Internally Heated Engine Inlet Screen for Aircraft Engines

Patent metadata

Field	Value
Publication number	US-2017268424-A1
Application number	US-201615072662-A
Country	US
Kind code	A1
Filing date	Mar 17, 2016
Priority date	Mar 17, 2016
Publication date	Sep 21, 2017
Grant date	—

Abstract

An apparatus for providing foreign object debris protection and anti-icing capabilities to an air intake of an aircraft engine. The apparatus includes a frame having at least a portion configured to conduct fluids. A tube is positioned such that different portions of the frame are fluidly connected. There is a discharge outlet defined within the frame that is configured to discharge fluids from the frame into the air intake. An inlet is defined within the frame and is fluidly connected to a compressor section of the aircraft engine. In this manner, air from the compressor section of the aircraft engine can flow through the inlet, through the tube, and through the discharge outlet, to return to the compressor section of the aircraft engine.

First claim

What is claimed is:

1 . An apparatus for providing foreign object debris protection and anti-icing capabilities to an air intake of an aircraft engine, the apparatus comprising;
a frame having at least a portion configured to conduct fluids; a tube through which different portions of the frame are fluidly connected; a discharge outlet defined within the frame that is configured to discharge fluid into the air intake; an inlet defined within the frame; and and wherein the inlet is fluidly connected to a compressor section of the aircraft engine such that air from the compressor section of the aircraft engine can flow through the inlet, through the tube, and through the discharge outlet, to return to the compressor section of the aircraft engine.

2 . The apparatus according to claim 1 , further comprising a plurality of tubes positioned within the frame.

3 . The apparatus according to claim 2 , wherein the frame is configured to support a mesh assembly formed of the tubes.

4 . The apparatus according to claim 3 , wherein the frame is also configured to support a mesh that is not configured to be heated.

5 . The apparatus according to claim 4 , wherein the frame is configured to be heated by hot air from the compressor section around its perimeter.

6 . The apparatus according to claim 5 , wherein the tubes are arranged in a tier and are positioned generally parallel to each other.

7 . The apparatus according to claim 6 , wherein the tubes are arranged in two tiers such that the tubes in each tier are parallel to tubes also in that tier and the tubes in each tier cross tubes of the other tier to form a mesh.

8 . The apparatus according to claim 7 , wherein the mesh is configured to prevent foreign object debris from entering the air intake of the engine.

9 . The apparatus according to claim 6 , wherein the tubes are in a first-tier and solid wire links are positioned in a second-tier such that the first year and the second tier together define a mesh.

10 . A method for providing anti-icing capabilities to the air intake of an aircraft engine wherein the aircraft intake is covered by mesh having at least a portion thereof configured to conduct fluids, the method comprising the steps of:
conducting heated air from a compressor section of the aircraft engine; conducting the heated air through the portion of mesh configured to conduct fluids; conducting heat through the mesh; elevating the temperature of the mesh; and returning the air to the compressor section of the aircraft engine.

11 . The method according to claim 10 , wherein the mesh includes a plurality of tubes positioned within a frame.

12 . The apparatus according to claim 11 , wherein the frame is configured to support a mesh assembly formed of the tubes.

13 . The apparatus according to claim 12 , wherein the frame is configured to be heated by hot air from the compressor section around its perimeter.

14 . The apparatus according to claim 13 , wherein the tubes are arranged in two tiers such that the tubes in each tier are parallel to tubes also in that tier and the tubes in each tier cross tubes of the other tier to form a mesh.

15 . The apparatus according to claim 14 , wherein the mesh is configured to prevent foreign object debris from entering the air intake of the engine.

16 . The apparatus according to claim 15 , wherein the tubes are in a first-tier and solid wire links are positioned in a second-tier such that the first tier and the second tier together define a mesh.

17 . An engine comprising:
a plurality of mesh screens formed of tubes that form at least a portion of the fluidly conductive circuit that includes the compressor section of the engine, the mesh screens, and an air intake portion of the engine.

18 . The engine according to claim 17 wherein the plurality of mesh screens are arranged in an array such that each screen is positioned over an associated air intake.

19 . The engine according to claim 18 wherein each of the mesh screens are fluidly connected with the compressor section of the engine via a bleed line.

20 . The engine according to claim 19 , wherein each of them mesh screens are fluidly connected to a manifold which is fluidly connected via a single bleed line to the compressor section of the engine.

Assignees

• Gen Electric

Inventors

• Grissino Alan Scott
• Manteiga John Alan
• Kerner Jonathan Harry

Classifications

• B64D2033/0293

  for turboprop engines · CPC title

• F02C7/047 Primary

  Heating to prevent icing · CPC title

• B64D33/02

  of combustion air intakes · CPC title

• F05D2220/32

  in gas turbines · CPC title

• B64D2033/022

  comprising bird or foreign object protections · CPC title