Aero-engine low pressure pump

Patent metadata

Field	Value
Publication number	US-10197062-B2
Application number	US-201615256108-A
Country	US
Kind code	B2
Filing date	Sep 2, 2016
Priority date	Oct 21, 2015
Publication date	Feb 5, 2019
Grant date	Feb 5, 2019

Abstract

An aero-engine low pressure pump is provided for supplying fuel at a raised pressure to a high pressure pump. The low pressure pump has a pumping mechanism which raises the pressure of fuel flowing though the mechanism. The low pressure pump further has electrical motor which drives the pumping mechanism. The low pressure pump further has a variable frequency motor drive which supplies electrical power to the electrical motor. The variable frequency motor drive measures the electrical power supplied to the electrical motor. The low pressure pump further has a control unit which compares the measured electrical power to a reference power, and, when the measured electrical power is less than the reference power by a predetermined amount, controls the motor drive to increase the power supplied to the electrical motor thereby increasing the pressure rise produced by the pumping mechanism.

First claim

The invention claimed is:

1. An aero-engine low pressure pump for supplying fuel at a raised pressure to a high pressure pump, the low pressure pump comprising:
a pumping mechanism that raises the pressure of fuel flowing though the mechanism;
an electrical motor that drives the pumping mechanism; and
a variable frequency motor drive that supplies electrical power to the electrical motor;
wherein the variable frequency motor drive measures the electrical power supplied to the electrical motor;
wherein the pump further has a control unit that compares the measured electrical power to a reference power, and, when the measured electrical power is less than the reference power by a predetermined amount, controls the motor drive to increase the power supplied to the electrical motor thereby increasing the pressure rise produced by the pumping mechanism; and
wherein the measurement of the supplied electrical power is synchronised to the frequency of a variable pulse-width modulation used by the variable frequency motor drive to supply the electrical power.

2. The low pressure pump according to claim 1 , wherein the reference power is determined from a stored model of pump performance.

3. The low pressure pump according to claim 1 , wherein the reference power is based on one or more previously determined electrical power measurements by the variable frequency motor drive.

4. The low pressure pump according to claim 1 , wherein the control unit repeats the comparison and correspondingly controls the motor drive to increase the power supplied to the electrical motor by repeated increments until the measured electrical power is no longer less than the reference power by the predetermined amount.

5. The low pressure pump according to claim 1 , wherein when the measured electrical power is greater than the reference power by a further predetermined amount, the control unit controls the variable frequency motor drive to decrease the power supplied to the electrical motor thereby decreasing the pressure rise produced by the pumping mechanism.

6. The low pressure pump according to claim 1 , wherein the fuel is sent to the low pressure pump by one or more fuel tank pumps, the control unit further monitoring the health of the one or more fuel tank pumps from the comparison of the measured electrical power to the reference power.

7. The low pressure pump according to claim 1 , wherein the pumping mechanism is a centrifugal impeller rotated by the electrical motor.

8. A fuel pumping unit for an aero-engine, the fuel pumping unit having a low pressure pump and a high pressure pump, the low pressure pump supplying fuel at a raised pressure to the high pressure pump for onward supply to a fuel metering unit of the engine, wherein the low pressure pump is a pump according to claim 1 .

9. A fuel pumping system for an aero-engine, the system having a fuel pumping unit according to claim 8 , and further having one or more fuel tank pumps that send fuel to the low pressure pump.

10. An aero-engine having a fuel pumping unit according to claim 8 .

11. An aero-engine having a fuel pumping system according to claim 9 .

Assignees

• Rolls Royce Plc

Inventors

• Brookes David
• Yates Martin K

Classifications

• F02C9/30

  characterised by variable fuel pump output · CPC title

• F04D29/22

  specially for centrifugal pumps · CPC title

• F05D2210/13

  mixed, e.g. two-phase fluid · CPC title

• F02C7/22

  Fuel supply systems · CPC title

• F04D15/0066 Primary

  by changing the speed, e.g. of the driving engine · CPC title