Patents by Inventor Frank Stiehler
Frank Stiehler 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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Patent number: 9982559Abstract: The present invention relates to a blade or vane for a turbomachine, having at least one impulse element housing with a first impact cavity, in which an impulse element is arranged with play of movement, wherein the impulse element housing has at least one second impact cavity, which is in alignment with the first impact cavity in a first matrix direction and in which an impulse element is arranged with play of movement, and has at least one third impact cavity, which is in alignment with the first impact cavity in a second matrix direction crosswise to the first matrix direction and in which an impulse element is arranged with play of movement.Type: GrantFiled: November 17, 2015Date of Patent: May 29, 2018Assignee: MTU AERO ENGINES AGInventors: Andreas Hartung, Hermann Klingels, Patrick Wackers, Manfred Feldmann, Frank Stiehler, Markus Schlemmer
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Patent number: 9970314Abstract: An inner ring for forming a guide blade ring for a turbomachine is disclosed, composed of at least two one-part ring segments having a plurality of openings, closed on the peripheral side, for accommodating journal bearings on the blade side, the outer diameter of the inner ring being at least 12 times larger than its height. Also disclosed are a guide blade ring having this type of inner ring and a turbomachine having this type of guide blade ring.Type: GrantFiled: May 1, 2012Date of Patent: May 15, 2018Assignee: MTU Aero Engines GmbHInventor: Frank Stiehler
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Patent number: 9951623Abstract: A blade cascade for a gas turbine, which has a first group with at least two, in particular at least three, first blade arrangements of the same type to one another, on which first element arrangements that are identical to one another and have at least one first element are movably mounted; and a second group with at least two, in particular at least three, second blade arrangements, which are of the same type to one another and are of different type from the first blade arrangements, on which second element arrangements, which are identical to one another and have at least one second element are movably mounted, wherein first and second element arrangements are different from each other.Type: GrantFiled: July 16, 2015Date of Patent: April 24, 2018Assignee: MTU AERO ENGINES AGInventors: Andreas Hartung, Frank Stiehler, Martin Pernleitner
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Patent number: 9920838Abstract: A brush seal for a gas turbine, in particular an aircraft engine, is disclosed. The brush seal includes a support ring which has a support plate and a support structure, where the support structure is arranged downstream with respect to the support plate. The brush seal also includes bristles which are arranged upstream with respect to the support ring, where ends of the bristles protrude radially inward beyond the support plate. The support structure yields when a scraping force acting radially outward occurs on a first lateral surface of the support structure, where the first lateral surface is directed radially inward, and the support structure does not yield when an axial operating force occurs on a second lateral surface of the support structure.Type: GrantFiled: July 2, 2015Date of Patent: March 20, 2018Assignee: MTU Aero Engines AGInventors: Stephan Klaen, Julian Weber, Frank Stiehler, Christoph Cernay, Thomas Hess
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Patent number: 9856736Abstract: A fish mouth seal carrier for a guide vane arrangement of a gas turbine comprises a first half-shell element and a second half-shell element bonded to it, which together form a box profile with two axial arms and two radial arms. A sealing element is arranged on one of the axial arms of the box profile. At least one of the two half-shell elements has an integrally formed axial flange for forming, with a guide vane platform, a fish mouth seal accommodating an axial flange of an adjoining moving blade radially between the guide vane platform and the axial flange of the seal carrier.Type: GrantFiled: October 17, 2013Date of Patent: January 2, 2018Assignee: MTU Aero Engines AGInventor: Frank Stiehler
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Patent number: 9850766Abstract: A blade cascade for a turbomachine, having a number of blades which include a monocrystalline material, each blade having a crystal orientation value, which is dependent on a crystal of first blades being less than a first limiting value and the crystal orientation values of second blades being at least equal to the first limiting value; and the blade cascade having at least one first sector, which includes at least three successive first blades, and having at least one second sector, which includes at least three successive second blades; and/or at least one first blade has a first body arrangement having at least one first body mounted so it is movable on the first blade and at least one second blade has a second body arrangement, which differs therefrom, having at least one second body mounted so it is movable on the second blade.Type: GrantFiled: December 15, 2014Date of Patent: December 26, 2017Assignee: MTU Aero Engines AGInventors: Andreas Hartung, Frank Stiehler, Martin Pernleitner
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Patent number: 9845685Abstract: Disclosed is a process for producing a run-in coating (20, 24, 32, 44) on a component of a turbomachine, in particular of a gas turbine. The run-in coating is applied and produced on the component of the turbomachine by a kinetic cold gas compacting process (K3). The invention also encompasses a run-in coating for a static or rotating component of a turbomachine and a static or rotating component of a turbomachine, in particular of a gas turbine, having at least one run-in coating.Type: GrantFiled: April 3, 2013Date of Patent: December 19, 2017Assignee: MTU AERO ENGINES GMBHInventors: Frank Stiehler, Manuel Hertter
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Patent number: 9840916Abstract: A blade (1) for a turbomachine, including a turbine blade (1.1) which has a channel (1.5), an impact chamber (2) having a constricted cross section being situated in the channel for the purpose of accommodating a single impulse body (3) is provided.Type: GrantFiled: May 21, 2014Date of Patent: December 12, 2017Assignee: MTU Aero Engines AGInventors: Frank Stiehler, Andreas Hartung
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Patent number: 9777588Abstract: A brush seal system for sealing a gap between components of a thermal gas turbine that may be moved relative to one another includes a gas seal housing that receives at least one brush head of a brush seal and a support element by means of which a brush packet projecting from the brush head of the brush seal may be supported against flexing. The support element and the brush seal housing are embodied as separate components. The invention furthermore relates to a method for producing such a brush seal system and to a thermal gas turbine having such a brush seal system.Type: GrantFiled: October 7, 2014Date of Patent: October 3, 2017Assignee: MTU AERO ENGINES AGInventors: Stephan Klan, Frank Stiehler, Julian Weber, Markus Schlemmer, Stephan Prostler
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Publication number: 20170268356Abstract: A guide vane (10, 10?) according to the invention for a guide vane ring of a turbomachine has a vane element as well as a guide vane plate (12) for its support on an inner ring (20). The guide vane plate has a cover surface (14) facing the vane element, a base surface (17) lying opposite to the cover surface, and an edge surface (15) joining the cover and base surfaces. In a first region (B1), the edge surface forms a chamfer (16) of the vane plate, and in a second region (B2), which forms the edge of a sector of the guide vane plate that is different from that of the first region (B1), the edge surface runs along a cylindrical surface. A method comprises inserting a plurality of guide vanes (10, 10?) according to the invention into respective uptakes (21) in an inner ring (20).Type: ApplicationFiled: March 7, 2017Publication date: September 21, 2017Inventor: Frank Stiehler
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Patent number: 9765625Abstract: A blade (1) for a turbomachine, including an impact chamber (2), a single impulse body (3) being situated in the impact chamber, a clearance (S1+S2) between the impulse body and the impact chamber being at least 10 ?m and/or at most 1.5 mm in at least one direction.Type: GrantFiled: May 21, 2014Date of Patent: September 19, 2017Assignee: MTU Aero Engines AGInventors: Frank Stiehler, Andreas Hartung
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Patent number: 9739151Abstract: A blade for a turbomachine is disclosed. At least one cooling channel is configured in the blade neck, whose inlet is disposed near a platform projection on the high-pressure side and whose outlet is disposed in the region of a platform projection on the low-pressure side. An integrally bladed rotor base body having a plurality of these types of blades as well as turbomachine with such a rotor base body is also disclosed.Type: GrantFiled: May 1, 2012Date of Patent: August 22, 2017Assignee: MTU Aero Engines GmbHInventor: Frank Stiehler
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Publication number: 20170226887Abstract: The invention relates to a guide vane system for a turbomachine with at least one guide vane, which can be rotatably mounted around an adjustment axis and is arranged with a radially inner end region in a corresponding recess of an inner ring, wherein the arrangement of the guide vane on the inner ring is secured by a securing element in a form-fitting manner. For an especially advantageous securing of this arrangement, it is provided that the securing element is designed as an oblong element, which is arranged at least in a recess and/or through-opening of the radially inner end region of the guide vane directed in the peripheral direction of the turbomachine and is arranged at least in a recess and/or through-opening of the inner ring directed in the peripheral direction of the turbomachine. In addition, the invention relates to a turbomachine, in particular an aircraft engine, and to a method for assembling a guide vane system.Type: ApplicationFiled: January 27, 2017Publication date: August 10, 2017Inventors: Joachim WULF, Frank STIEHLER
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Patent number: 9677403Abstract: A securement system for securing an attachment portion of at least one rotor blade or rotor blade segment in a mounting site of a rotor base. The securement system has at least one holder element and a second holder element, each of which has a holding portion and a connecting portion. The connecting portions can be introduced into the mounting site so as to establish a clip connection and can be locked together in the mounting site. The holding portions are configured so as to fasten the attachment portion of the at least one rotor blade or of the rotor blade segment in the mounting site in the locked state of the connecting portions. Further disclosed is a method for securing an attachment portion of at least one rotor blade or rotor blade segment in a mounting site of a rotor base and a rotor having a securement system.Type: GrantFiled: April 4, 2014Date of Patent: June 13, 2017Assignee: MTU Aero Engines AGInventors: Frank Stiehler, Felix Kern
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Publication number: 20160273380Abstract: A protective device (10) for a turbomachine, in particular a gas turbine, having a containment ring (12) which is disposed on the radially inner side of a casing element (14) of the turbomachine and which at least substantially prevents the casing element (14) from being penetrated by a fragment of a component of the turbomachine in the event of a structural failure of this component is provided. The containment ring (12) is composed, at least in the circumferential direction, of a plurality of ring segments (16) which are form-fittingly interconnected. A second aspect of the present invention relates to an aircraft engine.Type: ApplicationFiled: March 17, 2016Publication date: September 22, 2016Inventors: Frank Stiehler, Lars Schellhorn
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Patent number: 9435216Abstract: A sealing arrangement (100) in an axial turbomachine between, on the one hand, a rotor (1) and, on the other hand, a stator (3) and/or a housing, including a support device (7, 7?) and a sealing element, whereby the support device (7, 7?) extends essentially in the radial direction (r). In the axial direction (u) of the turbomachine, the support device (7, 7?) has an axial contour that effectuates a stiffening effect for the support device (7, 7?).Type: GrantFiled: September 2, 2014Date of Patent: September 6, 2016Assignee: MTU Aero Engines GmbHInventor: Frank Stiehler
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Publication number: 20160201486Abstract: An extruded profile for manufacturing a blade of an outlet guide vane of a turbine engine. A cross-sectional area has an axial length LAX and a thickness D/LAX relative to the axial length LAX. A cross-sectional area has an at least nearly axisymmetric leading edge region, a first transition region having a varying relative thickness D/LAX. A first constant region has a relative thickness D/LAX at least substantially constant and, relative to a leading edge of the extruded profile, begins at the closest at 10% LAX and ends at the furthest at 50% LAX. A second transition region has a varying relative thickness D/LAX and, relative to the leading edge of the extruded profile, begins at the closest at 30% LAX and ends at the furthest at 90% LAX. A second constant region has a relative thickness D/LAX at least substantially constant and an axial length X of 40% LAX at most; and an at least nearly axisymmetric trailing edge region.Type: ApplicationFiled: January 12, 2015Publication date: July 14, 2016Inventors: Andreas HARTUNG, Frank STIEHLER, Martin PERNLEITNER
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Publication number: 20160146041Abstract: The present invention relates to a blade (100) or vane for a turbomachine, having at least one impulse element housing (1.1, 1.2) with a first impact cavity (10), in which an impulse element (11) is arranged with play of movement, wherein the impulse element housing has at least one second impact cavity (20), which is in alignment with the first impact cavity in a first matrix direction (A) and in which an impulse element (21) is arranged with play of movement, and has at least one third impact cavity (30), which is in alignment with the first impact cavity in a second matrix direction (B) crosswise to the first matrix direction and in which an impulse element (31) is arranged with play of movement.Type: ApplicationFiled: November 17, 2015Publication date: May 26, 2016Inventors: Andreas Hartung, Hermann Klingels, Patrick Wackers, Manfred Feldmann, Frank Stiehler, Markus Schlemmer
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Publication number: 20160024945Abstract: The present invention relates to a turbomachine blade (100; 200) with a base element, which has a blade part (1) for flow diversion and a blade root (2), a first guide (110; 210), fixed on the base element, in which a first element (111; 211) is movably guided, and a second guide (120; 220), fixed on the base element, in which a second element (121; 221) is movably guided, wherein a dynamic of the first element in the first guide and a dynamic of the second element in the second guide are designed differently, and the first guide (110; 210) is arranged in a half, nearer to the base root, of a radial height (H) of the base element, and the second guide is arranged in a half, more remote from the blade root, of the radial height of the base element.Type: ApplicationFiled: July 16, 2015Publication date: January 28, 2016Inventors: Frank Stiehler, Martin Pernleitner, Andreas Hartung
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Publication number: 20160024928Abstract: The present invention relates to a blade cascade for a gas turbine, which has a first group with at least two, in particular at least three, first blade arrangements of the same type to one another (A1, . . . A5; U1, U2), on which first element arrangements that are identical to one another and have at least one first element (a) are movably mounted; and a second group with at least two, in particular at least three, second blade arrangements (B1, B2; V1, . . . V4), which are of the same type to one another and are of different type from the first blade arrangements, on which second element arrangements, which are identical to one another and have at least one second element (b) are movably mounted, wherein first and second element arrangements are different from each other.Type: ApplicationFiled: July 16, 2015Publication date: January 28, 2016Inventors: Andreas Hartung, Frank Stiehler, Martin Pernleitner