| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 415173200 | Selectively adjustable | 13 |
| 20080310953 | Carbon hydrostatic face seal - A force balanced seal for use with a rotor in the turbomachine has a member in opposed facing disposition to the rotor with a face dam portion of the member having a surface parallel with the sealing surface of the rotor, a groove in the member facing the rotor and bounding the face dam surface, an air bearing surface in the member facing the sealing surface of the rotor, a second passageway through the member from the air bearing surface to a radially outwardly facing surface of the member and a first passageway through the member from the groove to a member surface facing oppositely from the air bearing surface. An operating clearance between the seal and rotor is maintained by a closing force, exerted through a plurality of springs, and an opposing opening force created by pressurized air venting through the second passageway to the first passageway. | 12-18-2008 |
| 20100232942 | ARRANGEMENT FOR OPTIMISING THE RUNNING CLEARANCE FOR TURBOMACHINES - An arrangement for optimizing the running clearance for turbomachines of the axial type, such as turbocompressors, gas turbines, and steam turbines, in particular for compressors of stationary gas turbines, by controlling the inner diameter, which is relevant to the running clearance, of at least one stator structure that surrounds a rotor blade ring, including: the stator structure has a closed, circular inner ring, a circular outer ring that is situated concentric to the inner ring at a radial distance therefrom, and a plurality of links that integrally connect the inner ring to the outer ring, the links being circumferentially inclined at a defined angle (α) to the radial direction and distributed around the circumference of the stator structure, and the arrangement includes an adjustment device for rotating the inner ring relative to the outer ring with elastic modification of the running clearance-relevant inner diameter (D) of the inner ring. | 09-16-2010 |
| 20100303615 | HYDRAULIC MACHINE, AN ENERGY CONVERSION INSTALLATION INCLUDING SUCH A MACHINE, AND A METHOD OF ADJUSTING SUCH A MACHINE - This hydraulic machine has a wheel ( | 12-02-2010 |
| 20110070072 | ROTARY MACHINE TIP CLEARANCE CONTROL MECHANISM - A tip clearance control mechanism for a rotary machine adapted for reducing leakage flows, and minimizing tip vortex size and penetration into main flow that will improve turbine efficiency. The tip clearance control mechanism includes inventive arrangements of a rotating shroud and a shape of the shroud, teeth of various shapes and locations on the rotating shroud, and one or more stator teeth of various shapes and locations on a stationary shroud or casing wall configurations providing comparable tip clearance control. The reduction in leakage flow is a function of how these components are assembled together, which defines a clearance passage between the rotating shroud and the stationary shroud. | 03-24-2011 |
| 20110103939 | TURBINE ROTOR BLADE TIP AND SHROUD CLEARANCE CONTROL - A gas turbine engine includes a turbine shell that is configured to retain a turbine rotor shroud adjacent to a turbine rotor blade. A heat pipe has a first end in thermal communication with the turbine shell and a second end extending outwardly of the shell. A heating/cooling system is in thermal communication with the second end of the heat pipe and has a thermal medium configurable to exchange thermal energy with the second end of the heat pipe. The thermal medium is configurable to remove thermal energy from the second end of the heat pipe to remove thermal energy from the turbine shell and is configurable to add thermal energy to the second end of the heat pipe to add thermal energy to the turbine shell. | 05-05-2011 |
| 20120301280 | TURBOMACHINE - A turbomachine which operates at enhanced operating temperatures includes a stationary component. A rotating component includes a clearance to avoid a rubbing contact between the stationary component and the rotating component, the clearance including a first value in a stationary state of the turbomachine and a second value in a steady-state operation of the machine, wherein during a transient operating phase between the stationary state and the steady-state operation, the clearance includes a value which traverses a curve having an extreme value on account of a different time variation of a rotational speed and a thermal expansion of different components. A compensating device includes a non-linear compensation mechanism configured to reduce or compensate the extreme value during the transient operating phase. | 11-29-2012 |
| 20130136583 | FLUID SEALING DEVICE FOR ROTATING MACHINES - A fluid sealing device for rotating machines having a rotor part including at least one disk carried by a rotating shaft rotating in and relatively to a stator part in the presence of a fluid is disclosed. The rotating shaft has a sealing system defining a first environment at a first pressure. The stator part has a wall in front of the disk of the stator part defining a second environment therewith containing a fluid at a second pressure. The device includes a movable ring placed between the wall of the stator part and the disk of the rotor part and has a front sealing gasket facing towards the disk. The movable ring is moved in the active position when the rotating machine is stopped to prevent the fluid passage from one environment to the other. | 05-30-2013 |
| 20130209240 | ADJUSTABLE BLADE OUTER AIR SEAL APPARATUS - An adjustable blade outer air seal apparatus includes a case structure that extends circumferentially, a support ring structure mounted radially inwards of the case structure and at least one blade outer air seal segment radially adjustably mounted relative to the support ring structure. | 08-15-2013 |
| 20130230389 | VALVE - A valve, for example for controlling a clearance at a tip of turbine blades, includes a piston and a supply mechanism supplying fluid under pressure to cause the piston to move inside a hollow body, and a mechanism detecting a position of the piston, including a shut-off element that moves as one with the piston and is mounted such that it can move in a fluid passage between two positions, open and closed respectively, the fluid passage connecting the supply mechanism to a pressure sensor that generates an output signal representative of the position of the piston of the valve. | 09-05-2013 |
| 20140064937 | FAN BLADE BRUSH TIP - A fan assembly is provided. The fan assembly includes a rotor having a hub and a plurality of rotor blades extending radially outward from the hub. Each rotor blade includes a blade tip at a radially distal end of each blade. The rotor blade tips define a rotor diameter. The fan assembly also includes a first cylindrical casing substantially axially aligned with the blade tips, the first casing including a first inner diameter that is greater than the rotor diameter. The fan assembly further includes a brush seal assembly coupled to the blade tip of a least one of the plurality of rotor blades, the brush seal assembly configured to contact the casing segment during a first operational mode of the fan assembly, the brush seal assembly configured to avoid contact with the casing segment during a second operational mode of the fan assembly. | 03-06-2014 |
| 20140271147 | BLADE TRACK ASSEMBLY WITH TURBINE TIP CLEARANCE CONTROL - A turbine shroud or blade track assembly adapted to extend around a turbine wheel assembly is disclosed. The turbine shroud includes a carrier and a blade track coupled to the carrier. The blade track is movable between a radially-inward position having a first inner diameter and a radially-outward position having a second inner diameter larger than the first inner diameter. | 09-18-2014 |
| 20150098807 | ADJUSTABLE TURBINE SEAL AND METHOD OF ASSEMBLING SAME - A system for providing sealing in a turbine is provided. The sealing system includes a retaining channel oriented within a housing structure proximate a moving turbine component. A seal member is coupled within the retaining channel. A first end of the seal member is secured to the housing structure. A second end of the seal member is movable relative to the retaining channel between first and second positions corresponding to a transient operational mode and a steady state operational mode, respectively. The transient operational mode defines a first clearance between the seal member and the moving turbine component. The steady state configuration defines a second clearance that is smaller than the first clearance. A take-up device coupled to the second end of the seal member moves the second end between the first and second positions. | 04-09-2015 |
| 20160186611 | BLADE TRACK ASSEMBLY WITH TURBINE TIP CLEARANCE CONTROL - A turbine shroud assembly or blade track assembly adapted to extend around a turbine wheel assembly is disclosed. The turbine shroud assembly includes a carrier and a blade track coupled to the carrier. The blade track is movable between a radially-inward position having a first inner diameter and a radially-outward position having a second inner diameter larger than the first inner diameter. | 06-30-2016 |
