Common-rail fuel system with ejector pump and method of use thereof

Patent metadata

Field	Value
Publication number	US-11092126-B2
Application number	US-201916558847-A
Country	US
Kind code	B2
Filing date	Sep 3, 2019
Priority date	Sep 3, 2019
Publication date	Aug 17, 2021
Grant date	Aug 17, 2021

Abstract

A method of operating an aircraft engine of an aircraft, the aircraft engine having a common-rail fuel injection system for injecting fuel into a combustion chamber of the aircraft engine, including: pressurizing fuel for circulation through the common-rail injection system; circulating a portion of the pressurized fuel through a motive flow inlet of an ejector pump; and entraining a flow through the ejector pump with the portion of the pressurized fuel circulating through the motive flow inlet.

First claim

The invention claimed is:

1. A method of operating an aircraft engine of an aircraft, the aircraft engine having a common-rail fuel injection system for injecting fuel into a combustion chamber of the aircraft engine, comprising:
pressurizing fuel with a high-pressure pump for flowing through the common-rail fuel injection system;
diverting a portion of the pressurized fuel flowing within at least one fuel conduit connecting the high-pressure pump to at least one common-rail injector into a bypass conduit, and flowing the diverted portion of the pressurized fuel from the bypass conduit to a motive flow inlet of an ejector pump, the bypass conduit connected to the at least one fuel conduit at a connection point located downstream of a common-rail of the common-rail fuel injection system and upstream of the at least one common-rail injector;
injecting a remainder of the pressurized fuel into the at least one common-rail injector thereby generating a backflow of fuel; and
entraining a flow through the ejector pump with both of the diverted portion of the pressurized fuel and the backflow of fuel both flowing through the motive flow inlet.

2. The method of claim 1 , comprising controlling an amount of fuel injected by the at least one common-rail injector as a function of a pressure in the high-pressure pump and a speed of the aircraft engine.

3. The method of claim 1 , wherein the ejector pump is fluidly connected to a source of fuel, the method comprising entraining fuel from the source of fuel through the ejector pump using both of the portion of the pressurized fuel and the backflow of fuel.

4. The method of claim 1 , further comprising regulating a flow rate of the diverted portion of the pressurized fuel.

5. The method of claim 4 , wherein regulating the flow rate includes constricting a flow of the diverted portion of the pressurized fuel.

6. The method of claim 1 , wherein the entraining of the flow through the ejector pump with both of the portion of the pressurized fuel and the backflow of fuel includes entraining fuel directly from a fuel tank.

7. The method of claim 1 , wherein the entraining of the flow through the ejector pump with both of the portion of the pressurized fuel and the backflow of fuel includes suctioning the fuel through a main fuel conduit fluidly connecting a source of fuel to the high-pressure pump.

8. A method of supplying fuel to an aircraft engine having a common-rail fuel injection system, comprising:
pressurizing fuel with a high-pressure pump to flow through the common-rail fuel injection system;
injecting a portion of the pressurized fuel in at least one common-rail injector of the common-rail fuel injection system thereby generating a backflow of fuel;
entraining fuel to be pressurized from a source of fuel though an ejector pump with the backflow of fuel flowing through a motive flow inlet of the ejector pump;
diverting fuel from at least one fuel conduit connecting the high-pressure pump to the at least one common-rail injector, the diverting of the fuel including diverting the fuel via a bypass conduit connected to the at least one fuel conduit at a connection point located downstream of a common-rail of the common-rail fuel injection system and upstream of the at least one common-rail injector; and
increasing a flow rate through the ejector pump by further injecting the diverted fuel into the motive flow inlet of the ejector pump.

9. The method of claim 8 , further comprising regulating a flow rate of the diverted fuel.

10. The method of claim 9 , wherein regulating the flow rate includes constricting a flow of the diverted fuel.

11. The method of claim 8 , wherein entraining the fuel from the source of fuel through the ejector pump includes entraining the fuel directly from a fuel tank.

12. The method of claim 8 , wherein entraining the fuel from the source of fuel through the ejector pump includes suctioning the fuel through a main fuel conduit fluidly connecting the source of fuel to the high-pressure pump.

13. The method of claim 8 , comprising controlling an amount of fuel injected by the at least one common-rail injector as a function of a pressure in the high-pressure pump and a speed of the aircraft engine.

14. An aircraft engine comprising: at least one combustion chamber; a common-rail fuel injection system having a common-rail fluidly connected to a source of fuel;
at least one common-rail injector each having a respective injector inlet fluidly connected to the common-rail via a respective fuel conduit, a respective first injector outlet fluidly connected to the at least one combustion chamber, and a respective second injector outlet for outputting a backflow of fuel; a bypass conduit stemming from the respective fuel conduit between the common-rail of the common-rail fuel injection system and the at least one common-rail injector; and an ejector pump having a motive flow inlet fluidly connected to both of the respective second injector outlet and the bypass conduit, and an entrained flow inlet for receiving fuel to be suctioned by the ejector pump.

15. The aircraft engine of claim 14 , comprising a flow control device being fluidly connected to the bypass conduit, the flow control device having an orifice, a size of the orifice being variable to vary a flow of fuel within the bypass conduit.

16. The aircraft engine of claim 14 , wherein the source of fuel is a fuel tank, the ejector pump located within the fuel tank.

17. The aircraft engine of claim 14 , further comprising a main fuel conduit fluidly connecting the source of fuel to the common-rail, and a boost pump fluidly connected to the main fuel conduit, the ejector pump being connected to the main fuel conduit upstream of the boost pump.

18. The aircraft engine of claim 14 , comprising a controller operatively connected to the at least one common-rail injector and to a high-pressure-fuel sensor operatively connected to the high-pressure pump for controlling an amount of fuel to be injected by the least one common-rail injector.

Assignees

• Pratt & Whitney Canada

Inventors

• Bergeron Sebastien
• Plamondon Etienne
• Gauvreau Jean-Gabriel
• Renaud Benjamin

Classifications

• F05D2260/601

  using an ejector or a jet pump · CPC title

• F05D2220/60

  making use of surplus or waste energy · CPC title

• F02C7/222 Primary

  Fuel flow conduits, e.g. manifolds · CPC title

• F01C11/006

  of dissimilar working principle · CPC title

• F02C9/263

  by means of fuel metering valves · CPC title