Model and method for modeling operation of an aircraft hybrid electric propulsion system

Patent metadata

Field	Value
Publication number	US-2026011187-A1
Application number	US-202418763875-A
Country	US
Kind code	A1
Filing date	Jul 3, 2024
Priority date	Jul 3, 2024
Publication date	Jan 8, 2026
Grant date	—

Abstract

A method of modeling the operation of a HEP system for an aircraft is provided. The HEP system includes a gas turbine engine and an electric motor. The method includes: modeling the operation of a HEP system using an engine model with a plurality of modules. Each module is configured with executable instructions to receive an input operational parameter and produce an output operational parameter. The input operational parameters include one or more of an input pressure, temperature, mass flow, or power, and the output operational parameters include one or more of an output pressure, temperature, mass flow, or power. The modeling includes providing a first output operational parameter from a first module to a second module as a first input operational parameter, and using the second module to produce a second output operational parameter using the first input operational parameter.

First claim

1 . A method of modeling the operation of a hybrid electric propulsion system for an aircraft, the hybrid electric propulsion system including a gas turbine engine and an electric motor, both configured to provide motive power to the aircraft, the gas turbine engine including a compressor section and a turbine section, the method comprising:
modeling the operation of a hybrid electric propulsion system using an engine model that includes a plurality of modules including a compressor module, a turbine module, a gearbox module, an engine air inlet module, an engine exhaust module, an inverter module, and an electric motor module, wherein each respective module of the plurality of modules is configured with executable instructions to receive an input operational parameter and produce an output operational parameter using the input operational parameter; wherein the input operational parameters for the plurality of modules include one or more of an input pressure value, an input temperature value, an input mass flow value, or an input power value, and the output operational parameters for the plurality of modules include one or more of an output pressure value, an output temperature value, an output mass flow value, or an output power value; and wherein the modeling includes providing a first output operational parameter from a first module of the plurality of modules to a second module of the plurality of modules as a first input operational parameter, and using the second module of the plurality of modules to produce a second output operational parameter using the first input operational parameter.

2 . The method of claim 1 , wherein the executable instructions for at least one respective module of the plurality of modules comprises a mathematical expression.

3 . The method of claim 2 , wherein the executable instructions for the compressor module includes a compressor performance map.

4 . The method of claim 2 , wherein the executable instructions for the turbine module includes a turbine performance map.

5 . The method of claim 1 , further comprising using the engine model to analyze an engine controller.

6 . The method of claim 5 , wherein the engine controller is an actual engine controller and the analysis is a hardware-in-the-loop analysis.

7 . The method of claim 5 , wherein the engine controller is a digital model of an engine controller and the analysis is a software-in-the-loop analysis.

8 . The method of claim 1 , further comprising using the engine model to analyze an engine controller, and the analysis is performed using a boundary condition; and
wherein the hybrid electric propulsion system is configured to drive a propulsion unit and the boundary condition is a power requirement for driving the propulsion unit, wherein the power requirement is satisfied by a combination of a first portion of the power requirement provided by the gas turbine engine and a second portion of the power requirement provided by the electric motor, and the modeling includes varying the relative amounts of the first portion and the second portion.

9 . The method of claim 1 , wherein the engine model is configured to simulate the hybrid electric propulsion system operating in a steady-state mode.

10 . The method of claim 9 , wherein in the steady state mode the engine model provides a power requirement for driving a propulsion unit, wherein the power requirement is satisfied by a combination of a first portion of the power requirement provided by the gas turbine engine and a second portion of the power requirement provided by the electric motor, and the modeling includes varying the relative amounts of the first portion and the second portion.

11 . The method of claim 9 , wherein in the steady state mode the engine model provides a power requirement for driving a propulsion unit, wherein the power requirement is satisfied by a combination of a first portion of the power requirement provided by the gas turbine engine and a second portion of the power requirement provided by the electric motor, and the power requirement is held constant; and
wherein the first module of the plurality of modules is the compressor module and the second module is the turbine module, and the first output operational parameter is a first pressure value and the second output operational parameter is a second pressure value.

12 . The method of claim 1 , wherein the engine model is configured to simulate the hybrid electric propulsion system operating in a transient mode.

13 . The method of claim 12 , wherein in the transient mode, the method includes using the engine model to simulate the operation of the hybrid electric propulsion system continuously from a starting state to an idle state, from the idle state to an ascent mode, a cruise mode, and a descent mode.

14 . The method of claim 13 , wherein in the transient mode, the method further includes using the engine model to simulate the operation of the hybrid electric propulsion system from the descent mode to a landing mode to a shutdown mode.

15 . A non-transitory computer-readable medium containing computer program instructions, wherein the computer program instructions are executable by a computer processor to perform a method of modeling the operation of a hybrid electric propulsion system for an aircraft, the hybrid electric propulsion system including a gas turbine engine and an electric motor, both configured to provide motive power to the aircraft, the gas turbine engine including a compressor section and a turbine section, the method comprising:
modeling the operation of a hybrid electric propulsion system using an engine model that includes a plurality of modules including a compressor module, a turbine module, a gearbox module, an engine air inlet module, an engine exhaust module, an inverter module, and an electric motor module, wherein each respective module of the plurality of modules is configured with executable instructions to receive an input operational parameter and produce an output operational parameter using the input operational parameter; wherein the input operational parameters for the plurality of modules include one or more of an input pressure value, an input temperature value, an input mass flow value, or an input power value, and the output operational parameters for the plurality of modules include one or more of an output pressure value, an output temperature value, an output mass flow value, or an output power value; and wherein the modeling includes providing a first output operational parameter from a first module of the plurality of modules to a second module of the plurality of modules as a first input operational parameter, and using the second module of the plurality of modules to produce a second output operational parameter using the first input operational parameter.

16 . The non-transitory computer-readable medium containing computer program instructions of claim 15 , wherein the engine model is configured to simulate the hybrid electric propulsion system operating in a steady-state mode.

17 . The non-transitory computer-readable medium containing computer program instructions of claim 15 , wherein the engine model is configured to simulate the hybrid electric propulsion system operating in a transient mode.

18 . The non-transitory computer-readable medium containing computer program instructions of claim 15 , wherein the method includes using the engine model to analyze an engine controller, and the engine controller is an actual engine controller and the analysis is a hardware-in-the-loo

Assignees

• Pratt & Whitney Canada

Inventors

• Lu Xuening
• Thomson Travis
• Plamondon Etienne
• Carrese Gino

Classifications

• G06F30/17

  Mechanical parametric or variational design · CPC title

• G07C5/0808 Primary

  Diagnosing performance data (testing of vehicles G01M17/00; testing of electrical installation on vehicles G01R31/005) · CPC title

• G06F2119/06

  Power analysis or power optimisation · CPC title

• G06F2111/10

  Numerical modelling · CPC title

• G06F30/20

  Design optimisation, verification or simulation (optimisation, verification or simulation of circuit designs G06F30/30) · CPC title