Patents by Inventor Brian L. Riedel
Brian L. Riedel 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: 11455979Abstract: A co-curable thermoset acoustic liner and method of forming the same includes a sound attenuating core having a plurality of core cells. An inner face sheet having a plurality of face sheet apertures is coupled to the core by an inner thermoset adhesive sheet, which has a plurality of adhesive sheet apertures. Each of the plurality of adhesive sheet apertures is aligned within a corresponding one of the plurality of face sheet apertures so that the plurality of core cells are placed in fluid communication with airflow over the inner face sheet to create a Single Degree of Freedom (SDOF) acoustic liner.Type: GrantFiled: December 19, 2019Date of Patent: September 27, 2022Assignee: The Boeing CompanyInventors: Marc J. Froning, Arnold J. Lauder, Stefan Ozog, Brian L. Riedel
-
Patent number: 11400620Abstract: Methods and apparatus for curing curved cylinder-like workpieces (e.g., in the shape of a half or full barrel) made of composite material, such as nacelle honeycomb core composite sandwich structures. These methods enable tailored curing of composite nacelle structures, to significantly reduce capital cost and fabrication cycle time. In lieu of an autoclave or oven, a pressurized ring-shaped cure volume is defined by a partitioned enclosure that mimics the cylinder-like shape of the composite nacelle structure with only limited clearance (e.g., a partitioned enclosure comprising inner and outer concentric cylinder-like walls). A tool (e.g., a mandrel) and at least one composite nacelle structure supported thereon are placed in the cure volume for curing. Integrally heated tooling, optionally in combination with other heating methods, such as infrared heaters, is utilized to provide the temperature profile necessary for cure.Type: GrantFiled: November 15, 2018Date of Patent: August 2, 2022Assignee: The Boeing CompanyInventor: Brian L. Riedel
-
Publication number: 20210363921Abstract: A compact inlet design including a single bulkhead and/or an acoustic panel extending into nacelle lip region for noise reduction.Type: ApplicationFiled: August 9, 2021Publication date: November 25, 2021Inventors: Holly J. Thomas, Brian L. Riedel, Alexandre D. Curaudeau, David W. Foutch, Steve G. Mackin
-
Patent number: 11125157Abstract: A compact inlet design including a single bulkhead and/or an acoustic panel extending into nacelle lip region for noise reduction. The compact inlet is used with a low power fluid ice protection system capable of preventing ice build-up on the acoustic panel in the nacelle lip region.Type: GrantFiled: January 25, 2018Date of Patent: September 21, 2021Assignee: THE BOEING COMPANYInventors: Holly J. Thomas, Brian L. Riedel, Alexandre D. Curaudeau, David W. Foutch, Steve G. Mackin
-
Patent number: 11047308Abstract: An acoustic panel includes a base, a cantilevered portion, a gap, and a support member. The base has a surface defining a plurality of cavities configured to attenuate noise from an engine. The cantilevered portion extends from the base and is configured to be removably coupled with a portion of a transcowl. The gap is defined by the base and the cantilevered portion. The support member is coupled to the cantilevered portion and the base, and the supporting member is configured to support the cantilevered portion.Type: GrantFiled: June 29, 2018Date of Patent: June 29, 2021Assignee: THE BOEING COMPANYInventors: Alexandre D. Curaudeau, Brian L. Riedel, Taurus L. Brackett, II
-
Publication number: 20210193100Abstract: A co-curable thermoset acoustic liner and method of forming the same includes a sound attenuating core having a plurality of core cells. An inner face sheet having a plurality of face sheet apertures is coupled to the core by an inner thermoset adhesive sheet, which has a plurality of adhesive sheet apertures. Each of the plurality of adhesive sheet apertures is aligned within a corresponding one of the plurality of face sheet apertures so that the plurality of core cells are placed in fluid communication with airflow over the inner face sheet to create a Single Degree of Freedom (SDOF) acoustic liner.Type: ApplicationFiled: December 19, 2019Publication date: June 24, 2021Applicant: The Boeing CompanyInventors: Marc J. Froning, Arnold J. Lauder, Stefan Ozog, Brian L. Riedel
-
Publication number: 20200003124Abstract: An acoustic panel includes a base, a cantilevered portion, a gap, and a support member. The base has a surface defining a plurality of cavities configured to attenuate noise from an engine. The cantilevered portion extends from the base and is configured to be removably coupled with a portion of a transcowl. The gap is defined by the base and the cantilevered portion. The support member is coupled to the cantilevered portion and the base, and the supporting member is configured to support the cantilevered portion.Type: ApplicationFiled: June 29, 2018Publication date: January 2, 2020Inventors: Alexandre D. Curaudeau, Brian L. Riedel, Taurus L. Brackett, II
-
Publication number: 20190093557Abstract: A compact inlet design including a single bulkhead and/or an acoustic panel extending into nacelle lip region for noise reduction. The compact inlet is used with a low power fluid ice protection system capable of preventing ice build-up on the acoustic panel in the nacelle lip region.Type: ApplicationFiled: January 25, 2018Publication date: March 28, 2019Applicant: The Boeing CompanyInventors: Holly J. Thomas, Brian L. Riedel, Alexandre D. Curaudeau, David W. Foutch, Steve G. Mackin
-
Publication number: 20190084193Abstract: Methods and apparatus for curing curved cylinder-like workpieces (e.g., in the shape of a half or full barrel) made of composite material, such as nacelle honeycomb core composite sandwich structures. These methods enable tailored curing of composite nacelle structures, to significantly reduce capital cost and fabrication cycle time. In lieu of an autoclave or oven, a pressurized ring-shaped cure volume is defined by a partitioned enclosure that mimics the cylinder-like shape of the composite nacelle structure with only limited clearance (e.g., a partitioned enclosure comprising inner and outer concentric cylinder-like walls). A tool (e.g., a mandrel) and at least one composite nacelle structure supported thereon are placed in the cure volume for curing. Integrally heated tooling, optionally in combination with other heating methods, such as infrared heaters, is utilized to provide the temperature profile necessary for cure.Type: ApplicationFiled: November 15, 2018Publication date: March 21, 2019Applicant: The Boeing CompanyInventor: Brian L. Riedel
-
Patent number: 10137607Abstract: Methods and apparatus for curing curved cylinder-like workpieces (e.g., in the shape of a half or full barrel) made of composite material, such as nacelle honeycomb core composite sandwich structures. These methods enable tailored curing of composite nacelle structures, to significantly reduce capital cost and fabrication cycle time. In lieu of an autoclave or oven, a pressurized ring-shaped cure volume is defined by a partitioned enclosure that mimics the cylinder-like shape of the composite nacelle structure with only limited clearance (e.g., a partitioned enclosure comprising inner and outer concentric cylinder-like walls). A tool (e.g., a mandrel) and at least one composite nacelle structure supported thereon are placed in the cure volume for curing. Integrally heated tooling, optionally in combination with other heating methods, such as infrared heaters, is utilized to provide the temperature profile necessary for cure.Type: GrantFiled: October 1, 2014Date of Patent: November 27, 2018Assignee: The Boeing CompanyInventor: Brian L. Riedel
-
Publication number: 20160096289Abstract: Methods and apparatus for curing curved cylinder-like workpieces (e.g., in the shape of a half or full barrel) made of composite material, such as nacelle honeycomb core composite sandwich structures. These methods enable tailored curing of composite nacelle structures, to significantly reduce capital cost and fabrication cycle time. In lieu of an autoclave or oven, a pressurized ring-shaped cure volume is defined by a partitioned enclosure that mimics the cylinder-like shape of the composite nacelle structure with only limited clearance (e.g., a partitioned enclosure comprising inner and outer concentric cylinder-like walls). A tool (e.g., a mandrel) and at least one composite nacelle structure supported thereon are placed in the cure volume for curing. Integrally heated tooling, optionally in combination with other heating methods, such as infrared heaters, is utilized to provide the temperature profile necessary for cure.Type: ApplicationFiled: October 1, 2014Publication date: April 7, 2016Applicant: THE BOEING COMPANYInventor: Brian L. Riedel
-
Patent number: 6688558Abstract: An inlet ice protection system, and methods for making and using ice protection systems. In one embodiment, the inlet includes a tapered acoustic liner positioned forward of the inlet throat and has a perforated face sheet, a perforated back sheet, and an acoustic core between the face sheet and the back sheet. The perforations through the face sheet are sized to allow acoustic energy to be transmitted to and dissipated in the acoustic core, and the perforations in the back sheet are sized to transmit hot gas through the acoustic liner to the surface of the inlet to heat the inlet and prevent and/or restrict ice formation on the inlet. The face sheet can have a higher porosity than the back sheet, and both the sheets and the core can be formed from titanium to withstand high gas temperatures.Type: GrantFiled: May 29, 2002Date of Patent: February 10, 2004Assignee: The Boeing CompanyInventors: Marlin D. Breer, Ronald F. Olsen, Robert K. Kunze, Jr., Brian L. Riedel
-
Publication number: 20020179773Abstract: An inlet ice protection system, and methods for making and using ice protection systems. In one embodiment, the inlet includes a tapered acoustic liner positioned forward of the inlet throat and has a perforated face sheet, a perforated back sheet, and an acoustic core between the face sheet and the back sheet. The perforations through the face sheet are sized to allow acoustic energy to be transmitted to and dissipated in the acoustic core, and the perforations in the back sheet are sized to transmit hot gas through the acoustic liner to the surface of the inlet to heat the inlet and prevent and/or restrict ice formation on the inlet. The face sheet can have a higher porosity than the back sheet, and both the sheets and the core can be formed from titanium to withstand high gas temperatures.Type: ApplicationFiled: May 29, 2002Publication date: December 5, 2002Inventors: Marlin D. Breer, Ronald F. Olsen, Robert K. Kunze, Brian L. Riedel
-
Patent number: 6457676Abstract: An inlet ice protection system, and methods for making and using ice protection systems. In one embodiment, the inlet includes an acoustic liner positioned forward of the inlet throat and has a perforated face sheet, a perforated back sheet, and an acoustic core between the face sheet and the back sheet. The perforations through the face sheet are sized to allow acoustic energy to be transmitted to and dissipated in the acoustic core, and the perforations in the back sheet are sized to transmit hot gas through the acoustic liner to the surface of the inlet to heat the inlet and prevent and/or restrict ice formation on the inlet. The face sheet can have a higher porosity than the back sheet, and both the sheets and the core can be formed from titanium to withstand high gas temperatures.Type: GrantFiled: October 2, 2001Date of Patent: October 1, 2002Assignee: The Boeing CompanyInventors: Marlin D. Breer, Ronald F. Olsen, Robert K. Kunze, Jr., Brian L. Riedel
-
Publication number: 20020047070Abstract: An inlet ice protection system, and methods for making and using ice protection systems. In one embodiment, the inlet includes an acoustic liner positioned forward of the inlet throat and has a perforated face sheet, a perforated back sheet, and an acoustic core between the face sheet and the back sheet. The perforations through the face sheet are sized to allow acoustic energy to be transmitted to and dissipated in the acoustic core, and the perforations in the back sheet are sized to transmit hot gas through the acoustic liner to the surface of the inlet to heat the inlet and prevent and/or restrict ice formation on the inlet. The face sheet can have a higher porosity than the back sheet, and both the sheets and the core can be formed from titanium to withstand high gas temperatures.Type: ApplicationFiled: October 2, 2001Publication date: April 25, 2002Inventors: Marlin D. Breer, Ronald F. Olsen, Robert K. Kunze, Brian L. Riedel
-
Patent number: 6371411Abstract: An inlet ice protection system, and methods for making and using ice protection systems. In one embodiment, the inlet includes an acoustic liner positioned forward of the inlet throat and has a perforated face sheet a perforated back sheet, and an acoustic core between the face sheet and the back sheet. The perforations through the face sheet are sized to allow acoustic energy to be transmitted to and dissipated in the acoustic core, and the perforations in the back sheet are sized to transmit hot gas through the acoustic liner to the surface of the inlet to heat the inlet and prevent and/or restrict ice formation on the inlet. The face sheet can have a higher porosity than the back sheet, and both the sheets and the core can be formed from titanium to withstand high gas temperatures.Type: GrantFiled: November 23, 1999Date of Patent: April 16, 2002Assignee: The Boeing CompanyInventors: Marlin D. Breer, Ronald F. Olsen, Robert K. Kunze, Jr., Brian L. Riedel
-
Publication number: 20010048048Abstract: A method of attaching acoustic panels to aircraft structures without loss of acoustic area due to the attachment means. The invention comprises the uses of high-shear blind fasteners in combination with acoustic panels having backside laminate and ply build-up area increased in thickness to retain the blind fastener, react the bearing loads and provide adequate stiffness for bending. The present structure and method reduces acoustic panel installation cycle time by an estimated 50% while providing noise reduction.Type: ApplicationFiled: January 13, 1999Publication date: December 6, 2001Inventors: BRIAN L RIEDEL, JOHN T STRUNK, RANDALL R CLARK