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AGTF30-e

NOTE: More details are provided in the User Guide found in the "Documentation" folder

The Advanced Geared Turbofan 30,000lbf - electrified (AGTF30-e) is an electrified geared turbofan that leverages the previously developed Advanced Geared Turbofan 30,000lbf (AGTF30) model. The AGTF30-e introduces a variety of electrification options. It has three primary modes of operation:

  1. standard/conventional engine (like the original AGTF30)
  2. boost capable engine - thrust augmentation with electric power on the fan
    • mimics a parallel hybrid architecture
  3. power extraction - significant power is extracted from the engine shafts for the purpose of producing thrust elsewhere on the airframe - mimics a partial turboelectric architecture There are also several secondary electrification options that can be implemented in combination with each other and the primary electrification options. These include:
  4. low engine power electric power transfer (EPT) - power transfer between the engine shafts at low engine power with the purpose of extending the operating range to lower thrust and fuel burn.
  5. Turbine Electrified Energy Management (TEEM) - use of the electrical power system during transients to improve transient operability, particularly with the compressors, and to enable better performing turbomachinery.
  6. Charging - use of additional power extraction during the mission to charge energy storage devices that have been discharged. The AGTF30-e also considers how the electric power system is integrated with the engine shafts. It offers two options.
  7. Dedicated electric machine (DEM) approach - one or more electric machines are integrated directly or through a gearbox to an engine shaft. Each electric machine can only influence a single engine shaft.
  8. Versatile Electrically Augmented Turbine Engine (VEATE) Planetary Gearbox (PGB) approach - the electric machines are integrated with the engine through a planetary gearbox that creates a coupling effect of the engine shafts through electric machine use. This approach has some potential benefits that could be explored with the model.

Like the AGTF30, the AGTF30-e utilizes the Toolbox for the Modeling and Analysis of Thermodynamic Systems (T-MATS) to create a steady-state and dynamic engine model within MATLAB/Simulink. The engine model is based upon a futuristic geared turbofan concept and allows steady-state operation throughout the flight envelope. Dynamic operation utilizes a baseline control that is versatile enough to enable all of the features listed above and to enable various other model changes without significant controller updates.

AGTF30-e preparation for use:

  1. Install Matlab and Simulink. Developed in MATLAB 2023b (AGTF30 developed in 2015aSP1).
  2. A copy of T-MATS is packaged with the AGTF30-e. No installation should be necessary. However, if one wishes to attempt to use the AGTF30-e with a different version of T-MATS one can download and install T-MATS (https://github.com/nasa/T-MATS/releases). It should be noted that the AGTF30-e has not been tested with all versions of T-MATS and is not guaranteed to be compatible with any installation other than the T-MATS files that come with the AGTF30-e download.

Running AGTF30-e simulation:

  1. Navigate to the AGTF30e folder
  2. Open the script "run_AGTF30e_script.m". This file provides a template for writing code to run the AGTF30-e.
  3. Run script. This should update the workspace with test scenario inputs, open the model, run the model, and plot some of the results.

Changing run conditions:

  1. Open the "AGTF30e_Inputs.xlsx" file within the "SimSetup" folder and modify the inputs
  2. Run the Setup_Simulation command (example in run_AGTF30e_script.m) to initialize the workspace. Make sure that the "inputMethod" variable is set to 2 and the "filename" entry is 'AGTF30e_Inputs.xlsx'. Also make sure that the spreadsheet with the data you wish to use as inputs is the first spreadsheet in the file.
  3. Run the simulation.

or

if and input structure that matches the structure of MWS.In already exists in the workspace you can

  1. Modify the input structure (Example: change the altitude from MWS.In.Alt = [0 0] to MWS.In.Alt = [35000 35000] to specify an altitude change from 0ft to 35,000ft. In this example the corresponding time vector MWS.In.t_Alt is a two-element vector, lets say MWS.In.t_Alt = [0 10] and the altitude is constant for the duration of the simulation)
  2. Run the Setup_Simulation command (example in run_AGTF30e_script.m) to initialize the workspace. Make sure that the "inputMethod" variable is set to 1 and the entry for the "In" input is the input structure you wish to use.
  3. Run the simulation.

Several system inputs are defined (within the MWS structure) as vectors with each value matching with a time vector. The linearization and steady-state systems will only make use of the initial values.

Outputs:

  1. Steady state simulation output structure: Out_SS, containing a large amount of data. This structure contains engine and solver data.
  2. Linearization simulation output structure: Out_Lin, containing a large amount of data. It contains all engine and solver data. Out_xdot and Out_y0 structures consolidates info for state derivatives and outputs.
  3. Dynamic simulation output structure: out_Dyn, containing a large amount of data. Additionally, it generate specific structures out_*

REFER TO THE USER GUIDE (FOUND IN THE DOCUMENTATION FOLDER) FOR MORE DETAILS

References:

  1. Jeffryes W. Chapman and Jonathan S. Litt. "Control Design for an Advanced Geared Turbofan Engine", 53rd AIAA/SAE/ASEE Joint Propulsion Conference, AIAA Propulsion and Energy Forum, (AIAA 2017-4820)
  2. Jones, S.M., Haller, W.J., Tong, M.T., “An N+3 Technology Level Reference Propulsion System”, NASA/TM-2017-219501, 2017.
  3. Kratz, J.L., "Advanced Geared Turbofan 30,000lbf - Electrified Engine Model User Guide", AGTF30-e software release documentation, 2023.
  4. Kratz, J.L., "The Advanced Geared Turbofan 30,000 lbf – electrified (AGTF30-e): A Virtual Testbed for Electrified Aircraft Propulsion Research", AIAA Aviation Forum, 2024. (Publication Pending).