Patents by Inventor Carsten Ralf Mehring
Carsten Ralf Mehring 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: 10618636Abstract: A laminar flow control surface having a foraminous section (also referred to below as a foraminous portion, 251) of a skin (250) of a vehicle to permit low temperature fluid to flow through the foraminous section to a heat exchanger (236), to reduce drag of the vehicle and to dissipate heat from the heat exchanger. The foraminous section (251) and the heat exchanger (236) synergistically reduce drag and transfer heat from the heat exchanger. The vehicle may be an aircraft with a laminar flow control system including a foraminous portion on a leading edge of the aircraft. While the aircraft is in flight, a portion of air impinging near the foraminous portion may flow laminarly about the leading edge, and another portion of the impingingair may flow through the foraminous portion to a heat exchanger to transfer heat from the heat exchanger to the air.Type: GrantFiled: March 4, 2015Date of Patent: April 14, 2020Assignee: Parker-Hannifin CorporationInventor: Carsten Ralf Mehring
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Publication number: 20160332724Abstract: A laminar flow control surface having a foraminous section (also referred to below as a foraminous portion, 251) of a skin (250) of a vehicle to permit low temperature fluid to flow through the foraminous section to a heat exchanger (236), to reduce drag of the vehicle and to dissipate heat from the heat exchanger. The foraminous section (251) and the heat exchanger (236) synergistically reduce drag and transfer heat from the heat exchanger. The vehicle may be an aircraft with a laminar flow control system including a foraminous portion on a leading edge of the aircraft. While the aircraft is in flight, a portion of air impinging near the foraminous portion may flow laminarly about the leading edge, and another portion of the impingingair may flow through the foraminous portion to a heat exchanger to transfer heat from the heat exchanger to the air.Type: ApplicationFiled: March 4, 2015Publication date: November 17, 2016Applicant: PARKER-HANNIFIN CORPORATIONInventor: Carsten Ralf Mehring
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Patent number: 9062609Abstract: A fuel injection system comprises a combustor liner, an air tube, a fuel manifold and a fuel injector. The combustor liner defines primary and secondary combustion zones. The air tube extends through the combustor liner along an axis to an exit aperture inside the combustor. The fuel manifold is positioned proximate the combustor line to deliver fuel through the air tube to the primary and secondary combustion zones. The fuel injector is coupled to the fuel manifold and positioned to inject the fuel along an axis of the air tube, such that the fuel has a substantially symmetric distribution at the exit aperture.Type: GrantFiled: January 9, 2012Date of Patent: June 23, 2015Assignee: Hamilton Sundstrand CorporationInventors: Carsten Ralf Mehring, James Peffley
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Patent number: 8572978Abstract: A gas turbine engine includes a reverse flow annular combustor having a liner with opposing ends. One end includes apertures configured to receive compressed air, and an outlet is provided at the other end and is configured to connect to a turbine nozzle. A fuel injector extends through the liner at a base and axially between the apertures and the outlet. The fuel injector includes a housing extending from the base to a dome and provides an exterior surface surrounding an injector cavity. The exterior surface has forward and rearward surfaces respectively facing the apertures and the outlet and provides shapes that are different than one another to influence and improve the aerodynamic flow field of the gas mixture (i.e., air, fuel and combustion-products) within the combustor volume.Type: GrantFiled: October 2, 2009Date of Patent: November 5, 2013Assignee: Hamilton Sundstrand CorporationInventor: Carsten Ralf Mehring
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Publication number: 20130174559Abstract: A fuel injection system comprises a combustor liner, an air tube, a fuel manifold and a fuel injector. The combustor liner defines primary and secondary combustion zones. The air tube extends through the combustor liner along an axis to an exit aperture inside the combustor. The fuel manifold is positioned proximate the combustor line to deliver fuel through the air tube to the primary and secondary combustion zones. The fuel injector is coupled to the fuel manifold and positioned to inject the fuel along an axis of the air tube, such that the fuel has a substantially symmetric distribution at the exit aperture.Type: ApplicationFiled: January 9, 2012Publication date: July 11, 2013Applicant: HAMILTON SUNDSTRAND CORPORATIONInventors: Carsten Ralf Mehring, James Peffley
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Patent number: 8351780Abstract: An imaging system to collect image data relating to a conical liquid film and its hollow conical spray emanating from an injector with a central spray axis includes a light source for emitting light into the film and spray generated by the injector; and a detector array located downstream from the injector along the central spray axis for panoramically detecting instantaneously for the entire film and spray the emitted light which has interacted with the spray to produce the image data.Type: GrantFiled: February 1, 2011Date of Patent: January 8, 2013Assignee: Hamilton Sundstrand CorporationInventor: Carsten Ralf Mehring
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Publication number: 20120195578Abstract: An imaging system to collect image data relating to a conical liquid film and its hollow conical spray emanating from an injector with a central spray axis includes a light source for emitting light into the film and spray generated by the injector; and a detector array located downstream from the injector along the central spray axis for panoramically detecting instantaneously for the entire film and spray the emitted light which has interacted with the spray to produce the image data.Type: ApplicationFiled: February 1, 2011Publication date: August 2, 2012Applicant: HAMILTON SUNDSTRAND CORPORATIONInventor: Carsten Ralf Mehring
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Publication number: 20120023964Abstract: A reverse flow annular combustor for a gas turbine includes a pre-vaporizer/pre-mixing region within a dome section, a liquid fuel injection system feeding the pre-mixing region, a combustion region downstream of the pre-vaporizer/pre-mixing region, a means for guaranteeing stable and sustained combustion in the combustion region, and a dilution region downstream of the combustion region.Type: ApplicationFiled: July 27, 2010Publication date: February 2, 2012Inventor: Carsten Ralf Mehring
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Publication number: 20110079013Abstract: A gas turbine engine includes a reverse flow annular combustor having a liner with opposing ends. One end includes apertures configured to receive compressed air, and an outlet is provided at the other end and is configured to connect to a turbine nozzle. A fuel injector extends through the liner at a base and axially between the apertures and the outlet. The fuel injector includes a housing extending from the base to a dome and provides an exterior surface surrounding an injector cavity. The exterior surface has forward and rearward surfaces respectively facing the apertures and the outlet and provides shapes that are different than one another to influence and improve the aerodynamic flow field of the gas mixture (i.e., air, fuel and combustion-products) within the combustor volume.Type: ApplicationFiled: October 2, 2009Publication date: April 7, 2011Inventor: Carsten Ralf Mehring
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Patent number: 7625173Abstract: An inlet plenum for coupling airflow from a radial airflow inlet to an axial compressor inlet for a compressor comprises a perforated inlet (PI) baffle that comprises a generally cylindrical baffle that circumscribes the compressor inlet and a plurality of apertures, each aperture perforating the baffle to pass the airflow from the radial airflow inlet to the compressor inlet and a plurality of stagnation vanes, each stagnation vane comprising a generally arc-shaped vane that extends proximate the PI baffle to establish an approximation of stagnant flow around the entire PI baffle to reduce flow distortion of the airflow between the radial airflow inlet and the axial compressor inlet.Type: GrantFiled: December 11, 2006Date of Patent: December 1, 2009Assignee: Hamilton Sundstrand CorporationInventor: Carsten Ralf Mehring