Ground-based aircraft movement

Patent metadata

Field	Value
Publication number	US-12258139-B2
Application number	US-202318152920-A
Country	US
Kind code	B2
Filing date	Jan 11, 2023
Priority date	Jan 13, 2022
Publication date	Mar 25, 2025
Grant date	Mar 25, 2025

Abstract

An engine system for an aircraft includes a gas turbine engine and a control system. The control system is configured to motor the gas turbine engine, absent fuel burn, during a taxi mode of the aircraft. The control system is further configured to accelerate a motoring speed of the gas turbine engine, absent fuel burn, above an idle speed of the gas turbine engine to provide propulsion during the taxi mode. The control system is configured to decrease the motoring speed of the gas turbine engine, absent fuel burn, based on a change in a starting mode of the gas turbine engine or the aircraft reaching a targeted new position.

First claim

What is claimed is:

1. An engine system for an aircraft, the engine system comprising:
a gas turbine engine;
a control system configured to:
motor the gas turbine engine, absent fuel burn, during a taxi mode of the aircraft;
accelerate a motoring speed of the gas turbine engine, absent fuel burn, above an idle speed of the gas turbine engine to provide propulsion during the taxi mode; and
decrease the motoring speed of the gas turbine engine, absent fuel burn, based on a change in a starting mode of the gas turbine engine or the aircraft reaching a targeted new position, wherein the motoring speed is driven by a motoring source comprising one or more of: an electric motor, a pneumatic drive, and a hydraulic drive powered by one or more of: an auxiliary power unit, a battery system, an electric generator, a hydraulic source, and a pneumatic source, and selection of the motoring source used to accelerate the gas turbine engine above the idle speed, absent fuel burn, changes between two or more taxiing events, wherein the idle speed comprises a lowest speed at which the gas turbine engine is operable with fuel burn when the aircraft is on ground.

2. The engine system of claim 1 , wherein the control system is further configured to:
initiate an engine start sequence of the gas turbine engine based on detecting an auto-start mode selection as the change in the starting mode.

3. The engine system of claim 2 , wherein the control system is further configured to:
control a starter, fuel flow, and ignitors of the gas turbine engine to start fuel combustion during the taxi mode based on detecting the auto-start mode selection.

4. The engine system of claim 1 , wherein the control system is further configured to power one or more electric actuators to drive the motoring speed and depower the one or more electric actuators after reaching the targeted new position.

5. The engine system of claim 1 , wherein the control system is further configured to decrease the motoring speed of the gas turbine engine to the idle speed or a below idle speed after reaching the targeted new position.

6. The engine system of claim 1 , wherein the decrease of the motoring speed of the gas turbine engine is performed by a reduction in pressure delivered to a starter of the gas turbine engine.

7. The engine system of claim 1 , wherein the motoring speed is reached based on controlling a starter to dry motor the gas turbine engine, wherein the starter is coupled to a high speed spool of the gas turbine engine, and the starter is controlled based on a speed of a low speed spool of the gas turbine engine and/or a taxi speed of the aircraft.

8. The engine system of claim 1 , wherein the motoring speed is reached based on controlling the electric motor.

9. The engine system of claim 1 , wherein the motoring speed is reached based on controlling a starter and the electric motor.

10. The engine system of claim 1 , wherein the gas turbine engine is a first gas turbine engine and further comprising a second gas turbine engine, wherein a starter provides a first motoring speed of the first gas turbine engine and a second electric motor provides a second motoring speed of the second gas turbine engine during the taxi mode.

11. A method of engine system control of an aircraft, the method comprising:
motoring a gas turbine engine, absent fuel burn, during a taxi mode of the aircraft;
accelerating a motoring speed of the gas turbine engine, absent fuel burn, above an idle speed of the gas turbine engine to provide propulsion during the taxi mode; and
decreasing the motoring speed of the gas turbine engine, absent fuel burn, based on a change in a starting mode of the gas turbine engine or the aircraft reaching a targeted new position, wherein the motoring speed is driven by a motoring source comprising one or more of: an electric motor, a pneumatic drive, and a hydraulic drive powered by one or more of: an auxiliary power unit, a battery system, an electric generator, a hydraulic source, and a pneumatic source, and selection of the motoring source used to accelerate the gas turbine engine above the idle speed, absent fuel burn, changes between two or more taxiing events, wherein the idle speed comprises a lowest speed at which the gas turbine engine is operable with fuel burn when the aircraft is on ground.

12. The method of claim 11 , further comprising:
initiating an engine start sequence of the gas turbine engine based on detecting an auto-start mode selection as the change in the starting mode.

13. The method of claim 12 , further comprising:
controlling a starter, fuel flow, and ignitors of the gas turbine engine to start fuel combustion during the taxi mode based on detecting the auto-start mode selection.

14. The method of claim 11 , further comprising:
powering one or more electric actuators to drive the motoring speed; and
depowering the one or more electric actuators after reaching the targeted new position.

15. The method of claim 11 , wherein the motoring speed of the gas turbine engine is decreased to the idle speed or a below idle speed after reaching the targeted new position.

16. The method of claim 11 , wherein the decrease of the motoring speed of the gas turbine engine is performed by a reduction in pressure delivered to a starter of the gas turbine engine.

17. The method of claim 11 , wherein the motoring speed is reached based on controlling a starter to dry motor the gas turbine engine, wherein the starter is coupled to a high speed spool of the gas turbine engine, and the starter is controlled based on a speed of a low speed spool of the gas turbine engine and/or a taxi speed of the aircraft.

18. The method of claim 11 , wherein the gas turbine engine is a first gas turbine engine and a starter provides a first motoring speed of the first gas turbine engine, and a second electric motor provides a second motoring speed of a second gas turbine engine of the aircraft during the taxi mode.

Assignees

• Rtx Corp

Inventors

• Witalis Stephen A
• Rajagopalan Ramesh
• Dhingra Manuj

Classifications

• B64D27/355

  using fuel cells · CPC title

• B64D31/18

  for hybrid-electric power plants · CPC title

• B64D27/33

  Hybrid electric aircraft · CPC title

• B64D31/06 Primary

  actuated automatically · CPC title

• F02C7/26 Primary

  Starting; Ignition · CPC title