Quotables
"It is my heart-warmed and world-embracing Christmas hope and aspiration that all of us, the high, the low, the rich, the poor, the admired, the despised, the loved, the hated, the civilized, the savage (every man and brother of us all throughout the whole earth), may eventually be gathered together in a heaven of everlasting rest and peace and bliss, except the inventor of the telephone. "
Mark Twain ; Christmas greetings, 1890
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| Number | Title | Issue Date |
| 8186945 | System and method for clearance control A system, in one embodiment, includes a turbine clearance controller. The turbine clearance controller is configured to independently adjust clearances of a plurality of shroud segments about a plurality of blades via first and second magnets opposite from one anoth... | 05/29/2012 |
| 8011883 | Gas turbine engine blade tip clearance apparatus and method A method for controlling blade tip clearance within a gas turbine engine includes a compressor having at least one first rotor assembly, wherein the blade tips in each of at least one first rotor assembly has a mating geometry with at least one of at least one blade... | 09/06/2011 |
| 7819626 | Plasma blade tip clearance control A gas turbine engine plasma blade tip clearance control system includes an annular shroud surrounding rotatable blade tips and an annular plasma generator spaced radially outwardly and apart from the blade tips. An exemplary embodiment of the annular plasma generato... | 10/26/2010 |
| 7766611 | Method for setting a radial gap of an axial-throughflow turbomachine and compressor The invention relates a method for improving the hot-starting behavior of a turbomachine. By virtue of the setting of a radial gap formed between a brushing edge of a blade profile and a guide face lying opposite this, in which setting a guide ring forming the guide... | 08/03/2010 |
| 7597537 | Thermal control of gas turbine engine rings for active clearance control A gas turbine engine thermal control apparatus includes at least one annular spray tube having spray holes oriented to impinge thermal control air onto a fillet between an outer casing and a forward thermal control ring and, in a more particular embodiment, into a c... | 10/06/2009 |
| 7422413 | Shroud tip clearance control ring The present invention is a shroud tip clearance control ring for use in a gas turbine engine in which a rotary blade and a shroud ring form a gap that forms a blade outer air seal, and where the shroud ring is formed of two shroud segment halves, each shroud segment... | 09/09/2008 |
| 7407369 | Gas turbine engine blade tip clearance apparatus and method A zero running clearance system for gas turbine engines includes a gas turbine engine compressor having one or more first rotor assemblies and one or more first stator assemblies disposed adjacent the one or more first rotor assemblies; a gas turbine engine turbine ... | 08/05/2008 |
| 7368827 | Electrical assembly for monitoring conditions in a combustion turbine operating environment An electrical assembly for use in various operating environments such as a casing of a combustion turbine 10 is provided. The assembly may include an electrical energy-harvesting device 51 disposed in a component within the casing of the turbine to con... | 05/06/2008 |
| 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 |
| 7341426 | Gas turbine engine blade tip clearance apparatus and method A gas turbine engine is provided that includes one or more rotor assemblies, one or more shroud segments, and an actuator. The rotor assemblies are rotatable around an axially extending rotational axis, and each rotor assembly has a plurality of blades. Each blade h... | 03/11/2008 |
| 7309209 | Device for tuning clearance in a gas turbine, while balancing air flows A device for tuning clearance at rotor blade tips in a gas turbine rotor, the device comprising at least one annular air flow duct that is mounted around the circumference of an annular casing of a stator of the turbine, the annular air flow duct being designed to d... | 12/18/2007 |
| 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 |
| 7289264 | Passive broad long wave and mid-wave infrared optical limiting prism Method for limiting the amount of radiation impinging on a radiation sensitive detector (RSD) responsive to signals having infrared wavelengths of approximately 3 to 14 microns. Method includes: directing radiation signal through prism toward RSD; permitting radiati... | 10/30/2007 |
| 7246994 | Spacing arrangement A spacing arrangement for a gas turbine engine 10. The spacing arrangement being arranged such that as a rotor blade 26 of a compressor 13 rotates, the rotor disc 28 will move outwards and forwards to maintain a substantially constant gap... | 07/24/2007 |
| 7220097 | Gas turbine apparatus with actuators to counteract deformations of housing A gas turbine apparatus includes a compressor and/or a turbine, having rotor blades mounted on a rotor that is rotatable relative to a stationary housing, with a clearance gap between the rotor blades and the housing. During operation, external forces tend to deform... | 05/22/2007 |
| 7201556 | Displacement casing A rotor system is provided whereby a rotary assembly such as a fan blade combination in a jet engine is brought into rub contact with a casing such that sensors detect vibration. The casing is then retreated in order to open the gap to a desired value for engine per... | 04/10/2007 |
| 7189057 | Turbine shroud segment attachment A turbine shroud segment attachment with a casing (1) and several shroud segments (2) arranged in the casing (1), wherein the individual shroud segments (2) are located in the casing (1) with a circumferential clearance (3) ... | 03/13/2007 |
| 7185498 | Modular gas turbine Method and arrangement for providing a gas turbine (1) having a duct (11) for carrying gas from a gas turbine inlet (9) to a gas turbine outlet (10) and an outer housing (19, 20, 21) arranged radially outside a wall structure (1... | 03/06/2007 |
| 7165937 | Methods and apparatus for maintaining rotor assembly tip clearances A method enables a gas turbine engine to be assembled. The method comprises coupling a rotor assembly including a plurality of circumferentially-spaced rotor blades downstream from, and in flow communication with, a compressor, coupling a casing assembly circumferen... | 01/23/2007 |
| 7147429 | Turbine assembly and turbine shroud therefor A turbine assembly includes a shroud for being mounted around a last stage of the low pressure turbine rotor. The shroud includes an arcuate body having spaced-apart forward and aft ends and spaced-apart circumferential ends. Attachments are provided for securing th... | 12/12/2006 |
| 7140261 | Acoustic wave flow sensor An acoustic wave flow sensor is disclosed, which includes a sensor substrate and an acoustic wave diaphragm etched upon the sensor substrate, wherein mechanical stress or strain is concentrated in the acoustic wave diaphragm. One or more interdigital transducers can... | 11/28/2006 |
| 7125223 | Method and apparatus for turbomachine active clearance control An apparatus for providing active clearance control between blade tips and seals in a turbomachine comprising: a first stator carrier segment, with stator seals centripetally disposed on it; a second stator carrier segment located along a same circumference as the f... | 10/24/2006 |
| 7114920 | Shroud and vane segments having edge notches Random air flow leakage between a shroud assembly and a stator vane assembly into the gas path of a gas turbine engine due to manufacturing tolerance stack-up is reduced by providing notches to inhibit interference caused by misalignment and/or mismatch of adjacent ... | 10/03/2006 |
| 7114914 | Device for controlling clearance in a gas turbine A device for controlling the clearance between the tips of rotary blades and a stationary ring assembly of a gas turbine, the device comprising a circular control box having at least two annular air circulation strips that are spaced apart from each other in the axi... | 10/03/2006 |
| 7094029 | Methods and apparatus for controlling gas turbine engine rotor tip clearances A method enables a gas turbine engine compressor including a stator assembly and a rotor assembly to be assembled. The method comprises providing a casing formed from a plurality of rings, and coupling a first of the casing rings around the rotor assembly such that ... | 08/22/2006 |
| 7079957 | Method and system for active tip clearance control in turbines A system for controlling blade tip clearance in a turbine. The system includes a stator including a shroud having a plurality of shroud segments and a rotor including a blade rotatable within the shroud. An actuator assembly is positioned radially around the shroud ... | 07/18/2006 |
| 6935836 | Compressor casing with passive tip clearance control and endwall ovalization control A passive clearance control system for a gas turbine engine component. The system provides a blade shroud that is isolated from the component case and can move radially to maintain blade clearance. A plurality of vane sectors define a stator ring including a blade s... | 08/30/2005 |
| 6918743 | Sheet metal turbine or compressor static shroud A static shroud for ducting an axial gas flow past an array of blades rotating about an axis, made of a sheet of metal bent to form a contiguous shroud body having a substantially uniform sheet thickness and a uniform axial profile, initiating with an upstream flang... | 07/19/2005 |
| 6846156 | Gas turbine In a gas turbine, blade ring cooling passages are provided inside a first blade ring and a second blade ring. The blade ring cooling passages are connected with each other through a communication pipe that is arranged in an axial direction of the blade ring. From ou... | 01/25/2005 |
| 6821084 | Torque tube bearing assembly A bearing assembly for use in a gas turbine engine to rotatably mount a torque tube in an access hole extending through a fan duct. The torque tube connects a variable stator vane bell crank positioned inside the fan duct to an actuator positioned outside the fan du... | 11/23/2004 |
| 6692222 | Micro gas turbine engine with active tip clearance control In a micro gas turbine engine, a capacitive sensor is used for measuring a tip clearance of a radial compressor section thereof, and an actuator is used for axially displacing a rotor shaft in response to an output from the capacitive sensor. Because the ... | 02/17/2004 |
| 6682298 | Rotating shaft confinement system In a double-ended Francis turbine, shaft whip at critical speed is alleviated by pitching tappets in the housing, around the rotor. The tappets are adjusted to lie closer to the rotor than the (labyrinth) seal grooves. The tappets are of polythene, and ar... | 01/27/2004 |
| 6676372 | Gas turbine with axially mutually displaceable guide parts A gas turbine with axially mutually displaceable guide parts that compensates for differing amounts of thermal expansion, comprising guide parts which can be displaced with respect to one another in the axial direction and enclose a funnel-like gas duct f... | 01/13/2004 |
| 6672831 | Device for setting the gap dimension for a turbomachine A device for setting the gap dimension for a turbomachine, in particular a gas turbine, with heat accumulation segments which are arranged on the guide-vane carrier of the rotor arrangement. At least one drive device projects radially through the turbine ... | 01/06/2004 |
| 6659716 | Gas turbine having thermally insulating rings A gas turbine capable of minimizing the clearance between each of the rotor blades and partition ring, uses a structure in which the upstream thermally insulating ring is installed on the downstream blade ring.... | 12/09/2003 |
| 6626635 | System for controlling clearance between blade tips and a surrounding casing in rotating machinery The clearance control system includes a closed air circuit having a heat exchanger, a circulation compressor and an air heater in series for flowing air heated or cooled to higher and lower system-set discharge temperatures in the casing of rotating machi... | 09/30/2003 |
| 6607350 | Gas turbine engine system Tip clearance apparatus for a gas turbine engine comprises a shroud ring having curved portions so as to allow eccentric offset and hence asymmetric movement of the shroud. The shroud ring is mounted within a guide also having corresponding curved portion... | 08/19/2003 |
| 6602048 | Gas turbine split ring In the gas turbine split ring, on an outer peripheral surface 1b between two cabin attachment flanges, a circumferential rib which extends in the circumferential direction and an axial rib which extends in the axial direction and has a height taller than ... | 08/05/2003 |
| 6508623 | Gas turbine segmental ring A gas turbine segmental ring has an increased rigidity to suppress a thermal deformation and enables less cooling air leakage by less number of connecting portions of segment structures. Cooling air (70) from a compressor flows through cooling holes (61) ... | 01/21/2003 |
| 6505834 | Pressure actuated brush seal An embodiment providing a seal assembly for turbomachinery for controlling flow of a fluid medium in a fluid path comprises a casing having an internal pressure load path and a seal carrier chamber. A movable seal carrier is disposed within the seal carri... | 01/14/2003 |
