公开(公告)号：US12123310B2

公开(公告)日：2024-10-22

申请号：US18480627

申请日：2023-10-04

Applicant: RTX CORPORATION

Inventor： Stephen G. Pixton ,  Gary Collopy ,  Ozhan Turgut

IPC: F01D15/12 ,  F02C3/00 ,  F02C7/32

CPC classification number: F01D15/12 ,  F02C3/00 ,  F02C7/32 ,  F05D2220/323

Abstract: A gas turbine engine according to an example of the present disclosure may include, among other things, a propulsor section including a propulsor having a plurality of propulsor blades, a geared architecture, a first spool including a first shaft that interconnects a first compressor and a first turbine, the first driving the propulsor through the geared architecture. The gas turbine engine is rated to provide an amount of thrust at ground idle, and the gas turbine engine is rated to provide an amount of thrust at maximum takeoff. A thrust ratio is defined as a ratio of the amount of thrust at ground idle divided by the amount of thrust at maximum takeoff. The thrust ratio can be less than or equal to 0.050.

公开(公告)号：US20240240569A1

公开(公告)日：2024-07-18

申请号：US18480627

申请日：2023-10-04

Applicant: RTX CORPORATION

Inventor： Stephen G. Pixton ,  Gary Collopy ,  Ozhan Turgut

IPC: F01D15/12 ,  F02C3/00 ,  F02C7/32

CPC classification number: F01D15/12 ,  F02C3/00 ,  F02C7/32 ,  F05D2220/323

Abstract: A gas turbine engine according to an example of the present disclosure may include, among other things, a propulsor section including a propulsor having a plurality of propulsor blades, a geared architecture, a first spool including a first shaft that interconnects a first compressor and a first turbine, the first driving the propulsor through the geared architecture. The gas turbine engine is rated to provide an amount of thrust at ground idle, and the gas turbine engine is rated to provide an amount of thrust at maximum takeoff. A thrust ratio is defined as a ratio of the amount of thrust at ground idle divided by the amount of thrust at maximum takeoff. The thrust ratio can be less than or equal to 0.050.