Patents by Inventor KARL ENGEL
KARL ENGEL 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: 20250003707Abstract: In one embodiment, a method of automated missile launcher reloading includes positioning a canister positioning device proximate to a canister. The canister positioning device is coupled to a pivot arm by one or more pivot joints and the pivot arm is coupled to a tower. The method also includes coupling the canister positioning device to the canister, attaching a hoist cable to the canister, and raising the pivot arm on the tower from a first position on the tower to a second position on the tower. The method further includes adjusting a positioning of the pivot arm to position the canister proximate to a launcher cell, adjusting a positioning of the pivot joints to align the canister with the launcher cell, and lowering the hoist cable to lower the canister into the launcher cell.Type: ApplicationFiled: November 28, 2022Publication date: January 2, 2025Inventors: Steven Wylie Mitchell, Timothy Michael Karl Engel, Weetek Foo
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Patent number: 10334897Abstract: A formulation for coating surfaces, for example gloves, with a tacky film comprises a hydrophobically modified biopolymer, where the hydrophobic modifications of the biopolymer correspond to between 1 and 90% of available functional groups, a plasticizer, and a volatile solvent. The formulation quickly dries into a tacky film that provides an enhanced friction of the surface.Type: GrantFiled: November 25, 2014Date of Patent: July 2, 2019Assignee: University of Maryland, College ParkInventors: Kevin Diehn, Chandamany Arya, Karl Engel, Matthew Furstenburg, Srinivasa R. Raghavan
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Patent number: 10041353Abstract: A blade cascade of a turbomachine whose at least one side wall is configured to be circumferentially undulated and which has at least two elevations and at least one depression or at least two depressions having at least one elevation, as well as a turbomachine having a blade cascade of this kind.Type: GrantFiled: August 6, 2014Date of Patent: August 7, 2018Assignee: MTU Aero Engines AGInventors: Jochen Gier, Yavuz Guendogdu, Karl Engel
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Patent number: 9863251Abstract: A turbomachine stage includes guide vanes and an airfoil platform forming a guide vane cascade, and rotor blades and an airfoil platform forming a rotor blade cascade. Airfoil platforms have cascade regions extending between circumferentially adjacent airfoils, and gap regions which radially and/or axially bound an axial gap extending axially between the guide vane cascade and the rotor blade cascade. A contour of at least one of these gap regions varies in the radial and/or axial direction around the circumference.Type: GrantFiled: November 28, 2012Date of Patent: January 9, 2018Assignee: MTU Aero Engines GmbHInventors: Inga Mahle, Jochen Gier, Kai Koerber, Karl Engel
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Patent number: 9745850Abstract: A blade cascade of a continuous-flow machine is disclosed. The blade cascade has at least one side wall that is constructed in a wave-like manner in the peripheral direction and has at least one elevation and at least one depression. At least a profile-like rib is integrated in or combined with the side wall, which has a blade profile with a pressure side and with an opposite suction side. A continuous-flow machine with such a blade cascade is also disclosed.Type: GrantFiled: May 23, 2014Date of Patent: August 29, 2017Assignee: MTU Aero Engines AGInventors: Yavuz Guendogdu, Jochen Gier, Karl Engel
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Patent number: 9453415Abstract: A blade cascade for a continuous-flow machine having a non-axisymmetrical side wall contour, whereby the side wall contour has at least one suction-side depression that, in the circumferential direction, is at a distance from a suction-side wall, and having a section located upstream from the leading edges and a section located downstream from the leading edges, it has a pressure-side elevation that makes a transition to a pressure-side wall and that is located in a front blade area, and it has a pressure-side depression that is located upstream from the pressure-side elevation, and also discloses a continuous-flow machine having such a blade cascade.Type: GrantFiled: July 31, 2013Date of Patent: September 27, 2016Assignee: MTU Aero Engines GmbHInventor: Karl Engel
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Publication number: 20150147468Abstract: A formulation for coating surfaces, for example gloves, with a tacky film comprises a hydrophobically modified biopolymer, where the hydrophobic modifications of the biopolymer correspond to between 1 and 90% of available functional groups, a plasticizer, and a volatile solvent. The formulation quickly dries into a tacky film that provides an enhanced friction of the surface.Type: ApplicationFiled: November 25, 2014Publication date: May 28, 2015Inventors: Kevin Diehn, Chandamany Arya, Karl Engel, Matthew Furstenburg, Srinivasa R. Raghavan
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Publication number: 20150044038Abstract: A blade cascade of a turbomachine whose at least one side wall is configured to be circumferentially undulated and which has at least two elevations and at least one depression or at least two depressions having at least one elevation, as well as a turbomachine having a blade cascade of this kind.Type: ApplicationFiled: August 6, 2014Publication date: February 12, 2015Inventors: Jochen Gier, Yavuz Guendogdu, Karl Engel
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Publication number: 20140348661Abstract: A blade row for a turbomachine is disclosed. The blade row has an inner lateral wall and an outer lateral wall for bordering a hot gas channel in the turbomachine through which hot gas passes. At least one of the lateral walls has a rounded lateral wall front edge, which is provided with a circumferentially asymmetrical edge contouring that is elliptical or is comprised of one or more segments of a circle.Type: ApplicationFiled: May 23, 2014Publication date: November 27, 2014Applicant: MTU Aero Engines AGInventors: Inga MAHLE, Martin Pernleitner, Karl Engel
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Publication number: 20140348660Abstract: A blade cascade of a continuous-flow machine is disclosed. The blade cascade has at least one side wall that is constructed in a wave-like manner in the peripheral direction and has at least one elevation and at least one depression. At least a profile-like rib is integrated in or combined with the side wall, which has a blade profile with a pressure side and with an opposite suction side. A continuous-flow machine with such a blade cascade is also disclosed.Type: ApplicationFiled: May 23, 2014Publication date: November 27, 2014Applicant: MTU Aero Engines AGInventors: Yavuz GUENDOGDU, Jochen Gier, Karl Engel
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Publication number: 20140037453Abstract: A blade cascade for a continuous-flow machine having a non-axisymmetrical side wall contour, whereby the side wall contour has at least one suction-side depression that, in the circumferential direction, is at a distance from a suction-side wall, and having a section located upstream from the leading edges and a section located downstream from the leading edges, it has a pressure-side elevation that makes a transition to a pressure-side wall and that is located in a front blade area, and it has a pressure-side depression that is located upstream from the pressure-side elevation, and also discloses a continuous-flow machine having such a blade cascade.Type: ApplicationFiled: July 31, 2013Publication date: February 6, 2014Inventor: Karl Engel
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Publication number: 20130330180Abstract: A transition duct for a turbomachine, in particular an aircraft engine, for forming a flow channel between an upstream flow cross section and a downstream flow cross section, including supporting ribs which extend between a radially inner duct wall and a radially outer duct wall and each of which has a profile for deflecting a flow from an inlet area to an outlet area of the transition duct, the supporting ribs each having a profile variation in the area of their trailing edge and/or at least one blow-out opening for blowing out a fluid; also disclosed is a turbomachine having a transition duct of this type.Type: ApplicationFiled: May 29, 2013Publication date: December 12, 2013Inventors: Yavuz Guendogdu, Karl Engel
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Publication number: 20130051996Abstract: A transition channel for a turbine unit with at least two components is configured as a flow channel from one component of a first pressure to a component of a second pressure. The transition channel has support ribs, extending between envelope surfaces of the transition channel and having a profile that is configured for the deflecting of a flow from an inlet cross section to an outlet cross section of the transition channel. Flow splitter blades are arranged between the support ribs, having a smaller relative profile thickness than the support ribs and/or a shorter axial design depth or profile chord length than the support ribs. Thanks to the integration of the slim and/or short flow splitter blades (tandem blades), it is possible to largely dissipate parasite secondary flows.Type: ApplicationFiled: August 29, 2012Publication date: February 28, 2013Applicant: MTU AERO ENGINES GMBHInventors: MARTIN HOEGER, KAI KOERBER, KARL ENGEL