公开(公告)号：US20190257318A1

公开(公告)日：2019-08-22

申请号：US15900891

申请日：2018-02-21

Applicant: General Electric Company

Inventor： Veeraraju Vanapalli ,  Bhaskar Nanda Mondal ,  Jagata Laxmi Narasimharao ,  Tsuguji Nakano ,  Subramanian Narayanan

IPC: F04D29/32 ,  F01D5/06 ,  F01D25/24

Abstract: The present disclosure is directed to a gas turbine engine including a compressor rotor. The compressor rotor includes a first stage compressor airfoil defined at an upstream-most stage of the compressor rotor. The first stage compressor airfoil defines a first stage pressure ratio of at least approximately 1.7 during operation of the gas turbine engine at a tip speed of at least approximately 472 meters per second.

公开(公告)号：US11231043B2

公开(公告)日：2022-01-25

申请号：US15900891

申请日：2018-02-21

Applicant: General Electric Company

Inventor： Veeraraju Vanapalli ,  Bhaskar Nanda Mondal ,  Jagata Laxmi Narasimharao ,  Tsuguji Nakano ,  Subramanian Narayanan

IPC: F04D29/32 ,  F01D5/06 ,  F01D25/24 ,  F04D19/02 ,  F01D5/14 ,  F02C3/04

Abstract: The present disclosure is directed to a gas turbine engine including a compressor rotor. The compressor rotor includes a first stage compressor airfoil defined at an upstream-most stage of the compressor rotor. The first stage compressor airfoil defines a first stage pressure ratio of at least approximately 1.7 during operation of the gas turbine engine at a tip speed of at least approximately 472 meters per second.