Abstract
Gas turbine performance models typically rely on component maps to characterize engine component performance throughout the operational regime. For the sub-idle case, the lack of reliable rig test data or inability to run design codes far from design conditions entails that component maps have to be generated from the extrapolation of existing data at higher speeds. This undermines the accuracy of whole-engine sub-idle performance models, at times impacting engine development and certification of aviation engines and the accuracy of start-up performance prediction in industrial gas turbines. One of the main components driving this issue is the core compression system, which can present operability concerns during light-up and which also sets the combustor airflow required for ignition. This paper presents, discusses, and draws on previous approaches to describe a method enabling the creation of sub-idle compressor maps from analytical and physical grounds. The method relies on the calculation of zero-speed and torque-free lines to generate a map down to zero speed along with analytical interpolation. A method for the interpolation process is described. A sensitivity study is carried out to assess the effects that different elements of the map generation process may have on the accuracy of the resulting performance calculation. Overall, a method for the generation of accurate, consistent maps from limited geometry data is identified.
Highlights
Stringent end-user requirements on the relight capabilities of aviation engines mean that designers must be able to accurately predict the engine’s behavior during in-flight relight events.[1]
The drive towards improved efficiency and lower fuel burn means that the design for ground-starts and long taxi periods, operating at low speed, must be taken into account, increasing the need for performance optimization at and below idle
This work presents a method to obtain consistent axial compressor sub-idle maps based on physical arguments and models
Summary
Stringent end-user requirements on the relight capabilities of aviation engines mean that designers must be able to accurately predict the engine’s behavior during in-flight relight events.[1] In addition, the drive towards improved efficiency and lower fuel burn means that the design for ground-starts and long taxi periods, operating at low speed, must be taken into account, increasing the need for performance optimization at and below idle. As opposed to large frame GT and GTCC power plants operating in a base-load capacity, “peaker” units will go through multiple cycles of start-up and shut down, making start-up performance and dispatch times increasingly important. In both aviation and industrial power generation cases, improved sub-idle performance prediction capability is required. It has become possible to generate predicted compressor maps for new compressor designs using
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More From: Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy
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