Patents by Inventor David F. Cerra
David F. Cerra 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: 11827373Abstract: Aircraft engine exhaust systems enabling short aft fairings are described. An example turbofan engine exhaust system of an aircraft includes a primary nozzle having a leading edge and a trailing edge, and a heat shield coupled to an aft strut fairing. The heat shield has an upstream end and a downstream end. The downstream end of the heat shield is substantially coterminous with the trailing edge of the primary nozzle.Type: GrantFiled: September 27, 2019Date of Patent: November 28, 2023Assignee: The Boeing CompanyInventors: Abhishek Sahay, David F. Cerra
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Publication number: 20220205409Abstract: Conventional commercial engine exhaust systems are defined with axi-symmetric surfaces (e.g., conical or nearly conical surfaces), which create an annular exhaust for the fan (bypass) nozzle of roughly constant duct-height around the circumference. In one example configuration, the fan sleeve has been sheared upward (towards the wing or pylon) causing a larger area and duct height near the pylon relative to the portion away from the pylon. For a given thrust generated by the turbofan engine housed in the nacelle, the shear toward the pylon mount realigns the thrust in the direction of flight which may, in some examples, reduce noise experienced downstream of the turbofan engine and decreases fuel consumed in the engine core.Type: ApplicationFiled: March 15, 2022Publication date: June 30, 2022Applicant: The Boeing CompanyInventors: Kurt E. Acheson, David F. Cerra, Robert H. Willie
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Patent number: 11306681Abstract: Conventional commercial engine exhaust systems are defined with axi-symmetric surfaces (e.g., conical or nearly conical surfaces), which create an annular exhaust for the fan (bypass) nozzle of roughly constant duct-height around the circumference. In one example configuration, the fan sleeve has been sheared upward (towards the wing or pylon) causing a larger area and duct height near the pylon relative to the portion away from the pylon. For a given thrust generated by the turbofan engine housed in the nacelle, the shear toward the pylon mount realigns the thrust in the direction of flight which may, in some examples, reduce noise experienced downstream of the turbofan engine and decreases fuel consumed in the engine core.Type: GrantFiled: January 15, 2019Date of Patent: April 19, 2022Assignee: THE BOEING COMPANYInventors: Kurt E. Acheson, David F. Cerra, Robert H. Willie
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Patent number: 10989114Abstract: Systems and methods for cooling bleed air from an aircraft engine are described. An example system includes a housing to bifurcate airflow exiting a fan of an engine fan system, a pre-cooler assembly disposed within the housing to remove heat from the bleed air, and an inlet duct within the housing to direct the airflow to the pre-cooler assembly. The example system also includes at least one diverter duct within the housing and coupled to the inlet duct to divert the airflow around the pre-cooler assembly. The at least one diverter duct includes an exit directing the airflow into a fan duct of the engine fan system. The example system also includes at least one valve to control an amount of airflow through the inlet duct and an amount of airflow through the at least one diverter duct.Type: GrantFiled: March 7, 2018Date of Patent: April 27, 2021Assignee: The Boeing CompanyInventors: David F. Cerra, Paul R. Tretow
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Publication number: 20210094699Abstract: Aircraft engine exhaust systems enabling short aft fairings are described. An example turbofan engine exhaust system of an aircraft includes a primary nozzle having a leading edge and a trailing edge, and a heat shield coupled to an aft strut fairing. The heat shield has an upstream end and a downstream end. The downstream end of the heat shield is substantially coterminous with the trailing edge of the primary nozzle.Type: ApplicationFiled: September 27, 2019Publication date: April 1, 2021Inventors: Abhishek Sahay, David F. Cerra
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Publication number: 20200224605Abstract: Conventional commercial engine exhaust systems are defined with axi-symmetric surfaces (e.g., conical or nearly conical surfaces), which create an annular exhaust for the fan (bypass) nozzle of roughly constant duct-height around the circumference. In one example configuration, the fan sleeve has been sheared upward (towards the wing or pylon) causing a larger area and duct height near the pylon relative to the portion away from the pylon. For a given thrust generated by the turbofan engine housed in the nacelle, the shear toward the pylon mount realigns the thrust in the direction of flight which may, in some examples, reduce noise experienced downstream of the turbofan engine and decreases fuel consumed in the engine core.Type: ApplicationFiled: January 15, 2019Publication date: July 16, 2020Applicant: The Boeing CompanyInventors: Kurt E. Acheson, David F. Cerra, Robert H. Willie
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Publication number: 20190277195Abstract: Systems and methods for cooling bleed air from an aircraft engine are described. An example system includes a housing to bifurcate airflow exiting a fan of an engine fan system, a pre-cooler assembly disposed within the housing to remove heat from the bleed air, and an inlet duct within the housing to direct the airflow to the pre-cooler assembly. The example system also includes at least one diverter duct within the housing and coupled to the inlet duct to divert the airflow around the pre-cooler assembly. The at least one diverter duct includes an exit directing the airflow into a fan duct of the engine fan system. The example system also includes at least one valve to control an amount of airflow through the inlet duct and an amount of airflow through the at least one diverter duct.Type: ApplicationFiled: March 7, 2018Publication date: September 12, 2019Inventors: David F. Cerra, Paul R. Tretow
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Patent number: 10094332Abstract: A core cowl for a turbofan engine may include a plurality of valleys formed in an outer surface of the core cowl. Each valley may include a convex portion upstream of a concave portion, and may be configured to disrupt a shock cell exiting a fan nozzle of the turbofan engine. Associated methods for reducing turbofan engine noise are also described.Type: GrantFiled: September 3, 2014Date of Patent: October 9, 2018Assignee: The Boeing CompanyInventors: David F. Cerra, Paul Robert Tretow, Robert H. Willie, Abhishek Sahay
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Patent number: 10040560Abstract: A turbine engine nozzle can include a primary outer wall extending from an engine core area to an annular wall terminus that surrounds an engine tail cone, to form a core nozzle. The turbine engine nozzle also includes a single engine core cowl extending from the engine core area to an annular cowl terminus to form a core compartment vent nozzle. The core compartment vent nozzle exhausts air from a core compartment in a trailing edge between the single engine core cowl and the primary outer wall.Type: GrantFiled: September 30, 2015Date of Patent: August 7, 2018Assignee: THE BOEING COMPANYInventors: Robert H. Willie, Paul R. Tretow, David F. Cerra
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Patent number: 10001080Abstract: A thrust reverse variable area nozzle system for a nacelle of an aircraft engine system may include a reverse thrust opening disposed in the nacelle, and a thrust reverser door pivotally movable relative to the nacelle for selectively covering the reverse thrust opening, wherein the thrust reverser door is pivotally movable between a first position for completely covering the reverse thrust opening, a second position for partially uncovering a forward portion of the reverse thrust opening and discharging a bypass airflow through the forward portion of the reverse thrust opening in a forward direction, and a third position for partially uncovering an aft portion of the reverse thrust opening and discharging the bypass airflow through the aft portion of the reverse thrust opening in an aft direction.Type: GrantFiled: August 19, 2014Date of Patent: June 19, 2018Assignee: The Boeing CompanyInventors: David F. Cerra, Robert H. Willie
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Patent number: 9964070Abstract: A gas turbine engine exhaust nozzle comprises a housing having an aft end that terminates in a row of chevrons. At least one surface of the housing has scalloped root regions proximate bases of adjacent chevrons. The scalloped root regions have a reduced thickness relative to the rest of the aft end.Type: GrantFiled: January 21, 2013Date of Patent: May 8, 2018Assignee: The Boeing CompanyInventors: David F. Cerra, Lie-Mine Gea, Robert H. Willie, Leonard J. Hebert, Donald E. Robinson
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Publication number: 20170298868Abstract: A gas turbine engine exhaust nozzle comprises a housing having an aft end that terminates in a row of chevrons. At least one surface of the housing has scalloped root regions proximate bases of adjacent chevrons. The scalloped root regions have a reduced thickness relative to the rest of the aft end.Type: ApplicationFiled: January 21, 2013Publication date: October 19, 2017Applicant: The Boeing CompanyInventors: David F. Cerra, Lie-Mine Gea, Robert H. Willie, Leonard J. Hebert, Donald E. Robinson
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Patent number: 9732700Abstract: A flow vectoring turbofan engine employs a fixed geometry fan sleeve and core cowl forming a nozzle incorporating an asymmetric convergent/divergent (con-di) and/or curvature section which varies angularly from a midplane for reduced pressure in a first operating condition to induce flow turning and axially symmetric equal pressure in a second operating condition for substantially axial flow.Type: GrantFiled: September 25, 2014Date of Patent: August 15, 2017Assignee: The Boeing CompanyInventors: David F. Cerra, Robert H. Willie, Alvaro Prieto
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Publication number: 20170088275Abstract: A turbine engine nozzle can include a primary outer wall extending from an engine core area to an annular wall terminus that surrounds an engine tail cone, to form a core nozzle. The turbine engine nozzle also includes a single engine core cowl extending from the engine core area to an annular cowl terminus to form a core compartment vent nozzle. The core compartment vent nozzle exhausts air from a core compartment in a trailing edge between the single engine core cowl and the primary outer wall.Type: ApplicationFiled: September 30, 2015Publication date: March 30, 2017Inventors: Robert H. Willie, Paul R. Tretow, David F. Cerra
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Patent number: 9546618Abstract: A flow vectoring turbofan engine employs a fixed geometry fan sleeve and core cowl forming a nozzle incorporating an asymmetric convergent/divergent (con-di) and/or curvature section which varies angularly from a midplane for reduced pressure in a first operating condition to induce flow turning and axially symmetric equal pressure in a second operating condition for substantially axial flow.Type: GrantFiled: October 24, 2013Date of Patent: January 17, 2017Assignee: THE BOEING COMPANYInventors: Robert H. Willie, David F. Cerra, Leonard J. Hebert
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Patent number: 9416801Abstract: A method and apparatus for draining fluid from a structure on an aircraft. The apparatus comprises a drainage tube, a housing, a number of inlet holes in the housing, and a number of outlet holes in the housing. The drainage tube has first end that connects to a structure on an aircraft and a second end opposite the first end. The housing connects to the structure. The drainage tube is located within the housing. Air flows into the housing during flight of the aircraft through the number of inlet holes in the housing. The air flows out of the housing during flight of the aircraft through the number of outlet holes. The air flowing into the housing through the number of inlet holes and out the housing through the number of outlet holes directs fluid out of the drainage tube and away from the structure during flight of the aircraft.Type: GrantFiled: June 12, 2014Date of Patent: August 16, 2016Assignee: THE BOEING COMPANYInventors: Robert Henry Willie, David F. Cerra
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Publication number: 20160061115Abstract: A core cowl for a turbofan engine may include a plurality of valleys formed in an outer surface of the core cowl. Each valley may include a convex portion upstream of a concave portion, and may be configured to disrupt a shock cell exiting a fan nozzle of the turbofan engine. Associated methods for reducing turbofan engine noise are also described.Type: ApplicationFiled: September 3, 2014Publication date: March 3, 2016Applicant: THE BOEING COMPANYInventors: David F. Cerra, Paul Robert Tretow, Robert H. Willie, Abhishek Sahay
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Publication number: 20160053718Abstract: A thrust reverse variable area nozzle system for a nacelle of an aircraft engine system may include a reverse thrust opening disposed in the nacelle, and a thrust reverser door pivotally movable relative to the nacelle for selectively covering the reverse thrust opening, wherein the thrust reverser door is pivotally movable between a first position for completely covering the reverse thrust opening, a second position for partially uncovering a forward portion of the reverse thrust opening and discharging a bypass airflow through the forward portion of the reverse thrust opening in a forward direction, and a third position for partially uncovering an aft portion of the reverse thrust opening and discharging the bypass airflow through the aft portion of the reverse thrust opening in an aft direction.Type: ApplicationFiled: August 19, 2014Publication date: February 25, 2016Inventors: David F. Cerra, Robert H. Willie
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Publication number: 20150361823Abstract: A flow vectoring turbofan engine employs a fixed geometry fan sleeve and core cowl forming a nozzle incorporating an asymmetric convergent/divergent (con-di) and/or curvature section which varies angularly from a midplane for reduced pressure in a first operating condition to induce flow turning and axially symmetric equal pressure in a second operating condition for substantially axial flow.Type: ApplicationFiled: September 25, 2014Publication date: December 17, 2015Inventors: David F. Cerra, Robert H. Willie, Alvaro Prieto
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Publication number: 20150361999Abstract: A method and apparatus for draining fluid from a structure on an aircraft. The apparatus comprises a drainage tube, a housing, a number of inlet holes in the housing, and a number of outlet holes in the housing. The drainage tube has first end that connects to a structure on an aircraft and a second end opposite the first end. The housing connects to the structure. The drainage tube is located within the housing. Air flows into the housing during flight of the aircraft through the number of inlet holes in the housing. The air flows out of the housing during flight of the aircraft through the number of outlet holes. The air flowing into the housing through the number of inlet holes and out the housing through the number of outlet holes directs fluid out of the drainage tube and away from the structure during flight of the aircraft.Type: ApplicationFiled: June 12, 2014Publication date: December 17, 2015Inventors: Robert Henry Willie, David F. Cerra