Performance Calculations of Gas Turbine Engine Components Based on Particular Instrumentation Methods

Răzvan Catană,Horațiu Șerbescu,Cornel Tărăbîc,Gabriel Dediu

doi:10.3390/app11104492

Răzvan Catană, Horațiu Șerbescu + Show 2 more

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https://doi.org/10.3390/app11104492

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Abstract

This paper presents an analytical method to determine various main parameters or performances of engine components when those parameters cannot be directly measured and it is necessary to determine them. Additionally, some variants of instrumentation methods are presented, for example: engine inlet, compressor, turbine or jet nozzle instrumentation. The purpose of the instrumentation methods is to directly measure the possible parameters, which are then used as inputs in a model to determine other parameters or performance metrics. This model is based on gasodynamic process equations, and it is used to compute the air and gas parameters, such as enthalpy and entropy, which are described in polynomial form, thus leading to a more realistic calculation. At the end, this paper presents a practical example of instrumentation applied on a Klimov TV2-117A turboshaft, with a series of experimental results, following the engine testing on the test bench.

Highlights

Turbine Engine Components BasedGenerally, most of the gas turbine engines that are in service, or are going to enter into service, have a standard minimal instrumentation [1,2], through which the engine can be monitored
In many cases, when the engine is ready to enter into service, due to intellectual property reasons, the engine manufacturer does not equip the engine with all the instrumentation ports [5] as it was equipped in the testing phase
This paper presents an applied method of instrumentation and applied calculation methods to determine specific engine main parameters or performances of the engine components, such as the compressor, turbine and jet nozzle

Summary

Introduction

Turbine Engine Components BasedGenerally, most of the gas turbine engines that are in service, or are going to enter into service, have a standard minimal instrumentation [1,2], through which the engine can be monitored. There are various situations when, technically, it is not possible to measure the diverse main parameters or engine performance directly [7], which applies to the mass air flow, the overall pressure ratio, the compressor and turbine efficiency or the engine power and thrust. These main parameters can be indirectly determined by models (algorithms) that use different measured parameters

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