Patents by Inventor Sergio Elorza Gomez
Sergio Elorza Gomez 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: 11927109Abstract: The present invention relates to a blade for a gas turbine, in particular of an aircraft engine, having a blade airfoil, which has a blade-root-side first profile section and a blade-tip-side second profile section, which is spaced apart from the first profile section in a radial direction, from the first profile section to the second profile section, by a blade airfoil height, wherein a stagger angle of the blade airfoil changes with a height in the radial direction over the first profile section at least over certain portions, wherein, in a first region between a first height and a second, greater height, the change in the stagger angle over the height does not decrease with increasing height at least over certain portions.Type: GrantFiled: December 8, 2020Date of Patent: March 12, 2024Assignee: MTU Aero Engines AGInventors: Sergio Elorza Gomez, Tobias Froebel, Nina Wolfrum, Sebastian Mann
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Publication number: 20240011434Abstract: The invention is directed to an engine that has a fan, a compressor with a high-pressure compressor, and a combustion chamber. The high-pressure compressor of the engine has a mean stage pressure ratio and an overall pressure ratio formed between the fan and the combustion chamber.Type: ApplicationFiled: June 30, 2023Publication date: January 11, 2024Applicant: MTU Aero Engines AGInventors: Sergio Elorza Gomez, Werner Humhauser, Roland Matzgeller
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Publication number: 20240003353Abstract: The invention relates to a compressor for an engine, wherein the compressor has compressor stages arranged in succession in a flow direction of the compressor and each compressor stage has a rotating blade cascade and a guide vane cascade arranged downstream of the rotating blade cascade and the rotating blade cascade and the guide vane cascade each have an aspect ratio.Type: ApplicationFiled: June 30, 2023Publication date: January 4, 2024Applicant: MTU Aero Engines AGInventors: Sergio Elorza Gomez, Werner Humhauser, Roland Matzgeller
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Publication number: 20230026899Abstract: The present invention relates to a blade for a gas turbine, in particular of an aircraft engine, having a blade airfoil, which has a blade-root-side first profile section and a blade-tip-side second profile section, which is spaced apart from the first profile section in a radial direction, from the first profile section to the second profile section, by a blade airfoil height, wherein a stagger angle of the blade airfoil changes with a height in the radial direction over the first profile section at least over certain portions, wherein, in a first region between a first height and a second, greater height, the change in the stagger angle over the height does not decrease with increasing height at least over certain portions.Type: ApplicationFiled: December 8, 2020Publication date: January 26, 2023Applicant: MTU Aero Engines AGInventors: Sergio Elorza Gomez, Tobias Froebel, Nina Wolfrum, Sebastian Mann
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Patent number: 11555500Abstract: The present invention relates to a guide vane, in particular an outlet guide vane and/or a guide vane for a compressor stage of a gas turbine, wherein the vane has a vane blade with a first vane blade portion and a second vane blade portion, and the first vane blade portion can be reversibly rotated in relation to the second vane blade portion about an axis of rotation from a first position to a second position, wherein, in at least one profile portion of the vane blade, the axis of rotation is arranged outside of a profile of the first vane blade portion, and/or a profile of the first vane blade portion has a suction side with a first contour portion and a second contour portion, which, in particular, is adjoined thereto, and a profile of the second vane blade portion has a pressure-side contour portion.Type: GrantFiled: July 29, 2021Date of Patent: January 17, 2023Assignee: MTU Aero Engines AGInventor: Sergio Elorza Gomez
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Publication number: 20220042514Abstract: The present invention relates to a guide vane, in particular an outlet guide vane and/or a guide vane for a compressor stage of a gas turbine, wherein the vane has a vane blade with a first vane blade portion and a second vane blade portion, and the first vane blade portion can be reversibly rotated in relation to the second vane blade portion about an axis of rotation from a first position to a second position, wherein, in at least one profile portion of the vane blade, the axis of rotation is arranged outside of a profile of the first vane blade portion, and/or a profile of the first vane blade portion has a suction side with a first contour portion and a second contour portion, which, in particular, is adjoined thereto, and a profile of the second vane blade portion has a pressure-side contour portion.Type: ApplicationFiled: July 29, 2021Publication date: February 10, 2022Applicant: MTU Aero Engines AGInventor: Sergio Elorza Gomez
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Patent number: 11085453Abstract: An engine, having a first, second, third and fourth quasi-stage, each with a stator and a downstream rotor, wherein a particular blade/vane solidity in the center section is in the first quasi-stage, at least 1.04 and at most 1.16 for the stator and at least 1.46 and at most 1.67 for the rotor; in the second quasi-stage, at least 1.13 and at most 1.32 for the stator and at least 1.32 and at most 1.61 for the rotor; in the third quasi-stage, at least 1.20 and at most 1.39 for the stator and at least 1.16 and at most 1.41 for the rotor; in the fourth quasi-stage, at least 1.37 and at most 1.63 for the stator and at least 1.15 and at most 1.41 for the rotor.Type: GrantFiled: July 22, 2019Date of Patent: August 10, 2021Assignee: MTU Aero Engines AGInventors: Harsimar Sahota, Alexander Halcoussis, Sergio Elorza Gomez
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Patent number: 10641288Abstract: Described is a method for operating a compressor of a turbomachine, in which, when considered in the direction of a main flow, an, in particular, radially averaged degree of reaction has dropped in a front compressor area from a maximum to a minimum, is held constant or virtually constant across a central compressor area up into a rear compressor area, an, in particular, radially averaged degree of reaction being adjusted in the rear compressors area which is closer to the minimum than to the maximum, and a residual swirl of at least 47° is present in the middle section, and a compressor and a turbomachine.Type: GrantFiled: November 22, 2016Date of Patent: May 5, 2020Assignee: MTU Aero Engines AGInventors: Tim Schneider, Sergio Elorza Gomez
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Publication number: 20200024948Abstract: The present invention relates to a high pressure compressor for an engine, having a first, second, third and fourth quasi-stage, each with a stator and a downstream rotor, wherein a particular blade/vane solidity in the center section is in the first quasi-stage, at least 1.04 and at most 1.16 for the stator and at least 1.46 and at most 1.67 for the rotor; in the second quasi-stage, at least 1.13 and at most 1.32 for the stator and at least 1.32 and at most 1.61 for the rotor; in the third quasi-stage, at least 1.20 and at most 1.39 for the stator and at least 1.16 and at most 1.41 for the rotor; in the fourth quasi-stage, at least 1.37 and at most 1.63 for the stator and at least 1.15 and at most 1.41 for the rotor.Type: ApplicationFiled: July 22, 2019Publication date: January 23, 2020Applicant: MTU Aero Engines AGInventors: Harsimar SAHOTA, Alexander HALCOUSSIS, Sergio ELORZA GOMEZ
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Patent number: 10337519Abstract: Disclosed is a method for operating a compressor of a turbomachine, in which, when viewed in the direction of a main flow, a slowly dropping degree of reaction being raised in one compressor area more quickly than previously dropped and the raised degree of reaction then being reduced again in a subsequent compressor area more slowly that it was previously raised, a compressor of a turbomachine including at least one degree of reaction rising more quickly in one compressor area in comparison to adjacent compressor areas with respectively a dropping degree of reaction, whereby a sawtooth-shaped curve of the degree of reaction results, and a turbomachine including a compressor of this type.Type: GrantFiled: November 23, 2016Date of Patent: July 2, 2019Assignee: MTU Aero Engines AGInventors: Sergio Elorza Gomez, Tim Schneider
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Patent number: 10208616Abstract: A turbomachine, particularly an aircraft engine, having a rotor, which is mounted rotatably around its longitudinal axis in a stator, and which has at least one row of rotating blades, which is formed by a plurality of rotating blades, is disclosed, wherein the stator has at least one abradable layer, and wherein each rotating blade has a blade tip that is lowered radially inward, at least in sections, proceeding from a leading edge on the side of the rotating blades in the direction of a trailing edge on the side of the rotating blades, and with a blade tip region that extends downstream from the leading edge runs into the abradable layer during operation of the turbomachine.Type: GrantFiled: June 26, 2015Date of Patent: February 19, 2019Assignee: MTU AERO ENGINES AGInventors: Axel Mattschas, Helmut Eibl, Sergio Elorza Gomez, Dirk Henrichs
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Patent number: 10208765Abstract: The present invention relates to an axial compressor for a gas turbine, in particular an aircraft engine, having at least one rotor blade or guide vane having a blade or vane element, which is arranged in a flow duct, and a leading edge and a trailing edge, which are joined to each other through a pressure side and a suction side, wherein, a new and novel profile section of the blade or vane element is provided.Type: GrantFiled: January 19, 2016Date of Patent: February 19, 2019Assignee: MTU Aero Engines AGInventors: Tobias Froebel, Sebastian Mann, Nina Wolfrum, Sergio Elorza Gomez
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Patent number: 10184339Abstract: A turbomachine including at least one blade-row group that is arranged in the main flow path and at least two rows of blades that are adjacent to each other in the main flow direction, each row having a plurality of blades (38, 40), whereby a narrow cross section and a degree of overlap between the blades of the upstream row of blades and the blades of the downstream row of blades vary starting at the center of the main flow path in the direction of at least one main flow limiter.Type: GrantFiled: February 6, 2013Date of Patent: January 22, 2019Assignee: MTU Aero Engines GmbHInventors: Sergio Elorza Gomez, Tim Schneider
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Patent number: 9822796Abstract: A stator vane assembly for a compressor of a gas turbine, in particular of an aircraft engine, including a plurality of stator vanes whose airfoil sections form a stagger angle with an axis of rotation of the compressor, which stagger angle varies along a duct height of the stator vane assembly. Along the duct height from the inside to the outside, the stagger angle increases to a local maximum in a second section adjoining a first, radially innermost section, and decreases to an outer local minimum in a third section adjoining this second section and, along the duct height from the inside to the outside, the stagger angle decreases from the initial value to an inner local minimum in the first, radially innermost section and/or increases from the outer local minimum to a final value in a fourth, radially outermost section adjoining the third section.Type: GrantFiled: July 15, 2014Date of Patent: November 21, 2017Assignee: MTU Aero Engines AGInventor: Sergio Elorza Gomez
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Publication number: 20170146017Abstract: Disclosed is a method for operating a compressor of a turbomachine, in which, when viewed in the direction of a main flow, a slowly dropping degree of reaction being raised in one compressor area more quickly than previously dropped and the raised degree of reaction then being reduced again in a subsequent compressor area more slowly that it was previously raised, a compressor of a turbomachine including at least one degree of reaction rising more quickly in one compressor area in comparison to adjacent compressor areas with respectively a dropping degree of reaction, whereby a sawtooth-shaped curve of the degree of reaction results, and a turbomachine including a compressor of this type.Type: ApplicationFiled: November 23, 2016Publication date: May 25, 2017Inventors: Sergio ELORZA GOMEZ, Tim Schneider
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Publication number: 20170146025Abstract: Described is a method for operating a compressor of a turbomachine, in which, when considered in the direction of a main flow, an, in particular, radially averaged degree of reaction has dropped in a front compressor area from a maximum to a minimum, is held constant or virtually constant across a central compressor area up into a rear compressor area, an, in particular, radially averaged degree of reaction being adjusted in the rear compressors area which is closer to the minimum than to the maximum, and a residual swirl of at least 47° is present in the middle section, and a compressor and a turbomachine.Type: ApplicationFiled: November 22, 2016Publication date: May 25, 2017Inventors: Tim Schneider, Sergio ELORZA GOMEZ
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Patent number: 9470091Abstract: A blade group arrangement for a turbomachine in order to form a blade-row group, whereby a front blade and a rear blade each form an overlapping area that has a contraction ratio of at least 1.2, and it also relates to a turbomachine having such a contraction ratio between a front blade and a rear blade.Type: GrantFiled: February 6, 2013Date of Patent: October 18, 2016Assignee: MTU Aero Engines GmbHInventors: Sergio Elorza Gomez, Alexander Hergt, Ulrich Siller, Tim Schneider
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Patent number: 9453423Abstract: A turbomachine is disclosed having at least one blade row group, which is situated in a main flow path and has at least two adjacent blade rows, viewed in the main flow direction, each blade row having a plurality of blades, the rear edges of the blades of the upstream blade row and the front edges of the blades of the downstream blade row in the peripheral direction being situated at an edge distance which varies starting from a main flow path center in the direction of at least one main flow limitation, the periphery-side edge distance increasing or decreasing on both sides.Type: GrantFiled: February 6, 2013Date of Patent: September 27, 2016Assignee: MTU Aero Engines GmbHInventors: Sergio Elorza Gomez, Tim Schneider
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Patent number: 9435207Abstract: A blade for a blade row of a turbomachine having wired sections, in particular a blade of a compressor rotor blade, as well as a method for wiring sections of such a blade, is disclosed. Sections of a blade are wired in such a way that a first central component of a second section is selected according to at least one central component of a first section.Type: GrantFiled: January 29, 2011Date of Patent: September 6, 2016Assignee: MTU Aero Engines GmbHInventors: Sergio Elorza Gomez, Peter Eibelshaeuser
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Publication number: 20160215788Abstract: The present invention relates to an axial compressor for a gas turbine, in particular an aircraft engine, having at least one rotor blade or guide vane having a blade or vane element (1), which is arranged in a flow duct, and a leading edge (LE) and a trailing edge (TE), which are joined to each other through a pressure side and a suction side (PS, SS), wherein, a new and novel profile section of the blade or vane element is provided.Type: ApplicationFiled: January 19, 2016Publication date: July 28, 2016Inventors: Tobias Froebel, Sebastian Mann, Nina Wolfrum, Sergio Elorza Gomez