Patent application number | Description | Published |
20090293627 | Pressure-Measuring Cell - A pressure sensor comprises a sensor platform; a measuring membrane, or diaphragm, which is held by the sensor platform, and can have a pressure applied to it and is deformable as a function of pressure; and at least two resistance elements having an A1 | 12-03-2009 |
20090301209 | Hydraulic pressure intermediary - A hydraulic pressure intermediary includes: a platform, which has a bowl-shaped surface having an annular, platform-surface edge region, a platform-surface central region depressed relative to the platform-surface edge region and surrounded by the platform-surface edge region, and an annular platform-surface transition region, which borders, on its inner side, the platform-surface central region and, on its outer side, the platform-surface edge region; a bowl-shaped, separating membrane having a flat, annular, separating-membrane edge region, a separating-membrane central region depressed relative to the separating-membrane edge region and an annular separating-membrane transition region, which borders, on its inner side, the separating-membrane central region and, on its outer side, the separating-membrane edge region. The separating membrane is connected with the platform-surface edge region within the separating-membrane edge region along a surrounding joint. Further, the separating-membrane transition region includes an annular moat having a moat outer side, a moat inner side, and a moat transition zone, wherein the moat outer side has a first annular inclined surface, which borders on the separating-membrane edge region, the moat inner side includes a second annular inclined surface, which borders on the separating-membrane central region, and the moat transition zone extends between the first and the second inclined surfaces. | 12-10-2009 |
20100140725 | PRESSURE SENSOR - A piezoresistive pressure sensor is especially suitable for measuring smaller pressures and has a small linearity error. The pressure sensor is manufactured from a BESOI wafer having first and second silicon layers and an oxide layer arranged therebetween. The pressure sensor includes, formed from the first silicon layer of the BESOI wafer, an active layer, in which piezoresistive elements are doped, and, formed from the second silicon layer of the BESOI wafer, a membrane carrier, which externally surrounds a cavity in the second silicon layer, via which a membrane forming region of the active layer and an oxide layer associated therewith are exposed, wherein, in an outer edge of the region of the oxide layer exposed by the cavity, a groove is provided surrounding the region. | 06-10-2010 |
20100308426 | PRESSURE MEASURING DEVICE - A pressure measuring device having a pedestal, an intermediate piece of semiconductor arranged on the pedestal and, connected with the pedestal and arranged on the intermediate piece and connected with the intermediate piece, a semiconductor pressure sensor having a support and a measuring membrane, or diaphragm. The pressure measuring device offers reliable protection of the sensitive measuring membrane, or diaphragm, against mechanical distortions. Provided extending in the interior of the i[ntermediate piece is an annular cavity, which surrounds a first cylindrical section and, pedestal end thereof, a second cylindrical section of the intermediate piece. The second cylindrical section has a greater outer diameter than the first cylindrical section. The cavity is open on an end of the intermediate piece toward the pedestal. The second cylindrical section has an end face facing the pedestal and lying on an end face of the pedestal, for forming a connecting area, via which the intermediate piece is mechanically connected with the pedestal. | 12-09-2010 |
20110209552 | RELATIVE PRESSURE SENSOR - A relative pressure sensor for registering pressure of a medium relative to surrounding atmospheric pressure includes: a pressure measuring cell having a measuring membrane and a platform, wherein pressure of the medium can act on a first side of the measuring membrane facing away from the platform, and wherein the platform has a reference air opening, through which surrounding atmospheric pressure can act on a second side of the measuring membrane facing the platform. A support body, through which a reference air duct extends between a first surface section and a second surface section of the support body is provided, wherein the pressure measuring cell is affixed to the support body with a pressure resistant, bonded adhesive. The reference air opening communicates with the reference air duct, in order to form a reference air path to the measuring membrane, wherein the bonded adhesive surrounds the reference air path, and the relative pressure sensor further includes a shield element, which protects the bonded adhesive from direct contact with reference air. | 09-01-2011 |
20120265455 | OVERLOAD SAFE PRESSURE SENSOR, ESPECIALLY PRESSURE DIFFERENCE SENSOR - A pressure sensor includes a sensor body with a sensor chamber in the interior, at least a first separating membrane, forming a first separating membrane chamber connected with the sensor body. A measuring membrane divides the sensor chamber into two chamber portions. A pressure transfer liquid, with which the first separating membrane chamber, the first chamber portion and a channel therebetween are filled, in order to transfer a pressure to the measuring membrane; wherein the pressure sensor is specified for a temperature range between a minimum temperature and a maximum temperature, as well as for a pressure range. At the minimum temperature, the pressure transfer liquid volume in the first chamber portion, the first channel and the first separating membrane chamber is sufficient over the total pressure range to transfer the pressure to the measuring membrane, without the first separating membrane coming to rest, and that when, in the case of overload at maximum temperature, the entire pressure transfer liquid volume moves out of the first separating membrane chamber into the first chamber portion, and is accommodated by the measuring membrane, the measuring membrane experiences no plastic deformation. | 10-18-2012 |
20120279310 | PRESSURE SENSOR, ESPECIALLY PRESSURE DIFFERENCE SENSOR - The pressure sensor of the invention includes at least one platform, at least one measuring membrane | 11-08-2012 |
20140021563 | Pressure Resistently Encapsulated, Pressure Difference Sensor - A pressure difference sensor includes a capsule, which has a ceramic capsule body. The capsule has a transducer seat in its interior, wherein there is arranged in the transducer seat a semiconductor pressure measuring transducer core, which has a measuring membrane body and at least one support body. The measuring membrane body is connected pressure-tightly with the at least one support body, which has a pressure inlet opening. Ducts extend respectively from an outer surface of the capsule into the transducer seat, wherein the pressure inlet opening communicates with the first duct A side of the measuring membrane is contactable with a pressure through the pressure inlet opening, wherein the support body contacts a joint, which surrounds the first pressure inlet opening and the opening of the first duct into the transducer seat and is connected pressure-tightly with a wall of the transducer seat, and wherein a second side of the measuring membrane is hydraulically isolated from its first side and communicates with the second duct. | 01-23-2014 |
20150369683 | HYDRAULIC MEASURING MECHANISM WITH COPLANAR PRESSURE INPUTS AND PRESSURE DIFFERENCE SENSOR HAVING SUCH A MEASURING MECHANISM - A hydraulic measuring mechanism for registering pressure differences, comprising a measuring mechanism platform 10 having a process connection surface 16 and two pressure input openings, in which, in each case, a pressure tube 20, 22 is arranged, which protrudes from a rear side of the measuring mechanism platform 10 to support a pressure difference measuring cell 40, wherein the pressure tubes 20, 22 are connected pressure-tightly with the measuring mechanism platform 10 from the process connection surface 16. | 12-24-2015 |
20160041054 | Mechanische Stabilisierung und elektrische sowie hydraulische Adaptierung eines Silizium Chips durch Keramiken - A pressure difference sensor includes a pressure difference measuring cell, which has a measuring cell platform with pressure contactable measuring chambers in its interior, a first mounting surface and a second mounting surface. The mounting surfaces have a variable separation under pressure loading of the measuring chambers. A first reinforcement element with a first planar reinforcement area and a second reinforcement element with a second planar reinforcement area. A deflection of the mounting surfaces due to a pressure loading of the measuring chambers is lessened by the reinforcement elements, wherein especially at least 50% of an effective stiffness K=1/(dx/dp) of the reinforcement elements connected by the pressure difference measuring cell is provided only by these connections of the reinforcement element with the measuring cell platform without additional connections between the reinforcement elements in a parallel branch, wherein x is the separation between the first mounting surface and the second mounting surface having the greatest pressure dependence dx/dp. | 02-11-2016 |
20160054191 | Sintered body comprising a plurality of materials and pressure measuring instrument comprising such a sintered body - A sintered body comprises a first region which comprises a first material having a first effective coefficient of thermal expansion α | 02-25-2016 |
20160103031 | Ceramic Pressure Sensor and Method for its Production - A ceramic pressure sensor is described which is produced using an alternative production method and has a ceramic base body, a ceramic measuring membrane which is disposed on the base body and is to be charged with a pressure to be measured, and a pressure measuring chamber enclosed in the base body below the measuring membrane. A method to produce the pressure sensor by means of which, in particular, more complex shapes of the measuring membrane and/or the base body are producible with minimal pores wherein the base body and/or the measuring membrane have layers applied on each other in a 3-D printing method and produced by the selective laser melting of nanopowder layers. | 04-14-2016 |
Patent application number | Description | Published |
20110261876 | METHOD FOR ENCODING A DIGITAL PICTURE, ENCODER, AND COMPUTER PROGRAM ELEMENT - A method for encoding a digital picture having a plurality of pixels is described, each pixel being associated with at least one of a plurality of groups of pixels comprising associating each group of pixels with a first coding mode; determining, for each group of pixels, a first encoding performance level according to its associated first coding mode; determining at least one group of pixels of the plurality of group of pixels such that the first encoding performance level of the at least one determined group of pixels fulfils a predetermined quality criterion; determining, for the determined group of pixels, a second encoding performance level according to a second coding mode; comparing the first performance level and the second performance level; associating the second coding mode with the determined group of pixels if the result of the comparison fulfils a predetermined association criterion; and encoding each group of pixels using its associated coding mode. | 10-27-2011 |
20110261887 | METHODS AND DEVICES FOR ESTIMATING MOTION IN A PLURALITY OF FRAMES - In various embodiments, a method for estimating motion in a plurality of frames is provided, the method including determining a first set of motion vectors with respect to a first frame and a second frame, the second frame being in succession with the first frame along a time direction, determining a second set of motion vectors with respect to a predicted frame and the second frame, the predicted frame being in succession with the first frame along the time direction; wherein some motion vectors of the second set of motion vectors are interpolated from motion vectors of the first set of motion vectors; and determining a third set of motion vectors based on the first set of motion vectors and the second set of motion vectors. | 10-27-2011 |
20120014451 | Image Encoding Methods, Image Decoding Methods, Image Encoding Apparatuses, and Image Decoding Apparatuses - In an embodiment, an image encoding method is provided. The image encoding method may include a first partial encoding step, wherein first partially encoded image data is generated based on first input data after the first input data is available; a second partial encoding step, wherein second partially encoded image data is generated based on second input data after the second input data is available, before the first input data is available; and an encoded image data generating step, wherein encoded image data is generated based on the first partially encoded image data and the second partially encoded image data. | 01-19-2012 |
20120063695 | METHODS FOR ENCODING A DIGITAL PICTURE, ENCODERS, AND COMPUTER PROGRAM PRODUCTS - In one embodiment, a method for encoding a digital picture of a sequence of digital pictures is provided, the digital picture comprising a plurality of pixels, wherein the plurality of pixels is associated at least partially with a first group of pixels and the plurality of pixels or a plurality of pixels of another digital picture is associated at least partially with at least one second group of pixels. The method comprises determining, for the second group of pixels, a second group of pixels coding mode, determining, for the first group of pixels, based on the second group of pixels coding mode, a first group of pixels coding mode, and encoding the digital picture using the first group of pixels coding mode for the first group of pixels. | 03-15-2012 |
20130004096 | Methods, Devices, and Computer Readable Mediums for Processing a Digital Picture - Embodiments provide a method for processing a digital picture, wherein the digital picture comprises a plurality of pixels. The method comprises dividing the digital picture into a plurality of blocks, each block comprising a plurality of pixels. The method further comprises determining a type of block for each block. The method further comprises associating each block with a filtering mode of a plurality of different filtering modes according to the type determined for the block. The method further comprises filtering each block using the associated filtering mode associated with the block. | 01-03-2013 |
20130287315 | METHOD, AN APPARATUS AND A COMPUTER PROGRAM PRODUCT FOR DEINTERLACING AN IMAGE HAVING A PLURALITY OF PIXELS - According to example embodiments, a method for deinterlacing an image having a plurality of pixels, the method comprising: calculating a difference between a first pixel of the image and each pixel of at least one pixel pair, each pixel pair comprising one pixel being positioned above the first pixel and another pixel being positioned below the first pixel; and deinterlacing the first pixel only if at least one difference corresponding to a pixel pair exceeds a predefined threshold. A corresponding apparatus and computer program product are also provided. | 10-31-2013 |
20130301741 | METHOD AND APPARATUS FOR PACKETIZING DATA - A method for packetizing data representing a video sequence comprising a first frame and a second frame. The method comprising determining for at least one first area of a plurality of first areas of the first frame a second area of a plurality of second areas of the second frame such that, for different first areas different second areas are determined and such that, for each of the first areas, a measure of the distance between the second area determined for the first area and an area of the second frame whose location within the second frame corresponds to the location of the first area is above a value. The method further comprising grouping, for each of the first areas, data which the first area may be reconstructed and data from which the second area determined for the first area may be reconstructed into a packet. | 11-14-2013 |
Patent application number | Description | Published |
20120319673 | Direct Coupled Biasing Circuit for High Frequency Applications - This invention eliminates the need for “capacitor coupling” or “transformer coupling,” and the associated undesirable parasitic capacitance and inductance associated with these coupling techniques when designing high frequency (˜60 GHz) circuits. At this frequency, the distance between two adjacent stages needs to be minimized. A resonant circuit in series with the power or ground leads is used to isolate a biasing signal from a high frequency signal. The introduction of this resonant circuit allows a first stage to be “directly coupled” to a next stage using a metallic trace. The “direct coupling” technique passes both the high frequency signal and the biasing voltage to the next stage. The “direct coupling” approach overcomes the large die area usage when compared to either the “AC coupling” or “transformer coupling” approach since neither capacitors nor transformers are required to transfer the high frequency signals between stages. | 12-20-2012 |
20130307613 | Method and Apparatus of Cancelling Inductor Coupling - This invention compensates for the unintentional magnetic coupling between a first and second inductor of two different closely spaced inductors separated by a conversion circuit. A cancellation circuit formed from transistors senses the magnetic coupling in the first inductor and feeds a current opposite to the induced magnetic coupling captured by the second inductor such that the coupled magnetic coupling can be compensated and allows the first and second inductors to behave independently with regards to the coupled magnetic coupling between the first and second inductors. This allows the distance between the first and second inductors to be minimized which saves silicon area. In addition, the performance is improved since the overall capacitance in both circuits can be decreased. This cancellation technique to reduce the magnetic coupling between two closed placed inductively loaded circuits allows the design of a more compact and faster performing circuit. | 11-21-2013 |
20140091869 | Method and Apparatus of a Crystal Oscillator with a Noiseless and Amplitude Based Start Up Control Loop - A large gain is used to start up the oscillation of the crystal quickly. Once the oscillation starts, the amplitude is detected. A control circuit determines based on the measured amplitude to disable a low resistance path in the controlled switch array to reduce the applied gain below the power dissipation specification of the crystal. Another technique introduces a mixed-signal controlled power supply multi-path resistive array which tailors the maximum current to the crystal. A successive approximation register converts the amplitude into several partitions and enables/disables one of several power routing paths to the inverter of the oscillator. This allows a better match between the crystal selected by the customer and the on-chip drive circuitry to power up the oscillator without stressing the crystal. The “l/f” noise of the oscillator circuit is minimized by operating transistors in the triode region instead of the linear region. | 04-03-2014 |
20150357999 | Direct Coupled Biasing Circuit for High Frequency Applications - This invention eliminates the need for “capacitor coupling” or “transformer coupling,” and the associated undesirable parasitic capacitance and inductance associated with these coupling techniques when designing high frequency (˜60 GHz) circuits. At this frequency, the distance between two adjacent stages needs to be minimized. A resonant circuit in series with the power or ground leads is used to isolate a biasing signal from a high frequency signal. The introduction of this resonant circuit allows a first stage to be “directly coupled” to a next stage using a metallic trace. The “direct coupling” technique passes both the high frequency signal and the biasing voltage to the next stage. The “direct coupling” approach overcomes the large die area usage when compared to either the “AC coupling” or “transformer coupling” approach since neither capacitors nor transformers are required to transfer the high frequency signals between stages. | 12-10-2015 |
20160056764 | Method and Apparatus to Detect LO Leakage and Image Rejection using a Single Transistor - LO leakage and Image are common and undesirable effects in typical transmitters. Typically, thirty complex hardware and algorithms are used to calibrate and reduce these two impairments. A single transistor that draws essentially no de current and occupies a very small area, is used to detect the LO leakage and Image Rejection signals. The single transistor operating as a square law device, is used to mix the signals at the input and output ports of the power amplifier (PA). The mixed signal generated by the single transistor enables the simultaneous calibration of the LO leakage and Image Rejection. | 02-25-2016 |
Patent application number | Description | Published |
20120007318 | SEAL INCLUDING FLEXIBLE SEAL STRIPS - A seal member for effecting a seal preventing fluid flow in an axial direction through an annular space formed between two relatively moving components including a rotatable shaft and a stator structure. The seal member includes a plurality of flexible seal strips. Each seal strip includes a planar plate extending radially through the annular space and having a radially outer end supported to the stator structure and a radially inner end defining a tip portion extending widthwise in the axial direction engaged in sliding contact with a peripheral surface of the rotatable shaft. At least one of the seal strips includes a plurality of perforations extending through the seal strip and located between a leading edge and a trailing edge of the seal strip for effecting an increased flexibility of the seal strip adjacent to the tip portion. | 01-12-2012 |
20130017080 | FLOW DIRECTING MEMBER FOR GAS TURBINE ENGINE - In a gas turbine engine, a flow directing member includes a platform supported on a rotor, a radially facing endwall, at least one axial surface extending radially inwardly from a junction with the endwall, an airfoil extending radially outwardly from the endwall, and a fluid flow directing feature. The fluid flow directing feature includes a groove extending axially into the axial surface and has radially inner and outer groove ends. The outer groove end defines an axially extending notch in the junction between the axial surface and the endwall and forms an opening in the endwall for directing a cooling fluid to the endwall. The groove further includes a first groove wall extending from the inner groove end to the outer groove end, and a second groove wall opposed from the first groove wall and extending from the inner groove end to the outer groove end. | 01-17-2013 |
20130017095 | FLOW DIRECTING MEMBER FOR GAS TURBINE ENGINEAANM Lee; Ching-PangAACI CincinnatiAAST OHAACO USAAGP Lee; Ching-Pang Cincinnati OH USAANM Tham; Kok-MunAACI OrlandoAAST FLAACO USAAGP Tham; Kok-Mun Orlando FL USAANM Vitt; Paul H.AACI Liberty TwpAAST OHAACO USAAGP Vitt; Paul H. Liberty Twp OH USAANM Williamson; Stephen R.AACI CincinnatiAAST OHAACO USAAGP Williamson; Stephen R. Cincinnati OH USAANM Montgomery; Matthew D.AACI JupiterAAST FLAACO USAAGP Montgomery; Matthew D. Jupiter FL USAANM Prakash; ChanderAACI OrlandoAAST FLAACO USAAGP Prakash; Chander Orlando FL USAANM Harris; MelissaAACI OrlandoAAST FLAACO USAAGP Harris; Melissa Orlando FL US - In a gas turbine engine, a flow directing member includes a platform supported on a rotor and includes a radially facing endwall and at least one axially facing axial surface extending radially inwardly from a junction with the endwall. The flow directing member further includes an airfoil extending radially outwardly from the endwall and a fluid flow directing feature. The fluid flow directing feature includes a groove extending axially into the axial surface. The groove has a radially inner groove end and a radially outer groove end, wherein the outer groove end defines an axially extending notch in the junction between the axial surface and the endwall and forms an opening in the endwall for directing a cooling fluid to the endwall. | 01-17-2013 |
20130058756 | FLOW DISCOURAGER INTEGRATED TURBINE INTER-STAGE U-RING - A gas turbine having rotor discs ( | 03-07-2013 |
20130202408 | GAS TURBINE ENGINE WITH IMPROVED COOLING BETWEEN TURBINE ROTOR DISK ELEMENTS - A gas turbine engine is provided comprising a forward rotor disk and blade assembly capable of rotating; an aft rotor disk and blade assembly capable of rotating; and a row of vanes positioned between the forward rotor disk and blade assembly and the aft rotor disk and blade assembly. The vane row and the forward rotor disk and blade assembly may define a forward cavity. The vane row may comprise at least one stator vane comprising: a main body and an inner shroud structure comprising a cover. The cover may include a first inner cavity receiving cooling air. The cover may further include at least one cooling flow passage. Cooling air flowing from the cooling flow passage has a tangential velocity component. | 08-08-2013 |
20130283813 | GAS TURBINE COMPRESSOR WITH BLEED PATH - A gas turbine engine includes a compressor for generating compressed air. The compressor includes a rotor defined by a plurality of axial disks including a first disk and a second disk. A first row of blades extends radially outwardly from the first disk, and a second row of blades extends radially outwardly from the second disk. A row of cantilevered vanes is located at an axial location between the first row of blades and the second row of blades. A bleed path extends at least partially through the second disk and includes an entrance at an axial location between the first row of blades and at least a portion of the row of cantilevered vanes. The entrance communicates with a compressed air flowpath through the compressor. | 10-31-2013 |
Patent application number | Description | Published |
20130156579 | AMBIENT AIR COOLING ARRANGEMENT HAVING A PRE-SWIRLER FOR GAS TURBINE ENGINE BLADE COOLING - A gas turbine engine including: an ambient-air cooling circuit ( | 06-20-2013 |
20140003919 | FINNED SEAL ASSEMBLY FOR GAS TURBINE ENGINES | 01-02-2014 |
20140123657 | EXTERNAL COOLING FLUID INJECTION SYSTEM IN A GAS TURBINE ENGINE - A cooling fluid air injection system for use in a gas turbine engine includes at an external cooling fluid source, at least one rotor cooling pipe, which is used to inject cooling fluid from the source into a rotor chamber, a piping system that provides fluid communication between the source and the rotor cooling pipe(s), a blower system for conveying the cooling fluid through the piping system and the rotor cooling pipe(s) into the rotor chamber, and a valve system. The valve system is closed during full load engine operation to prevent cooling fluid from the source from passing through the piping system, and open during less than full load engine operation to allow cooling fluid from the source to pass through the piping system. | 05-08-2014 |
20140123675 | AIR INJECTION SYSTEM IN A GAS TURBINE ENGINE - An air injection system for use in a gas turbine engine includes at least one outlet port through which air is extracted from the engine only during less than full load operation, at least one rotor cooling pipe, which is used to inject the air extracted from the outlet port(s) into a rotor chamber, a piping system that provides fluid communication between the one outlet port(s) and the rotor cooling pipe(s), a blower system for extracting air from the engine through the outlet port(s) and for conveying the extracted air through the piping system and the rotor cooling pipe(s) into the rotor chamber, and a valve system. The valve system is closed during full load engine operation to prevent air from passing through the piping system, and open during less than full load engine operation to allow air to pass through the piping system. | 05-08-2014 |
20140147250 | TURBINE BLADE ANGEL WING WITH PUMPING FEATURES - A gas turbine engine, including: a plurality of blades ( | 05-29-2014 |
20140205443 | SEAL ASSEMBLY INCLUDING GROOVES IN AN AFT FACING SIDE OF A PLATFORM IN A GAS TURBINE ENGINE - A seal assembly between a disc cavity and a hot gas path in a gas turbine engine includes a stationary vane assembly and a rotating blade assembly axially upstream from the vane assembly. A platform of the blade assembly has a radially outwardly facing first surface, an axially downstream facing second surface defining an aft plane, and a plurality of grooves extending into the second surface such that the grooves are recessed from the aft plane The grooves are arranged such that a circumferential space is defined between adjacent grooves During operation of the engine, the grooves impart a circumferential velocity component to purge air flowing out of a disc cavity through the grooves to guide the purge air toward a hot gas path such that the purge air flows in a desired direction with reference to a direction of hot gas flow through the hot gas path. | 07-24-2014 |
20140234076 | OUTER RIM SEAL ASSEMBLY IN A TURBINE ENGINE - A seal assembly between a hot gas path and a disc cavity in a turbine engine includes a non-rotatable vane assembly including a row of vanes and an inner shroud, a rotatable blade assembly adjacent to the vane assembly and including a row of blades and a turbine disc that forms a part of a turbine rotor, and an annular wing member located radially between the hot gas path and the disc cavity. The wing member extends generally axially from the blade assembly toward the vane assembly and includes a plurality of circumferentially spaced apart flow passages extending therethrough from a radially inner surface thereof to a radially outer surface thereof. The flow passages effect a pumping of cooling fluid from the disc cavity toward the hot gas path during operation of the engine. | 08-21-2014 |
20140271103 | VANE CARRIER THERMAL MANAGEMENT ARRANGEMENT AND METHOD FOR CLEARANCE CONTROL - A thermal management arrangement ( | 09-18-2014 |
20140311157 | VANE CARRIER TEMPERATURE CONTROL SYSTEM IN A GAS TURBINE ENGINE - A vane carrier temperature control system for use in a gas turbine engine includes a first cooling air source, a second cooling air source, and an air temperature control system. The first cooling air source supplies a first portion of vane carrier cooling air extracted from a compressor section of the engine to a first section of a vane carrier that supports a plurality of rows of vanes within a turbine section of the engine. The second cooling air source supplies a second portion of vane carrier cooling air extracted from the compressor section to a second section of the vane carrier spaced from the first section in an axial direction defined by a direction of hot working gas flow through the turbine section. The air temperature control system controls a temperature of at least one of the first and second portions of vane carrier cooling air. | 10-23-2014 |
20150071763 | OUTER RIM SEAL ASSEMBLY IN A TURBINE ENGINE - A seal assembly between a hot gas path and a disc cavity in a turbine engine includes a non-rotatable vane assembly including a row of vanes and an inner shroud, a rotatable blade assembly axially adjacent to the vane assembly and including a row of blades and a turbine disc that forms a part of a turbine rotor, and an annular wing member located radially between the hot gas path and the disc cavity. The wing member extends generally axially from the blade assembly toward the vane assembly and includes a plurality of circumferentially spaced apart flow passages extending therethrough from a radially inner surface thereof to a radially outer surface thereof. The flow passages each include a portion that is curved as the passage extends radially outwardly to effect a scooping of cooling fluid from the disc cavity into the flow passages and toward the hot gas path. | 03-12-2015 |
20150240651 | TURBINE ABRADABLE LAYER WITH PROGRESSIVE WEAR ZONE MULTI LEVEL RIDGE ARRAYS - Turbine and compressor casing abradable component embodiments for turbine engines, with composite grooves and vertically projecting alternating rows of first and second height ridges in planform patterns, to reduce, redirect and/or block blade tip airflow leakage downstream into the grooves rather than from turbine blade airfoil high to low pressure sides. The first ridges have a first ridge height greater than that of the second ridges. These ridge or rib embodiments have first lower and second upper wear zones. The lower zone, at and below the second ridge height, optimizes engine airflow characteristics, while the upper zone, between tips of the second and first ridges, is optimized to minimize blade tip gap and wear by being more easily abradable than the lower zone. | 08-27-2015 |
20150240653 | TURBINE ABRADABLE LAYER WITH ZIG ZAG GROOVE PATTERN - Turbine and compressor casing abradable component embodiments for turbine engines, with zig-zag pattern abradable surface ridges and grooves. Some embodiments include distinct forward upstream and aft downstream composite multi orientation groove and vertically projecting ridges planform patterns, to reduce, redirect and/or block blade tip airflow leakage downstream into the grooves rather than from turbine blade airfoil high to low pressure sides. Ridge or rib embodiments have first lower and second upper wear zones. The lower zone optimizes engine airflow characteristics while the upper zone is optimized to minimize blade tip gap and wear by being more easily abradable than the lower zone. | 08-27-2015 |