Passive internal ice protection systems for engine inlets

Patent metadata

Field	Value
Publication number	US-10036320-B2
Application number	US-201514947325-A
Country	US
Kind code	B2
Filing date	Nov 20, 2015
Priority date	Nov 20, 2015
Publication date	Jul 31, 2018
Grant date	Jul 31, 2018

Abstract

A system includes an engine cover covering a side-facing rotorcraft engine and having an opening and an ice protection member mounted on the engine cover between the opening and the engine, an area of the ice protection member smaller than an area of the opening. The ice protection member is configured to partially cover the opening to prevent ice having a particular size from entering into the engine and to allow air flow downstream into the engine.

First claim

The invention claimed is:

1. A system comprising:
an engine cover configured to cover a flush type engine inlet of a side-facing helicopter gas turbine engine, the engine cover having an opening and inside edges defining a front end and a back end of the opening;
an ice protection member comprising a first part and a second part, the second part extending downwards from the opening and having an upper end mounted on the inside edge of the engine cover defining the back end of the opening and a lower end disposed below the opening, the first part comprising a frame surrounding a mesh screen extending from the lower end of the second part in a first direction from the back end towards the front end such a portion of the opening remains open at all times;
wherein the ice protection member is configured to partially cover the opening to prevent ice having a particular size from entering into the engine and to allow air flow downstream into the engine; and
a filter positioned below the opening of the engine cover and between the ice protection member and the engine.

2. The system of claim 1 , wherein the second part further comprises one or more framed mesh screens.

3. The system of claim 2 , wherein the mesh screen of the second part and the one or more framed mesh screens of the first part are configured to catch and hold the ice with suction generated by an air flow into the engine, the particular size of the ice larger than a size certified for the engine.

4. The system of claim 3 , wherein the ice protection member is configured to catch the ice with the particular size of about slightly wider than a half of the opening.

5. The system of claim 2 , wherein the mesh screen comprises a plurality of pores each having a pore size of about 0.25 inch up to 0.50 inch.

6. The system of claim 2 , wherein the mesh screen comprises stainless steel.

7. The system of claim 2 , wherein the frame comprises fiberglass.

8. The system of claim 7 , wherein the ice protection member is mounted on the engine cover by fastening the upper end of the second part onto the engine cover.

9. The system of claim 1 , wherein the engine cover is configured to be mounted on a side surface of a rotorcraft that comprises a front end and a back end, and
wherein the ice protection member is mounted on the engine cover close to the back end such that a particular portion of the opening close to the front end remains open.

10. The system of claim 9 , wherein an area of the particular portion of the opening together with an area of porosity of the ice protection member is about 85% of the area of the opening.

11. The system of claim 9 , wherein the first part and the second part are positioned with a folding angle.

12. The system of claim 11 , wherein the folding angle is about 90 degree, and the second part extends upwards to the opening in a second direction perpendicular to the first direction.

13. The system of claim 11 , wherein the first part comprises one or more folding lines parallel to the first direction to accommodate a shape of the engine cover.

14. The system of claim 13 , further comprising one or more brackets configured to hold the first part under the one or more folding lines and be fastened to the second part and further to the engine cover.

15. A method comprising:
framing a mesh screen to form an ice protection member comprising a first part and a second part;
mounting the ice protection member on an engine cover configured to cover a flush type engine inlet of a side-facing helicopter gas turbine engine, the engine cover having an opening and inside edges defining a front end and a back end of the opening, the second part of the ice protection member extending downwards from the opening and having an upper end mounted on the inside edge of the engine cover defining the back end of the opening and a lower end disposed below the opening, the first part of the ice protection member comprising a frame surrounding a mesh screen extending from the lower end of the second part in a first direction from the back end towards the front end such a portion of the opening remains open at all times;
mounting the engine cover to cover a side-facing rotorcraft engine, such that the ice protection member is positioned between the opening of the engine cover and the engine;
positioning a filter below the opening of the engine cover and between the ice protection member and the engine; and
wherein, during operation, air flows downstream into the engine through the opening and the ice protection member prevents ice with a particular size entering into the engine.

16. The method of claim 15 , wherein mounting the engine cover comprises mounting the engine cover on a side surface of a rotorcraft that comprises a front end and a back end, and
wherein the ice protection member is mounted on the engine cover close to the back end such that a particular portion of the opening close to the front end remains open.

17. The method of claim 16 , wherein an area of the particular portion of the opening together with an area of porosity of the ice protection member is about 85% of the area of the opening, and the ice protection member is configured to hold the ice with the particular size larger than a size certified for the engine.

18. The method of claim 16 , wherein the first part and the second part are positioned with a folding angle, and
wherein mounting the ice protection member comprises: holding the first part with one or more brackets along one or more respective folding lines of the first part and fastening the one or more brackets to the second part and further to the engine cover.

Assignees

• Bell Helicopter Textron Inc

Inventors

• Aubert Roger J

Classifications

• B64C27/06

  with single rotor · CPC title

• B64D33/02

  of combustion air intakes · CPC title

• F02C7/047

  Heating to prevent icing · CPC title

• F05D2230/60

  Assembly methods · CPC title

• F05D2220/329

  in helicopters · CPC title