Patents by Inventor Benjamin E. Heneveld

Benjamin E. Heneveld 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).

  • Publication number: 20240087839
    Abstract: A workpiece mounting system comprising a chuck and a base is disclosed. The emissivity of the base is increased to allow more heat transfer from the chuck to the base. In some embodiments, the emissivity of the base may be controllable so that for ion beams with lower power levels, the emissivity remains low, enabling the chuck to reach the desired temperature quickly. For ion beams with higher power levels, the emissivity may increase to allow more heat transfer to the base, allowing the chuck to maintain the desired temperature. High emissivity coatings may be applied to the top surface of the base. In other embodiments, a set of movable shields may be disposed between the chuck and the base. The position of the shields may be a function of the power level of the incoming ion beam.
    Type: Application
    Filed: September 13, 2022
    Publication date: March 14, 2024
    Inventors: Dawei Sun, Eric D. Hermanson, Benjamin E. Heneveld
  • Patent number: 11229950
    Abstract: A method of forming an article including: contacting a fugitive tool with a powdered parent material; densifying the powdered material; and destructively removing the fugitive tool. A coating of a different material may be formed against the parent material using a similar approach.
    Type: Grant
    Filed: April 23, 2018
    Date of Patent: January 25, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: John R. Paulus, Jon T. Moore, Benjamin E. Heneveld
  • Publication number: 20180304362
    Abstract: A method of forming an article including: contacting a fugitive tool with a powdered parent material; densifying the powdered material; and destructively removing the fugitive tool. A coating of a different material may be formed against the parent material using a similar approach.
    Type: Application
    Filed: April 23, 2018
    Publication date: October 25, 2018
    Inventors: John R. Paulus, Jon T. Moore, Benjamin E. Heneveld
  • Patent number: 9551227
    Abstract: A cooling channel (36, 36B) cools an exterior surface (40 or 42) or two opposed exterior surfaces (40 and 42). The channel has a near-wall inner surface (48, 50) with a width (W1). Interior side surfaces (52, 54) may converge to a reduced channel width (W2). The near-wall inner surface (48, 50) may have fins (44) aligned with a coolant flow (22). The fins may highest at mid-width of the near-wall inner surface. A two-sided cooling channel (36) may have two near-wall inner surfaces (48, 50) parallel to two respective exterior surfaces (40, 42), and may have an hourglass shaped transverse sectional profile. The tapered channel width (W1, W2) and the fin height profile (56A, 56B) increases cooling flow (22) into the corners (C) of the channel for more uniform and efficient cooling.
    Type: Grant
    Filed: June 9, 2014
    Date of Patent: January 24, 2017
    Assignees: Mikro Systems, Inc., Siemens Energy, Inc.
    Inventors: Ching-Pang Lee, John J. Marra, Gary B. Merrill, Benjamin E. Heneveld, Jill Klinger
  • Patent number: 9039371
    Abstract: A gas turbine engine component, including: a pressure side (12) having an interior surface (34); a suction side (14) having an interior surface (36); a trailing edge portion (30); and a plurality of suction side and pressure side impingement orifices (24) disposed in the trailing edge portion (30). Each suction side impingement orifice is configured to direct an impingement jet (48) at an acute angle (52) onto a target area (60) that encompasses a tip (140) of a chevron (122) within a chevron arrangement (120) formed in the suction side interior surface. Each pressure side impingement orifice is configured to direct an impingement jet at an acute angle onto an elongated target area that encompasses a tip of a chevron within a chevron arrangement formed in the pressure side interior surface.
    Type: Grant
    Filed: October 31, 2013
    Date of Patent: May 26, 2015
    Assignees: SIEMENS AKTIENGESELLSCHAFT, MIKRO SYSTEMS, INC.
    Inventors: Ching-Pang Lee, Benjamin E. Heneveld, Glenn E. Brown, Jill Klinger
  • Publication number: 20150118034
    Abstract: A gas turbine engine component, including: a pressure side (12) having an interior surface (34); a suction side (14) having an interior surface (36); a trailing edge portion (30); and a plurality of suction side and pressure side impingement orifices (24) disposed in the trailing edge portion (30). Each suction side impingement orifice is configured to direct an impingement jet (48) at an acute angle (52) onto a target area (60) that encompasses a tip (140) of a chevron (122) within a chevron arrangement (120) formed in the suction side interior surface. Each pressure side impingement orifice is configured to direct an impingement jet at an acute angle onto an elongated target area that encompasses a tip of a chevron within a chevron arrangement formed in the pressure side interior surface.
    Type: Application
    Filed: October 31, 2013
    Publication date: April 30, 2015
    Inventors: Ching-Pang Lee, Benjamin E. Heneveld, Glenn E. Brown, Jill Klinger
  • Patent number: 9004866
    Abstract: A turbine blade (10) including an airfoil (12) having multiple interior wall portions (70) each separating at least one chamber from another one of multiple chambers (46, 48, 50, 58, 60). In one embodiment a first wall portion (70-2) between first and second chambers (60, 52) includes first and second pluralities of flow paths (86P, 86S) extending through the first wall portion. The first wall portion includes a first region R1 having a first thickness, t, measurable as a distance between the chambers. One of the paths extends a first path distance, d, as measured from an associated path opening (78) in the first chamber (60), through the first region and to an exit opening (82) in the second chamber (52) which path distance is greater than the first thickness.
    Type: Grant
    Filed: December 6, 2011
    Date of Patent: April 14, 2015
    Assignees: Siemens Aktiengesellschaft, Mikro Systems, Inc.
    Inventors: Ching-Pang Lee, Glenn E. Brown, Benjamin E. Heneveld
  • Patent number: 8951004
    Abstract: A cooling arrangement (82) for a gas turbine engine component, the cooling arrangement (82) having a plurality of rows (92, 94, 96) of airfoils (98), wherein adjacent airfoils (98) within a row (92, 94, 96) define segments (110, 130, 140) of cooling channels (90), and wherein outlets (114, 134) of the segments (110, 130) in one row (92, 94) align aerodynamically with inlets (132, 142) of segments (130, 140) in an adjacent row (94, 96) to define continuous cooling channels (90) with non continuous walls (116, 120), each cooling channel (90) comprising a serpentine shape.
    Type: Grant
    Filed: October 23, 2012
    Date of Patent: February 10, 2015
    Assignees: Siemens Aktiengesellschaft, Mikro Systems, Inc.
    Inventors: Ching-Pang Lee, Benjamin E. Heneveld
  • Patent number: 8936067
    Abstract: A ceramic casting core, including: a plurality of rows (162, 166, 168) of gaps (164), each gap (164) defining an airfoil shape; interstitial core material (172) that defines and separates adjacent gaps (164) in each row (162, 166, 168); and connecting core material (178) that connects adjacent rows (170, 174, 176) of interstitial core material (172). Ends of interstitial core material (172) in one row (170, 174, 176) align with ends of interstitial core material (172) in an adjacent row (170, 174, 176) to form a plurality of continuous and serpentine shaped structures each including interstitial core material (172) from at least two adjacent rows (170, 174, 176) and connecting core material (178).
    Type: Grant
    Filed: October 23, 2012
    Date of Patent: January 20, 2015
    Assignees: Siemens Aktiengesellschaft, Mikro Systems, Inc.
    Inventors: Ching-Pang Lee, Benjamin E. Heneveld
  • Publication number: 20140286791
    Abstract: A cooling channel (36, 36B) cools an exterior surface (40 or 42) or two opposed exterior surfaces (40 and 42). The channel has a near-wall inner surface (48, 50) with a width (W1). Interior side surfaces (52, 54) may converge to a reduced channel width (W2). The near-wall inner surface (48, 50) may have fins (44) aligned with a coolant flow (22). The fins may highest at mid-width of the near-wall inner surface. A two-sided cooling channel (36) may have two near-wall inner surfaces (48, 50) parallel to two respective exterior surfaces (40, 42), and may have an hourglass shaped transverse sectional profile. The tapered channel width (W1, W2) and the fin height profile (56A, 56B) increases cooling flow (22) into the corners (C) of the channel for more uniform and efficient cooling.
    Type: Application
    Filed: June 9, 2014
    Publication date: September 25, 2014
    Inventors: Ching-Pang Lee, John J. Marra, Gary B. Merrill, Benjamin E. Heneveld, Jill Klinger
  • Patent number: 8764394
    Abstract: A cooling channel (36, 36B) cools an exterior surface (40 or 42) or two opposed exterior surfaces (40 and 42). The channel has a near-wall inner surface (48, 50) with a width (W1). Interior side surfaces (52, 54) may converge to a reduced channel width (W2). The near-wall inner surface (48, 50) may have fins (44) aligned with a coolant flow (22). The fins may highest at mid-width of the near-wall inner surface. A two-sided cooling channel (36) may have two near-wall inner surfaces (48, 50) parallel to two respective exterior surfaces (40, 42), and may have an hourglass shaped transverse sectional profile. The tapered channel width (W1, W2) and the fin height profile (56A, 56B) increases cooling flow (22) into the corners (C) of the channel for more uniform and efficient cooling.
    Type: Grant
    Filed: January 6, 2011
    Date of Patent: July 1, 2014
    Assignees: Siemens Energy, Inc., Mikro Systems, Inc.
    Inventors: Ching-Pang Lee, John J. Marra, Gary B. Merrill, Benjamin E. Heneveld, Jill Klinger
  • Publication number: 20140110559
    Abstract: A ceramic casting core, including: a plurality of rows (162, 166, 168) of gaps (164), each gap (164) comprising an airfoil shape; interstitial core material (172) that defines and separates adjacent gaps (164) in each row (162, 166, 168); and connecting core material (178) that connects adjacent rows (170, 174, 176) of interstitial core material (172). Ends of interstitial core material (172) in one row (170, 174, 176) align with ends of interstitial core material (172) in an adjacent row (170, 174, 176) to form a plurality of continuous and serpentine shaped structures each comprising interstitial core material (172) from at least two adjacent rows (170, 174, 176) and connecting core material (178).
    Type: Application
    Filed: October 23, 2012
    Publication date: April 24, 2014
    Inventors: CHING-PANG LEE, BENJAMIN E. HENEVELD
  • Publication number: 20140112799
    Abstract: A cooling arrangement (82) for a gas turbine engine component, the cooling arrangement (82) having a plurality of rows (92, 94, 96) of airfoils (98), wherein adjacent airfoils (98) within a row (92, 94, 96) define segments (110, 130, 140) of cooling channels (90), and wherein outlets (114, 134) of the segments (110, 130) in one row (92, 94) align aerodynamically with inlets (132, 142) of segments (130, 140) in an adjacent row (94, 96) to define continuous cooling channels (90) with non continuous walls (116, 120), each cooling channel (90) comprising a serpentine shape.
    Type: Application
    Filed: October 23, 2012
    Publication date: April 24, 2014
    Inventors: CHING-PANG LEE, BENJAMIN E. HENEVELD
  • Publication number: 20130333855
    Abstract: An investment casting process wherein the wax pattern tool (42) is flexible to provide compliant support for an enclosed ceramic core (10) and to facilitate removal of the tool from the cast wax pattern (52) even when the cast shape would otherwise require multiple pull planes. Positioning pins (106) may extend from the flexible tool to make compliant contact against the core during the wax injection step. The pins may cooperate with a pedestal (128) formed on the core to support the core along multiple axes during wax injection, thereby allowing a higher wax injection pressure without damage to the core.
    Type: Application
    Filed: May 3, 2013
    Publication date: December 19, 2013
    Inventors: GARY B. MERRILL, Allister Williams James, Kevin C. Sheehan, Benjamin E. Heneveld, Iain Alasdair Fraser
  • Publication number: 20130142666
    Abstract: A turbine blade (10) including an airfoil (12) having multiple interior wall portions (70) each separating at least one chamber from another one of multiple chambers (46, 48, 50, 58, 60). In one embodiment a first wall portion (70-2) between first and second chambers (60, 52) includes first and second pluralities of flow paths (86P, 86S) extending through the first wall portion. The first wall portion includes a first region R1 having a first thickness, t, measurable as a distance between the chambers. One of the paths extends a first path distance, d, as measured from an associated path opening (78) in the first chamber (60), through the first region and to an exit opening (82) in the second chamber (52) which path distance is greater than the first thickness.
    Type: Application
    Filed: December 6, 2011
    Publication date: June 6, 2013
    Inventors: Ching-Pang Lee, Glenn E. Brown, Benjamin E. Heneveld
  • Publication number: 20110132564
    Abstract: An investment casting process wherein the wax pattern tool (44) is flexible to facilitate removal of the tool from the cast wax pattern (52) even when the cast shape would otherwise require multiple pull planes. The flexible tool may include a flexible insert (42) precisely indexed to a surrounding coffin mold (40), and thereby to an enclosed ceramic core (10). Positioning pins (106) may extend from the flexible tool to make compliant contact against the core prior to a wax injection step. The surface of the resulting wax pattern may contain an engineered topography (36) replicated through the flexible surface from a master tool (12). The flexible tool may encase thermally conductive or magnetic particles (92), or other active device (96) such as a sensor or vibrator which is operable during wax injection.
    Type: Application
    Filed: December 7, 2010
    Publication date: June 9, 2011
    Inventors: Gary B. Merrill, Allister W. James, Andrew J. Burns, Kevin C. Sheehan, Benjamin E. Heneveld, Iain A. Fraser