Valve for aircraft environmental control system conduit

Patent metadata

Field	Value
Publication number	US-11260978-B2
Application number	US-201916402925-A
Country	US
Kind code	B2
Filing date	May 3, 2019
Priority date	May 3, 2019
Publication date	Mar 1, 2022
Grant date	Mar 1, 2022

Abstract

A compressed air conduit can have a cross-sectional area, and a valve, the valve having at least one arm being deployable laterally into the cross-sectional area of the conduit to restrict flow within the conduit.

First claim

The invention claimed is:

1. An environmental control system for an aircraft, the environmental control system having a conduit having a cross-sectional area and a valve, the valve having at least one arm being deployable laterally from a retracted position offset from the cross-sectional area to a fully deployed position into the cross-sectional area of the conduit, the at least one arm configured to occupy at least 5% of the cross-sectional area of the conduit and to restrict flow within the conduit when fully deployed, at least a portion of the cross-sectional area being free of the at least one arm when fully deployed.

2. The environmental control system of claim 1 wherein the valve has a plurality of arms circumferentially interspaced from one another around a circumference of the cross-sectional area, each arm being pivotally deployable into the cross-sectional area of the conduit.

3. The environmental control system of claim 2 further comprising an annular slot surrounding the cross-sectional area of the conduit, the arms being pivotally retractable into the annular slot.

4. The environmental control system of claim 3 wherein each arm has a planar body with an obstructing portion projecting from a pivot in a first direction, and an actuating portion projecting from the pivot in a second direction, the obstructing portion snugly conforming in shape to a portion of the slot.

5. The environmental control system of claim 4 further comprising an actuating ring mechanically interconnecting the actuating portion of all the arms.

6. The environmental control system of claim 1 wherein each arm has a planar body with an obstructing portion projecting from a pivot in a first direction, and an actuating portion projecting from the pivot in a second direction.

7. The environmental control system of claim 1 further comprising an actuator configured to selectively deploy or retract the arm.

8. The environmental control system of claim 7 wherein the actuator has a piston configured to be moved within a cylinder based on a pressure differential between two piston sides in the cylinder, a first fluid conduit connecting the first piston side to a first inlet upstream of the valve, and a second fluid conduit connecting the second piston side to a second inlet downstream of the valve.

9. The environmental control system of claim 8 further comprising a biasing member biasing the piston to a default position.

10. The environmental control system of claim 8 further comprising a shutoff valve in the first fluid conduit, the shutoff valve being configured to selectively open or close the first fluid conduit based on an electromagnetic signal input.

11. A method of operating an aircraft environmental control system having a conduit, the method comprising:
contingent upon receiving an indication of a pressure reduction at a sensing point along the conduit, deploying an arm into a cross-sectional area of the conduit, upstream of the sensing point, the deployed arm reducing the flow rate along the conduit towards the sensing point by at least 5%.

12. The method of claim 11 wherein deploying includes pivoting a portion of the arm into the cross-sectional area of the conduit.

13. The method of claim 12 wherein deploying includes collectively pivoting a plurality of circumferentially interspaced arms into the cross-sectional area of the conduit.

14. The method of claim 11 wherein deploying includes a differential of pressure causing a deploying force to be exerted onto the arm.

15. The method of claim 14 wherein the differential of pressure is a differential of pressure between two points interspaced along the conduit, including the sensing point, and the differential of pressure is conveyed via fluid lines.

16. The method of claim 15 wherein the differential of pressure causes a sliding of a piston inside a cylinder, the piston being mechanically connected to deploy the arm.

17. A gas turbine engine comprising a compressed air conduit extending from a compressed air bleed point, the compressed air conduit having a cross-sectional area, and a valve, the valve having at least one arm being deployable laterally from a retracted position offset from the cross-sectional area to a fully deployed position into the cross-sectional area of the conduit to restrict flow within the conduit, at least a portion of the cross-sectional area being free of the at least one arm when fully deployed.

18. The gas turbine engine of claim 17 wherein the gas turbine engine is a turbofan engine and includes a fan, a core engine, and a bypass path, wherein the compressed air bleed point is in the bypass path.

19. The gas turbine engine of claim 17 wherein the operation of the valve is powered mechanically by a differential of pressure.

Assignees

• Pratt & Whitney Canada

Inventors

• Caron Jean-Francois

Classifications

• F16K3/06

  in the form of closure plates arranged between supply and discharge passages (F16K3/10 takes precedence) · CPC title

• F05D2260/50

  Kinematic linkage, i.e. transmission of position · CPC title

• F15B15/1476

  Special return means · CPC title

• B64D2013/0603

  Environmental Control Systems · CPC title

• F01D17/145

  by means of valves, e.g. for steam turbines (valves in general F16K) · CPC title