-
公开(公告)号：US12110830B2
公开(公告)日：2024-10-08
申请号：US18137123
申请日：2023-04-20
Applicant: ROLLS-ROYCE plc
Inventor： Pascal Dunning , Roderick M. Townes , Michael J. Whittle
CPC classification number: F02C7/36 , F01D5/284 , F01D5/3084 , F02C3/073 , F05D2240/12 , F05D2240/30
Abstract: 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.
-
公开(公告)号：US11560853B2
公开(公告)日：2023-01-24
申请号：US17466086
申请日：2021-09-03
Applicant: ROLLS-ROYCE PLC
Inventor： Craig W Bemment , Pascal Dunning
Abstract: 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.
-
公开(公告)号：US11466617B2
公开(公告)日：2022-10-11
申请号：US17345328
申请日：2021-06-11
Applicant: ROLLS-ROYCE plc
Inventor： Pascal Dunning , Michael J Whittle , Roderick M Townes
Abstract: 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.
-
公开(公告)号：US11053842B2
公开(公告)日：2021-07-06
申请号：US16558417
申请日：2019-09-03
Applicant: ROLLS-ROYCE plc
Inventor： Craig W Bemment , Pascal Dunning
Abstract: 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 . A core temperature rise as: the compressor exit temperature the fan rotor entry temperature , A core to fan tip temperature rise ratio of: the core temperature rise the fan tip temperature rise is in the range from 2.845-3.8.
-
公开(公告)号：US11898489B2
公开(公告)日：2024-02-13
申请号：US18123091
申请日：2023-03-17
Applicant: ROLLS-ROYCE plc
Inventor： Craig W Bemment , Pascal Dunning
CPC classification number: F02C3/04 , F02C7/36 , F02K3/06 , F05D2200/14 , F05D2220/323 , F05D2220/36 , F05D2240/307 , F05D2260/4031
Abstract: 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.
-
Patent Agency Ranking
公开(公告)号：US11136922B2
公开(公告)日：2021-10-05
申请号：US16545003
申请日：2019-08-20
Applicant: ROLLS-ROYCE plc
Inventor： Craig W Bemment , Pascal Dunning
Abstract: 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 . A turbine to fan tip temperature change ratio of: the low pressure turbine temperature change the fan tip temperature rise is in the range from 1.46 to 2.0.
-
公开(公告)号：US10794294B1
公开(公告)日：2020-10-06
申请号：US16695472
申请日：2019-11-26
Applicant: ROLLS-ROYCE plc
Inventor： Pascal Dunning , Craig W Bemment
Abstract: A gas turbine engine includes: an engine core, compressor system, and core shaft. A compressor exit pressure is defined as an average airflow pressure at the exit of the highest pressure compressor at cruise conditions. The core has an annular splitter and bypass flow. Stagnation streamlines around the engine circumference form a streamsurface. A fan is upstream the core with blades having leading and trailing edges, and a radially inner portion within the streamtube. A fan root entry pressure is an average airflow pressure across the radially inner portion leading edge of each fan blade at cruise conditions. An overall pressure ratio, OPR, is defined as the compressor exit pressure divided by the fan root entry pressure. A bypass jet velocity is defined as the jet velocity of air flow exiting the bypass exhaust nozzle at cruise conditions. A jet velocity to OPR ratio is in a range between 4.7 m/s and 7.7 m/s.
-
公开(公告)号：US12146440B2
公开(公告)日：2024-11-19
申请号：US18583395
申请日：2024-02-21
Applicant: ROLLS-ROYCE PLC
Inventor： Roderick M Townes , Michael J Whittle , Pascal Dunning
Abstract: 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.
-
公开(公告)号：US11668246B2
公开(公告)日：2023-06-06
申请号：US17209989
申请日：2021-03-23
Applicant: ROLLS-ROYCE PLC
Inventor： Pascal Dunning , Roderick M Townes , Michael J Whittle
CPC classification number: F02C7/36 , F01D5/284 , F01D5/3084 , F02C3/073 , F05D2240/12 , F05D2240/30
Abstract: 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.
-
公开(公告)号：US11635021B2
公开(公告)日：2023-04-25
申请号：US17697630
申请日：2022-03-17
Applicant: ROLLS-ROYCE PLC
Inventor： Craig W Bemment , Pascal Dunning
Abstract: 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.
-
-
-
-
-
-
-
-
-
Search Results
15
records
(took 0.021 seconds)
