Jet engine

Patent metadata

Field	Value
Publication number	US-11073041-B2
Application number	US-201816199799-A
Country	US
Kind code	B2
Filing date	Nov 26, 2018
Priority date	Nov 30, 2017
Publication date	Jul 27, 2021
Grant date	Jul 27, 2021

Abstract

An aircraft engine having an oil circuit and a transmission that can be supplied with oil via the oil circuit. Oil fed to the transmission can be directed out of the transmission into an oil reservoir, from which oil can be introduced directly back into the transmission via a hydraulic line path. According to the invention, the oil fed to the oil reservoir can only be fed to the hydraulic line path below a defined filling level of the oil reservoir. When the defined filling level of the oil reservoir is reached, oil can also be introduced into a further hydraulic line path.

First claim

The invention claimed is:

1. An aircraft engine comprising:
a transmission;
an oil circuit supplyinq oil to the transmission and further comprising:
an oil reservoir including:
a defined filling level;
an inlet through which oil is discharged into the oil reservoir from the transmission; and
an air-oil volume flow which is predominately air;

a first hydraulic line path;
a second hydraulic line path including an opening;
an oil separator located in the air-oil volume flow at the oil reservoir between the inlet of the oil reservoir and the opening of the second hydraulic line path;
wherein oil fed to the transmission is directed out of the transmission into the oil reservoir, and wherein oil is directed out of the oil reservoir and introduced directly back into the transmission via the first hydraulic line path;
wherein, when a level of oil in the oil reservoir is below the defined filling level, oil is only fed to the first hydraulic line path; and
wherein, when the defined filling level of the oil reservoir is reached, oil is also introduced into the second hydraulic line path.

2. The aircraft engine according to claim 1 , wherein the opening of the second hydraulic line path is arranged at the defined filling level of the oil reservoir.

3. The aircraft engine according to claim 1 , further comprising a transfer region, via which oil is introduced from the oil reservoir into the second hydraulic line path once the defined filling level of the oil reservoir has been reached.

4. The aircraft engine according to claim 1 , wherein the first hydraulic line path includes a pump, by which oil is pumped out of the oil reservoir into the transmission.

5. The aircraft engine according to claim 4 , wherein the pump is driven by the transmission.

6. The aircraft engine according to claim 4 , wherein an operative connection between the transmission and the pump is activated or deactivated.

7. The aircraft engine according to claim 4 , wherein the first hydraulic line path in a region between the pump and the transmission comprises a valve unit, by which oil pumped out of the oil reservoir by the pump is directed in one chosen from a direction of the transmission, back into the oil reservoir, and into the second hydraulic line path.

8. The aircraft engine according to claim 1 , wherein the oil separator comprises an inertial separator.

9. The aircraft engine according to claim 1 , wherein the air-oil volume flow emerges from the transmission, flowing from the inlet in a direction of the opening of the second hydraulic line path, wherein the oil separator includes a porous medium, through which the air-oil volume flow is passed, and wherein oil separated from the air-oil volume flow in a region of the porous medium flows off in a direction of the oil reservoir.

10. The aircraft engine according to claim 2 , further comprising:
an opening of the first hydraulic line path, and wherein the oil reservoir includes a lower inner region associated with the opening of the first hydraulic line path; and
a retention device between the opening of the first hydraulic line path and the opening of the second hydraulic line path, and wherein the retention device limits a flow of oil in the oil reservoir from the lower inner region in a direction of the opening of the second hydraulic line path.

11. The aircraft engine according to claim 10 , further comprising a housing region of the oil reservoir which delimits the lower inner region, and wherein the housing region is funnel-shaped, at least in some region or regions.

12. The aircraft engine according to claim 10 ,
wherein the oil reservoir includes an upper inner region associated with the opening of the second hydraulic line path;
wherein the retention device includes a retaining wall, which extends between the opening of the first hydraulic line path and the opening of the second hydraulic line path;
wherein the lower inner region into which the first hydraulic line path opens is delimited by the retaining wall;
wherein the upper inner region into which the second hydraulic line path opens is delimited by the retaining wall; and
wherein the retention device includes at least one passage, wherein the at least one passage in each case includes a connection between the lower inner region of the oil reservoir and the upper inner region of the oil reservoir.

13. The aircraft engine according to claim 12 , wherein the retaining wall includes a funnel-shaped region of the retaining wall.

14. The aircraft engine according to claim 13 , further comprising a funnel-shaped housing region of the oil reservoir which delimits the lower inner region, and wherein the funnel-shaped housing region and the funnel-shaped region of the retaining wall are matched to one another in such a way that a defined oil volume is retained by the retention device in the lower inner region in various orientations of an aircraft embodied with the aircraft engine that deviate from horizontal flight of the aircraft.

15. The aircraft engine according to claim 10 ,
wherein the oil separator further comprises a perforated feed pipe,
wherein the perforated feed pipe includes a pipe region and a pipe elbow,
wherein the inlet of the oil reservoir is connected to the perforated feed pipe;
wherein the pipe region extends substantially above the retention device;
wherein the pipe elbow is arranged between the inlet and the pipe region and in a region of which the air-oil volume flow flowing in via the inlet is deflected and oil is separated out of the air-oil volume flow; and
wherein the pipe region includes a plurality of holes, from which the air-oil volume flow and oil separated out in the perforated feed pipe is discharged.

16. The aircraft engine according to claim 1 , wherein the oil separator further comprises an extension of the inlet of the oil reservoir, wherein the extension discharges the air-oil volume flow from the transmission, wherein the extension extends from an upper boundary wall in a direction of a lower boundary wall of the oil reservoir, through a retention device, into the oil reservoir, wherein the air-oil volume flow flowing into the oil reservoir via the inlet is introduced from the inlet into an oil volume stored in the oil reservoir when the extension of the inlet dips into the oil volume stored in the oil reservoir.

17. The aircraft engine according to claim 1 , wherein the oil separator includes a cyclone, which is shaped as one chosen from straight and tapered, and when tapered, tapers from the inlet of the oil reservoir for the air-oil volume flow that is discharged from the transmission in a direction of an outlet of the cyclone.

18. An aircraft engine comprising:
a transmission;
an oil circuit supplying oil to the transmission and further comprising:
an oil reservoir including a defined filling level and an inlet through which oil is discharged into the oil reservoir from the transmission;
a first hydraulic line path including:
a pump, wherein the pump pumps oil out of the oil reservoir into the transmission; and
a valve unit located in a region between the pump and the transmission;

a second hydraulic line path;
wherein the valve unit in the first hydraulic line path directs oil pumped out of the oil reservoir by the pump in one chosen from a direction of the transmission, back into the oil reservoir, and into the second hydraulic line path;
wherein oil fed to the transmission is directed out of the transmission into the oil reservoir, and wherein oil is directed out of the oil reservoir and introdu

Assignees

• Rolls Royce Deutschland Ltd & Co Kg

Inventors

• Uhkoetter Stephan
• Kracht Uwe
• Astley Thomas Philip

Classifications

• F01M11/08

  Separating lubricant from air or fuel-air mixture before entry into cylinder (separating in general B01D) · CPC title

• F05D2260/609

  Deoiling or demisting · CPC title

• B64D37/22

  facilitating emptying in any position of tank · CPC title

• F01M11/067

  inverted, e.g. for inverted flight · CPC title

• F16N39/002

  by deaeration (degasification of liquids B01D19/00) · CPC title