Balancing the power of two turboshaft engines of an aircraft

Patent metadata

Field	Value
Publication number	US-9346553-B2
Application number	US-76482507-A
Country	US
Kind code	B2
Filing date	Jun 19, 2007
Priority date	Jun 19, 2006
Publication date	May 24, 2016
Grant date	May 24, 2016

Abstract

The present invention relates to a method and to an associated fuel metering system for balancing the power delivered by two aircraft turboshaft engines by determining first and second limiting margins of the engines (M 1 , M 2 ) which are transformed into first and second power margins. Thereafter, the values of the first and second power margins are compared in order to determine a primary difference between said first and second power margins. Finally, the engine having the greater power margin is accelerated in order to balance the first and second engines in power by minimizing the primary difference to as great as extent as possible.

First claim

What is claimed is:

1. A method of balancing the power delivered by first and second turboshaft engines, each engine having a plurality of surveillance parameters (Ng, Cm, T 45 ) each of a different type, the surveillance parameter amongst the surveillance parameters of the first engine that is closest to its limit is of a first type and the surveillance parameter amongst the surveillance parameters of the second engine that is closest to its limit is of a second type different than the first type, the method comprising:
a) determining in real time an individual margin for each surveillance parameter (Ng, Cm, T 45 ) of each engine, the individual margin available for the surveillance parameter (Ng, Cm, T 45 );
b1) selecting for the purpose of balancing power delivered by the engines based on a comparison with one another (i) the surveillance parameter amongst the surveillance parameters of the first engine that is the closest to its limit and (ii) the surveillance parameter amongst the surveillance parameters of the second engine that is the closest to its limit, wherein the selected surveillance parameters are of different types from one another as the selected surveillance parameter of the first engine is of the first type and the selected surveillance parameter of the second engine is of the second type different than the first type;
b2) determining a first limiting margin for the first engine, the first limiting margin being equal to the individual margin of the selected surveillance parameter of the first engine, and determining a second limiting margin for the second engine, the second limiting margin being equal to the individual margin of the selected surveillance parameter of the second engine;
c) transforming the first and second limiting margins into first and second power margins, reducing the first and second limiting margins to a scale comparable to the power developed by the engines;
d) comparing the values of the first and second power margins whereby the selected surveillance parameters of the engines are compared with one another and then determining a primary difference between the first and second power margins; and
e) at least one of (i) accelerating the engine having the greater power margin and (ii) decelerating the engine having the smaller power margin in order to bring the first and second engines into power balance, minimizing the primary difference between the first and second power margins to as great an extent as possible;
wherein for a surveillance parameter being the speed of rotation (Ng) of a gas generator of each of the engines, during step d), a first secondary difference is monitored between a first speed of rotation of the gas generator of the first engine and a second speed of rotation of the gas generator of the second engine in order to ensure that the first secondary difference does not exceed a first predetermined threshold.

2. The method according to claim 1 , wherein each individual margin of a surveillance parameter (Ng, Cm, T 45 ) is equal to the individual difference in real time between a current value minus a limit value for the surveillance parameter (Ng, Cm, T 45 ).

3. The method according to claim 2 , wherein the limit value of a surveillance parameter (Ng, Cm, T 45 ) is established while taking account in real time of the outside pressure (P 0 ) and of the outside temperature (T 0 ).

4. A system for metering the supply of fuel to first and second turboshaft engines of an aircraft so that the first and second engines are balanced in power, each engine having a plurality of surveillance parameters (Ng, Cm, T 45 ) each of a different type, the surveillance parameter amongst the surveillance parameters of the first engine that is closest to its limit is of a first type and the surveillance parameter amongst the surveillance parameters of the second engine that is closest to its limit is of a second type different than the first type, the system comprising:
sensors for acquiring the current values of the surveillance parameters (Ng, Cm, T 45 ) of the engines;
regulation means for activating a fuel metering unit of each of the first and second engines;
processor means that determine an individual margin for each surveillance parameter (Ng, Cm, T 45 ) of each engine, select for the purpose of balancing power delivered by the engines based on a comparison with one another (i) the surveillance parameter amongst the surveillance parameters of the first engine that is the closest to its limit and (ii) the surveillance parameter amongst the surveillance parameters of the second engine that is the closest to its limit, wherein the selected surveillance parameters are of different types from one another as the selected surveillance parameter of the first engine is of the first type and the selected surveillance parameter of the second engine is of the second type different than the first type, and then determine first and second limiting margins respectively for the first and second engines, the first and second limiting margins being equal to the individual margin of the selected surveillance parameter respectively of the first and second engines;
control means that transform the first and second limiting margins into first and second power margins, reducing the first and second limiting margins to a scale comparable to the power developed by the engines; and
the control means activating the regulation means in order to balance the power delivered by the engines by at least one of (i) accelerating the engine having the greater power margin and (ii) decelerating the engine having the smaller power margin;
wherein the control means monitor a first secondary difference between a first speed of rotation of a gas generator of the first engine and a second speed of rotation of a gas generator of the second engine in order to prevent the first secondary difference exceeding a first predetermined threshold.

5. The system according to claim 4 , wherein the control means monitor a second secondary difference between a first torque from the first engine and a second torque from the second engine in order to prevent the second secondary difference exceeding a second predetermined threshold.

6. The system according to claim 4 , wherein the control means and the processor means are integrated in a controlling electronic computer.

7. The system according to claim 6 , wherein for each engine being controlled by a respective controlling electronic computer, each controlling electronic computer includes control means and regulation means for controlling the fuel metering unit of the engine to which it is connected.

8. The system according to claim 4 , wherein the processor means is integrated in a first limitation instrument and the control means is integrated in a controlling electronic computer.

9. A method of balancing power delivered by first and second turboshaft engines, each engine having a plurality of surveillance parameters each of a different type, the method comprising:
determining an individual margin for each surveillance parameter of each engine;
selecting for comparison with one another (i) the surveillance parameter amongst the surveillance parameters of the first engine that is the closest to its limit and (ii) the surveillance parameter amongst the surveillance parameters of the second engine that is the closest to its limit;
determining a first limiting margin for the first engine, the first limiting margin being the individual margin of the selected surveillance parameter of the first engine, and determining a second limiting margin for the second engine, the second limiting margin being the individual margin of the selected surveillance parameter of the second engine;
transforming the first an

Assignees

• Gaulmin François-Xavier
• Iraudo Lionel
• Chaniot Daniel
• Airbus Helicopters

Inventors

• Gaulmin François-Xavier
• Iraudo Lionel
• Chaniot Daniel

Classifications

• F02C9/42

  specially adapted for the control of two or more plants simultaneously · 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

• B64D31/12 Primary

  for equalising or synchronising power plants · CPC title