Fast engine re-start for multi-engine system and method

Patent metadata

Field	Value
Publication number	US-11859554-B2
Application number	US-202117388308-A
Country	US
Kind code	B2
Filing date	Jul 29, 2021
Priority date	Jul 29, 2021
Publication date	Jan 2, 2024
Grant date	Jan 2, 2024

Abstract

A method of operating a multi-engine system of an aircraft having first and second engines includes accumulating compressed air in a pressure vessel external to the engines, and operating the first and second engines asymmetrically, by controlling the first engine to operate in an active operating condition providing sufficient power and/or rotor speed for demands of the aircraft, and controlling the second engine to operate in a standby operating condition wherein the second engine produces less power output than the first engine. In response to a power demand request, the second engine is accelerated out of the standby operating condition by introducing therein compressed air from the pressure vessel at a location upstream of a combustor of the second engine.

First claim

The invention claimed is:

1. A method of operating a multi-engine system of an aircraft having a first engine and a second engine, the method comprising:
accumulating compressed air in a pressure vessel external to the first and second engines;
when the aircraft is in flight at an altitude above the ground, operating the first and second engines asymmetrically, by controlling the first engine to operate in an active operating condition providing sufficient power and/or rotor speed for demands of the aircraft, and controlling the second engine to operate in a standby operating condition wherein the second engine produces less power output than the first engine; and
in response to a power demand request, and when the aircraft is in flight at an altitude above the ground, accelerating the second engine by: introducing the compressed air from the pressure vessel into the second engine at a location upstream of a combustor of the second engine; and, prior to the introducing of the compressed air from the pressure vessel into the second engine at said location upstream of the combustor, blocking a main gas path of the second engine upstream of said location to prevent back-flow of the compressed air through the main gas path.

2. The method of claim 1 , wherein the accumulating includes extracting bleed air from one or more of the first engine and the second engine, and feeding the bleed air into the pressure vessel.

3. The method of claim 2 , wherein the extracting the bleed air includes extracting the bleed air from one or more of a high pressure compressor of the first engine and a high pressure compressor of the second engine.

4. The method of claim 2 , wherein the extracting includes extracting the bleed air from the second engine prior to the second engine being controlled to produce less power output than the first engine.

5. The method of claim 2 , wherein the accumulating includes gradually extracting the bleed air from the one or more of the first and second engines from a beginning of a flight mission, after the one or more of the first and second engines is started or after the aircraft has taken-off.

6. The method of claim 2 , wherein the accumulating includes using one or more valves to control the extracting of the bleed air.

7. The method of claim 1 , wherein the introducing the compressed air from the pressure vessel includes injecting the compressed air into the second engine upstream of a high pressure compressor of the second engine, to rapidly spin a high pressure spool of the second engine having the high pressure compressor.

8. The method of claim 1 , wherein the controlling the second engine to operate in the standby operating condition includes operating the second engine to provide minimal or no propulsive power to the aircraft.

9. The method of claim 1 , wherein the second engine is shut down in the standby operating condition, and the accelerating the second engine includes accelerating the second engine from shut down to an active operating condition corresponding to that of the first engine.

10. The method of claim 1 , wherein operating the second engine in the standby operating condition comprises, in flight, operating the second engine to produce substantially no motive power to the aircraft.

11. A method of operating a multi-engine system of an aircraft having a first engine and a second engine, the method comprising:
accumulating compressed air in a pressure vessel external to the first and second engines, including extracting additional bleed air from the first engine after the second engine has been controlled to produce less power output than the first engine;
when the aircraft is in flight at an altitude above the ground, operating the first and second engines asymmetrically, by controlling the first engine to operate in an active operating condition providing sufficient power and/or rotor speed for demands of the aircraft, and controlling the second engine to operate in a standby operating condition wherein the second engine produces less power output than the first engine; and
in response to a power demand request, and when the aircraft is in flight at an altitude above the ground, accelerating the second engine by: introducing the compressed air from the pressure vessel into the second engine at a location upstream of a combustor of the second engine.

12. A method of operating a multi-engine system of an aircraft having a first engine and a second engine, the method comprising:
accumulating compressed air in a pressure vessel external to the first and second engines, including extracting bleed air from one or more of the first engine and the second engine and feeding the bleed air into the pressure vessel, wherein both the extracting bleed air to accumulate the compressed air in the pressure vessel and the introducing the compressed air into the second engine is carried out via one or more common ports in the second engine;
when the aircraft is in flight at an altitude above the ground, operating the first and second engines asymmetrically, by controlling the first engine to operate in an active operating condition providing sufficient power and/or rotor speed for demands of the aircraft, and controlling the second engine to operate in a standby operating condition wherein the second engine produces less power output than the first engine; and
in response to a power demand request, and when the aircraft is in flight at an altitude above the ground, accelerating the second engine by: introducing the compressed air from the pressure vessel into the second engine at a location upstream of a combustor of the second engine.

13. A multi-engine system for an aircraft comprising:
a first engine and a second engine driving a common gearbox configured to drive a load, the first engine and the second engine respectively including a first compressor and a second compressor;
a pressure vessel external to the first engine and the second engine, the pressure vessel in fluid flow communication with one or both of the first and second compressors via: an accumulation flow path along which compressed air produced by one or both of the first and second compressors flows to reach the pressure vessel; and an injection flow path along which compressed air accumulated within the pressure vessel flows to reach an injection port in at least the second engine;
a valve in fluid communication with the accumulation flow path and the injection flow path, the valve being operable to move between a closed position and an open position, wherein in the open position the compressed air is permitted to flow either along the accumulation flow path or along the injection flow path;
a flow blocking system disposed in at least the second engine upstream of the injection port, the flow blocking system being configured to block a main gas path upstream of the injection port to prevent back-flow of the compressed air through the main gas path when the compressed air flows through the injection point into the second engine; and
an engine controller configured to control the first engine to operate in an active operating condition and to control the second engine to operate in a standby operating condition, wherein in the active operating condition the first engine provides sufficient power and/or rotor speed for demands for the aircraft, and in the standby operating condition the second engine provides provide minimal or no propulsive power to the aircraft, wherein the engine controller is in communication with the valve to control operation thereof, the engine controller operable to position the valve at one or more intermediate positions between the closed position and

Assignees

• Pratt & Whitney Canada

Inventors

• Coutu Daniel
• Beauchesne-Martel Philippe

Classifications

• F02C7/26 Primary

  Starting; Ignition · CPC title

• F02C6/206 Primary

  the vehicles being airscrew driven · CPC title

• B64D31/00

  Power plant control systems; Arrangement of power plant control systems in aircraft · CPC title

• F02C6/20

  Adaptations of gas-turbine plants for driving vehicles · CPC title

• F02C9/18

  by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages {(F02C3/113 takes precedence)} · CPC title