公开(公告)号：US12098681B2

公开(公告)日：2024-09-24

申请号：US18202550

申请日：2023-05-26

Applicant: RTX Corporation

Inventor： Stephen G. Pixton ,  Matthew R. Feulner ,  Marc J. Muldoon ,  Xinwen Xiao

IPC: F02C7/36

CPC classification number: F02C7/36 ,  F05D2220/36 ,  F05D2260/40311

Abstract: A fan section includes a fan with fan blades. The fan section drives air along a bypass flow path in a bypass duct. A gear reduction is in driving engagement with the fan and has a gear reduction ratio of greater than 3.0 and less than 4.0. A low spool includes a low pressure turbine that drives a low pressure compressor and drives the gear reduction to drive the fan at a speed slower than the low pressure turbine. The low pressure compressor is a four-stage low pressure compressor. The low pressure turbine is a three-stage low pressure turbine. A high spool including a high pressure turbine that drives a high pressure compressor. The high pressure compressor is a nine-stage high pressure compressor. The high pressure turbine is a two-stage high pressure turbine. An exhaust gas exit temperature of greater than 900 degrees Fahrenheit and less than 1000 degrees Fahrenheit at maximum take-off.

公开(公告)号：US12203385B1

公开(公告)日：2025-01-21

申请号：US18431050

申请日：2024-02-02

Applicant: RTX Corporation

Inventor： Jeffrey T. Morton ,  Stephen G. Pixton

IPC: F01D5/14

Abstract: An assembly for an aircraft propulsion system includes a propulsor rotor and a guide vane structure. The propulsor rotor is configured to rotate about an axis. The guide vane structure includes a plurality of guide vanes arranged circumferentially about the axis. The guide vane structure is axially next to and downstream of the propulsor rotor. The guide vanes include a first guide vane. The first guide vane includes a camber line, a leading edge, a trailing edge, a leading edge section and a trailing edge section. The first guide vane extends longitudinally along the camber line from the leading edge to the trailing edge. The leading edge section forms the leading edge. The trailing edge section forms the trailing edge. The leading edge section is configured to move longitudinally along the camber line relative to the trailing edge section to change a camber of the first guide vane.

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.