公开(公告)号：EP4435248A1

公开(公告)日：2024-09-25

申请号：EP23182738.7

申请日：2023-06-30

申请人： General Electric Company

发明人： MONDAL, Bhaskar Nanda ,  PAYYOOR, Narayanan ,  KAMAT, Pranav

IPC分类号： F02K3/06 ,  F01D5/02

CPC分类号： F02K3/06 ,  F05D2260/9620130101 ,  F05D2240/6020130101 ,  F05D2260/94120130101 ,  F01D5/06

摘要： A turbomachine engine (100, 210, 300, 410, 500) includes an engine core (123, 231, 344, 418) including a high-pressure compressor (112, 224, 318, 428, 518), a high-pressure turbine (116, 230, 432, 534), and a combustion chamber in flow communication with the high-pressure compressor (112, 224, 318, 428, 518) and the high-pressure turbine (116, 230, 432, 534). The engine core (123, 231, 344, 418) has a length (LCORE), and the high-pressure compressor (112, 224, 318, 428, 518) has an exit stage diameter (DCORE). A high-pressure shaft (122, 234, 548, 700) is coupled to the high-pressure compressor (112, 224, 318, 428, 518) and the high-pressure turbine (116, 230, 432, 534). The high-pressure shaft (122, 234, 548, 700) is characterized by a high-speed shaft (348, 436) rating (HSR) from 1.5 to 6.2, and a ratio of LCORE/DCORE is from 2.1 to 4.3.

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

申请人： General Electric Company

发明人： KAMAT, Pranav ,  MONDAL, Bhaskar Nanda ,  CLEMENTS, Jeffrey

IPC分类号： F02C7/36 ,  F02K3/06

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.