Patents by Inventor Cesare A. HALL
Cesare A. HALL 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: 11692454Abstract: An aircraft engine comprising a fan, the fan having a diameter D and including a plurality of fan blades, the fan blades having a sweep metric Stip, each fan blade having a leading edge, and a forward-most portion on the leading edge of each fan blade being in a first reference plane. The aircraft engine further comprises a nacelle, comprising an intake portion forward of the fan, a forward edge on the intake portion being in a second reference plane, wherein the intake portion has a length L measured along an axis of the aircraft engine between the first reference plane and the second reference plane, the aircraft engine having a cruise design point condition Mrel, wherein Mrel is between 0.4 and 0.93, L/D is between 0.2 and 0.45 and Stip is from ?1 to 0.1.Type: GrantFiled: November 4, 2021Date of Patent: July 4, 2023Inventors: Benjamin Mohankumar, Mark J. Wilson, Cesare A. Hall
-
Patent number: 11598214Abstract: An aircraft engine comprising a fan, the fan having a diameter D and including a plurality of fan blades, the fan blades having a sweep metric S, each fan blade having a leading edge, and a forward-most portion on the leading edge of each fan blade being in a first reference plane. The aircraft engine further comprises a nacelle, comprising an intake portion forward of the fan, a forward edge on the intake portion being in a second reference plane, wherein the intake portion has a length L measured along an axis of the aircraft engine between the first reference plane and the second reference plane, the aircraft engine having a cruise design point condition Mrel, wherein Mrel is between 0.4 and 0.93, and L/D is between 0.2 and 0.45.Type: GrantFiled: August 26, 2021Date of Patent: March 7, 2023Inventors: Benjamin Mohankumar, Mark J. Wilson, Cesare A. Hall
-
Publication number: 20220162957Abstract: An aircraft engine comprising a fan, the fan having a diameter D and including a plurality of fan blades, the fan blades having a sweep metric Stip, each fan blade having a leading edge, and a forward-most portion on the leading edge of each fan blade being in a first reference plane. The aircraft engine further comprises a nacelle, comprising an intake portion forward of the fan, a forward edge on the intake portion being in a second reference plane, wherein the intake portion has a length L measured along an axis of the aircraft engine between the first reference plane and the second reference plane, the aircraft engine having a cruise design point condition Mrel, wherein Mrel is between 0.4 and 0.93, L/D is between 0.2 and 0.45 and Stip is from ?1 to 0.1.Type: ApplicationFiled: November 4, 2021Publication date: May 26, 2022Applicant: ROLLS-ROYCE plcInventors: Benjamin MOHANKUMAR, Mark J. WILSON, Cesare A. HALL
-
Publication number: 20220074308Abstract: An aircraft engine comprising a fan, the fan having a diameter D and including a plurality of fan blades, the fan blades having a sweep metric S, each fan blade having a leading edge, and a forward-most portion on the leading edge of each fan blade being in a first reference plane. The aircraft engine further comprises a nacelle, comprising an intake portion forward of the fan, a forward edge on the intake portion being in a second reference plane, wherein the intake portion has a length L measured along an axis of the aircraft engine between the first reference plane and the second reference plane, the aircraft engine having a cruise design point condition Mrel, wherein Mrel is between 0.4 and 0.93, and L/D is between 0.2 and 0.45.Type: ApplicationFiled: August 26, 2021Publication date: March 10, 2022Applicant: ROLLS-ROYCE plcInventors: Benjamin MOHANKUMAR, Mark J. WILSON, Cesare A. HALL
-
Patent number: 11208895Abstract: A gas turbine engine for an aircraft including: an engine core including a turbine, compressor, and core shaft connecting turbine to the compressor; a fan located upstream of engine core, the fan containing a plurality of fan blades mounted for rotation about an engine axis, each blade of the plurality of fan blades having a leading edge and trailing edge extending across a span of an airflow duct from blade root to tip; and a gearbox that receives an input from core shaft and outputs drive to fan so as to drive the fan at a lower rotational speed than the core shaft, wherein the trailing edge of each blade is characterized by a metric M defined as a rate of change of an angle of trailing edge between 0.4 and 0.8 of the span divided by an area averaged trailing edge angle, M being not less than around 4.Type: GrantFiled: October 7, 2020Date of Patent: December 28, 2021Assignee: ROLLS-ROYCE plcInventors: Benjamin Mohankumar, Mark J Wilson, Cesare A Hall
-
Publication number: 20210222563Abstract: A gas turbine engine for an aircraft including: an engine core including a turbine, compressor, and core shaft connecting turbine to the compressor; a fan located upstream of engine core, the fan containing a plurality of fan blades mounted for rotation about an engine axis, each blade of the plurality of fan blades having a leading edge and trailing edge extending across a span of an airflow duct from blade root to tip; and a gearbox that receives an input from core shaft and outputs drive to fan so as to drive the fan at a lower rotational speed than the core shaft, wherein the trailing edge of each blade is characterized by a metric M defined as a rate of change of an angle of trailing edge between 0.4 and 0.8 of the span divided by an area averaged trailing edge angle, M being not less than around 4.Type: ApplicationFiled: October 7, 2020Publication date: July 22, 2021Applicant: ROLLS-ROYCE plcInventors: Benjamin MOHANKUMAR, Mark J WILSON, Cesare A HALL
-
Publication number: 20180073377Abstract: A boundary layer Ingesting (BLI) fan system operates with a highly non-uniform flow field that propagates through the fan stage. The fan stage suffers from hub separations, increased wake thicknesses and casing losses. These loss sources can be reduced or eliminated by varying the inlet metal angles and/or chordal lengths of the downstream fan stators.Type: ApplicationFiled: August 16, 2017Publication date: March 15, 2018Applicant: ROLLS-ROYCE plcInventors: Cesare A. HALL, Ewan J. GUNN, Sarah E. TOOZE