Auxiliary device system of aircraft engine

Patent metadata

Field	Value
Publication number	US-11384694-B2
Application number	US-201917279138-A
Country	US
Kind code	B2
Filing date	Sep 27, 2019
Priority date	Sep 27, 2018
Publication date	Jul 12, 2022
Grant date	Jul 12, 2022

Abstract

An auxiliary device system includes a motor generator, an auxiliary device motor, a converter configured to convert electric power generated by the motor generator, an inverter configured to drive the motor generator and the auxiliary device motor, a switch configured to be switched between a motor generator control state in which the inverter controls the motor generator and an auxiliary device motor control state in which the inverter controls the auxiliary device motor, and a controller configured to control the switch. When a condition in which a motor generator drive command is generated is satisfied, the controller sets the switch to the motor generator control state. When the condition is not satisfied, the controller sets the switch to the auxiliary device motor control state.

First claim

The invention claimed is:

1. An auxiliary device system of an aircraft engine,
the auxiliary device system comprising:
a motor generator configured to drive an aircraft engine;
at least one auxiliary device motor configured to drive an auxiliary device mounted on the aircraft engine;
a converter configured to convert electric power generated by the motor generator;
at least one inverter provided separately from the converter and configured to drive the motor generator and the auxiliary device motor;
at least one switch configured to be switched between a motor generator control state in which the inverter controls the motor generator and an auxiliary device motor control state in which the inverter controls the auxiliary device motor; and
a controller configured to control the switch, wherein:
when a condition in which a motor generator drive command has been generated is satisfied, the controller sets the switch to the motor generator control state; and
when the condition is not satisfied, the controller sets the switch to the auxiliary device motor control state.

2. The auxiliary device system according to claim 1 , wherein when a rotational frequency of the aircraft engine is less than a predetermined rotational frequency threshold, the controller generates the motor generator drive command.

3. The auxiliary device system according to claim 2 , wherein:
the auxiliary device motor is a pump driving motor configured to drive a fuel supply pump of the aircraft engine; and
the rotational frequency threshold is set to a value larger than a predetermined ignition rotational frequency of the aircraft engine.

4. The auxiliary device system according to claim 2 , wherein:
the auxiliary device motor is a pump driving motor configured to drive a fuel supply pump of the aircraft engine;
the switch is configured to be switched to a simultaneous control state in which the inverter controls both the motor generator and the pump driving motor;
when the rotational frequency of the aircraft engine is less than the rotational frequency threshold, the controller sets the switch to the motor generator control state;
when the rotational frequency of the aircraft engine reaches the rotational frequency threshold, the controller switches the switch from the motor generator control state to the simultaneous control state; and
after a predetermined switching condition is satisfied, the controller switches the switch from the simultaneous control state to the auxiliary device motor control state.

5. The auxiliary device system according to claim 2 , wherein:
the at least one auxiliary device motor comprises first and second pump driving motors configured to respectively drive first and second fuel supply pumps of the aircraft engine;
the at least one inverter comprises first and second inverters configured to respectively drive the first and second pump driving motors;
the at least one switch comprises a first switch interposed between the first inverter and the first pump driving motor and a second switch interposed between the second inverter and the second pump driving motor;
when the rotational frequency of the aircraft engine is less than the rotational frequency threshold, the controller sets the first and second switches to the motor generator control state;
when the rotational frequency of the aircraft engine reaches the rotational frequency threshold, the controller maintains the motor generator control state of the second switch and switches the first switch from the motor generator control state to the auxiliary device motor control state; and
after a predetermined switching condition is satisfied, the controller maintains the auxiliary device motor control state of the first switch and switches the second switch from the motor generator control state to the auxiliary device motor control state.

6. The auxiliary device system according to claim 5 , wherein the switching condition is a condition in which the rotational frequency of the aircraft engine has reached a predetermined self-sustaining rotation threshold.

7. The auxiliary device system according to claim 2 , wherein the controller generates the motor generator drive command in a period from when the aircraft engine is in a stop state until when the rotational frequency of the aircraft engine reaches the rotational frequency threshold.

Assignees

• Kawasaki Heavy Ind Ltd

Inventors

• Shibayama Yoshiyasu
• Okuwa Tatsuya
• Yuda Yoshiaki

Classifications

• F05D2270/304

  Spool rotational speed · CPC title

• F02C7/32 Primary

  Arrangement, mounting, or driving, of auxiliaries · CPC title

• F02C7/275 Primary

  Mechanical drives · CPC title

• F05D2270/06

  to match engine to driven device · CPC title

• B64D41/00

  Power installations for auxiliary purposes · CPC title