Dual valve apparatus for aircraft engine ice protection and related methods

• US 7,959,109 B2
• Filed: 07/02/2008
• Issued: 06/14/2011
• Est. Priority Date: 07/02/2008
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: DiRusso, Joseph M., Langhofer, Erik Marc, El-Gabalawy, Hosam El Din, Dasilva, Olubusola Anthony, Conn, Heath Alan
• Primary Examiner(s): SWIATEK, ROBERT P
• Application Number:
  US12/167,164
• Publication Number:
  US 20100001138A1
• Time in Patent Office: 1,077 Days
• Field of Search: 244/53.B, 244/134.R, 244/134.B, 60/390.93
• US Class Current: 244/134.00R
• CPC Class Codes: B64D 15/04 Hot gas application
• CPC Class Codes: B64D 2033/0233 comprising de-icing means
• CPC Class Codes: F02C 7/047 Heating to prevent icing
• CPC Class Codes: F05D 2270/3032 excessive temperatures, e.g. caused by overheating
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A thermal anti-ice system in an aircraft. A controlled valve receives air from a compressor bleed port of an engine of the aircraft. A self-regulating valve is fluidly connected between the controlled valve and an inlet of the engine. A first pressure sensor senses pressure between the valves. A second pressure sensor senses pressure between the self-regulating valve and the inlet. The system can be used to de-ice aircraft inlet lip skins made of composite materials that have comparatively lower design temperatures than other comparable materials.

Claims

1. A thermal anti-ice system in an aircraft comprising:

a controlled valve configured to receive air from a compressor bleed port of an engine of the aircraft;

a self-regulating valve fluidly connected between the controlled valve and an inlet of the engine;

a first pressure sensor configured to sense pressure between the valves; and

a second pressure sensor configured to sense pressure between the self-regulating valve and the inlet.

2. The system of claim 1, wherein the controlled valve is controlled based on the sensed pressures.

3. The system of claim 1, wherein the controlled valve comprises a pressure-regulating shut-off valve (PRSOV).

4. The system of claim 1, wherein the self-regulating valve comprises a pressure-regulating valve (PRV).

5. The system of claim 1, wherein the controlled valve is controlled by a control module via a valve controller.

6. The system of claim 1, wherein the controlled valve is regulated to a pressure value that varies as a function of one or more selectable parameters.

7. The system of claim 1, wherein the self-regulating valve regulates to a predetermined downstream pressure.

8. The system of claim 1, wherein the self-regulating valve comprises a shut-off valve (SOV).

9. The system of claim 8, wherein the shut-off valve regulates to an upstream pressure.

10. A thermal anti-ice system in an aircraft comprising:

a controlled valve configured to receive air from a compressor bleed port of an engine of the aircraft;

a self-regulating valve in series with the controlled valve and through which air travels from the controlled valve to an inlet of the engine;

a first pressure sensor configured to sense pressure between the valves; and

a second pressure sensor configured to sense pressure between the self-regulating valve and the inlet;

the pressure sensors configured to provide values for evaluating performance of the valves.

11. The system of claim 10, further comprising a valve controller for controlling the controlled valve, the valve controller configured to provide control to the controlled valve based on values provided by the pressure sensors.

12. The system of claim 10, wherein the controlled valve comprises a pressure-regulating shut-off valve (PRSOV).

13. The system of claim 10, wherein the self-regulating valve comprises a pressure-regulating valve (PRV).

14. The system of claim 10, wherein the self-regulating valve self-regulates to an upstream pressure.

15. The system of claim 10, wherein the self-regulating valve comprises a shut-off valve (SOV).

16. The system of claim 15, wherein the shut-off valve regulates to an upstream pressure.

17. The system of claim 10, wherein one of the valves is subject to built-in testing (BIT) using at least one of the pressure sensors.

18. The system of claim 10, wherein one of the pressure sensors is subject to built-in testing (BIT) using at least one of the valves.

19. The system of claim 10, wherein, in the event that one of the pressure sensors is non-operational, thermal anti-icing is performed without using the non-operational sensor.

20. The system of claim 10, wherein one of the pressure sensors is subject to built-in testing (BIT) using the other pressure sensor and at least one aircraft parameter.

21. A control-module-performed method of providing thermal anti-icing in an aircraft, the method comprising:

controlling a valve that receives air from a compressor bleed port of an engine of the aircraft and is fluidly connected with an inlet of the engine through a self-regulating valve;

receiving a first input representing pressure in a fluid connection between the controlled valve and the self-regulating valve;

receiving a second input representing pressure in a fluid connection between the self-regulating valve and the inlet;

the controlling performed based on the first and second inputs.

22. The method of claim 21, further comprising positioning at least one of the valves in a predefined position.

23. The method of claim 22, performed when anti-ice is selected on and when engine idle speed is raised, the method further comprising raising the idle speed as a function of one or more aircraft parameters.

24. The method of claim 21, further comprising performing the controlling based on one or more aircraft parameters.

25. The method of claim 24, performed when anti-ice is selected on and when engine idle speed is raised, the method further comprising raising the idle speed as a function of the one or more aircraft parameters.

26. The method of claim 21, further comprising regulating the controlled valve to a pressure lower than a pressure to which the self-regulating valve regulates, the regulating of the controlled valve performed based on a speed of the engine.

27. The method of claim 26, performed during high-speed operation of the engine, the method further comprising, during low-speed operation of the engine, regulating the controlled valve to a pressure higher than a pressure to which the self-regulating valve regulates.

28. The method of claim 21, further comprising regulating the controlled valve to a pressure lower than a pressure to which the self-regulating valve regulates, and wherein the self-regulating valve regulates to upstream pressure.