Aircraft propulsion system

Patent metadata

Field	Value
Publication number	US-11795834-B2
Application number	US-202217683388-A
Country	US
Kind code	B2
Filing date	Mar 1, 2022
Priority date	Mar 9, 2021
Publication date	Oct 24, 2023
Grant date	Oct 24, 2023

Abstract

An aircraft propulsion system includes a gas turbine engine; a generator; a storage battery; a motor which drives a rotor, using at least one of the electric power which is output from the generator and the electric power which is output from the storage battery; a detection unit which detects the number of revolutions of the engine shaft; an engine control unit which controls at least a fuel flow rate of the gas turbine engine; and a generator control unit which controls the operation of the generator. When the number of revolutions satisfies a predetermined condition, at least the generator control unit executes a control for reducing a sudden change in the number of revolutions.

First claim

What is claimed is:

1. An aircraft propulsion system comprising:
a gas turbine engine mounted on an aircraft;
a generator which is coupled to an engine shaft of the gas turbine engine and generates electricity using rotation of the engine shaft;
a storage battery which stores an electric power generated by the generator;
a motor which drives a rotor, using at least one of the electric power which is output from the generator or the electric power which is output from the storage battery;
a detection unit which detects the revolutions per minute (rpm) of the engine shaft;
an engine controller which controls at least a fuel flow rate of the gas turbine engine; and
a generator controller which controls the operation of the generator,
wherein when the rpm satisfies a predetermined condition, at least the generator controller executes a control to suppress a change in rpm from an initial rpm;
wherein the predetermined condition is that regarding a first threshold value and a second threshold value determined depending on an operating point determined based on the rpm and a torque of the engine shaft, and one of:
a first condition, in which the rpm exceeds the first threshold value; or
a second condition, in which the rpm falls below the second threshold value smaller than the first threshold value, is satisfied;
wherein, when the first condition is satisfied:
the generator controller increases an amount of power generation of the generator as compared with the amount of power generation of the generator before the first condition is satisfied; and
the engine controller reduces the fuel flow rate depending on a rate of change in the rpm of the engine shaft; and
wherein when the second condition is satisfied:
the generator controller reduces the amount of power generation of the generator as compared with the amount of power generation of the generator before the second condition is satisfied.

2. The aircraft propulsion system according to claim 1 , wherein when the first condition is satisfied, the generator controller increases the amount of power generation of the generator to an upper limit value of the amount of power generation, and the engine controller reduces the fuel flow rate to a lower limit value of the flow rate.

3. The aircraft propulsion system according to claim 1 , wherein when the second condition is satisfied, the engine controller increases the fuel flow rate depending on the rate of change in the rpm.

4. The aircraft propulsion system according to claim 1 , wherein when the second condition is satisfied, the generator controller increases an amount of power running of the generator, and the engine controller increases the fuel flow rate to an upper limit value of the flow rate.

5. The aircraft propulsion system according to claim 1 , wherein when the second condition is satisfied and the rpm does not reach a target value within a predetermined time, the generator controller increases an amount of power running of the generator.

6. The aircraft propulsion system according to claim 1 , wherein regarding a third threshold value and a fourth threshold value defined according to the operating point, when one of a third condition, in which the torque exceeds the third threshold value, and
a fourth condition, in which the torque falls below the fourth threshold value smaller than the third threshold value, is satisfied, the generator controller executes a control to suppress a change in the torque from an initial torque.

7. An aircraft propulsion system comprising:
a gas turbine engine mounted on an aircraft;
a generator which is coupled to an engine shaft of the gas turbine engine and generates electricity using rotation of the engine shaft;
a storage battery which stores an electric power generated by the generator;
a motor which drives a rotor, using at least one of the electric power which is output from the generator or the electric power which is output from the storage battery;
a detection unit which detects a torque of the engine shaft;
an engine controller which controls at least a fuel flow rate of the gas turbine engine; and
a generator controller which controls the operation of the generator,
wherein when the rate of change in the torque satisfies a predetermined condition, at least the generator controller executes a control to suppress a change in the torque from an initial torque,
wherein the predetermined condition is that regarding a first threshold value and a second threshold value determined depending on an operating point determined based on a rpm and the torque of the engine shaft, and one of:
a first condition, in which the torque exceeds the first threshold value; or
a second condition, in which the torque falls below the second threshold value smaller than the first threshold value, is satisfied;

wherein, when the first condition is satisfied:
the generator controller increases an amount of power generation of the generator as compared with the amount of power generation of the generator before the first condition is satisfied; and
the engine controller reduces the fuel flow rate depending on a rate of change in the torque of the engine shaft; and

wherein when the second condition is satisfied:
the generator controller reduces the amount of power generation of the generator as compared with the amount of power generation of the generator before the second condition is satisfied.

Assignees

• Honda Motor Co Ltd

Inventors

• Matsumoto Takeshi
• Kita Akinori

Classifications

• B64D35/022

  of hybrid-electric type · CPC title

• B64D31/18

  for hybrid-electric power plants · CPC title

• B64D27/357

  using batteries · CPC title

• B64D27/33

  Hybrid electric aircraft · CPC title

• F01D15/10 Primary

  Adaptations for driving, or combinations with, electric generators · CPC title