Assessment of conservatism level in an aircraft turbine engine design
AssigneeThe United States of America as represented by the Administrator of the National Aeronautics and Space Administration
InventorsJeffrey T. Csank, Sanjay Garg
Life of this patent
Estimating the term…
Abstract
A system and method of analyzing an engine model is disclosed. The system and method include performing a Dynamic Systems Analysis on the engine model that includes modifying a transient allowance of the engine model to determine an optimal balance between performance and operability and assessing the conservatism level of the engine model.
Claims18
A computer implemented method of analyzing aircraft engine performance comprising:
- designing an initial engine model with a specified surge margin allowance;
- designing a controller for the initial engine model;
- modifying a high pressure compressor requirement of the initial engine model by modifying the surge margin allowance;
- designing a transient allowance limiter comprising an acceleration limiter to restrict fluid flow during acceleration;
- creating a modified engine model;
- testing a controller of the modified engine model using the modified surge margin allowance to determine changes to the performance and/or operability of the modified engine model from the initial engine model;
- running a simulation by varying engine life to determine how performance varies throughout both the engine life cycle and with varying acceleration limit;
- determining if a designer defined number of modifications is satisfied;
- and
- repeating the method beginning at modifying a high pressure compressor requirement of the initial engine model if the designer defined number of modifications is not satisfied.
A computing system for analyzing an aircraft engine model to improve performance and operability comprising:
- a processor that executes the following computer executable components stored in a memory;
- a first design component that allows a designer to create an initial engine model with a specified surge margin allowance;
- a first modification component that modifies a high pressure compressor requirement of the initial engine model by modifying the surge margin allowance;
- a second modification component that designs a transient allowance limiter of the initial engine model comprising an acceleration limiter to restrict fluid flow during acceleration;
- a second design component that creates a modified engine model based on the results of the first modification component and the second modification component;
- a testing component that allows the designer to test a controller of the modified engine model;
- an analysis component that analyzes the results and determines if the results meet performance and/or operability requirements;
- and
- a third modification component that modifies the initial engine model if the analysis component determines that the results are unacceptable.
A non-transitory computer-readable storage device storing executable instructions that, in response to execution, cause a computing system comprising a processor to perform operations comprising:
- analyzing an aircraft engine model to improve a performance and operability of the engine model comprising:
- designing an initial engine model with a specified surge margin allowance;
- reducing the surge margin allowance of the initial engine model;
- designing a transient allowance limiter comprising an acceleration limiter to restrict fluid flow during acceleration;
- creating a modified engine model;
- testing a controller of the modified engine model to determine if the reduction in the surge margin allowance provides an optimum balance between performance and/or operability of the modified engine model;
- running a simulation by varying engine life and observing the impact over the anticipated engine life;
- determining if a designer defined number of modifications is satisfied;
- and
- repeating beginning at reducing the surge margin allowance of the initial engine model if the designer defined number of modifications is not satisfied.
Dependencies are inferred from the claim text.