Patents by Inventor Daniel Edward Mollmann

Daniel Edward Mollmann 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).

  • Patent number: 11111815
    Abstract: An airfoil defining a span extending between a root and a tip and a chord at each point along the span extending between a leading edge and a trailing edge. The airfoil includes a frangible airfoil portion at the tip extending between the leading edge and the trailing edge and extending between the tip and a frangible line along the span. The frangible airfoil portion includes an exterior surface. The exterior surface at least partially defines at least one fusion cavity at least partially defining the frangible line. The airfoil further includes a residual airfoil portion extending from the frangible line to the root along the span. The residual airfoil portion meets the frangible airfoil portion at the frangible line. As such, the frangible airfoil portion deforms or partially or fully detaches relative to the residual airfoil portion at the frangible line following an event creating imbalance.
    Type: Grant
    Filed: October 16, 2018
    Date of Patent: September 7, 2021
    Assignee: General Electric Company
    Inventors: Nicholas Joseph Kray, Nitesh Jain, Daniel Edward Mollmann
  • Patent number: 10920607
    Abstract: A blade for a propulsion apparatus. The blade includes a body having opposed pressure and suction sides. The blade extends in span between a root and a tip and the blade extends in chord between a leading edge and a trailing edge. The blade includes a fracture structure that is defined within the body and positioned such that it is spaced-away from the tip. The fracture structure includes at least one chamber. A first fracture wall is disposed between the at least one chamber and the pressure side, and a second fracture wall is disposed between the at least one chamber and the suction side. The fracture structure is configured to fail when a predetermined force is applied to the tip such that the tip separates from the remainder of the body.
    Type: Grant
    Filed: September 28, 2018
    Date of Patent: February 16, 2021
    Assignee: General Electric Company
    Inventors: Nitesh Jain, Kishore Budumuru, Nicholas Joseph Kray, Daniel Edward Mollmann
  • Publication number: 20200116045
    Abstract: An airfoil defining a span extending between a root and a tip and a chord at each point along the span extending between a leading edge and a trailing edge. The airfoil includes a frangible airfoil portion at the tip extending between the leading edge and the trailing edge and extending between the tip and a frangible line along the span. The frangible airfoil portion includes an exterior surface. The exterior surface at least partially defines at least one fusion cavity at least partially defining the frangible line. The airfoil further includes a residual airfoil portion extending from the frangible line to the root along the span. The residual airfoil portion meets the frangible airfoil portion at the frangible line. As such, the frangible airfoil portion deforms or partially or fully detaches relative to the residual airfoil portion at the frangible line following an event creating imbalance.
    Type: Application
    Filed: October 16, 2018
    Publication date: April 16, 2020
    Inventors: Nicholas Joseph Kray, Nitesh Jain, Daniel Edward Mollmann
  • Publication number: 20200116044
    Abstract: An airfoil defining a span extending between a root and a tip. The airfoil includes a frangible airfoil portion extending between a leading edge and a trailing edge and extending between the tip and a fusion line along the span. The frangible airfoil portion includes a first material defining a first modulus of elasticity and further defines an internal cavity. The airfoil includes a residual airfoil portion coupled to the frangible airfoil portion extending from the fusion line to the root along the span and including a second material defining a second modulus of elasticity greater than the first modulus of elasticity. The residual airfoil portion meets the frangible airfoil portion at the fusion line.
    Type: Application
    Filed: October 16, 2018
    Publication date: April 16, 2020
    Inventors: Nitesh Jain, David William Crall, Nicholas Joseph Kray, Daniel Edward Mollmann
  • Patent number: 10422348
    Abstract: A containment structure comprising an annular structure configured to provide close tolerance to a rotation structure. The containment structure includes a first abradable structure, a second abradable structure, and a shroud that is defined in part by the first abradable structure and in part by the second abradable structure. An annular surface of the shroud is defined by the first abradable structure and by the second abradable structure. The first abradable structure is harder than the second abradable structure.
    Type: Grant
    Filed: January 10, 2017
    Date of Patent: September 24, 2019
    Assignee: General Electric Company
    Inventors: Nicholas Joseph Kray, Daniel Edward Mollmann, Andrew Breeze-Stringfellow
  • Publication number: 20190063747
    Abstract: A method for operating a gas turbine engine includes receiving data indicative of an operational vibration within a section of the gas turbine engine; and providing electrical power to a shaker mechanically coupled to one or more components of the section of the gas turbine engine to generate a canceling vibration to reduce or minimize the operational vibration within the section of the gas turbine engine.
    Type: Application
    Filed: August 29, 2017
    Publication date: February 28, 2019
    Inventor: Daniel Edward Mollmann
  • Publication number: 20180195527
    Abstract: A containment structure comprising an annular structure configured to provide close tolerance to a rotation structure. The containment structure includes a first abradable structure, a second abradable structure, and a shroud that is defined in part by the first abradable structure and in part by the second abradable structure. An annular surface of the shroud is defined by the first abradable structure and by the second abradable structure. The first abradable structure is harder than the second abradable structure.
    Type: Application
    Filed: January 10, 2017
    Publication date: July 12, 2018
    Inventors: Nicholas Joseph Kray, Daniel Edward Mollmann, Andrew Breeze-Stringfellow
  • Patent number: 9121294
    Abstract: A gas turbine engine airfoil includes leading and trailing edges, pressure and suction sides extending from airfoil base to airfoil tip, trailing edge cladding made of cladding material bonded to composite core made of composite material, cladding material less brittle than composite material, composite core including central core portion extending downstream from leading edge portion to trailing edge portion of composite core, and trailing edge cladding including wavy wall and trailing edge. Pressure and suction side flanks of trailing edge cladding may be bonded to pressure and suction side surfaces of trailing edge portion. Waves of wavy wall may extend normal to and away from the pressure and suction side surfaces. Trailing edge cladding may include wavy pressure and suction side trailing edge guards including waves of wavy wall. Airfoil may extend outwardly from platform of a blade. Root may include integral dovetail.
    Type: Grant
    Filed: December 20, 2011
    Date of Patent: September 1, 2015
    Assignee: General Electric Company
    Inventors: Nicholas Joseph Kray, Daniel Edward Mollmann, Dong-Jin Shim, Trevor Howard Wood
  • Publication number: 20130156592
    Abstract: A gas turbine engine airfoil includes leading and trailing edges, pressure and suction sides extending from airfoil base to airfoil tip, trailing edge cladding made of cladding material bonded to composite core made of composite material, cladding material less brittle than composite material, composite core including central core portion extending downstream from leading edge portion to trailing edge portion of composite core, and trailing edge cladding including wavy wall and trailing edge. Pressure and suction side flanks of trailing edge cladding may be bonded to pressure and suction side surfaces of trailing edge portion. Waves of wavy wall may extend normal to and away from the pressure and suction side surfaces. Trailing edge cladding may include wavy pressure and suction side trailing edge guards including waves of wavy wall. Airfoil may extend outwardly from platform of a blade. Root may include integral dovetail.
    Type: Application
    Filed: December 20, 2011
    Publication date: June 20, 2013
    Inventors: Nicholas Joseph Kray, Daniel Edward Mollmann, Dong-Jin Shim, Trevor Howard Wood
  • Patent number: 8313279
    Abstract: Vibration is monitored in a dual rotor engine. A first total vibration of the engine is measured during operation. Relative phase of the two rotors is then clocked, and a second total vibration of the engine is then measured during operation. First and second total unbalances are then resolved at a common response frequency from the measured total vibrations. First and second rotor unbalances are then resolved for the corresponding rotors from the first and second total unbalances. In a further method, corresponding corrective balance weights may be determined for offsetting the resolved rotor unbalances.
    Type: Grant
    Filed: April 21, 2008
    Date of Patent: November 20, 2012
    Assignee: General Electric Company
    Inventor: Daniel Edward Mollmann
  • Patent number: 8180596
    Abstract: A processor-implemented method of assembling a rotatable machine is provided. The machine includes a plurality of blades that extend radially outwardly from a rotor. The method includes determining a geometric parameter for each blade in a row of blades that is relative to a ratio, R of an inlet area and an outlet area of a predetermined volume defined between each pair of blades, determining an initial sequence map for the row of blades that facilitates minimizing a difference of R between circumferentially adjacent pairs of blades, and iteratively remapping the sequence of the blades to facilitate reducing a moment weight vector sum of the rotor to a value that is less than a predetermined value.
    Type: Grant
    Filed: July 13, 2004
    Date of Patent: May 15, 2012
    Assignee: General Electric Company
    Inventors: Thomas Richard Henning, John Douglas Mickol, Daniel Edward Mollmann, Michael Harvey Schneider
  • Patent number: 7972109
    Abstract: A method for fabricating a fan assembly is provided, wherein the method includes providing a rotor having a plurality of rotor blades. At least one rotor blade is fabricated from a frangible material. The method also includes coupling a casing substantially circumferentially about the rotor, and positioning the casing a distance from the plurality of rotor blades. The distance is selected to facilitate increasing an amount of initial resistance created between the casing and the plurality of rotor blades after a bladeout.
    Type: Grant
    Filed: December 28, 2006
    Date of Patent: July 5, 2011
    Assignee: General Electric Company
    Inventors: David William Crall, Frank Worthoff, Daniel Edward Mollmann, Nicholas Joseph Kray, Max Farson
  • Patent number: 7920973
    Abstract: Embodiments described herein generally relate to a method of measuring the vibration of an aircraft engine. One embodiment herein provides an engine monitoring system either connected to and/or positioned in close proximity to an aircraft engine. Also provided is a clearance measuring device within the engine monitoring system. The clearanceometer collects clearance data that is later converted into vibration data.
    Type: Grant
    Filed: December 21, 2006
    Date of Patent: April 5, 2011
    Assignee: General Electric Company
    Inventors: Daniel Edward Mollmann, Tod R. Steen
  • Patent number: 7780410
    Abstract: A method of assembling a gas turbine engine includes providing at least one blade assembly. The method also includes forming at least one blade tip fuse within at least a portion of the at least one blade assembly. The method further includes coupling the at least one blade assembly into the gas turbine engine. The blade assembly includes an airfoil and a metal leading edge (MLE) coupled to at least a portion of the airfoil. The MLE includes the at least one blade tip fuse.
    Type: Grant
    Filed: December 27, 2006
    Date of Patent: August 24, 2010
    Assignee: General Electric Company
    Inventors: Nicholas Joseph Kray, David William Crall, Daniel Edward Mollmann
  • Patent number: 7685876
    Abstract: Methods and systems of balancing a rotatable member are provided. A method includes separately balancing a first portion and a second portion of the rotatable member wherein the second portion mateable to said first portion, coupling the first and second portions to each other, measuring a physical dimension of the coupled first and second portions, and determining a balance weight magnitude and position based on the measured physical dimension.
    Type: Grant
    Filed: December 20, 2006
    Date of Patent: March 30, 2010
    Assignee: General Electric Company
    Inventors: Daniel Edward Mollmann, Steven Alan Ross, Stephen Wade Faw, Enzo Luigi Morabito, Jeffrey Scott Allen
  • Publication number: 20090263247
    Abstract: Vibration is monitored in a dual rotor engine. A first total vibration of the engine is measured during operation. Relative phase of the two rotors is then clocked, and a second total vibration of the engine is then measured during operation. First and second total unbalances are then resolved at a common response frequency from the measured total vibrations. First and second rotor unbalances are then resolved for the corresponding rotors from the first and second total unbalances. In a further method, corresponding corrective balance weights may be determined for offsetting the resolved rotor unbalances.
    Type: Application
    Filed: April 21, 2008
    Publication date: October 22, 2009
    Inventor: Daniel Edward Mollmann
  • Patent number: 7416389
    Abstract: Methods and systems for ordering blades in a rotatable machine is provided. The method includes receiving at least one geometric parameter measurement of each blade in a row of blades, determining a root sum squared value of a difference of a selected one of the received geometric parameter measurements between adjacent blades in the row of blades, determining a vector sum of a selected other one of the received geometric parameter measurements, determining a moment weight vector sum of each blade to be positioned on the rotor, and determining, using a computer, a sequence map of each blade using the root sum squared value of the difference of the geometric parameter measurement between adjacent blades in the row of blades, the vector sum of a selected other one of the received geometric parameter measurements, and the moment weight vector sum.
    Type: Grant
    Filed: November 9, 2005
    Date of Patent: August 26, 2008
    Assignee: General Electric Company
    Inventors: Thomas Richard Henning, John Douglas Mickol, Daniel Edward Mollmann
  • Publication number: 20080159854
    Abstract: A method for fabricating a fan assembly is provided, wherein the method includes providing a rotor having a plurality of rotor blades. At least one rotor blade is fabricated from a frangible material. The method also includes coupling a casing substantially circumferentially about the rotor, and positioning the casing a distance from the plurality of rotor blades. The distance is selected to facilitate increasing an amount of initial resistance created between the casing and the plurality of rotor blades after a bladeout.
    Type: Application
    Filed: December 28, 2006
    Publication date: July 3, 2008
    Inventors: David William Crall, Frank Worthoff, Daniel Edward Mollmann, Nicholas Joseph Kray, Max Farson
  • Publication number: 20080159868
    Abstract: A method of assembling a gas turbine engine includes providing at least one blade assembly. The method also includes forming at least one blade tip fuse within at least a portion of the at least one blade assembly. The method further includes coupling the at least one blade assembly into the gas turbine engine. The blade assembly includes an airfoil and a metal leading edge (MLE) coupled to at least a portion of the airfoil. The MLE includes the at least one blade tip fuse.
    Type: Application
    Filed: December 27, 2006
    Publication date: July 3, 2008
    Inventors: Nicholas Joseph Kray, David William Crall, Daniel Edward Mollmann
  • Publication number: 20080149049
    Abstract: Embodiments described herein generally relate to a method of measuring the vibration of an aircraft engine. One embodiment herein provides an engine monitoring system either connected to and/or positioned in close proximity to an aircraft engine. Also provided is a clearance measuring device within the engine monitoring system. The clearanceometer collects clearance data that is later converted into vibration data.
    Type: Application
    Filed: December 21, 2006
    Publication date: June 26, 2008
    Inventors: Daniel Edward Mollmann, Tod R. Steen