Systems and methods for preventing ice accumulation

Patent metadata

Field	Value
Publication number	US-2016376010-A1
Application number	US-201615165264-A
Country	US
Kind code	A1
Filing date	May 26, 2016
Priority date	Jun 26, 2015
Publication date	Dec 29, 2016
Grant date	—

Abstract

A device configured to prevent ice accumulation includes at least one wall defining a leading edge and a pneumatic passage configured to receive pressurized fluid. The device also includes at least one ejection port formed in at least one of the leading edge and the at least one wall, the at least one ejection portion fluidly coupled to the pneumatic passage to receive the pressurized fluid therefrom, the at least one ejection port configured to form fluid jets to divert liquid water droplets away from the leading edge of the device.

First claim

1 . A device configured to prevent ice accumulation, the device comprising:
at least one wall defining a leading edge; a pneumatic passage configured to receive pressurized fluid; and at least one ejection port formed in at least one of the leading edge and the at least one wall, the at least one ejection portion fluidly coupled to the pneumatic passage to receive the pressurized fluid therefrom, the at least one ejection port configured to form fluid jets to divert liquid water droplets away from the leading edge of the device.

2 . The device of claim 1 , wherein the at least one wall includes converging first and second walls

3 . The device of claim 1 , wherein the device is wedge-shaped or the device is airfoil-shaped.

4 . The device of claim 1 , wherein the at least one ejection port is an elongated slot.

5 . The device of claim 1 , wherein the at least one ejection port is formed in the leading edge.

6 . The device of claim 1 , wherein the at least one ejection port is formed in the at least one wall at a location that is not at the leading edge.

7 . The device of claim 1 , wherein the pneumatic passage is configured to receive heated, pressurized air, and the at least one ejection port is configured to form heated air jets.

8 . A probe assembly comprising:
a base platform; a probe coupled to the base platform; a device coupled to at least one of the base platform and the probe, the device configured to be positioned in an airflow upstream of the probe and to prevent ice accumulation thereon, the device comprising:
at least one wall defining a leading edge;
a pneumatic passage configured to receive pressurized fluid; and
at least one ejection port formed in at least one of the leading edge and the at least one wall, the at least one ejection portion fluidly coupled to the pneumatic passage to receive the pressurized fluid therefrom, the at least one ejection port configured to form heated fluid jets to divert liquid water droplets away from the leading edge of the device.

9 . The assembly of claim 8 , wherein the device is wedge-shaped.

10 . The assembly of claim 8 , wherein the device is airfoil-shaped.

11 . The assembly of claim 8 , wherein the at least one ejection port is an elongated slot.

12 . The assembly of claim 8 , wherein the at least one ejection port is formed in the leading edge.

13 . The assembly of claim 8 , wherein the at least one ejection port is formed in the at least one wall at a location that is not at the leading edge.

14 . The assembly of claim 8 , further comprising a pneumatic connector coupled to the base platform, the pneumatic connector fluidly coupled to the pneumatic passage.

15 . An aircraft engine comprising:
a housing; a fan; a compressor; and a probe assembly disposed upstream of the compressor, the probe assembly comprising:
a base platform;
a probe coupled to the base platform;
a device coupled to at least one of the base platform and the probe, the device configured to be positioned in an airflow upstream of the probe and to prevent ice accumulation thereon, the device comprising:
at least one wall defining a leading edge;
a pneumatic passage configured to receive pressurized fluid; and
at least one ejection port formed in at least one of the leading edge and the at least one wall, the at least one ejection portion fluidly coupled to the pneumatic passage to receive the pressurized fluid therefrom, the at least one ejection port configured to form heated fluid jets to divert liquid water droplets away from the leading edge of the device.

16 . The aircraft engine of claim 15 , wherein the at least one ejection port is formed in the leading edge.

17 . The aircraft engine of claim 15 , wherein the at least one ejection port is formed in the at least one wall at a location that is not at the leading edge.

18 . The aircraft engine of claim 15 , further comprising a pneumatic connector coupled to the base platform, the pneumatic connector fluidly coupled to the pneumatic passage.

19 . The aircraft engine of claim 15 , wherein the pneumatic passage is fluidly coupled to the compressor, wherein the pressurized air is heated and supplied by the compressor.

Assignees

• Rosemount Aerospace Inc

Inventors

• Gmach Matthew James-Thomas
• Sable Robert Edward
• Wigen Scott
• Kunkel Matthew John

Classifications

• B64D15/04 Primary

  Hot gas application · CPC title

• B64D15/20

  Means for detecting icing or initiating de-icing · CPC title

• G01K13/028 Primary

  for use in total air temperature [TAT] probes · CPC title