DRAINAGE MAST OF THE COMPARTMENT OF AN AIRCRAFT SUBJECTED TO A NEGATIVE PRESSURE

• US 20150021438A1
• Filed: 07/21/2014
• Published: 01/22/2015
• Est. Priority Date: 07/22/2013
• Status: Active Grant

• Current Assignee: Airbus Operations SL (Airbus SE)
• Original Assignee: Airbus Operations SL (Airbus SE)
• Inventors: Casado Montero, Carlos, Hernanz Manrique, Jose Angel, Grana Otero, Jose, Parra Fabian, Ignacio Esteban, Gallego Lorenzo, Miguel Angel
• Granted Patent: US 9,452,833 B2
• Time in Patent Office: Days
• US Class Current: 244/136
• CPC Class Codes: B64C 1/1453 Drain masts
• CPC Class Codes: B64D 1/16 Dropping or releasing powdered, liquid, or gaseous matter, e.g. for fire-fighting jettisoning fuel B64D37/26

Abstract

A drainage mast able to drain effectively the liquid contained in the compartment of an aircraft when the pressure within the compartment is lower than the outside pressure without using any pressure control active device and without causing any significant perturbation to the aerodynamic behavior of the aircraft. The drainage mast is configured with a cross section area decreasing from its entry section to the compartment to its outlet section and is disposed at an acute angle α relative to the compartment in the airflow direction. The entry and outlet sections have two perpendicular symmetry axes of different length, the entry section is arranged with its longer axis of symmetry substantially parallel to the airflow direction. The drainage mast has a symmetrical configuration with respect to a plane substantially perpendicular to the fuselage envelope passing through the longer axis of symmetry of the entry section.

Claims

1. A drainage mast to drain fluids from one compartment of an aircraft into the atmosphere by gravity even when the pressure in the compartment is below atmospheric pressure, the drainage mast being disposed at an acute angle a with respect to the compartment in the airflow direction and configured with a cross section having a decreasing area from its entry section in the bottom zone of the compartment to its outlet section, the drainage mast further comprising:

entry and outlet sections each having two perpendicular axes of symmetry of different length;

the entry section being arranged with its longer axis of symmetry substantially parallel to the airflow direction;

a symmetrical configuration with respect to a plane substantially perpendicular to the fuselage envelope, passing through the longer axis of symmetry of the entry section;

the ratio between the shorter axis and the longer axis of the outlet section being between 0.2 and 0.6.

2. The drainage mast according to claim 1, wherein the outlet section is disposed in a plane forming an angle β

between 60-120°

with the plane of the entry section, its longer axis being parallel to the plane of the entry section and its projection over said plane being perpendicular to the longer axis of the entry section.

3. The drainage mast according to claim 2, wherein the angle β

is between 70-85°

.

4. The drainage mast according to claim 1 wherein the entry section has an elliptical shape and the outlet section has one of an elliptical, oval and dome-ended rectangular shape.

5. The drainage mast according to claim 1, wherein the areas of the outlet section and the inlet section have values such that the ratio between them is the one in which the value of the flow rate needed to evacuate a predetermined volume of liquid in the compartment and the value of the flow rate evacuated by the drainage mast, when is fully primed, match.

6. An aircraft having a drainage mast to drain fluids from one compartment of the aircraft into the atmosphere by gravity even when the pressure in the compartment is below atmospheric pressure, the drainage mast being disposed at an acute angle α

with respect to the compartment in the airflow direction and configured with a cross section having a decreasing area from its entry section in the bottom zone of the compartment to its outlet section, the drainage mast further comprising;

entry and outlet sections each having two perpendicular axes of symmetry of different length;

the entry section being arranged with its longer axis of symmetry substantially parallel to the airflow direction;

a symmetrical configuration with respect to a plane substantially perpendicular to the fuselage envelope, passing through the longer axis of symmetry of the entry section;

the ratio between the shorter axis and the longer axis of the outlet section being between 0.2 and 0.6.