Oil tank filling system

Patent metadata

Field	Value
Publication number	US-11156124-B2
Application number	US-201916387953-A
Country	US
Kind code	B2
Filing date	Apr 18, 2019
Priority date	May 2, 2018
Publication date	Oct 26, 2021
Grant date	Oct 26, 2021

Abstract

An oil tank filling system for filling the oil tank of a gas turbine engine. The system includes an oil tank located within a core of the engine, an oil filling reservoir located within a bifurcation that extends from the core of the engine, an oil tank filling pipe that leads from the oil filling reservoir to a tank filling port on the oil tank, and an oil pump. The system is configured so that the oil pump pumps oil from the oil filling reservoir through the oil tank filling pipe and the tank filling port to fill the oil tank. A method of filling the oil tank of a gas turbine engine and a gas turbine engine that includes the oil tank filling system are also disclosed.

First claim

We claim:

1. An oil tank filling system for filling an oil tank of a gas turbine engine that has a fan nacelle and a fan case that is covered by the fan nacelle, the oil tank filling system comprises:
an oil tank located within a core of the gas turbine engine;
an oil filling reservoir located within a bifurcation that extends from the core of the gas turbine engine, wherein the bifurcation is located downstream of outlet guide vanes of the gas turbine engine, and wherein the bifurcation has a bifurcation base that is attached to the fan case;
an engine oil filling port for charging the oil filling reservoir with oil, wherein the engine oil filling port is located on the bifurcation base and accessed through an opening in the fan nacelle;
an oil tank filling pipe that leads from the oil filling reservoir to a tank filling port on the oil tank; and
an oil pump;
the oil tank filling system being configured so that the oil pump pumps oil from the oil filling reservoir through the oil tank filling pipe and the tank filling port to fill the oil tank.

2. The oil tank filling system of claim 1 wherein the oil tank has an oil tank top and an oil tank bottom and the tank filling port is located on or adjacent the oil tank top.

3. The oil tank filling system of claim 1 wherein the oil tank is shaped to curve around one or both sides of the engine within the core of the engine.

4. The oil tank filling system of claim 1 wherein the oil tank is located between opposing outlet guide vanes.

5. The oil tank filling system of claim 1 wherein one or more temperature and/or pressure sensors are provided alongside one or more sections of the oil tank filling pipe and communicate with a controller to provide an alert should the oil tank filling pipe burst or become blocked.

6. The oil tank filling system of claim 1 wherein the oil pump is an auxiliary pump for an auxiliary oil system.

7. The oil tank filling system of claim 1 wherein the oil pump is located within the bifurcation.

8. The oil tank filling system of claim 7 wherein the oil filling reservoir is part of the oil pump.

9. The oil tank filling system of claim 1 wherein the oil pump is located within a lower portion of the core and pumps oil through the oil tank filling pipe to the tank filling port to fill the oil tank.

10. The oil tank filling system of claim 1 wherein the oil pump is located within an upper portion of the core and draws oil through the oil tank filling pipe to the tank filling port to fill the oil tank.

11. The oil tank filling system of claim 1 wherein the oil pump is located on the core of the engine.

12. The oil tank filling system of claim 1 that includes an oil pump controller that controls the operation of the oil pump in the filling of the oil tank.

13. A gas turbine engine that includes the oil tank filling system of claim 1 .

14. The gas turbine engine of claim 13 for an aircraft wherein the gas turbine engine comprises an engine core comprising:
a turbine;
a compressor;
a core shaft connecting the turbine to the compressor; and
a fan located upstream of the engine core, the fan comprising a plurality of fan blades and a gearbox that receives an input from the core shaft and outputs drive to the fan so as to drive the fan at a lower rotational speed than the core shaft.

15. A method of filling an oil tank of a gas turbine engine that is located within a core of the gas turbine engine, the method comprising the steps of:
supplying oil to an oil filling reservoir that is located within a bifurcation that extends from the core of the gas turbine engine, wherein the bifurcation is located downstream of outlet guide vanes of the gas turbine engine, wherein the bifurcation has a bifurcation base that is attached to a fan case of the gas turbine engine, wherein the fan case is covered by a fan nacelle of the gas turbine engine, and wherein an engine oil filling port for charging the oil filling reservoir with oil is located on the bifurcation base and accessed through an opening in the fan nacelle; and
pumping the oil from the oil filling reservoir through an oil tank filling pipe that leads to a tank filling port on the oil tank that is located within the core of the gas turbine engine.

Assignees

• Rolls Royce Plc

Inventors

• White Samuel W
• Malewicz William A
• Ray Sebastian
• Diaz Garcia Cristina
• Edwards David A

Classifications

• F05D2260/98

  Lubrication · CPC title

• F16N7/00

  Arrangements for supplying oil or unspecified lubricant from a stationary reservoir or the equivalent in or on the machine or member to be lubricated · CPC title

• F16N2210/02

  Turbines · CPC title

• F05D2230/72

  Maintenance · CPC title

• F05D2220/36

  specially adapted for the fan of turbofan engines · CPC title