Patents by Inventor David Shapiro
David Shapiro 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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Publication number: 20120276620Abstract: Disclosed is portable organ transportation system including a mobile cart and an organ container. At least one of the mobile cart and the organ container include a latch for releasably attaching the organ container to the mobile cart. The organ container may be a portable organ preservation device or a portable organ perfusion apparatus.Type: ApplicationFiled: April 29, 2011Publication date: November 1, 2012Applicant: Lifeline Scientific, Inc.Inventors: David Kravitz, Aaron Randall Ferber, Ross Lockwood, Rodney Hal Monson, Evan David Shapiro
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Publication number: 20120247124Abstract: A composite annular shroud supported by a support assembly including at least two single piece full 360 degree rings and at least partially disposed within an innermost one of the rings. The shroud is biased against and in sealing engagement with an inner flange of the innermost ring. A three ring assembly includes the inner ring disposed radially inwardly of a middle ring disposed radially inwardly of an outer ring and the shroud at least partially disposed within the inner ring. At least three clocking pins extend radially inwardly from the middle ring through slots in the inner ring into notches in the shroud. The middle ring may be an aft end of a support ring fixedly connected to an engine backbone. Mounting pins may be press fitted into pin holes in the middle ring and extend radially outwardly from the middle ring through radial holes in the outer ring.Type: ApplicationFiled: March 30, 2011Publication date: October 4, 2012Inventors: Jason David Shapiro, Jared Peter Buhler, Brian Kenneth Corsetti
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Patent number: 8172522Abstract: A method and system of supporting removable static components in a turbine engine stator assembly is described. The method comprises the steps of engaging a stator hanger located at a first location on a first static component with a post located on a first static structure whereby the post supports at least a part of the weight of the first static component, engaging a stator stopper located at a second location on the first static component that is located circumferentially apart from the first location with the stator hanger that is located on a second static component, and engaging a hook located at a third location on the first static component with a second static structure whereby the second static structure supports at least a part of the weight of the first static component.Type: GrantFiled: March 31, 2008Date of Patent: May 8, 2012Assignee: General Electric CompanyInventors: Jason David Shapiro, Victor Hugo Silva Correia
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Patent number: 8172504Abstract: A turbine nozzle for a gas turbine engine includes: (a) spaced-apart arcuate inner and outer bands; (b) a hollow, airfoil-shaped turbine vane extending between the inner and outer bands, the interior of the vane defining at least a forward cavity and a mid-cavity positioned aft of the forward cavity; (c) a hollow impingement insert received inside the mid-cavity, the impingement insert having walls which are pierced with at least one impingement cooling hole; (d) a passage in the turbine vane at a radially outer end of the forward cavity adapted to be coupled to a source of cooling air; and (e) a passage in the inner band in fluid communication with a radially inner end of the forward cavity and a radially inner end of the impingement insert.Type: GrantFiled: March 25, 2008Date of Patent: May 8, 2012Assignee: General Electric CompanyInventors: David Allen Flodman, Jason David Shapiro, Robert Francis Manning, Mark Douglas Gledhill, Tyler Frederick Hooper
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Patent number: 8123473Abstract: A shroud hanger for a gas turbine engine has an arcuate body with opposed inner and outer faces and opposed forward and aft ends, the channel having at least one cooling passage therein which includes: (a) a generally axially-aligned channel extending through the body, the channel having one end open to an exterior of the body; and (b) a generally radially-aligned diffuser extending through the inner face and intersecting the channel.Type: GrantFiled: October 31, 2008Date of Patent: February 28, 2012Assignee: General Electric CompanyInventor: Jason David Shapiro
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Patent number: 8103530Abstract: Insight-driven interactions with customers may be enhanced in a holistic approach. A customer relationship management (“CRM”) methodology may include: (1) evaluating a customer strategy; (2) identifying customer segments from a customer base; (3) forming an interaction strategy; (4) defining a series of experiences based on the strategy; (5) applying those interactions with customers during interactions; and (6) monitoring the results of the customer interactions. A computer aid may preferably guide a user through some of these steps. A modular, vendor-independent, centralized, rules-based engine may perform processing to deliver tailored customer experiences, relying on values for prioritized experiences identified through use of the computer aid.Type: GrantFiled: March 26, 2004Date of Patent: January 24, 2012Assignee: Accenture Global Services LimitedInventors: Kevin N. Quiring, Tore Berg, Vincent U. Dell'Anno, Julio J. Hernandez, Alyse S. Kornfeld, Steven L. Lew, Dawn E. Palmer, David A. Shapiro, David Slaw, Sajid Usman, Rodney B. Whitsett, Robert E. Wollan
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Patent number: 8103531Abstract: Insight-driven interactions with customers may be enhanced in a holistic approach. A customer relationship management (“CRM”) methodology may include: (1) evaluating a customer strategy; (2) identifying customer segments from a customer base; (3) forming an interaction strategy; (4) defining a series of experiences based on the strategy; (5) applying those interactions with customers during interactions; and (6) monitoring the results of the customer interactions. A computer aid may preferably guide a user through some of these steps. A modular, vendor-independent, centralized, rules-based engine may perform processing to deliver tailored customer experiences, relying on values for prioritized experiences identified through use of the computer aid.Type: GrantFiled: March 26, 2004Date of Patent: January 24, 2012Assignee: Accenture Global Services LimitedInventors: Robert E. Wollan, Tore Berg, Vincent U. Dell'Anno, Julio J. Hernandez, Alyse S. Kornfeld, Steven L. Lew, Dawn E. Palmer, Kevin N. Quiring, David A. Shapiro, David Slaw, Sajid Usman, Rodney B. Whitsett
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Patent number: 8092163Abstract: A reaction mount system that provides support for the stator vane for a gas turbine engine is described comprising a stator hanger located on an outer band at a first location and a stator stopper located at a second location that is located circumferentially apart from the first location. A stator assembly for a gas turbine engine is described, the stator assembly comprising a stator vane having an airfoil, an outer band located on a radially outer end of the airfoil, a shroud hanger located axially adjacent to the outer band, the shroud hanger comprising a post wherein at least a portion of the post extends in an axial direction over a portion of the outer band, and a reaction mount system located on the outer band wherein the reaction mount system engages with the post to provide support for the stator vane.Type: GrantFiled: March 31, 2008Date of Patent: January 10, 2012Assignee: General Electric CompanyInventors: Jason David Shapiro, Victor Hugo Silva Correia
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Patent number: 8079807Abstract: A turbine shroud apparatus is provided for a gas turbine engine having a central axis. The apparatus includes: (a) an annular support member; (b) a turbine shroud disposed in the support member, the shroud being a continuous ring comprising a low-ductility material and having opposed flowpath and back surfaces, and opposed forward and aft ends; and (c) a spring mounted between the support member and the shroud and arranged to resiliently urge the shroud to a concentric position within the structural member.Type: GrantFiled: January 29, 2010Date of Patent: December 20, 2011Assignee: General Electric CompanyInventors: Jason David Shapiro, Roger Lee Doughty, Aaron Dziech, Victor Correia, Elias Lampes, Robert Carella, Brian Corsetti
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Publication number: 20110189009Abstract: A turbine shroud apparatus is provided for a gas turbine engine having a central axis. The apparatus includes: (a) an annular support member; (b) a turbine shroud disposed in the support member, the shroud being a continuous ring comprising a low-ductility material and having opposed flowpath and back surfaces, and opposed forward and aft ends; and (c) a spring mounted between the support member and the shroud and arranged to resiliently urge the shroud to a concentric position within the structural member.Type: ApplicationFiled: January 29, 2010Publication date: August 4, 2011Applicant: GENERAL ELECTRIC COMPANYInventors: Jason David Shapiro, Roger Lee Doughty, Aaron Dziech, Victor Correia, Elias Lampes, Robert Carella, Brian Corsetti
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Publication number: 20110178099Abstract: The present invention relates to a pharmaceutical combination which may be useful for the treatment of diseases which involve cell proliferation, which involve migration or apoptosis of myeloma cells, which involve angiogenesis or which involve fibrosis. The invention also relates to a method for the treatment of said diseases, comprising simultaneous, separate or sequential administration of effective amounts of specific active compounds and/or co-treatment with radiation therapy, in a ratio which provides an additive and synergistic effect, and to the combined use of these specific compounds and/or radiotherapy for the manufacture of corresponding pharmaceutical combination preparations.Type: ApplicationFiled: June 4, 2009Publication date: July 21, 2011Applicant: BOEHRINGER INGELHEIM INTERNATIONAL GMBHInventors: Martin Friedrich Stefanic, Frank Hilberg, Rolf Kaiser, David Shapiro
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Patent number: 7946801Abstract: A cooling arrangement for a gas turbine engine includes: (a) a turbine nozzle having: (i) spaced-apart arcuate inner and outer bands; and (ii) a hollow, airfoil-shaped turbine vane extending between the inner and outer bands, the vane disposed in a primary flowpath of the engine; (b) a supporting structure coupled to the outer band such that an outer band cavity is defined between the outer band and the stationary structure; (c) a first conduit passing through the outer band cavity and communicating with the interior of the vane, the first conduit coupled to a first source of cooling air within the engine; and (d) a second conduit communicating with the outer band cavity, the second conduit coupled to a second source of cooling air within the engine.Type: GrantFiled: December 27, 2007Date of Patent: May 24, 2011Assignee: General Electric CompanyInventors: Jason David Shapiro, David Allen Flodman, Samuel Ross Rulli, Samir Dimitri Sayegh, Norman Clement Brackett
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Publication number: 20100281879Abstract: A cooling arrangement for a gas turbine engine includes: (a) a turbine nozzle having: (i) spaced-apart arcuate inner and outer bands; and (ii) a hollow, airfoil-shaped turbine vane extending between the inner and outer bands, the vane disposed in a primary flowpath of the engine; (b) a supporting structure coupled to the outer band such that an outer band cavity is defined between the outer band and the stationary structure; (c) a first conduit passing through the outer band cavity and communicating with the interior of the vane, the first conduit coupled to a first source of cooling air within the engine; and (d) a second conduit communicating with the outer band cavity, the second conduit coupled to a second source of cooling air within the engine.Type: ApplicationFiled: December 27, 2007Publication date: November 11, 2010Applicant: General Electric CompanyInventors: Jason David Shapiro, David Allen Flodman, Samuel Ross Rulli, Samir Dimitri Sayegh, Norman Clement Brackett
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Publication number: 20100111670Abstract: A shroud hanger for a gas turbine engine has an arcuate body with opposed inner and outer faces and opposed forward and aft ends, the channel having at least one cooling passage therein which includes: (a) a generally axially-aligned channel extending through the body, the channel having one end open to an exterior of the body; and (b) a generally radially-aligned diffuser extending through the inner face and intersecting the channel.Type: ApplicationFiled: October 31, 2008Publication date: May 6, 2010Applicant: General Electric CompanyInventor: Jason David Shapiro
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Publication number: 20090246014Abstract: A method and system of supporting removable static components in a turbine engine stator assembly is described. The method comprises the steps of engaging a stator hanger located at a first location on a first static component with a post located on a first static structure whereby the post supports at least a part of the weight of the first static component, engaging a stator stopper located at a second location on the first static component that is located circumferentially apart from the first location with the stator hanger that is located on a second static component, and engaging a hook located at a third location on the first static component with a second static structure whereby the second static structure supports at least a part of the weight of the first static component.Type: ApplicationFiled: March 31, 2008Publication date: October 1, 2009Inventors: Jason David Shapiro, Victor Hugo Silva Correia
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Publication number: 20090245999Abstract: A turbine nozzle for a gas turbine engine includes: (a) spaced-apart arcuate inner and outer bands; (b) a hollow, airfoil-shaped turbine vane extending between the inner and outer bands, the interior of the vane defining at least a forward cavity and a mid-cavity positioned aft of the forward cavity; (c) a hollow impingement insert received inside the mid-cavity, the impingement insert having walls which are pierced with at least one impingement cooling hole; (d) a passage in the turbine vane at a radially outer end of the forward cavity adapted to be coupled to a source of cooling air; and (e) a passage in the inner band in fluid communication with a radially inner end of the forward cavity and a radially inner end of the impingement insert.Type: ApplicationFiled: March 25, 2008Publication date: October 1, 2009Applicant: GENERAL ELECTRIC COMPANYInventors: David Allen Flodman, Jason David Shapiro, Robert Francis Manning, Mark Douglas Gledhill, Tyler Frederick Hooper
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Publication number: 20090246012Abstract: A reaction mount system that provides support for the stator vane for a gas turbine engine is described comprising a stator hanger located on an outer band at a first location and a stator stopper located at a second location that is located circumferentially apart from the first location. A stator assembly for a gas turbine engine is described, the stator assembly comprising a stator vane having an airfoil, an outer band located on a radially outer end of the airfoil, a shroud hanger located axially adjacent to the outer band, the shroud hanger comprising a post wherein at least a portion of the post extends in an axial direction over a portion of the outer band, and a reaction mount system located on the outer band wherein the reaction mount system engages with the post to provide support for the stator vane.Type: ApplicationFiled: March 31, 2008Publication date: October 1, 2009Inventors: Jason David Shapiro, Victor Hugo Silva Correia
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Publication number: 20090220331Abstract: A turbine nozzle segment includes: (a) an arcuate outer band segment; (b) a hollow, airfoil-shaped turbine vane extending radially inward from the outer band segment; (c) a manifold cover secured to the outer band such that the manifold cover and the outer band segment cooperatively define an impingement cavity; and (d) an impingement blanket disposed in the impingement cavity, the impingement blanket having at least one impingement hole formed therethrough which is arranged to direct cooling air at the outer band segment. A method is provided for impingement cooling the outer band segment.Type: ApplicationFiled: February 29, 2008Publication date: September 3, 2009Applicant: General Electric CompanyInventors: Jason David Shapiro, David Allen Flodman
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Patent number: D655063Type: GrantFiled: April 29, 2011Date of Patent: February 28, 2012Assignee: Lifeline Scientific, Inc.Inventors: David Kravitz, Aaron Randall Ferber, Ross Lockwood, Rodney Hal Monson, Evan David Shapiro
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Patent number: D671653Type: GrantFiled: April 29, 2011Date of Patent: November 27, 2012Assignee: Lifeline Scientific, Inc.Inventors: David Kravitz, Aaron Randall Ferber, Ross Lockwood, Rodney Hal Monson, Evan David Shapiro