System and method for preventing ice crystal accretion in gas turbine engines

Patent metadata

Field	Value
Publication number	US-9683489-B2
Application number	US-201314014560-A
Country	US
Kind code	B2
Filing date	Aug 30, 2013
Priority date	Aug 9, 2013
Publication date	Jun 20, 2017
Grant date	Jun 20, 2017

Abstract

A system and method of operating an engine anti-ice system includes supplying heat from one or more heat sources to one or more components on or within a gas turbine engine, sensing data representative of one or more parameters related to ice crystal accretion, and based on the data, at least selectively inhibiting at least selected ones of the one or more heat sources from supplying heat to at least selected ones of the one or more components on or within the gas turbine engine.

First claim

What is claimed is:

1. An engine anti-ice system, comprising:
one or more heat sources configured to selectively heat one or more components on or within a gas turbine engine;
one or more sensor data sources configured to supply data representative of one or more parameters related to ice crystal accretion; and
a controller coupled to receive the data from the one or more sensors and configured, in response to the data, to (i) determine if one or more criteria are met, and (ii) when the one or more criteria are met, at least inhibit at least selected ones of the one or more heat sources from supplying heat to at least selected ones of the one or more components on or within the gas turbine engine,
wherein the one or more criteria comprise ice crystal presence in the air has been detected.

2. The system of claim 1 , wherein the one or more criteria further comprise:
ambient temperature outside the aircraft is less than or equal to a predetermined temperature; and
aircraft altitude is at or above a predetermined altitude.

3. The system of claim 1 , wherein the one or more criteria further comprise aircraft altitude is at or above a predetermined altitude.

4. The system of claim 1 , wherein the one or more heat sources comprise engine bleed air.

5. The system of claim 1 , wherein the one or more heat sources comprise a lubricant.

6. The system of claim 1 , wherein the one or more heat sources comprise one or more electrical heaters.

7. The system of claim 1 , wherein the one or more heat sources comprise one or more ultrasonic heaters.

8. The system of claim 1 , wherein the one or more components comprise a spinner.

9. The system of claim 1 , wherein the one or more components comprise one or more guide vanes.

10. The system of claim 1 , wherein the one or more sensor data sources comprise:
one or more altitude sensors; and
one or more temperature sensors.

11. The system of claim 1 , wherein the one or more sensor data sources comprise a weather radar system.

12. The system of claim 1 , wherein the one or more sensor data sources comprise a Coherent Rayleigh Lidar System.

13. A method of operating an engine anti-ice system, comprising the steps of:
supplying heat from one or more heat sources to one or more components on or within a gas turbine engine;
sensing data representative of one or more parameters related to ice crystal accretion;
processing the data to determine when there is ice crystal presence in the air; and
when there is ice crystal presence in the air, inhibiting at least selected ones of the one or more heat sources from supplying heat to at least selected ones of the one or more components on or within the gas turbine engine.

Assignees

• Honeywell Int Inc

Inventors

• Dischinger Dave
• Goodwin Ronald
• Kington Harry Lester

Classifications

• F05D2270/311

  Air humidity · CPC title

• F05D2270/313

  Air temperature · CPC title

• F05D2270/312

  Air pressure · CPC title

• F02C7/00 Primary

  Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants (controlling F02C9/00) · CPC title

• F05D2260/231

  Preventing heat transfer · CPC title