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| Number | Title | Issue Date |
| 8132417 | Cooling of a gas turbine engine downstream of combustion chamber A gas turbine system includes a combustion chamber (2), a turbine (3), a radially inward and/or radially outward axial gap (4; 16, 17) between the combustion chamber (2) and the turbine (3), at which gap inner and/or outer combusti... | 03/13/2012 |
| 8104292 | Duplex turbine shroud A gas turbine engine shroud includes a row of different first and second shroud segments alternating circumferentially therearound. The first segments have a first pattern of first cooling holes extending therethrough. The second segments have a second pattern of se... | 01/31/2012 |
| 8087253 | Methods, apparatus and systems concerning the circumferential clocking of turbine airfoils in relation to combustor cans and the flow of cooling air through the turbine hot gas flowpath A method of operating a turbine engine, wherein the turbine engine includes a compressor, a combustor, a turbine, a plurality of successive axially stacked stages that include a row of circumferentially spaced stator blades and circumferentially spaced rotor blades,... | 01/03/2012 |
| 8061146 | Heat transfer augmentation in a compact heat exchanger pedestal array A compact heat exchanger pedestal array for augmenting heat transfer in a machine is disclosed. The compact heat exchanger pedestal array includes a wall having first and second surfaces. The first surface faces a heated flow path and the second surface partially fo... | 11/22/2011 |
| 8033119 | Gas turbine transition duct A transition member between a combustion section and a turbine section in a gas turbine engine. The transition member includes a casing inner wall and a plurality of spanning members. The spanning members extend radially outwardly from a radially outer surface of th... | 10/11/2011 |
| 7937951 | System for cooling the impeller of a centrifugal compressor A system for cooling the impeller of a centrifugal compressor in a turbomachine is disclosed. The compressor supplies an annular diffuser. The diffuser includes an end-piece that extends downstream and along the impeller of the compressor and is covered on the upstr... | 05/10/2011 |
| 7926292 | Partial oxidation gas turbine cooling A power generation system and method in which a fuel gas is introduced into a combustor and at least a portion of the fuel gas is combusted in the combustor, producing an exhaust gas having no appreciable available oxygen. The exhaust gas is introduced as a working ... | 04/19/2011 |
| 7921654 | Cooled turbine stator vane A first stage turbine stator vane used in an industrial gas turbine engine, the vane having an outer endwall and an inner endwall with the airfoil extending between the two endwalls. A showerhead arrangement of film cooling holes is located along the leading edge re... | 04/12/2011 |
| 7861536 | Ejector controlled twin air source gas turbine pressurizing air system A passive pressurizing air system for a gas turbine engine includes a flow path for directing an air flow having a low temperature and low pressure, extending through a cavity to a pressurized area of the engine. The cavity contains pressurized air having a high tem... | 01/04/2011 |
| 7836703 | Reciprocal cooled turbine nozzle A turbine nozzle includes first and second vanes joined to outer and inner bands. The vanes include outboard sides defining outboard flow passages containing axial splitlines, and opposite inboard sides defining an inboard flow passage without axial splitline. The t... | 11/23/2010 |
| 7775053 | Heat transfer augmentation in a compact heat exchanger pedestal array A compact heat exchanger pedestal array for augmenting heat transfer in a machine is disclosed. The compact heat exchanger pedestal array includes a wall having first and second surfaces. The first surface faces a heated flow path and the second surface partially fo... | 08/17/2010 |
| 7712317 | Flow control systems A flow control system comprises includes a fluidic control device having a main fluid path for a flow of fluid through the device, and a control fluid path for a control flow of fluid through the device. At least part of the control fluid path coincides with at leas... | 05/11/2010 |
| 7712316 | Turbine blade with reverse cooling air film hole direction A gas turbine engine includes turbine blades having film cooling holes at an outer face of an airfoil wherein the film cooling holes are designed to be better filled with air. In a disclosed embodiment, the film cooling holes include a meter section extending along ... | 05/11/2010 |
| 7677048 | Turbine last stage blade with forced vortex driven cooling air A gas turbine engine with a turbine section having at least a first stage turbine blade and a last stage turbine blade. The first stage turbine blade includes cooling fluid passages therein in which a compressed cooling fluid, usually from the compressor section of ... | 03/16/2010 |
| 7669425 | Closed loop turbine cooling fluid reuse system for a turbine engine A cooling fluid reuse system for a turbine engine for capturing spent cooling fluids from row one turbine vanes and directing those fluids into a mixing chamber to be mixed with liner cooling fluids and used in a combustor. The cooling fluid reuse system may be form... | 03/02/2010 |
| 7665310 | Gas turbine engine having a cooling-air nacelle-cowl duct integral with a nacelle cowl A gas turbine engine includes an engine core extending along a core axis, a cooling-air delivery duct on the engine core, and a removable nacelle cowl overlying the engine core. A cooling-air nacelle-cowl duct delivers cooling air to the cooling-air delivery duct. A... | 02/23/2010 |
| 7434402 | System for actively controlling compressor clearances Aspects of the invention relate to a system and method for actively controlling compressor clearances in a turbine engine by passing a thermal fluid in heat exchanging relation through a compressor vane carrier. During some operational conditions, such as hot restar... | 10/14/2008 |
| 7424360 | Overspeed control system for gas turbine electric powerplant A turbine overspeed control system for use with a gas turbine engine of a gas turbine electrical powerplant. The overspeed control system preferably comprises a first and second overspeed control subsystem. When an overspeed condition of the gas turbine engine is de... | 09/09/2008 |
| 7413399 | Method and apparatus for distributing fluid into a turbomachine An apparatus for distributing a fluid in a gas flow path inside a turbomachine, comprising: a device for introducing the fluid into the gas flow path; and wherein the device is positioned within the gas flow path. A method for installing an apparatus that will distr... | 08/19/2008 |
| 7412834 | Annular combustion chamber for a turbomachine with an improved inner fastening flange An annular combustion chamber for a turbomachine comprises inner and outer annular walls united by a transverse wall, the inner and outer walls are extended at their downstream ends by inner and outer fastener flanges for fastening respectively to inner and outer sh... | 08/19/2008 |
| 7383686 | Secondary flow, high pressure turbine module cooling air system for recuperated gas turbine engines A secondary flow, turbine cooling air system for the uniform cooling of high pressure turbine module components such as the turbine shroud, turbine blade tips, turbine nozzle, transion liner, and turbine bearing support housing in a recuperated gas turbine engine is... | 06/10/2008 |
| 7360987 | Stator of a high-pressure turbine of a turbomachine, and a method of assembling it A method of assembling sectored elements of an annular stator of a high-pressure turbine of a turbomachine about a longitudinal axis of said turbine, in which method an angular distribution pattern is defined for distributing elements of the stator over a predetermi... | 04/22/2008 |
| 7340880 | Compressed air bypass valve and gas turbine It is the objective of the present invention to enable smooth rotation of the grid plate and normal operation of the bypass valve, regardless of the operational state of the gas turbine. The bypass valve according to the present invention is provided with a frame, w... | 03/11/2008 |
| 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 |
| 7329086 | Rotor shaft, in particular for a gas turbine A rotor shaft, particularly for a gas turbine, includes a cooling air supply disposed inside the rotor shaft and a plurality of cooling air ducts connected to the cooling air supply and extending essentially radially outward toward an outside of the shaft, wherein e... | 02/12/2008 |
| 7287384 | Bearing chamber pressurization system A method and device for improved pressure balancing in a bearing chamber pressurization system for gas turbine engines employ a partition member to substantially separate first and second air-oil seals of the bearing housing. ... | 10/30/2007 |
| 7287955 | Gas turbine clearance control devices A clearance control device for controlling clearance between rotary blade tips and a stationary bushing of a gas turbine having a casing that is provided with at least two annular ridges, the clearance control device including a circular tuning unit that includes ai... | 10/30/2007 |
| 7269955 | Methods and apparatus for maintaining rotor assembly tip clearances A method of operating a gas turbine engine is provided. The gas turbine engine includes at least one engine casing and at least one rotor assembly. The method includes directing airflow through a supply pipe and into a heat exchanger, lowering the temperature of the... | 09/18/2007 |
| 7263834 | Method for cooling a gas turbine system and a gas turbine system for performing this method A gas turbine system comprises a compressor that takes in suction air on the inlet side and compresses it to compressor end air that is available on the outlet side, a combustor in which a fuel is burned by using the compressor end air while resulting in the formati... | 09/04/2007 |
| 7237386 | Process for controlling the cooling air mass flow of a gas turbine set A process is provided for the control of the amount of cooling air of a gas turbine set. Suitable means are provided in the cooling system to enable the amount of cooling air to be varied. The control of this means takes place in dependence on an operating parameter... | 07/03/2007 |
| 7234304 | Aerodynamic trip to improve acoustic transmission loss and reduce noise level for gas turbine engine 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 combustor; and a turbine, that generate a flow of hot gas from the combustor ... | 06/26/2007 |
| 7231769 | Gas turbine cooling system A cooling system for a gas turbine engine includes a fuel deoxygenator for increasing the cooling capacity of the fuel. The fuel deoxygenator removes dissolved gases from the fuel to prevent the formation of insoluble deposits. The prevention of insoluble deposits i... | 06/19/2007 |
| 7229248 | Blade structure in a gas turbine In the blade structure in a gas turbine, front-edge including angles are made large. As a result, a curve of a relative relationship between incidence angles ic1 and is1 and pressure loss becomes mild. Entrance metal angles are made small. As a result,... | 06/12/2007 |
| 7225624 | Method and apparatus for increasing the pressure of cooling fluid within a gas turbine engine A system located with the housing of a gas turbine engine for increasing the pressure of working fluid from the compressor that will be utilized to cool a component. In one form the system includes a pump rotatable with a turbine component to increase the pressure o... | 06/05/2007 |
| 7213391 | Cooling systems Apparatus for maintaining the temperature of a component of a gas turbine engine below a predetermined maximum working temperature comprises a reservoir for a cooling fluid having a boiling point below the working temperature and in which the component is immersed o... | 05/08/2007 |
| 7195456 | Turbine engine guide vane and arrays thereof An exit guide vane array for a turbine engine includes a set of guide vanes 28 having a solidity and defining fluid flow passages 74 with a chordwisely converging forward portion 80. The high solidity and convergent passage portion 80 res... | 03/27/2007 |
| 7178341 | Multi-zone tubing assembly for a transition piece of a gas turbine A replaceable section (25) of force-cooling tubing assembly (21, 22) for attachment to a transition piece (5) of a gas turbine is comprised of two ends (54, 70) fashioned for attachment by removable unions (52) to adjoining parts o... | 02/20/2007 |
| 7162876 | Ejector for cooling air supply pressure optimization A system for optimizing cooling air supply pressure includes a high pressure fluid source which receives bleed air from the exit of a high pressure compressor and a nozzle and ejector assembly for supplying fluid to a point of use at a pressure sufficient to maintai... | 01/16/2007 |
| 7154931 | Laser with Brayton cycle outlet pump A chemical oxygen-iodine laser (COIL) comprises an oxygen generator and a nozzle for accelerating generated oxygen to a high or supersonic velocity. A laser cavity is coupled to the nozzle, wherein the accelerated fluid, with injected iodine, is employed as a laser ... | 12/26/2006 |
| 7143573 | Gas turbine set A gas turbine set, with a cooling air system through which at least one cooling air mass flow flows from a compressor to thermally highly loaded components of the gas turbine set. Pressure increasing ejectors are arranged in a cooling air duct of the cooling air sys... | 12/05/2006 |
