Translating inlet for adjusting airflow distortion in gas turbine engine

Patent metadata

Field	Value
Publication number	US-2017284297-A1
Application number	US-201615085047-A
Country	US
Kind code	A1
Filing date	Mar 30, 2016
Priority date	Mar 30, 2016
Publication date	Oct 5, 2017
Grant date	—

Abstract

Systems and methods for adjusting airflow distortion in a gas turbine engine using a translating inlet assembly are provided. In one embodiment, a core engine of a gas turbine engine can include a compressor section, a combustion section, and a turbine section in series flow and defining at least in part an engine airflow path. The compressor section can include an inner flowpath surface. A core casing can enclose the core engine. A forward end of the core casing can include a translating inlet assembly moveable between a first position and a second position. The translating inlet assembly and the inner flowpath surface can together define an inlet to an engine airflow path. A translating inlet assembly can define a first inlet area in the first position and a second inlet area in the second position, the first inlet area being greater than the second inlet area.

First claim

What is claimed is:

1 . A core engine for a gas turbine engine, comprising:
a compressor section, a combustion section, and a turbine section defining at least in part an engine airflow path for the core engine; an inner flowpath surface positioned at least partially within the compressor section and defining at least in part the engine airflow path; a core casing at least partially enclosing the compressor section and defining a forward end, the core casing comprising a translating inlet assembly at the forward end, the translating inlet assembly and inner flowpath surface together defining an inlet to the compressor section, the translating inlet assembly moveable between a first position defining a first inlet area at the inlet and a second position defining a second inlet area at the inlet, the first inlet area being greater than the second inlet area.

2 . The core engine of claim 1 , wherein the translating inlet assembly allows a first engine airflow at a first airflow speed into the engine airflow path in the first position, wherein the translating inlet assembly allows a second engine airflow at a second airflow speed into the engine airflow path in the second position, wherein at least one of the first engine airflow is greater than the second engine airflow or the first engine airflow speed is less than the second engine airflow speed.

3 . The core engine of claim 1 , wherein the translating inlet assembly is configured to be controlled based on an airflow distortion in the engine airflow path, and wherein the airflow distortion is an inlet airflow distortion.

4 . The core engine of claim 1 , wherein the compressor section includes a first compressor and a second compressor, wherein the translating inlet assembly is configured to be controlled based on an airflow distortion in the engine airflow path, and wherein the airflow distortion is an airflow mismatch between the first and second compressors.

5 . The core engine of claim 1 , wherein the translating inlet assembly is configured to be controlled based on an airflow distortion in the engine airflow path, the core engine further comprising:
one or more pressure sensor devices located at least partially in the engine airflow path for obtaining one or more measurements associated with airflow distortion; wherein the translating inlet assembly is configured to be controlled based at least in part on signals from the one or more pressure sensor devices.

6 . The core engine of claim 1 , wherein the core engine defines a circumferential direction, wherein the translating inlet assembly is movable between the first position and the second position in a substantially uniform manner about the circumferential direction of the core engine.

7 . The core engine of claim 1 , wherein the translating inlet assembly is additionally movable to an intermediate position, wherein the intermediate position defines an intermediate inlet area, wherein the intermediate inlet area is less than the first inlet area and greater than the second inlet area.

8 . The core engine of claim 7 , wherein the translating inlet assembly is movable between the first, second, and intermediate positions based on signals from a controller to adjust an airflow distortion in the engine airflow path.

9 . The core engine of claim 1 , wherein the translating inlet assembly defines a front edge, wherein the core engine defines an axial direction, wherein the front edge of the translating inlet assembly moves between the first position and the second position at least partially along the axial direction.

10 . The core engine of claim 1 , wherein the translating inlet assembly defines a front edge, wherein the core engine defines a circumferential direction, wherein the front edge defines a first circumference in the first position, wherein the front edge defines a second circumference in the second position, wherein the second circumference is less than the first circumference.

11 . A method for adjusting airflow distortion in a gas turbine engine on an aircraft, the gas turbine engine comprising a compressor section, a combustion section, and a turbine section in series flow, the compressor section, combustion section, and turbine section defining at least in part an engine airflow path, the gas turbine engine further comprising an inner flow path surface positioned at least partially within the compressor section and defining at least in part the engine airflow path, the gas turbine engine further comprising a core casing at least partially enclosing the compressor section and defining a forward end, the method comprising:
determining, by one or more control devices, an airflow distortion condition associated with the engine airflow path; and controlling, by the one or more control devices, a translating inlet assembly to adjust the airflow distortion condition of the gas turbine engine, wherein the core casing comprises the translating inlet assembly at the forward end, the translating inlet assembly and inner flow path surface together defining an inlet to the compressor section, the translating inlet assembly moveable between a first position defining a first inlet area and a second position defining a second inlet area, the first inlet area being greater than the second inlet area.

12 . The method of claim 11 , wherein the translating inlet assembly is additionally movable to an intermediate position, wherein the intermediate position defines an intermediate inlet area, wherein the intermediate inlet area is less than the first inlet area and greater than the second inlet area.

13 . The method of claim 12 , wherein the translating inlet assembly allows a first engine airflow into the engine airflow path in the first position, wherein the translating inlet assembly allows a second engine airflow into the engine airflow path in the second position, wherein the translating inlet assembly allows an intermediate engine airflow into the engine airflow path in the intermediate position, wherein the intermediate engine airflow is less than the first engine airflow and greater than the second engine airflow.

14 . The method of claim 12 , wherein controlling the translating inlet assembly comprises moving the translating inlet assembly between the first, second, and intermediate positions.

15 . The method of claim 11 , wherein controlling the translating inlet assembly to adjust the airflow distortion condition comprises controlling the translating inlet assembly to reduce the airflow distortion condition.

16 . The method of claim 11 , wherein determining the airflow distortion condition associated with the engine airflow path comprises obtaining one or more measurements using one or more pressure sensor devices, wherein controlling the translating inlet assembly to adjust the airflow distortion comprises controlling the translating inlet assembly based at least in part on the one or more measurements obtained using the one or more pressure sensor devices.

17 . The method of claim 11 , wherein the translating inlet assembly defines a front edge, wherein the core engine defines an axial direction, wherein the front edge of the translating inlet assembly moves between the first position and the second position along the axial direction.

18 . The method of claim 11 , wherein the translating inlet assembly defines a front edge, wherein the core engine defines a circumferential direction, wherein the front edge defines a first circumference in the first position, wherein the front edge defines a second circumference in the secon

Assignees

• Gen Electric

Inventors

• Nestico Brian Francis
• Kestner Brian K
• Miller Brandon Wayne

Classifications

• F02C9/20 Primary

  by throttling; by adjusting vanes · CPC title

• F02C3/04

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title

• F02C7/057 Primary

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

• F04D27/0253

  by throttling (F04D27/0246 takes precedence) · CPC title

• F05D2270/101

  Compressor surge or stall · CPC title