公开(公告)号：US20210355952A1

公开(公告)日：2021-11-18

申请号：US17385150

申请日：2021-07-26

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Edward J. Gallagher ,  Byron R. Monzon ,  Shari L. Bugaj

IPC: F04D29/02 ,  F02K3/06 ,  F01D5/28 ,  F01D5/14 ,  F02K1/06 ,  F01D15/12 ,  F02C7/36 ,  F04D29/053 ,  F04D29/32 ,  F04D29/38 ,  F04D29/52 ,  F04D29/56 ,  F02C3/06

Abstract: A gas turbine engine includes a gear assembly, a bypass flow passage, a fan located upstream of the bypass flow passage, a first shaft and a second shaft, a first turbine coupled through the gear assembly to the fan, a first compressor coupled with the first shaft, and a second turbine coupled with the second shaft. The fan has a bypass ratio of greater than 8.5. The fan includes a hub and a row of fan blades that extend from the hub. The row includes a number (N) of the fan blades that is from 16 to 20, a solidity value (R) at tips of the fan blades, and a ratio of N/R that is from 12.3 to 20.

公开(公告)号：US11073157B2

公开(公告)日：2021-07-27

申请号：US16515506

申请日：2019-07-18

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Edward J. Gallagher ,  Byron R. Monzon ,  Shari L. Bugaj

IPC: F02C7/36 ,  F04D29/02 ,  F02K3/06 ,  F01D5/28 ,  F01D5/14 ,  F02K1/06 ,  F01D15/12 ,  F04D29/053 ,  F04D29/32 ,  F04D29/38 ,  F04D29/52 ,  F04D29/56 ,  F02C3/06

Abstract: A gas turbine engine includes a gear assembly, a bypass flow passage, a fan located upstream of the bypass flow passage, a first shaft and a second shaft, a first turbine coupled through the gear assembly to the fan, a first compressor coupled with the first shaft, and a second turbine coupled with the second shaft. The fan includes a hub and a row of fan blades that extend from the hub. The row includes a number (N) of the fan blades that is from 16 to 20, a solidity value (R) at tips of the fan blades, and a ratio of N/R that is from 12.3 to 20.