Anti-clog lubricant distribution assembly

• US 10,480,636 B2
• Filed: 10/13/2015
• Issued: 11/19/2019
• Est. Priority Date: 10/17/2014
• Status: Active Grant

• Current Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Original Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Inventors: Hodgkinson, Eric James
• Primary Examiner(s): Riegelman, Michael A
• Application Number:
  US15/519,743
• Publication Number:
  US 20170254406A1
• Time in Patent Office: 1,498 Days
• CPC Class Codes: B64C 27/12 Rotor drives
• CPC Class Codes: F16H 57/0404 Lubricant filters
• CPC Class Codes: F16H 57/042 Guidance of lubricant
• CPC Class Codes: F16H 57/0434 relating to lubrication supply, e.g. pumps arrangement of pumps F16H57/0441; Pressure control grooves with pumping effect for supplying lubricant F16H57/0428; generation and variation of line pressure for transmission control F16H61/0021
• CPC Class Codes: F16H 57/0436 Pumps
• CPC Class Codes: F16H 57/045 Lubricant storage reservoirs, e.g. reservoirs in addition to a gear sump for collecting lubricant in the upper part of a gear case
• CPC Class Codes: F16N 29/02 for influencing the supply of lubricant

Abstract

A fluid distribution assembly for distributing a fluid includes a first inlet housing; an outlet housing fluidly coupled to the first inlet housing; and a second inlet housing fluidly coupled to the outlet housing; the second inlet housing having a first end and a second end, the second end coupled to the outlet housing at a stagnation dam, the stagnation dam controlling direction of fluid flow through the second inlet housing in response to velocity of fluid flow in the outlet housing.

Claims

1. A fluid distribution assembly for distributing a fluid, the assembly comprising:

a first inlet housing;

an outlet housing fluidly coupled to the first inlet housing; and

a second inlet housing fluidly coupled to the outlet housing, the outlet housing being fluidically connected between the first inlet housing and the second inlet housing;

the second inlet housing having a first end and a second end, the second end coupled to the outlet housing at a stagnation dam, the stagnation dam controlling direction of fluid flow through the second inlet housing in response to a change in velocity of fluid flow in the outlet housing from the first inlet housing.

2. The fluid distribution assembly of claim 1 further comprising:

an inlet screen positioned at an inlet of the second inlet housing.

3. The fluid distribution assembly of claim 1 further comprising:

a filter between the first inlet housing and the outlet housing,

wherein;

when the filter is unblocked, the stagnation dam controls the fluid flow from the second end to the first end of the second inlet housing, and

when the filter is blocked, the stagnation dam controls the fluid flow from the first end to the second end of the second inlet housing.

4. The fluid distribution assembly of claim 1 wherein:

when the first inlet housing is unblocked, fluid flows from the second end of the second inlet housing to the first end of the second inlet housing.

5. The fluid distribution assembly of claim 1 wherein:

when the first inlet housing is blocked, fluid flows from the first end of the second inlet housing to the second end of the second inlet housing.

6. The fluid distribution assembly of claim 1 wherein:

the stagnation dam controls direction of fluid flow through the second inlet housing in response to static pressure and dynamic pressure.

7. A rotary wing aircraft comprising:

a rotor;

a gearbox coupled to the rotor;

an engine coupled to the gearbox; and

a lubricant distribution system providing lubricant from a sump to the gearbox, the lubricant distribution system including;

a first inlet housing fluidly coupled to the sump;

an outlet housing fluidly couple to the first inlet housing, the outlet housing being fluidically connected between the first inlet housing and the second inlet housing; and

a second inlet housing fluidly coupled to the outlet housing;

the second inlet housing having a first end fluidly connected to the sump and a second end coupled to the outlet housing, the second end including a stagnation dam controlling direction of fluid flow through the second inlet housing in response to a change in velocity of fluid flow in the outlet housing from the first inlet housing.

8. The rotary wing aircraft of claim 7 further comprising:

an inlet screen positioned at an inlet of the second inlet housing.

9. The rotary wing aircraft of claim 7 further comprising:

a filter between the first inlet housing and the outlet housing,

wherein;

when the filter is unblocked, the stagnation dam controls the fluid flow from the second end to the first end of the second inlet housing, and

when the filter is blocked, the stagnation dam controls the fluid flow from the first end to the second end of the second inlet housing.

10. The rotary wing aircraft of claim 7, wherein:

when the first inlet housing is unblocked, fluid flows from the second end of the second inlet housing to the first end of the second inlet housing.

11. The rotary wing aircraft of claim 7, wherein:

when the first inlet housing is blocked, fluid flows from the first end of the second inlet housing to the second end of the second inlet housing.

12. The rotary wing aircraft of claim 7, wherein:

the stagnation dam controls direction of fluid flow through the second inlet housing in response to static pressure and dynamic pressure.

13. The rotary wing aircraft of claim 7, further comprising:

a pump coupled to the outlet housing, the pump directing lubricant through the first inlet housing and the second inlet housing.