-
公开(公告)号：EP4417800A1
公开(公告)日：2024-08-21
申请号：EP23196758.9
申请日：2023-09-12
CPC分类号： F02C7/36 , F02K3/06 , F05D2260/4031120130101
摘要： A turbomachinery engine includes a fan assembly, a low-pressure turbine, and a gearbox. The fan assembly includes a plurality of fan blades. The low-pressure turbine includes 3-5 rotating stages. The low-pressure turbine includes an area ratio equal to the annular exit area of an aft-most rotating stage of the low-pressure turbine divided by the annular exit area of a forward-most rotating stage of the low-pressure turbine. In some instances, the area ratio is within a range of 2.0-6.5. Additionally (or alternatively) the low-pressure turbine includes an area-EGT ratio within a range of 1.3-1.6.
-
公开(公告)号：EP4043710A1
公开(公告)日：2022-08-17
申请号：EP22154537.9
申请日：2022-02-01
摘要： A turbomachinery engine includes an unducted rotor assembly, a low-pressure turbine, a low-pressure shaft, a gearbox, and an engine correlation parameter. The unducted rotor assembly includes a plurality of rotor blades arranged in a single row and defining a blade diameter. The gearbox includes an input, an output, and a gear ratio. The input of the gearbox is coupled to the low-pressure shaft (which is coupled to the LPT), and the output of the gearbox is coupled to the unducted rotor assembly. The engine correlation parameter is greater than 0.17 and less than 0.83. The engine correlation parameter equals D/N/GR, where D is the blade tip diameter measured in feet, N is the stage count of the low-pressure turbine, and GR is the gear ratio of the gearbox. The unducted propulsor assembly optionally includes a disk loading within a range of 60-180 HP/ft 2 at a takeoff flight condition.
-
公开(公告)号：EP4321743A3
公开(公告)日：2024-03-06
申请号：EP23189337.1
申请日：2023-08-02
发明人： CLEMENTS, Jeffrey
摘要： A turbomachinery engine comprises a ducted fan, a high-pressure compressor, a low-pressure turbine, a gearbox, and a ducted engine correlation parameter (DECP). The DECP is within a range of 0.10-0.25 and is defined as 10 ∗ D/GR/N LPT 2 /N HPC , where D is a fan blade tip diameter at a leading edge of the ducted fan measured in feet, GR is a gear ratio of the gearbox, N LPT is a stage count of the low-pressure turbine, and N HPC is a stage count of the high-pressure compressor.
-
公开(公告)号：EP4321743A2
公开(公告)日：2024-02-14
申请号：EP23189337.1
申请日：2023-08-02
发明人： CLEMENTS, Jeffrey
摘要： A turbomachinery engine comprises a ducted fan, a high-pressure compressor, a low-pressure turbine, a gearbox, and a ducted engine correlation parameter (DECP). The DECP is within a range of 0.10-0.25 and is defined as 10 ∗ D/GR/N LPT 2 /N HPC , where D is a fan blade tip diameter at a leading edge of the ducted fan measured in feet, GR is a gear ratio of the gearbox, N LPT is a stage count of the low-pressure turbine, and N HPC is a stage count of the high-pressure compressor.
-
公开(公告)号：EP4219919A1
公开(公告)日：2023-08-02
申请号：EP22213270.6
申请日：2022-12-13
发明人： PIAZZA, Andrea , CLEMENTS, Jeffrey
摘要： A turbomachine engine can include a fan assembly, a vane assembly, a core engine, a gearbox, and an overall engine efficiency rating. The fan assembly can include a plurality of fan blades. The vane assembly can include a plurality of vanes, and the vanes can, in some instances, be disposed aft of the fan blades. The core engine can include a low-pressure turbine. The gearbox includes an input and an output. The input of the gearbox is coupled to the low-pressure turbine of the core engine and comprises a first rotational speed, the output of the gearbox is coupled to the fan assembly and has a second rotational speed, and a gear ratio of the first rotational speed to the second rotational speed is within a range of 3.2-4.0. The overall engine efficiency rating is within a range of 0.57-8.0.
-
-
-
-
搜索结果
5 条记录 (耗时 0.019 秒)
