Patents by Inventor Pascal DUNNING
Pascal DUNNING 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: 11898489Abstract: A gas turbine engine for an aircraft comprises an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor, wherein a compressor exit temperature is defined as an average temperature of airflow at the exit from the compressor; and a fan located upstream of the engine core, the fan comprising a plurality of fan blades extending from a hub, each fan blade having a leading edge and a trailing edge, wherein a fan rotor entry temperature is defined as an average temperature of airflow across the leading edge of each fan blade at cruise conditions and a fan tip rotor exit temperature is defined as an average temperature of airflow across a radially outer portion of each fan blade at the trailing edge at cruise conditions. A core to fan tip temperature rise ratio is in the range from 2.845 to 3.8.Type: GrantFiled: March 17, 2023Date of Patent: February 13, 2024Assignee: ROLLS-ROYCE plcInventors: Craig W Bemment, Pascal Dunning
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Publication number: 20230272752Abstract: A highly efficient gas turbine engine is provided. The fan of the gas turbine engine is driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.Type: ApplicationFiled: April 20, 2023Publication date: August 31, 2023Applicant: ROLLS-ROYCE plcInventors: Pascal DUNNING, Roderick M. TOWNES, Michael J. WHITTLE
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Publication number: 20230228232Abstract: A gas turbine engine for an aircraft comprises an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor, wherein a compressor exit temperature is defined as an average temperature of airflow at the exit from the compressor; and a fan located upstream of the engine core, the fan comprising a plurality of fan blades extending from a hub, each fan blade having a leading edge and a trailing edge, wherein a fan rotor entry temperature is defined as an average temperature of airflow across the leading edge of each fan blade at cruise conditions and a fan tip rotor exit temperature is defined as an average temperature of airflow across a radially outer portion of each fan blade at the trailing edge at cruise conditions. A core to fan tip temperature rise ratio is in the range from 2.845 to 3.8.Type: ApplicationFiled: March 17, 2023Publication date: July 20, 2023Applicant: ROLLS-ROYCE plcInventors: Craig W BEMMENT, Pascal DUNNING
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Patent number: 11668246Abstract: A highly efficient gas turbine engine is provided. The fan of the gas turbine engine is driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.Type: GrantFiled: March 23, 2021Date of Patent: June 6, 2023Assignee: ROLLS-ROYCE plcInventors: Pascal Dunning, Roderick M Townes, Michael J Whittle
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Patent number: 11635021Abstract: A gas turbine engine for an aircraft comprises an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor, wherein a compressor exit temperature is defined as an average temperature of airflow at the exit from the compressor; and a fan located upstream of the engine core, the fan comprising a plurality of fan blades extending from a hub, each fan blade having a leading edge and a trailing edge, wherein a fan rotor entry temperature is defined as an average temperature of airflow across the leading edge of each fan blade at cruise conditions and a fan tip rotor exit temperature is defined as an average temperature of airflow across a radially outer portion of each fan blade at the trailing edge at cruise conditions. A core to fan tip temperature rise ratio is in the range from 2.845 to 3.8.Type: GrantFiled: March 17, 2022Date of Patent: April 25, 2023Assignee: ROLLS-ROYCE plcInventors: Craig W Bemment, Pascal Dunning
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Patent number: 11560853Abstract: A gas turbine engine for an aircraft includes an engine core including a first, lower pressure, turbine, a first compressor, and a first core shaft connecting the first turbine to the first compressor; and a second, higher pressure, turbine, a second compressor, and a second core shaft connecting the second turbine to the second compressor, and a fan located upstream of the engine core and including a plurality of fan blades extending from a hub. A turbine to fan tip temperature change ratio of a low pressure turbine temperature change to a fan tip temperature rise is in the range from 1.46 to 2.0.Type: GrantFiled: September 3, 2021Date of Patent: January 24, 2023Assignee: ROLLS-ROYCE plcInventors: Craig W Bemment, Pascal Dunning
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Patent number: 11466617Abstract: A highly efficient gas turbine engine includes the fan of the gas turbine engine driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.Type: GrantFiled: June 11, 2021Date of Patent: October 11, 2022Assignee: ROLLS-ROYCE PLCInventors: Pascal Dunning, Michael J Whittle, Roderick M Townes
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Publication number: 20220307448Abstract: A highly efficient gas turbine engine is provided. The fan of the gas turbine engine is driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.Type: ApplicationFiled: January 27, 2022Publication date: September 29, 2022Applicant: ROLLS-ROYCE plcInventors: Roderick M. TOWNES, Pascal DUNNING, Michael J. WHITTLE
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Publication number: 20220268216Abstract: A highly efficient gas turbine engine is a system wherein the fan of the gas turbine engine is driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.Type: ApplicationFiled: April 28, 2022Publication date: August 25, 2022Applicant: ROLLS-ROYCE plcInventors: Roderick M TOWNES, Michael J WHITTLE, Pascal DUNNING
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Publication number: 20220205386Abstract: A gas turbine engine for an aircraft comprises an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor, wherein a compressor exit temperature is defined as an average temperature of airflow at the exit from the compressor; and a fan located upstream of the engine core, the fan comprising a plurality of fan blades extending from a hub, each fan blade having a leading edge and a trailing edge, wherein a fan rotor entry temperature is defined as an average temperature of airflow across the leading edge of each fan blade at cruise conditions and a fan tip rotor exit temperature is defined as an average temperature of airflow across a radially outer portion of each fan blade at the trailing edge at cruise conditions. A core to fan tip temperature rise ratio is in the range from 2.845 to 3.8.Type: ApplicationFiled: March 17, 2022Publication date: June 30, 2022Applicant: ROLLS-ROYCE PLCInventors: Craig W BEMMENT, Pascal DUNNING
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Patent number: 11326512Abstract: A gas turbine engine for an aircraft comprises an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor, wherein a compressor exit temperature is defined as an average temperature of airflow at the exit from the compressor; and a fan located upstream of the engine core, the fan comprising a plurality of fan blades extending from a hub, each fan blade having a leading edge and a trailing edge, wherein a fan rotor entry temperature is defined as an average temperature of airflow across the leading edge of each fan blade at cruise conditions and a fan tip rotor exit temperature is defined as an average temperature of airflow across a radially outer portion of each fan blade at the trailing edge at cruise conditions. A core to fan tip temperature rise ratio is in the range from 2.845 to 3.8.Type: GrantFiled: June 11, 2021Date of Patent: May 10, 2022Assignee: ROLLS-ROYCE plcInventors: Craig W Bemment, Pascal Dunning
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Publication number: 20220099035Abstract: A gas turbine engine for an aircraft includes an engine core including a first, lower pressure, turbine, a first compressor, and a first core shaft connecting the first turbine to the first compressor; and a second, higher pressure, turbine, a second compressor, and a second core shaft connecting the second turbine to the second compressor, and a fan located upstream of the engine core and including a plurality of fan blades extending from a hub. A turbine to fan tip temperature change ratio of a low pressure turbine temperature change to a fan tip temperature rise is in the range from 1.46 to 2.0.Type: ApplicationFiled: September 3, 2021Publication date: March 31, 2022Applicant: ROLLS-ROYCE PLCInventors: Craig W BEMMENT, Pascal DUNNING
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Publication number: 20210310408Abstract: A highly efficient gas turbine engine includes the fan of the gas turbine engine driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.Type: ApplicationFiled: June 11, 2021Publication date: October 7, 2021Applicant: ROLLS-ROYCE plcInventors: Pascal DUNNING, Michael J. WHITTLE, Roderick M. TOWNES
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Publication number: 20210310407Abstract: A gas turbine engine for an aircraft comprises an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor, wherein a compressor exit temperature is defined as an average temperature of airflow at the exit from the compressor; and a fan located upstream of the engine core, the fan comprising a plurality of fan blades extending from a hub, each fan blade having a leading edge and a trailing edge, wherein a fan rotor entry temperature is defined as an average temperature of airflow across the leading edge of each fan blade at cruise conditions and a fan tip rotor exit temperature is defined as an average temperature of airflow across a radially outer portion of each fan blade at the trailing edge at cruise conditions. A core to fan tip temperature rise ratio is in the range from 2.845 to 3.8.Type: ApplicationFiled: June 11, 2021Publication date: October 7, 2021Applicant: ROLLS-ROYCE PLCInventors: Craig W BEMMENT, Pascal DUNNING
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Patent number: 11136922Abstract: A gas turbine engine for an aircraft includes an engine core including a first, lower pressure, turbine, a first compressor, and a first core shaft connecting the first turbine to the first compressor; and a second, higher pressure, turbine, a second compressor, and a second core shaft connecting the second turbine to the second compressor, and a fan located upstream of the engine core and including a plurality of fan blades extending from a hub. A low pressure turbine temperature change is defined as: the ? ? first ? ? turbine ? ? entrance ? ? temperature the ? ? first ? ? turbine ? ? exit ? ? temperature . A fan tip temperature rise is defined as: the ? ? fan ? ? tip ? ? rotor ? ? exit ? ? temperature the ? ? fan ? ? rotor ? ? entry ? ? temperature .Type: GrantFiled: August 20, 2019Date of Patent: October 5, 2021Assignee: ROLLS-ROYCE plcInventors: Craig W Bemment, Pascal Dunning
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Publication number: 20210222632Abstract: A gas turbine engine comprises a fan, a compressor, a low pressure turbine and a high pressure turbine. The fan diameter is greater than 250 cm and less than 381 cm; and the gas turbine engine has a first thrust at sea level static conditions and a second thrust at end of runway conditions; and a thrust take-off ratio greater than 1.32; wherein the thrust take-off ratio is the ratio of the first thrust to the second thrust.Type: ApplicationFiled: January 7, 2021Publication date: July 22, 2021Applicant: ROLLS-ROYCE PLCInventors: Craig W. BEMMENT, Pascal DUNNING
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Publication number: 20210207528Abstract: A highly efficient gas turbine engine is provided. The fan of the gas turbine engine is driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.Type: ApplicationFiled: March 23, 2021Publication date: July 8, 2021Applicant: ROLLS-ROYCE PLCInventors: Pascal DUNNING, Roderick M. TOWNES, Michael J. WHITTLE
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Patent number: 11053842Abstract: An engine core including turbine, compressor, and core shaft connecting the turbine to the compressor, wherein a compressor exit temperature has an average airflow; and a fan upstream including a plurality of fan blades extending from a hub, each fan blade having a leading and trailing edge, wherein a fan rotor entry temperature has an average airflow across the leading edge of each blade at cruise conditions and fan tip rotor exit temperature has an average temperature of airflow across a radially outer portion of each blade at the trailing edge cruise conditions. A fan tip temperature rise as: the ? ? fan ? ? tip ? ? rotor ? ? exit ? ? temperature the ? ? fan ? ? rotor ? ? entry ? ? temperature .Type: GrantFiled: September 3, 2019Date of Patent: July 6, 2021Assignee: ROLLS-ROYCE plcInventors: Craig W Bemment, Pascal Dunning
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Patent number: 11047301Abstract: A highly efficient gas turbine engine includes the fan of the gas turbine engine driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.Type: GrantFiled: May 14, 2019Date of Patent: June 29, 2021Assignee: ROLLS-ROYCE PLCInventors: Pascal Dunning, Michael J Whittle, Roderick M Townes
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Patent number: 10989112Abstract: A highly efficient gas turbine engine is provided. The fan of the gas turbine engine is driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.Type: GrantFiled: May 14, 2019Date of Patent: April 27, 2021Assignee: ROLLS-ROYCE PLCInventors: Pascal Dunning, Roderick M Townes, Michael J Whittle