Patents by Inventor Philip Clarke
Philip Clarke has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Patent number: 7590008Abstract: Circuits, methods, and apparatus that provide the calibration of input and output circuits for a high-speed memory interface. Timing errors caused by the fly-by routing of a clock signal provided by the memory interface are calibrated for both read and write paths. This includes adjusting read and write DQS signal timing for each DQ/DQS group, as well as inserting or bypassing registers when timing errors are more than one clock cycle. Timing skew caused by trace and driver mismatches between CK, DQ, and DQS signals are compensated for. One or more of these calibrations may be updated by a tracking routine during device operation.Type: GrantFiled: November 6, 2007Date of Patent: September 15, 2009Assignee: Altera CorporationInventors: Manoj B. Roge, Andrew Bellis, Philip Clarke, Joseph Huang, Michael H. M. Chu, Yan Chong
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Patent number: 7589556Abstract: Circuits, methods, and apparatus for the dynamic control of calibration data that adjusts the timing of input and output signals on an integrated circuit. This dynamic control allows input and output circuits to self-calibrate by compensating for temperature and voltage changes in an efficient manner, without the need for device reconfiguration. Calibration settings can be maintained while new calibration settings are loaded. Skew between clock and data signals, as well as among multiple data signals, can be reduced. Dynamic control is achieved while consuming only a minimal resources including route paths.Type: GrantFiled: October 26, 2007Date of Patent: September 15, 2009Assignee: Altera CorporationInventors: Johnson Tan, Andrew Bellis, Philip Clarke, Yan Chong, Joseph Huang, Michael H. M. Chu, Chiakang Sung
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Publication number: 20080291758Abstract: Circuits, methods, and apparatus for transferring data from a device's input clock domain to a core clock domain. One example achieves this by using a retiming element between input and core circuits. The retiming element is calibrated by incrementally sweeping a delay and receiving data at each increment. Minimum and maximum delays where data is received without errors are averaged. This average can then be used to adjust the timing of a circuit element inserted in an input path between an input register clocked by an input strobe signal and an output register clocked by a core clock signal. In one example, an input signal may be delayed by an amount corresponding to the delay setting. In other examples, each input signal is registered using an intermediate register between the input register and the output register, where a clock signal is delayed by an amount corresponding to the delay setting.Type: ApplicationFiled: November 5, 2007Publication date: November 27, 2008Applicant: Altera CorporationInventors: Michael H.M. Chu, Joseph Huang, Chiakang Sung, Yan Chong, Andrew Bellis, Philip Clarke, Manoj B. Roge
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Publication number: 20070162613Abstract: Control messages constructed in accordance with a first communications protocol for use in a communications network each include a first address identifier having a format defined by the first protocol. The control message is processed to derive a second address identifier having a format defined by a second communications protocol. The control message is re-formatted for transmission, in accordance with the second protocol, to a network system associated with the second address identifier.Type: ApplicationFiled: March 15, 2007Publication date: July 12, 2007Applicant: BRITISH TELECOMMUNICATIONS public limited companyInventors: Alan O'Neill, Philip Clarke, Paul Felton, Caroline Beauchamps, Shaun Baker
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Publication number: 20070028821Abstract: An embroidered electrode (10) consists of embroidered elements (12, 13, 14) of electrically conductive thread sewn on a backing material (11). Within a given element the orientation of stitching is selected to be parallel to the direction in which the element extends.Type: ApplicationFiled: May 21, 2004Publication date: February 8, 2007Applicant: Koninklijke Philips Electronics N.V.Inventors: Genevieve Bennett, Philip Clarke, Warren Valentine
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Patent number: 7147432Abstract: A turbine shroud assembly asymmetrical cooling element such as a shroud segment or a baffle includes an arcuate panel. The panel has a plurality of cooling apertures extending through the panel and an axially extending midline of the panel parallel to an axis of rotation of the arcuate panel. A symmetric portion of the cooling apertures have a symmetrical density of aperture inlets that is symmetric with respect to the axially extending midline. An asymmetric portion of the cooling apertures have an asymmetrical density of aperture inlets that is asymmetric with respect to the axially extending midline. One exemplary cooling element includes a high density area of the cooling apertures in the asymmetric portion having a higher density of aperture inlets than in the symmetric portion. A low density area of the cooling apertures in the asymmetric portion has a lower density of aperture inlets than in the symmetric portion of the cooling apertures.Type: GrantFiled: November 24, 2003Date of Patent: December 12, 2006Assignee: General Electric CompanyInventors: Cedric Carlton Lowe, Andrew Charles Powis, Jonathan Philip Clarke
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Patent number: 7093335Abstract: A method is provided for repairing a surface portion of an article including a metallic environmental resistant coating on a substrate. The coating includes a coating outer portion bonded with the substrate through a diffusion zone that includes at least one feature, for example Al and/or an intermetallic phase, in an amount detrimental to application of a metallic replacement coating and/or repair of the article. The method comprises removing the coating outer portion to expose a surface of the diffusion zone. The substrate and the diffusion zone are heated at a temperature and for a time sufficient to diffuse and/or dissolve at least a portion of the at least one feature in the exposed surface and in a portion of the diffusion zone beneath the exposed surface to a level below the detrimental amount. This provides a replacement surface portion integral with diffusion zone. Then a metallic replacement coating outer portion is applied to the replacement surface portion.Type: GrantFiled: July 3, 2002Date of Patent: August 22, 2006Assignee: General Electric CompanyInventors: Jeffrey Allen Conner, Roger Dale Wustman, Jonathan Philip Clarke
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Patent number: 7008179Abstract: A gas turbine engine turbine blade includes a hollow airfoil extending radially from a blade root to a radially outer airfoil tip. The airfoil includes an airfoil outer wall having transversely spaced apart pressure and suction side walls meeting along chordally spaced apart leading and trailing edges of the airfoil. A radially extending cooling air supply channel within the airfoil includes a bank of pins integral with and extending transversely between the pressure and suction side walls. The bank of the pins is tuned such that a natural frequency of the blade associated with an engine forced driving mode of the blade is sufficiently away from a steady state engine operating frequency to substantially avoid natural frequency resonance of the blade during steady state engine operation. The bank of the pins is tuned by locations of the pins within the cooling air supply channel.Type: GrantFiled: December 16, 2003Date of Patent: March 7, 2006Assignee: General Electric Co.Inventors: Gerard Anthony Rinck, Jonathan Philip Clarke, Mark Edward Stegemiller, Hardev Singh, Steven Robert Brassfield
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Patent number: 7008185Abstract: A turbine nozzle bifurcated impingement baffle includes axially forward and aft chambers with a gap therebetween, impingement holes through forward and aft baffle walls of the forward and aft chambers respectively, and a plenum chamber in fluid flow communication with the forward and aft chambers. An exemplary embodiment of the bifurcated impingement baffle further includes a single cooling air inlet to the plenum chamber enclosed within a plenum chamber enclosure the plenum chamber. A sealing plate is mounted between and sealed to the plenum chamber enclosure and the forward and aft chambers. The sealing plate has forward and aft inlet apertures disposed between the plenum chamber and the forward and aft chambers respectively. Forward and aft end plates cap radially inner ends of the forward and aft chambers. An outlet aperture in the forward end plate has an interstage seal cavity feed tube disposed therethrough.Type: GrantFiled: February 27, 2003Date of Patent: March 7, 2006Assignee: General Electric CompanyInventors: Jonathan Jordan Peterman, Andrew Charles Powis, Ronald Eugene McRae, Jr., Jonathan Philip Clarke, Robert Alan Frederick, Edward Eugene Gibler, Brian David Keith
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Patent number: 6969233Abstract: A turbine nozzle segment includes a single hollow airfoil extending radially between radially outer and inner band segments. The airfoil has an airfoil wall with pressure and suction sides extending axially between leading and trailing edges of the airfoil. The airfoil wall surrounds a bifurcated cavity and a bifurcating rib extends through the bifurcated cavity and between the pressure and suction sides of the airfoil wall dividing the bifurcated cavity into forward and aft cavities. A stiffening rib extends radially outwardly from and along a radially outer surface of the outer band segment and axially and circumferentially from a pressure side forward corner of the outer band segment to the bifurcating rib. The outer and inner band segments, the bifurcating rib, and the stiffening rib are integral and made from a unitary one-piece casting.Type: GrantFiled: February 27, 2003Date of Patent: November 29, 2005Assignee: General Electric CompanyInventors: Andrew Charles Powis, Ronald Eugene McRae, Jr., Jonathan Philip Clarke, Jonathan Jordan Peterman, Robert Alan Frederick, Edward Eugene Gibler, Brian David Keith
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Patent number: 6932568Abstract: A turbine nozzle segment includes at least one hollow airfoil extending radially between radially outer and inner band segments, a clockwise open hook on a clockwise end at an aft end of the outer band segment, and counter-clockwise open hook on a counter-clockwise end at the aft end of the outer band segments. An exemplary embodiment of the turbine nozzle segment includes a load stop extending radially outwardly from the outer band segment. At least one aftwardly facing load face is at the aft end of the nozzle segment at the outer band segment. The clockwise open hook is C-shaped and the counter-clockwise open hook is a shiplap hook. Another embodiment of the turbine nozzle segment has only one hollow airfoil with an airfoil wall surrounding a bifurcated cavity divided into forward and aft cavities by a bifurcating rib extending between pressure and suction sides of the airfoil wall.Type: GrantFiled: February 27, 2003Date of Patent: August 23, 2005Assignee: General Electric CompanyInventors: Andrew Charles Powis, Ronald Eugene McRae, Jr., Jonathan Philip Clarke, Jonathan Jordan Peterman, Robert Alan Frederick, Edward Eugene Gibler, Brian David Keith
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Publication number: 20040170499Abstract: A turbine nozzle segment includes a single hollow airfoil extending radially between radially outer and inner band segments. The airfoil has an airfoil wall with pressure and suction sides extending axially between leading and trailing edges of the airfoil. The airfoil wall surrounds a bifurcated cavity and a bifurcating rib extends through the bifurcated cavity and between the pressure and suction sides of the airfoil wall dividing the bifurcated cavity into forward and aft cavities. A stiffening rib extends radially outwardly from and along a radially outer surface of the outer band segment and axially and circumferentially from a pressure side forward corner of the outer band segment to the bifurcating rib. The outer and inner band segments, the bifurcating rib, and the stiffening rib are integral and made from a unitary one-piece casting.Type: ApplicationFiled: February 27, 2003Publication date: September 2, 2004Inventors: Andrew Charles Powis, Ronald Eugene McRae, Jonathan Philip Clarke, Jonathan Jordan Peterman, Robert Alan Frederick, Edward Eugene Gibler, Brian David Keith
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Publication number: 20040170496Abstract: A turbine nozzle segment includes at least one hollow airfoil extending radially between radially outer and inner band segments, a clockwise open hook on a clockwise end at an aft end of the outer band segment, and counter-clockwise open hook on a counter-clockwise end at the aft end of the outer band segments. An exemplary embodiment of the turbine nozzle segment includes a load stop extending radially outwardly from the outer band segment. At least one aftwardly facing load face is at the aft end of the nozzle segment at the outer band segment. The clockwise open hook is C-shaped and the counter-clockwise open hook is a shiplap hook. Another embodiment of the turbine nozzle segment has only one hollow airfoil with an airfoil wall surrounding a bifurcated cavity divided into forward and aft cavities by a bifurcating rib extending between pressure and suction sides of the airfoil wall.Type: ApplicationFiled: February 27, 2003Publication date: September 2, 2004Inventors: Andrew Charles Powis, Ronald Eugene McRae, Jonathan Philip Clarke, Jonathan Jordan Peterman, Robert Alan Frederick, Edward Eugene Gibler, Brian David Keith
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Publication number: 20040170498Abstract: A turbine nozzle bifurcated impingement baffle includes axially forward and aft chambers with a gap therebetween, impingement holes through forward and aft baffle walls of the forward and aft chambers respectively, and a plenum chamber in fluid flow communication with the forward and aft chambers. An exemplary embodiment of the bifurcated impingement baffle further includes a single cooling air inlet to the plenum chamber enclosed within a plenum chamber enclosure the plenum chamber. A sealing plate is mounted between and sealed to the plenum chamber enclosure and the forward and aft chambers. The sealing plate has forward and aft inlet apertures disposed between the plenum chamber and the forward and aft chambers respectively. Forward and aft end plates cap radially inner ends of the forward and aft chambers. An outlet aperture in the forward end plate has an interstage seal cavity feed tube disposed therethrough.Type: ApplicationFiled: February 27, 2003Publication date: September 2, 2004Inventors: Jonathan Jordan Peterman, Andrew Charles Powis, Ronald Eugene McRae, Jonathan Philip Clarke, Robert Alan Frederick, Edward Eugene Gibler, Brian David Keith
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Patent number: 6652220Abstract: A method for assembling a turbine nozzle for a gas turbine engine facilitates improving cooling efficiency of the turbine nozzle. The method includes providing a hollow doublet including a leading airfoil and a trailing airfoil coupled by at least one platform, wherein each airfoil includes a first sidewall and a second sidewall that extend between a respective leading and trailing edge. The method also includes inserting an insert into at least one of the airfoils, wherein the insert includes a first sidewall including a first plurality of cooling openings that extending therethrough, and a second sidewall including a second plurality of cooling openings extending therethrough, and wherein the first plurality of cooling openings facilitate more cooling of the airfoil than the second plurality of cooling openings.Type: GrantFiled: November 15, 2001Date of Patent: November 25, 2003Assignee: General Electric CompanyInventors: Andrew Charles Powis, Jonathan Philip Clarke, Judd Dodge Tressler
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Patent number: 6609880Abstract: A method for assembling a turbine nozzle for a gas turbine engine facilitates improving cooling efficiency of the turbine nozzle. The method includes providing a hollow doublet including a leading airfoil and a trailing airfoil coupled by at least one platform, wherein each airfoil includes a first sidewall and a second sidewall that extend between a respective leading and trailing edge. The method also includes inserting an insert into at least one of the airfoils, wherein the insert includes a first sidewall including a first plurality of cooling openings that extending therethrough, and a second sidewall including a second plurality of cooling openings extending therethrough, and wherein the first plurality of cooling openings facilitate more airfoil vane sidewall cooling than the second plurality of cooling openings.Type: GrantFiled: November 15, 2001Date of Patent: August 26, 2003Assignee: General Electric CompanyInventors: Andrew Charles Powis, Jonathan Philip Clarke, Judd Dodge Tressler
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Patent number: 6605364Abstract: A method is provided for repairing a surface portion of an article including a metallic environmental resistant coating on a substrate. The coating includes a coating outer portion bonded with the substrate through a diffusion zone that includes at least one feature, for example Al and/or an intermetallic phase, in an amount detrimental to application of a metallic replacement coating and/or repair of the article. The method comprises removing the coating outer portion to expose a surface of the diffusion zone. The substrate and the diffusion zone are heated at a temperature and for a time sufficient to diffuse and/or dissolve at least a portion of the at least one feature in the exposed surface and in a portion of the diffusion zone beneath the exposed surface to a level below the detrimental amount. This provides a replacement surface portion integral with diffusion zone. Then a metallic replacement coating outer portion is applied to the replacement surface portion.Type: GrantFiled: July 18, 2000Date of Patent: August 12, 2003Assignee: General Electric CompanyInventors: Jeffrey Allen Conner, Roger Dale Wustman, Jonathan Philip Clarke
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Publication number: 20030113201Abstract: A method for assembling a turbine nozzle for a gas turbine engine facilitates improving cooling efficiency of the turbine nozzle. The method includes providing a hollow doublet including a leading airfoil and a trailing airfoil coupled by at least one platform, wherein each airfoil includes a first sidewall and a second sidewall that extend between a respective leading and trailing edge. The method also includes inserting an insert into at least one of the airfoils, wherein the insert includes a first sidewall including a first plurality of cooling openings that extending therethrough, and a second sidewall including a second plurality of cooling openings extending therethrough, and wherein the first plurality of cooling openings facilitate more cooling of the airfoil than the second plurality of cooling openings.Type: ApplicationFiled: November 15, 2001Publication date: June 19, 2003Inventors: Andrew Charles Powis, Jonathan Philip Clarke, Judd Dodge Tressler
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Publication number: 20030091427Abstract: A method for assembling a turbine nozzle for a gas turbine engine facilitates improving cooling efficiency of the turbine nozzle. The method includes providing a hollow doublet including a leading airfoil and a trailing airfoil coupled by at least one platform, wherein each airfoil includes a first sidewall and a second sidewall that extend between a respective leading and trailing edge. The method also includes inserting an insert into at least one of the airfoils, wherein the insert includes a first sidewall including a first plurality of cooling openings that extending therethrough, and a second sidewall including a second plurality of cooling openings extending therethrough, and wherein the first plurality of cooling openings facilitate more airfoil vane sidewall cooling than the second plurality of cooling openings.Type: ApplicationFiled: November 15, 2001Publication date: May 15, 2003Inventors: Andrew Charles Powis, Jonathan Philip Clarke, Judd Dodge Tressler
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Patent number: RE40658Abstract: A method for assembling a turbine nozzle for a gas turbine engine facilitates improving cooling efficiency of the turbine nozzle. The method includes providing a hollow doublet including a leading airfoil and a trailing airfoil coupled by at least one platform, wherein each airfoil includes a first sidewall and a second sidewall that extend between a respective leading and trailing edge. The method also includes inserting an insert into at least one of the airfoils, wherein the insert includes a first sidewall including a first plurality of cooling openings that extending therethrough, and a second sidewall including a second plurality of cooling openings extending therethrough, and wherein the first plurality of cooling openings facilitate more cooling of the airfoil than the second plurality of cooling openings.Type: GrantFiled: November 23, 2005Date of Patent: March 10, 2009Assignee: General Electric CompanyInventors: Andrew Charles Powis, Jonathan Philip Clarke, Judd Dodge Tressler