Speed card-controlled override fuel pump assist

Patent metadata

Field	Value
Publication number	US-9732678-B2
Application number	US-201514602412-A
Country	US
Kind code	B2
Filing date	Jan 22, 2015
Priority date	Sep 11, 2011
Publication date	Aug 15, 2017
Grant date	Aug 15, 2017

Abstract

A system and method for supplementing fuel feed pressure and flow within an aircraft fuel system. The fuel system includes boost and override fuel pumps delivering fuel from the tanks to a fuel manifold, and a jettison fuel pump. The method includes the steps of: (a) sensing whether the aircraft engine is operating near maximum power; (b) upon sensing the condition, operating the jettison fuel pump in fluid interconnection with the override fuel pump to deliver fuel to the fuel manifold; and (c) upon sensing the cessation of the condition, deactivating the jettison fuel pump. The system includes a monitoring circuit signaling when the aircraft engine speed is greater than a predetermined threshold, and a fuel system control circuit operating a jettison fuel pump enable circuit portion in response to the signal while omitting other jettisoning operations. The jettison fuel pump consequently functions as an override fuel pump assist.

First claim

What is claimed is:

1. An override-based aircraft fuel system for fueling an aircraft engine, the aircraft fuel system comprising:
a fuel manifold;
a primary fuel tank including a first boost fuel pump fluidly connected to the fuel manifold;
an auxiliary fuel tank including an override fuel pump fluidly connected to the fuel manifold and a jettison fuel pump fluidly connectable to the fuel manifold;
an engine monitoring circuit including (a) an aircraft engine speed sensor operatively connected to a comparator and (b) a control relay selectively providing a signal output, wherein the comparator is configured to drive the control relay to provide the signal output when the aircraft engine speed sensor detects an aircraft engine speed greater than a predetermined threshold; and
a fuel system control circuit including a first operating relay operatively connected to a jettison fuel pump enable circuit portion, wherein the signal output operates the first operating relay and the jettison fuel pump enable circuit portion, and wherein the jettison fuel pump enable circuit portion operatively controls the jettison fuel pump to deliver fuel to the fuel manifold.

2. The override-based aircraft fuel system of claim 1 , further comprising a jettison transfer valve fluidly connected to the jettison fuel pump, wherein the fuel system control circuit is configured to operate the jettison fuel pump enable circuit portion and jettison fuel pump without operating the jettison transfer valve so as to permit the jettisoning of fuel.

3. The override-based aircraft fuel system of claim 1 , wherein the engine speed sensor senses a rotor speed of an N 2 rotor of the aircraft engine.

4. The override-based aircraft fuel system of claim 3 , wherein the predetermined threshold of the comparator includes a hysteresis filter having a first rotor speed of an N 2 rotor for generally increasing rotor speeds and a second rotor speed of the N 2 rotor for generally decreasing rotor speeds, where the first rotor speed is greater than the second rotor speed.

5. The override-based aircraft fuel system of claim 4 , wherein the first rotor speed is about 83% of a maximum rated rotor speed of the N 2 rotor of the aircraft engine and the second rotor speed is about 72% of the maximum rated rotor speed of the N2 rotor of the aircraft engine.

6. The override-based aircraft fuel system of claim 1 , wherein the fuel system control circuit includes a second operating relay operatively connected to the jettison fuel pump enable circuit portion, and wherein the signal output operates the second operating relay to provide a path to ground for the signal output operating the jettison fuel pump enable circuit portion.

7. The override-based aircraft fuel system of claim 3 , wherein the comparator is configured to delay deactivation of the control relay by a predetermined period of time after sensing that the rotor speed of the N 2 rotor has dropped below the predetermined threshold.

8. The override-based aircraft fuel system of claim 1 , wherein the engine speed sensor senses an aircraft engine throttle setting of the aircraft engine.

9. The override-based aircraft fuel system of claim 8 , wherein the predetermined threshold of the comparator includes a hysteresis filter having a first aircraft engine throttle setting for generally increasing throttle settings and a second aircraft engine throttle setting for generally decreasing throttle settings, where the first aircraft engine throttle setting is greater than the second aircraft engine throttle setting.

10. The override-based aircraft fuel system of claim 9 , wherein the first aircraft engine throttle setting is about 83% of a maximum throttle of the aircraft engine and the second aircraft engine throttle setting is about 72% of the maximum throttle of the aircraft engine.

11. The override-based aircraft fuel system of claim 8 , wherein the comparator is configured to delay deactivation of the control relay by a predetermined period of time after sensing that the aircraft engine throttle setting has dropped below the predetermined threshold.

12. The override-based aircraft fuel system of claim 1 , wherein the signal output additionally operates a transfer valve so as to place the jettison fuel pump in fluid communication with the override fuel pump via the outputs of the jettison and override fuel pumps.

13. The override-based aircraft fuel system of claim 1 , wherein the jettison fuel pump is fluidly connected to the auxiliary fuel tank contents, and fluidly connectable to the fuel manifold, but not fluidly connected or connectable to other aircraft fuel systems.

14. A retrofit system for installation in an aircraft having a fuel manifold, at least one primary fuel tank including at least one boost fuel pump fluidly connected to the fuel manifold, at least one auxiliary fuel tank including at least one override fuel pump fluidly connected to the fuel manifold, and an engine monitoring circuit including an aircraft engine speed sensor, the retrofit system comprising:
a fuel system control circuit having a first operating relay operatively connected to a jettison fuel pump enable circuit portion, the first operating relay being operably connectable to a control relay of the engine monitoring circuit for selective passing of a signal output of the control relay to the jettison fuel pump enable circuit portion,
wherein the first operating relay is operably connected to an electrical load shedding portion of the jettison fuel pump enable circuit portion and to an input of a GFI portion of the jettison fuel pump enable circuit portion.

15. The retrofit system of claim 14 , wherein the fuel system control circuit is configured to operate the jettison fuel pump enable circuit portion and a jettison fuel pump without operating a jettison transfer valve so as to permit the jettisoning of fuel.

16. A retrofit system for installation in an aircraft having a fuel manifold, at least one primary fuel tank including at least one boost fuel pump fluidly connected to the fuel manifold, at least one auxiliary fuel tank including at least one override fuel pump fluidly connected to the fuel manifold, and an engine monitoring circuit including an aircraft engine speed sensor, the retrofit system comprising:
a fuel system control circuit having a first operating relay operatively connected to a jettison fuel pump enable circuit portion, the first operating relay being operably connectable to a control relay of the engine monitoring circuit for selective passing of a signal output of the control relay to the jettison fuel pump enable circuit portion,
further comprising at least one jettison fuel pump installable within the at least one auxiliary fuel tank, said at least one jettison fuel pump being fluidly connectable to said fuel manifold and operably connectable to said jettison fuel pump enable circuit portion for selective control by said control relay.

17. A retrofit system for installation in an aircraft having a fuel manifold, at least one primary fuel tank including at least one boost fuel pump fluidly connected to the fuel manifold, at least one auxiliary fuel tank including at least one override fuel pump fluidly connected to the fuel manifold, and an engine monitoring circuit including an aircraft engine speed sensor, the retrofit system comprising:
a fuel system control circuit having a first operating relay operatively connected to a jettison fuel pump enable circuit portion, the first operating relay being operably connectable to a control relay of the engine monitoring circuit for sele

Assignees

• Boeing Co

Inventors

• Mccabe William H

Classifications

• F02C9/30 Primary

  characterised by variable fuel pump output · CPC title

• F02C7/236 Primary

  Fuel delivery systems comprising two or more pumps · CPC title

• F02C7/222

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

• F02C9/28

  Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed (F02C9/30 - F02C9/38, F02C9/44 take precedence) · CPC title

• F05D2260/80

  Diagnostics · CPC title