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公开(公告)号：EP4123142A1
公开(公告)日：2023-01-25
申请号：EP22185719.6
申请日：2022-07-19
发明人： PIXTON, Stephen G. , HASEL, Karl L.
摘要： A gas turbine engine (20) includes a fan drive turbine driving a low pressure compressor (44), and driving a gear reduction to in turn drive a fan rotor (42) at a speed slower than the fan drive turbine. The turbine section (28) further includes a high pressure turbine (54) driving the high pressure compressor (52). The fan drive turbine and low pressure compressor (44) are connected by a shaft (40) and the fan drive turbine, the shaft (40) and the low pressure compressor (44) define a low pressure spool. The gas turbine engine (20) is rated to provide an amount of thrust at maximum takeoff, and a low spool thrust ratio defined as a ratio of a torque on the low pressure spool at maximum takeoff in ft-lbs and the maximum takeoff thrust being defined in lbf, with the low spool torque ratio being greater than or equal to 0.70 ft-lb/lbf (0.21 Nm/N), and less than or equal to 1.2 ft-lb/lbf (0.37 Nm/N).
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公开(公告)号：EP4123141A1
公开(公告)日：2023-01-25
申请号：EP22185711.3
申请日：2022-07-19
发明人： PIXTON, Stephen G. , HASEL, Karl L.
摘要： A gear reduction (48) drives a fan rotor (42) at a speed slower than a fan drive turbine. The turbine section further includes a high pressure turbine (54) driving a high pressure compressor (52). The fan drive turbine and low pressure compressor (44) are connected by a shaft (40). The low pressure turbine, the shaft (40) and the low pressure compressor (44) define a low pressure spool (30). The low pressure spool (30) has a torque at maximum takeoff defined in ft-lbs and also has a low pressure spool power defined in horsepower and at maximum takeoff. A ratio of the low pressure spool torque to the low pressure spool power is defined, and the ratio of the low pressure spool torque to the low pressure spool power is greater than or equal to 0.6 ft-lb/hp (0.0011 Nm/Nm.s -1 ) and less than or equal to 1.2 ft-lb/hp (0.022 Nm/Nm.s -1 ).
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公开(公告)号：EP3770415A1
公开(公告)日：2021-01-27
申请号：EP20192702.7
申请日：2013-03-12
摘要： A gas turbine engine includes a fan with a plurality of fan blades rotatable about an axis, and a compressor section (24) that includes at least first and second compressor sections (44, 52). An average exit temperature of the compressor section is between about 1000 °F and about 1500 °F. The engine also includes a combustor that is in fluid communication with the compressor section, (24) and a turbine section that is in fluid communication with the combustor. A geared architecture (48) is driven by the turbine section for rotating the fan about the axis.
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公开(公告)号：EP3933181A1
公开(公告)日：2022-01-05
申请号：EP21192905.4
申请日：2014-07-16
摘要： A ratio of an outer diameter (d 1 ) of a fan hub (209) at a leading edge (210) of the blades (42) to an outer tip diameter (d 2 ) of the blades (42) at the leading edge (210) is greater than or equal to about 0.24 and less than or equal to about 0.38. The fan tip diameter (d 2 ) is greater than or equal to about 84 inches (213.36 centimeters) and a fan tip speed is less than or equal to about 1050 ft / second (320.04 meters / second). A bypass ratio, a gear ratio and an AN 2 value are also claimed. The fan drive turbine (46; 106) has between three and six stages.
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公开(公告)号：EP2904254B8
公开(公告)日：2020-11-04
申请号：EP13843958.3
申请日：2013-03-12
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