Patents by Inventor Markus Weinert

Markus Weinert 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: 11761340
    Abstract: A blade component of a compressor or turbine stage of a gas turbine, in particular of a gas turbine engine is provided. The blade component has at least two structural elements which can be connected together by means of a connection process, in particular sintering. The at least two structural elements can be coupled and/or connected to at least one means for internal cooling of the blade component, and/or the means for internal cooling of the blade component is arranged in at least one of the least two structural elements. The at least two structural elements, when assembled, can be coupled to a cooling insert inside the blade component, wherein during operation, cooling air flowing into the cooling insert can be guided in targeted fashion via impingement cooling openings onto the inside of the blade component, in particular as impingement flow cooling.
    Type: Grant
    Filed: December 16, 2021
    Date of Patent: September 19, 2023
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Thomas Wunderlich, Markus Weinert
  • Publication number: 20220195875
    Abstract: A blade component of a compressor or turbine stage of a gas turbine, in particular of a gas turbine engine is provided. The blade component has at least two structural elements which can be connected together by means of a connection process, in particular sintering. The at least two structural elements can be coupled and/or connected to at least one means for internal cooling of the blade component, and/or the means for internal cooling of the blade component is arranged in at least one of the least two structural elements. The at least two structural elements, when assembled, can be coupled to a cooling insert inside the blade component, wherein during operation, cooling air flowing into the cooling insert can be guided in targeted fashion via impingement cooling openings onto the inside of the blade component, in particular as impingement flow cooling.
    Type: Application
    Filed: December 16, 2021
    Publication date: June 23, 2022
    Inventors: Thomas WUNDERLICH, Markus WEINERT
  • Patent number: 10526904
    Abstract: A rotor for an engine is provided. The rotor comprising a rotor base part that has fastening grooves for rotor blades that are arranged in succession around a rotational axis along a circumferential direction, multiple rotor blades that are respectively supported in a form-fit manner inside a corresponding fastening groove by means of a blade root, and at least one securing element for the axial securing—with respect to a rotational axis of at least one of the rotor blades at the rotor base part. The at least one securing element has two edges that are arranged at a radial distance to one another and through which the securing element is supported in a form-fit manner at the rotor base part, on the one hand, and, on the other hand, at the at least one rotor blade.
    Type: Grant
    Filed: April 18, 2017
    Date of Patent: January 7, 2020
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Markus Weinert, Tobias Leymann
  • Patent number: 10450866
    Abstract: A rotor of an aircraft engine includes a disk wheel and at least two turbine blades. A damping device is arranged below a blade platform and inside a cavity between the blades in the radial direction. The cavity is formed by a respective recess at adjoining blades, with respective recesses having an outer guide surface in the radial direction, acting together with the damping device during operation of the rotor. The guide surface extends radially, from the lateral edge area of the blade to the central area of the blade. The respective recess extends circumferentially from a boundary plane defined by the lateral edge area of the blade to a side surface that delimitates the guide surface towards the blade center. The recess of at least one of the adjacent blades completely receives the damping device.
    Type: Grant
    Filed: July 22, 2016
    Date of Patent: October 22, 2019
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Markus Weinert, Tobias Leymann
  • Patent number: 10321972
    Abstract: A device for simultaneously identifying a plurality of surgical instruments or instrument groups includes a first detecting device having a first detection technology for detecting instruments and, if applicable, related instrument-specific information. The device also includes a second detecting device having a second different detection technology for detecting instruments and instrument information. Moreover, the device includes a comparing device for comparing the detection results of the two detecting devices. The comparing device outputs a positive evaluation regarding the correctness of the detected instruments if the two detection results are matching.
    Type: Grant
    Filed: February 27, 2018
    Date of Patent: June 18, 2019
    Assignee: Aesculap AG
    Inventors: Markus Weinert, Nicola Giordano, Pedro Morales, Dieter Weisshaupt
  • Patent number: 10196895
    Abstract: A cooled turbine runner for a gas turbine, in particular an aircraft engine, with turbine blades that are radially arranged at the circumferential surface of a rotor disk, wherein respectively a turbine blade is inserted with a profiled blade root into a correspondingly profiled disk finger groove at the circumferential surface of the rotor disk. A cooling device with at least one cooling air supply channel is provided, which extends at least substantially axially and at least over a part of the axial length of the blade root, and which has at least one inlet with an inlet opening at an inflow side of the blade root, wherein the inlet is embodied with a projection. A middle axis of the inlet has, in a direction oriented towards the inlet opening and in the area of the inlet opening, an extension component in the rotational direction of the rotor disk.
    Type: Grant
    Filed: July 20, 2016
    Date of Patent: February 5, 2019
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Markus Weinert, Tobias Leymann
  • Patent number: 10082031
    Abstract: A rotor of a turbine of a gas turbine, having a rotor hub and a plurality of blade platforms, each carrying at least one turbine blade, and having one each cooling air chamber for passing cooling air formed by adjacent blade platforms. At least one damping element and/or sealing element is arranged radially beneath a platform intermediate gap provided between adjacent blade platforms. The cooling air chamber and/or the platform intermediate gap are designed such that starting from a side of the blade platform facing the adjacent blade platform, at least one outflow pocket open to the platform upper side and connected to the cooling air chamber is formed, and at least one cooling air pocket opened radially inwards to the cooling air chamber is provided in the wall of the cooling air chamber and opens towards the damping element and/or the sealing element or the platform intermediate gap.
    Type: Grant
    Filed: March 3, 2016
    Date of Patent: September 25, 2018
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Markus Weinert, Tobias Leymann
  • Patent number: 10041352
    Abstract: A stator of a turbine of a gas turbine, having a flow duct in which stator vanes are arranged, each vane having an outer and an inner vane platform, and each having a cooling air chamber formed by adjacent vane platforms for passing through cooling air, characterized in that the resultant cooling air chamber and/or a platform intermediate gap are designed such that starting from a side of the vane platform facing the adjacent vane platform, at least one outflow pocket open to a platform upper side and connected to the cooling air chamber is formed, and that in the wall of the cooling air chamber, at least one cooling air pocket opened radially inwards to the cooling air chamber and limited by an intermediate element or a sealing strip is formed and opens to the platform intermediate gap.
    Type: Grant
    Filed: March 1, 2016
    Date of Patent: August 7, 2018
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Markus Weinert, Tobias Leymann
  • Publication number: 20180214243
    Abstract: A device for simultaneously identifying a plurality of surgical instruments or instrument groups includes a first detecting device having a first detection technology for detecting instruments and, if applicable, related instrument-specific information. The device also includes a second detecting device having a second different detection technology for detecting instruments and instrument information. Moreover, the device includes a comparing device for comparing the detection results of the two detecting devices. The comparing device outputs a positive evaluation regarding the correctness of the detected instruments if the two detection results are matching.
    Type: Application
    Filed: February 27, 2018
    Publication date: August 2, 2018
    Inventors: Markus Weinert, Nicola Giordano, Pedro Morales, Dieter Weisshaupt
  • Patent number: 9937010
    Abstract: A device for simultaneously identifying a plurality of surgical instruments or instrument groups includes a first detecting device having a first detection technology for detecting instruments and, if applicable, related instrument-specific information. The device also includes a second detecting device having a second different detection technology for detecting instruments and instrument information. Moreover, the device includes a comparing device for comparing the detection results of the two detecting devices. The comparing device outputs a positive evaluation regarding the correctness of the detected instruments if the two detection results are matching.
    Type: Grant
    Filed: August 2, 2013
    Date of Patent: April 10, 2018
    Assignee: Aesculap AG
    Inventors: Markus Weinert, Nicola Giordano, Pedro Morales, Dieter Weisshaupt
  • Publication number: 20170306771
    Abstract: A rotor for an engine is provided. The rotor comprising a rotor base part that has fastening grooves for rotor blades that are arranged in succession around a rotational axis along a circumferential direction, multiple rotor blades that are respectively supported in a form-fit manner inside a corresponding fastening groove by means of a blade root, and at least one securing element for the axial securing—with respect to a rotational axis—of at least one of the rotor blades at the rotor base part. The at least one securing element has two edges that are arranged at a radial distance to one another and through which the securing element is supported in a form-fit manner at the rotor base part, on the one hand, and, on the other hand, at the at least one rotor blade.
    Type: Application
    Filed: April 18, 2017
    Publication date: October 26, 2017
    Inventors: Markus WEINERT, Tobias LEYMANN
  • Publication number: 20170096903
    Abstract: A securing device with multiple securing segments for the axial retaining of at least one rotor blade at a disc wheel a rotor device of a continuous-flow machine. The securing device has at least one effective area that is arranged in a radially inner area and that in the mounted state is embodied for acting together with the disc wheel in the axial direction of the rotor device, and a further effective area that is arranged in a radially outer area at a securing segment and that in the mounted state is embodied for acting together with at least one rotor blade in the axial direction of the rotor device. At least one securing segment has an additional effective area, that in the mounted state is embodied for acting together with the disc wheel in the radial direction of the rotor device. What is further described is a rotor device with such a securing device.
    Type: Application
    Filed: October 6, 2016
    Publication date: April 6, 2017
    Inventors: Thomas SCHIESSL, Markus WEINERT
  • Publication number: 20170022818
    Abstract: A cooled turbine runner for a gas turbine, in particular an aircraft engine, with turbine blades that are radially arranged at the circumferential surface of a rotor disk, wherein respectively a turbine blade is inserted with a profiled blade root into a correspondingly profiled disk finger groove at the circumferential surface of the rotor disk. A cooling device with at least one cooling air supply channel is provided, which extends at least substantially axially and at least over a part of the axial length of the blade root, and which has at least one inlet with an inlet opening at an inflow side of the blade root, wherein the inlet is embodied with a projection. A middle axis of the inlet has, in a direction oriented towards the inlet opening and in the area of the inlet opening, an extension component in the rotational direction of the rotor disk.
    Type: Application
    Filed: July 20, 2016
    Publication date: January 26, 2017
    Inventors: Markus WEINERT, Tobias LEYMANN
  • Publication number: 20170022819
    Abstract: A rotor of an aircraft engine includes a disk wheel and at least two turbine blades. A damping device is arranged below a blade platform and inside a cavity between the blades in the radial direction. The cavity is formed by a respective recess at adjoining blades, with respective recesses having an outer guide surface in the radial direction, acting together with the damping device during operation of the rotor. The guide surface extends radially, from the lateral edge area of the blade to the central area of the blade. The respective recess extends circumferentially from a boundary plane defined by the lateral edge area of the blade to a side surface that delimitates the guide surface towards the blade center. The recess of at least one of the adjacent blades completely receives the damping device.
    Type: Application
    Filed: July 22, 2016
    Publication date: January 26, 2017
    Inventors: Markus WEINERT, Tobias LEYMANN
  • Publication number: 20160258294
    Abstract: A rotor of a turbine of a gas turbine, having a rotor hub and a plurality of blade platforms, each carrying at least one turbine blade, and having one each cooling air chamber for passing cooling air formed by adjacent blade platforms. At least one damping element and/or sealing element is arranged radially beneath a platform intermediate gap provided between adjacent blade platforms. The cooling air chamber and/or the platform intermediate gap are designed such that starting from a side of the blade platform facing the adjacent blade platform, at least one outflow pocket open to the platform upper side and connected to the cooling air chamber is formed, and at least one cooling air pocket opened radially inwards to the cooling air chamber is provided in the wall of the cooling air chamber and opens towards the damping element and/or the sealing element or the platform intermediate gap.
    Type: Application
    Filed: March 3, 2016
    Publication date: September 8, 2016
    Inventors: Markus WEINERT, Tobias LEYMANN
  • Publication number: 20160258293
    Abstract: A stator of a turbine of a gas turbine, having a flow duct in which stator vanes are arranged, each vane having an outer and an inner vane platform, and each having a cooling air chamber formed by adjacent vane platforms for passing through cooling air, characterized in that the resultant cooling air chamber and/or a platform intermediate gap are designed such that starting from a side of the vane platform facing the adjacent vane platform, at least one outflow pocket open to a platform upper side and connected to the cooling air chamber is formed, and that in the wall of the cooling air chamber, at least one cooling air pocket opened radially inwards to the cooling air chamber and limited by an intermediate element or a sealing strip is formed and opens to the platform intermediate gap.
    Type: Application
    Filed: March 1, 2016
    Publication date: September 8, 2016
    Inventors: Markus WEINERT, Tobias LEYMANN
  • Publication number: 20150190202
    Abstract: A device for simultaneously identifying a plurality of surgical instruments or instrument groups includes a first detecting device having a first detection technology for detecting instruments and, if applicable, related instrument-specific information. The device also includes a second detecting device having a second different detection technology for detecting instruments and instrument information. Moreover, the device includes a comparing device for comparing the detection results of the two detecting devices. The comparing device outputs a positive evaluation regarding the correctness of the detected instruments if the two detection results are matching.
    Type: Application
    Filed: August 2, 2013
    Publication date: July 9, 2015
    Inventors: Markus Weinert, Nicola Giordano, Pedro Morales, Dieter Weisshaupt