Turbine engine having a variable engine intake system

Patent metadata

Field	Value
Publication number	US-12529335-B1
Application number	US-202418910956-A
Country	US
Kind code	B1
Filing date	Oct 9, 2024
Priority date	Oct 9, 2024
Publication date	Jan 20, 2026
Grant date	Jan 20, 2026

Abstract

A turbine engine including a fan having a plurality of fan blades, a nacelle that extends circumferentially about the fan, an engine intake including an engine inlet, and a variable engine intake system. The nacelle includes a fan cowl and an inlet cowl that is movable with respect to the fan cowl. The engine inlet is defined from a leading edge of the inlet cowl to the plurality of fan blades. The engine inlet defines a droop axis at the leading edge of the inlet cowl. The inlet cowl is tilted at a droop angle that is defined as an angle of the droop axis with respect to an axial plane of the turbine engine. The variable engine intake system adjusts the droop angle of the inlet cowl during operation of the turbine engine.

First claim

The invention claimed is:

1 . A turbine engine comprising:
a fan having a plurality of fan blades; a nacelle that extends circumferentially about the fan, the nacelle including a fan cowl and an inlet cowl that is movable with respect to the fan cowl, the inlet cowl including a leading edge, a first droop portion, and a second droop portion, the inlet cowl having an inlet diameter, and being oriented at a droop angle, the droop angle being defined by a droop axis and a radial plane of the turbine engine, the droop axis being defined at the leading edge of the inlet cowl; and a variable engine intake system including an engine inlet defined from the leading edge of the inlet cowl to the plurality of fan blades, the variable engine intake system being configured to axially translate the inlet cowl to adjust the droop angle of the inlet cowl during operation of the turbine engine by translating the first droop portion while the second droop portion remains stationary, the inlet diameter of the inlet cowl remaining constant during the operation of the turbine engine.

2 . The turbine engine of claim 1 , wherein the turbine engine includes a heating system disposed through the inlet cowl that heats the inlet cowl.

3 . The turbine engine of claim 1 , wherein the variable engine intake system includes one or more actuators and a controller that controls the one or more actuators to adjust the droop angle of the inlet cowl.

4 . The turbine engine of claim 1 , wherein the variable engine intake system is configured to adjust the droop angle of the inlet cowl based on wind conditions about the turbine engine, the wind conditions including at least one of crosswind conditions or wind shear conditions.

5 . The turbine engine of claim 1 , wherein the variable engine intake system is configured to adjust the droop angle of the inlet cowl based on an angle of attack of the turbine engine.

6 . The turbine engine of claim 1 , wherein the droop angle is positioned at a nominal angle, and the variable engine intake system is configured to adjust the droop angle to any angle in a range of −8° to 8°, inclusive, from the nominal angle.

7 . The turbine engine of claim 1 , wherein the variable engine intake system adjusts a circumferential orientation of the droop axis to move a circumferential location of the first droop portion and the second droop portion.

8 . The turbine engine of claim 7 , further comprising a motor that is drivingly coupled to the inlet cowl, the motor configured to rotate the inlet cowl to adjust the circumferential orientation of the droop axis.

9 . The turbine engine of claim 7 , wherein the turbine engine defines a radial direction, and the variable engine intake system is configured to adjust the circumferential orientation of the droop axis to any angle in a range of −90° to 90°, inclusive, from the radial direction.

10 . The turbine engine of claim 1 , wherein the variable engine intake system includes a plurality of wind condition sensors for sensing wind conditions about the turbine engine.

11 . A method of operating a turbine engine, the method comprising:
operating the turbine engine, the turbine engine including a fan, a nacelle that extends circumferentially about the fan and having a fan cowl and an inlet cowl, the inlet cowl including a leading edge, a first droop portion, and a second droop portion, the inlet cowl having an inlet diameter, and being oriented at a droop angle, the droop angle being defined by a droop axis and a radial plane of the turbine engine, the droop axis being defined at the leading edge of the inlet cowl; and axially translating the first droop portion while the second droop portion remains stationary to adjust the droop angle of the inlet cowl, the inlet diameter of the inlet cowl remaining constant during operation of the turbine engine.

12 . The method of claim 11 , further comprising heating the inlet cowl with a heating system.

13 . The method of claim 11 , further comprising controlling one or more actuators to adjust the droop angle of the inlet cowl.

14 . The method of claim 11 , further comprising adjusting the droop angle of the inlet cowl based on wind conditions about the turbine engine, the wind conditions including at least one of crosswind conditions or wind shear conditions.

15 . The method of claim 11 , further comprising adjusting the droop angle of the inlet cowl based on an angle of attack of the turbine engine.

16 . The method of claim 11 , wherein the droop angle is positioned at a nominal angle, the method further comprising adjusting the droop angle to any angle in a range of −8° to 8°, inclusive, from the nominal angle.

17 . The method of claim 11 , further comprising adjusting a circumferential orientation of the droop axis to move a circumferential location of the first droop portion and the second droop portion.

18 . The method of claim 17 , further comprising rotating the inlet cowl to adjust the circumferential orientation of the droop axis.

19 . The method of claim 17 , wherein the turbine engine defines a radial direction, the method further comprising adjusting the circumferential orientation of the droop axis to any angle in a range of −90° to 90°, inclusive, from the radial direction.

20 . The method of claim 11 , further comprising receiving one or more first wind condition sensor signals from one or more first wind condition sensors and one or more second wind condition sensor signals from one or more second wind condition sensors, and adjusting the droop angle of the inlet cowl if the one or more first wind condition sensor signals and the one or more second wind condition sensor signals are different.

Assignees

• Gen Electric

Inventors

• Sibbach Arthur W
• Miller Brandon W
• Blodgett Keith E
• Solomon William J
• Schimmels Scott Alan

Classifications

• F02C7/057

  Control or regulation (conjointly with fuel supply control F02C9/50, with nozzle area control F02K1/16) · CPC title

• B64D29/00

  Power-plant nacelles, fairings or cowlings · CPC title

• F02C7/042 Primary

  having variable geometry · CPC title

• F02K3/06

  with front fan · CPC title

• B64D2033/0286

  for turbofan engines · CPC title