Method and system for setting fuel flow for engine start as a function of aircraft speed

Patent metadata

Field	Value
Publication number	US-10801416-B2
Application number	US-201715585847-A
Country	US
Kind code	B2
Filing date	May 3, 2017
Priority date	May 3, 2017
Publication date	Oct 13, 2020
Grant date	Oct 13, 2020

Abstract

Herein provided are methods and systems for setting a fuel flow schedule for starting a gas turbine engine of an aircraft. Aircraft speed and engine rotational speed are obtained. A compressor inlet recovered pressure is estimated by combining a first component influenced by the aircraft speed and a second component influenced by the engine rotational speed, and a fuel flow schedule is selected for engine start in accordance with the estimated compressor inlet recovered pressure.

First claim

The invention claimed is:

1. A method for setting a fuel flow schedule for starting a gas turbine engine of an aircraft, the method comprising:
obtaining an aircraft speed and an engine rotational speed;
estimating a pressure at an entrance of a compressor of the gas turbine engine by combining a first component on which the aircraft speed has an effect and a second component on which the engine rotational speed has an effect; and
applying a fuel flow bias associated with the pressure as estimated to a fuel flow schedule for engine start, wherein a change in pressure as estimated results in a change of the fuel flow bias.

2. The method of claim 1 , wherein estimating the pressure at the entrance of the compressor comprises using characterization data of losses at the entrance of the compressor of the engine due to the aircraft speed and due to the engine rotational speed.

3. The method of claim 2 , wherein estimating the pressure comprises converting the aircraft speed into a Mach number and plotting Mach number versus a ratio of the pressure at the entrance of the compressor of the engine and an isentropic total air pressure to obtain the first component.

4. The method of claim 3 , wherein estimating the pressure comprises using a curve plotting a normalized engine rotational speed versus the ratio of the pressure over the isentropic total air pressure to obtain the second component.

5. The method of claim 4 , wherein the first component corresponds to a first value for the ratio and the second component corresponds to a second value for the ratio, wherein the first value and the second value are multiplied together, and wherein a result of the multiplication is multiplied by the isentropic total air pressure to obtain the pressure as estimated.

6. The method of claim 1 , further comprising applying the fuel flow schedule during an open loop step of engine start.

7. The method of claim 6 , further comprising setting the fuel flow schedule with the fuel flow bias applied as a minimum fuel flow limit during a closed loop step of engine start.

8. A system for setting a fuel flow schedule for starting a gas turbine engine of an aircraft, the system comprising:
a processing unit; and
a non-transitory computer-readable memory having stored thereon program instructions executable by the processing unit for:
obtaining an aircraft speed and an engine rotational speed;
estimating a pressure at an entrance of a compressor of the gas turbine engine by combining a first component on which the aircraft speed has an effect and a second component on which the engine rotational speed has an effect; and
applying a fuel flow bias associated with the pressure as estimated to a fuel flow schedule for engine start, wherein a change in pressure as estimated results in a change of the fuel flow bias.

9. The system of claim 8 , wherein estimating the pressure at the entrance of the compressor comprises using characterization data of losses at the entrance of the compressor of the engine due to the aircraft speed and due to the engine rotational speed.

10. The system of claim 9 , wherein estimating the pressure comprises converting the aircraft speed into a Mach number and plotting Mach number versus a ratio of the pressure at the entrance of the compressor of the engine and an isentropic total air pressure to obtain the first component.

11. The system of claim 10 , wherein estimating the pressure comprises using a curve plotting a normalized engine rotational speed versus the ratio of the pressure over the isentropic total air pressure to obtain the second component.

12. The system of claim 11 , wherein the first component corresponds to a first value for the ratio and the second component corresponds to a second value for the ratio, wherein the first value and the second value are multiplied together, and wherein a result of the multiplication is multiplied by the isentropic total air pressure to obtain the pressure as estimated.

13. The system of claim 8 , wherein the program instructions are further executable for applying the fuel flow schedule during an open loop step of engine start.

14. The system of claim 8 , wherein the program instructions are further executable for setting the fuel flow schedule with the fuel flow bias applied as a minimum fuel flow limit during a closed loop step of engine start.

15. A computer readable medium having stored thereon program code executable by a processor for setting a fuel flow schedule for starting a gas turbine engine of an aircraft, the program code comprising instructions for:
obtaining an aircraft speed and an engine rotational speed;
estimating a pressure at an entrance of a compressor of the gas turbine engine by combining a first component on which the aircraft speed has an effect and a second component on which the engine rotational speed has an effect; and
applying a fuel flow bias associated with the pressure as estimated to a fuel flow schedule for engine start, wherein a change in pressure as estimated results in a change of the fuel flow bias.

16. The computer readable medium of claim 15 , wherein estimating the pressure at the entrance of the compressor comprises using characterization data of losses at the entrance of the compressor of the engine due to the aircraft speed and due to the engine rotational speed.

Assignees

• Pratt & Whitney Canada

Inventors

• Lamarre Sylvain
• Hebert Jeremie
• Alexandre Pierre

Classifications

• B64D31/06

  actuated automatically · CPC title

• F05D2270/3011

  Inlet pressure · CPC title

• F05D2260/85

  Starting · CPC title

• F02C9/28 Primary

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

• F02C9/44

  responsive to the speed of aircraft, e.g. Mach number control, optimisation of fuel consumption · CPC title