 | Fogging device for gas turbines A fogging device (26) for introducing water and/or vapor into an intake air flow (10, 27) of a gas turbine (1–3) includes a sound-absorbing device (31, 35). This device may in particular be designed in the form of Venturi tubes (31 | 09/12/2006 |
| 7104749 | Intake silencer for gas turbines A silencer (25a) for the attenuation of noise occurring in an intake airstream (10, 27) of a gas turbine (1–3) includes a device or devices (31, 32, 33, 34) for the introduction of water and/or steam into the intake airstream ( | 09/12/2006 |
| 7104751 | Hot gas path assembly A hot gas path assembly, suitable for use in the hot gas path of a gas turbine, has as a hot gas duct wall an impact-cooled gas-impermeable element and a transpiration-cooled gas permeable element. The gas-permeable element is a run-on covering for the sealing tip, ... | 09/12/2006 |
| 7094020 | Swirl-enhanced aerodynamic fastener shield for turbomachine A fastener shield for use in a fluid flow path within a gas turbine engine for reducing fluid drag and heating generated by fluid flow over a plurality of circumferentially spaced bolts. The fastener shield has a radially-extending, downstream-facing mounting flange... | 08/22/2006 |
| 7077623 | Fluid flow machine with integrated fluid circulation system A fluid-flow machine includes at least one rotor and a free number of stators flown by a fluid, with at least one blade thereof positioned on throat-confining surfaces provided with both a device for fluid removal from the flow path and a device for fluid supply int... | 07/18/2006 |
| 7043905 | Gas energy conversion apparatus and method An apparatus having a pressure control system that balances the natural gas flow rate passing through a multi-stage, axial-flow, impulse turbogenerator to produce an electrical power output is provided. The pressure control system includes a primary bypass conduit c... | 05/16/2006 |
| 7029232 | Abradable seals A sealing element for a turbine of a gas turbine engine includes a radially inner surface region provided with an integrally formed seal structure comprising a plurality of radially inwardly projecting walls. The walls may be abradable and may define cells for recei... | 04/18/2006 |
| 6916151 | Ventilation device for a high pressure turbine rotor of a turbomachine A ventilation device for a high pressure turbine rotor in a turbomachine, the turbine comprising upstream and downstream turbine disks fitted with blades, the device comprising a cooling circuit being supplied by a cooling airflow D taken from the back of the combus... | 07/12/2005 |
| 6907727 | Gas energy conversion apparatus and method An apparatus having a pressure control system that balances the natural gas flow rate passing through a multi-stage, axial-flow, impulse turbogenerator to produce an electrical power output is provided. The pressure control system includes a primary bypass conduit c... | 06/21/2005 |
| 6884023 | Integral swirl knife edge injection assembly The present invention relates to a system for delivering cooling air to a seal arrangement in a turbine stage of a gas turbine engine. The system comprises at least one vane having a passageway extending from an outer platform of the at least one vane to an inner pl... | 04/26/2005 |
| 6659715 | Axial compressor and method of cleaning an axial compressor An axial compressor includes a nozzle for injecting a cleaning fluid. The cleaning fluid is injected through the nozzles in a flow duct during operation, so that rear blading rows are also cleaned.... | 12/09/2003 |
| 6487491 | System and method of controlling clearance between turbine engine blades and case based on engine components thermal growth model A system and method of controlling clearance in a turbomachine includes adjusting the machine case cooling air in response to the difference between the desired clearance and the actual clearance. An accurate estimate of the actual clearance is made with ... | 11/26/2002 |
| 6398518 | Method and apparatus for increasing the efficiency of a multi-stage compressor A multi-stage compressor, including a system for the injection of a cooling liquid into at least a portion of the compressor stages to increase the efficiency of the multi-stage compressor by reducing the temperature of the compressed gas produced in the ... | 06/04/2002 |
| 6394108 | Inside out gas turbine cleaning method The inside out gas turbine cleaning method is a new method to clean axial gas turbine compressors. This is done by inserting a specially and fabricated flexible hose with nozzles on it into the first several stages of an off line gas turbine compressor. H... | 05/28/2002 |
| 6394749 | Apparatus and methods for relieving thermally induced stresses in inner and outer bands of thermally cooled turbine nozzle stages To control the temperature mismatch between the inner and outer bands and covers forming plenums with the inner and outer bands on sides thereof remote from the hot gas path, passages extend from the leading edge of the covers in communication with the ho... | 05/28/2002 |
| 6382903 | Rotor bore and turbine rotor wheel/spacer heat exchange flow circuit In a turbine having closed-circuit steam-cooling passages about the rim of the rotor during steady-state operation, compressor discharge air is supplied to the rotor bore for passage radially outwardly into the wheel space cavities between the wheels and ... | 05/07/2002 |
| 6352404 | Thermal control passages for horizontal split-line flanges of gas turbine engine casings A casing for a gas turbine engine having a longitudinal axis extending therethrough, including a first casing portion having a substantially arcuate section and a split-line flange extending from each end thereof and a second casing portion having a subst... | 03/05/2002 |
| 6324847 | Dual flow turbine housing for a turbocharger in a divided manifold exhaust system having E.G.R. flow An internal combustion engine, particularly suitable for a vehicle, is provided with a plurality of combustion cylinders, a first exhaust manifold, a second exhaust manifold and an intake manifold. Each exhaust manifold is coupled with a plurality of the ... | 12/04/2001 |
| 6234746 | Apparatus and methods for cooling rotary components in a turbine A cooling system for turbomachinery includes a compressor bleed air passageway for supplying bleed cooling air to a plurality of circumferentially spaced, generally axially extending passages in communication with a cavity within the inner barrel in which... | 05/22/2001 |
| 6233937 | Cooling spray application to a turbine and exhaust region of a steam turbine A dual-fluid cooling spray device for use with a steam turbine. The steam turbine includes a casing, a plurality of rotating blades and a plurality of stationary vanes. The dual fluid spray device includes a nozzle adjacent to one row of rotating blades a... | 05/22/2001 |
| 6231303 | Gas turbine having a turbine stage with cooling-air distribution A gas turbine includes a first turbine stage having a first guide blade, a first moving blade and a cooling configuration. The cooling configuration has a first cooling-air feed at the first guide blade for cooling the first guide blade, a first cooling-a... | 05/15/2001 |
| 6227801 | Turbine engine having improved high pressure turbine cooling A turbine engine having improved high pressure turbine cooling is disclosed. In the engine, relatively cool intermediate pressure (P2x) air is diverted from a region of a compressor section and over a high work turbine blade at a lower static pressure tha... | 05/08/2001 |
| 6217280 | Turbine inter-disk cavity cooling air compressor A combustion turbine may have a cooling circuit for directing a cooling medium through the combustion turbine to cool various components of the combustion turbine. This cooling circuit may include a compressor, a combustor shell and a component of the com... | 04/17/2001 |
| 6164911 | Low aspect ratio compressor casing treatment A compressor for a gas turbine engine, comprising a casing having an inner surface defining a plurality of circumferentially spaced-apart grooves adjacent the tips of a row of rotor blades. Each groove as a depth which is less than half the width thereof ... | 12/26/2000 |
| 6155778 | Recessed turbine shroud A turbine shroud includes a panel having inner and outer surfaces extending between forward and aft opposite ends. The panel includes forward and aft hooks for supporting the panel radially atop a row of turbine rotor blades. The panel includes a pluralit... | 12/05/2000 |
| 6146090 | Cooling/heating augmentation during turbine startup/shutdown using a seal positioned by thermal response of turbine parts and consequent relative movement thereof In a turbine rotor, a thermal mismatch between various component parts of the rotor occurs particularly during transient operations such as shutdown and startup. A thermal medium flows past and heats or cools one part of the turbine which may have a delet... | 11/14/2000 |
| 6142731 | Low thermal expansion seal ring support Today, the trend is to increase the temperature of operation of gas turbine engines. To cool the components with compressor discharge air, robs air which could otherwise be used for combustion and creates a less efficient gas turbine engine. The present l... | 11/07/2000 |
| 6126389 | Impingement cooling for the shroud of a gas turbine An inner shroud 22 is coupled to an outer shroud 20 which receives cooling air through an inlet 54 for flow to the inner shroud. The inner shroud includes a wall 42 which defines in part the hot gas path 16 and a plurality of cavities 44 on an opposite si... | 10/03/2000 |
| 6077034 | Blade cooling air supplying system of gas turbine In the present disclosure, an air pipe extends through a stationary blade between outer and inner shrouds. Further, an air passage is directed to a lower portion of the stationary blade and is communicated with the air pipe so that a serpentine cooling pa... | 06/20/2000 |
| 6074554 | Aeration system A system for dissolved air floatation treatment of a liquid stream where the system includes a pump having an impeller cavity with input and output ports, and an impeller with an eye disposed adjacent the input port. The impeller draws liquid through the ... | 06/13/2000 |
| 6065282 | System for cooling blades in a gas turbine A gas turbine comprises: a first closed circuit in which cooling gas is supplied to a casing, allowed to pass through stationary blades, and removed to the outside of casing after cooling the stationary blades; a second closed circuit in which cooling air... | 05/23/2000 |
