Patents by Inventor Karl Schreiber

Karl Schreiber 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: 10024234
    Abstract: An aircraft gas turbine with a fan disk on which are fastened fan blades spread over the circumference and forming an intermediate space with one another, with a sealing disk arranged at the rear of the fan disk and with an inlet cone mounted at the front of the fan disk, as well as with filler elements arranged in the intermediate spaces, where the sealing disk has an annular groove and where the filler elements are at the rear inserted into the annular groove and at the front held underneath a rim area of the inlet cone, characterized in that the filler elements are designed as bending beams and that on the radially inner side of the filler element at least one rib-like reinforcing area is provided, extending in the axial direction and longitudinally to the filler element.
    Type: Grant
    Filed: September 11, 2015
    Date of Patent: July 17, 2018
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Pierangelo Duó, Karl Schreiber
  • Patent number: 9964117
    Abstract: The present invention relates to a compressor blade of a gas turbine having an airfoil and a blade root, said blade root and airfoil being made in one piece from a fiber-composite material, as well as a leading edge protector made from a sheet metal material, characterized in that the airfoil is provided with a radial groove extending substantially over the entire length of the airfoil and that the leading edge protector is detachably clamped onto the airfoil and is fixed with a sheet metal flange in the radial groove of the airfoil.
    Type: Grant
    Filed: December 17, 2015
    Date of Patent: May 8, 2018
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Karl Schreiber, Werner Hufenbach, Albert Langkamp, Tino Wollmann
  • Patent number: 9908173
    Abstract: A method for manufacturing a metallic component especially configured and designed for a turbomachine includes a) for a precision-casting process, a wax model with a wax structure is produced, subsequently b) the tip of the wax structure is thermally and/or mechanically treated such that a region with an undercut is formed on the wax structure, subsequently c) the metallic component is manufactured from the wax model in the precision-casting process, with a component structural element with an undercut forming on a surface of the component, and d) the component structural element is provided at least partially with a ceramic coating, a plastic-containing coating, in particular a fiber composite layer and/or a plastic component.
    Type: Grant
    Filed: April 2, 2012
    Date of Patent: March 6, 2018
    Assignee: ROLLS-ROYCE DEUTSCHLAND & CO KG
    Inventor: Karl Schreiber
  • Publication number: 20170363100
    Abstract: A bearing element for at least one adjustable guide vane of a turbomachine, in particular an aircraft engine, is provided. The bearing element comprising a porous matrix made of carbon and/or graphite and at least one metallic phase or a metal salt that is at least partially arranged inside the pores of the matrix, so that what results is a metal-infiltrated or a metal-salt-infiltrated material.
    Type: Application
    Filed: June 16, 2017
    Publication date: December 21, 2017
    Inventors: Bjorn ULRICHSOHN, Susanne SCHRUEFER, Karl SCHREIBER
  • Patent number: 9828860
    Abstract: A compressor blade of a gas turbine includes an airfoil made of a fiber-reinforced plastic and a leading-edge element connected to said airfoil. The leading-edge element includes two partial elements, which are fabricated as separate elements and connected to one another, with the leading-edge element being connected to the airfoil essentially using the clamping effect of the two partial elements.
    Type: Grant
    Filed: July 30, 2013
    Date of Patent: November 28, 2017
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Karl Schreiber
  • Patent number: 9664069
    Abstract: An aircraft gas turbine with a fan disc at which fan blades, distributed around the circumference and forming an intermediate space in between each other, are attached, with a sealing disc that is arranged on the back side of the fan disc, and with an inlet cone that is mounted at the front side of the fan disc, as well as with filling elements that are arranged in the intermediate spaces, wherein the inlet cone includes strip-shaped lugs which are configured in one piece with the same and which can be inserted into the intermediate spaces, with their free ends being inserted into a ring groove that is formed at the sealing disc, and in that a filling element is arranged on each strip-shaped lug.
    Type: Grant
    Filed: September 2, 2015
    Date of Patent: May 30, 2017
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Pierangelo Duó, Karl Schreiber
  • Patent number: 9429026
    Abstract: The present invention relates to a compressor blade of a gas turbine having an airfoil made of a fiber-reinforced plastic, which is fastened by means of a blade root to a disk, as well as a metallic leading-edge element, which is arranged on the leading-edge side of the airfoil and partially encompasses the latter, with the leading-edge element itself being fastened to the disk.
    Type: Grant
    Filed: July 30, 2013
    Date of Patent: August 30, 2016
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Karl Schreiber
  • Publication number: 20160177969
    Abstract: The present invention relates to a compressor blade of a gas turbine having an airfoil and a blade root, said blade root and airfoil being made in one piece from a fiber-composite material, as well as a leading edge protector made from a sheet metal material, characterized in that the airfoil is provided with a radial groove extending substantially over the entire length of the airfoil and that the leading edge protector is detachably clamped onto the airfoil and is fixed with a sheet metal flange in the radial groove of the airfoil.
    Type: Application
    Filed: December 17, 2015
    Publication date: June 23, 2016
    Inventors: Karl SCHREIBER, Werner HUFENBACH, Albert LANGKAMP, Tino WOLLMANN
  • Patent number: 9360438
    Abstract: The present invention relates to a method for radiographically inspecting a component by means of X-rays, where at least one component surface to be radiographed is provided with a surface structure, with at least the surface provided with the surface structure being smoothed by means of a smoothing material to level out the surface structure, with at least one organic compound and at least one metal powder being used as smoothing material, with the X-ray absorption behavior of the smoothing material essentially equaling the X-ray absorption behavior of the material of the component, as well as to a smoothing material for carrying out the method in accordance with Claim.
    Type: Grant
    Filed: August 9, 2011
    Date of Patent: June 7, 2016
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Karl Schreiber, Josef Geitner
  • Publication number: 20160069355
    Abstract: An aircraft gas turbine with a fan disk on which are fastened fan blades spread over the circumference and forming an intermediate space with one another, with a sealing disk arranged at the rear of the fan disk and with an inlet cone mounted at the front of the fan disk, as well as with filler elements arranged in the intermediate spaces, where the sealing disk has an annular groove and where the filler elements are at the rear inserted into the annular groove and at the front held underneath a rim area of the inlet cone, characterized in that the filler elements are designed as bending beams and that on the radially inner side of the filler element at least one rib-like reinforcing area is provided, extending in the axial direction and longitudinally to the filler element.
    Type: Application
    Filed: September 11, 2015
    Publication date: March 10, 2016
    Inventors: Pierangelo DUÓ, Karl SCHREIBER
  • Publication number: 20160069217
    Abstract: An aircraft gas turbine with a fan disc at which fan blades 31, distributed around the circumference and forming an intermediate space in between each other, are attached, with a sealing disc that is arranged on the back side of the fan disc, and with an inlet cone that is mounted at the front side of the fan disc, as well as with filling elements that are arranged in the intermediate spaces, characterized in that the inlet cone includes strip-shaped lugs which are configured in one piece with the same and which can be inserted into the intermediate spaces, with their free ends being inserted into a ring groove that is formed at the sealing disc, and in that a filling element is arranged on each strip-shaped
    Type: Application
    Filed: September 2, 2015
    Publication date: March 10, 2016
    Inventors: Pierangelo DUÓ, Karl SCHREIBER
  • Patent number: 9278385
    Abstract: A method for manufacturing a workpiece 1, 2 uses a forming tool 4, 5 having a cavity 3. An embossing element 6 profiled on at least one surface is arranged on at least one surface of the forming tool 4, 5 for producing a surface structure, and with the profile of the embossing tool 6 is imparted to the surface of the workpiece 1, 2 during a forming process.
    Type: Grant
    Filed: July 20, 2011
    Date of Patent: March 8, 2016
    Assignees: Rolls-Royce Deutschland Ltd & Co KG, FormTech GmbH
    Inventors: Karl Schreiber, Werner Beck
  • Patent number: 9126361
    Abstract: When manufacturing hybrid components, especially the fan blades or stator vanes of an aircraft gas turbine including a metallic enveloping structure and a supporting structure in fiber-composite material, the mating faces of the metallic structure are cleaned and roughened with plasma prior to fitting the fiber-composite material and the metallic molecules activated so that high attractive forces take effect and an intimate, extremely strong adhesive connection is produced between the metal and the fiber-composite material. Fan blades or stator vanes of the fan structure of a gas-turbine engine which are manufactured according to this method are capable of transmitting high loads and feature a long service life.
    Type: Grant
    Filed: November 19, 2009
    Date of Patent: September 8, 2015
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Karl Schreiber
  • Patent number: 8831172
    Abstract: With filmless radiographic inspection of components by means of digital X-ray technology, an uneven surface geometry of the component is smoothened by defining a digital virtual smoothening layer for better, preferably automated, recognition of defects, where the digital radiation signals generated by an X-ray detector are overlaid with digitized surface measurement signals, so that a change in absorption and intensity of radiation due to the surface topography of the component, i.e. due to an uneven surface, is compensated for and only a density caused by internal material defects is represented in the X-ray image.
    Type: Grant
    Filed: August 5, 2011
    Date of Patent: September 9, 2014
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Karl Schreiber, Josef Geitner
  • Patent number: 8827654
    Abstract: A compressor blade 1 of a gas-turbine engine has a flow-exposed leading edge 2. A component 3, made of wear-resistant material and featuring a higher erosive wear resistance than the base material, is attached to at least part of a length of the leading edge 2 The component 3 forming the flow-exposed leading edge 2 is strip-shaped, has an essentially rectangular cross-section and, with reference to a sectional plane perpendicular to the radial direction, is arranged only on an inflow side of the compressor blade profile in a partial area of a sectional surface of the inflow area.
    Type: Grant
    Filed: July 22, 2011
    Date of Patent: September 9, 2014
    Assignees: Rolls-Royce Deutschland Ltd & Co KG, Formtech GmbH
    Inventors: Karl Schreiber, Werner Beck
  • Patent number: 8777577
    Abstract: With a hybrid fan blade, the supporting structure (1) in fiber-composite material is enclosed by an enveloping structure (2) only in an area of the airfoil, with a suction-side sheet-metal cover of the enveloping structure being pre-stressed in tension and a pressure-side sheet-metal cover of the enveloping structure being pre-stressed in compression. This reduces the hazard of delamination between the enveloping structure and the supporting structure.
    Type: Grant
    Filed: December 21, 2007
    Date of Patent: July 15, 2014
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Karl Schreiber
  • Publication number: 20140127005
    Abstract: A method for manufacturing a metallic component especially configured and designed for a turbomachine includes a) for a precision-casting process, a wax model with a wax structure is produced, subsequently b) the tip of the wax structure is thermally and/or mechanically treated such that a region with an undercut is formed on the wax structure, subsequently c) the metallic component is manufactured from the wax model in the precision-casting process, with a component structural element with an undercut forming on a surface of the component, and d) the component structural element is provided at least partially with a ceramic coating, a plastic-containing coating, in particular a fibre composite layer and/or a plastic component.
    Type: Application
    Filed: April 2, 2012
    Publication date: May 8, 2014
    Applicant: ROLLS-ROYCE DEUTSCHLAND LTD. & CO KG
    Inventor: Karl Schreiber
  • Patent number: 8685297
    Abstract: With a method for the manufacture of fiber-composite components, more particularly of fan blades for aircraft engines, dry fiber mats are superimposed in a lay-up mold, correctly positioned and fixed with locating pins and subsequently sewn in the mold. Metallic indicators are provided on at least one mat. The preformed entity of fiber mats is whipped at its edges with thermoplastic material and subsequently smoothed by application of heat. Remaining fiber residues are cut off. The blank thus available is infiltrated with synthetic resin in an infiltration mold or a sheathing remaining on the component. The fiber mats are checked for correct positioning by non-destructive inspection procedures. The fiber-composite component thus formed conforms to high quality requirements.
    Type: Grant
    Filed: November 13, 2007
    Date of Patent: April 1, 2014
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Karl Schreiber
  • Patent number: 8677622
    Abstract: On an intake cone made of fiber compound material for a gas turbine engine, the conical part, the attachment part and the fairing part are manufactured as one piece from a plurality of mutually crossing and covering winding layers (1) forming an interlace (2). The winding layers include parallel, alternately adjacent glass fiber strands and carbon fiber strands of equal thickness. The one-piece intake cone is producible and mountable cost-effectively and is characterized by elasticity, stiffness and impact resistance.
    Type: Grant
    Filed: March 12, 2007
    Date of Patent: March 25, 2014
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Karl Schreiber
  • Patent number: 8646279
    Abstract: The present invention relates to a segment component in high-temperature casting material for an annular combustion chamber of an aircraft engine, characterized by a combustion-chamber wall which in operation shields a fuel flame extending along a burner axis from the environment, with the combustion-chamber wall having a bulge which points in a direction facing away from the burner axis. The invention furthermore relates to an annular combustion chamber, an aircraft engine with an annular combustion chamber as well as a method for the manufacture of an annular combustion chamber.
    Type: Grant
    Filed: May 25, 2012
    Date of Patent: February 11, 2014
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Karl Schreiber, Miklos Gerendas