Aero-Thermodynamic Modelling and Gas Path Simulation for a Twin Spool Turbo Jet Engine

2013 ◽  
Author(s):  
Balaji Sankar ◽  
Thennavarajan Subramanian ◽  
Brijeshkumar Shah ◽  
Vijayendranath Vanam ◽  
Soumendu Jana ◽  
...  
Keyword(s):  
Simulation Model ◽  
Gas Turbine ◽  
Simulation Models ◽  
Operating Conditions ◽  
Test Bed ◽  
Jet Engine ◽  
Turbine Engine ◽  
Design Point ◽  
Engine Simulation ◽  
Engine Components

The user community of civil and military aircraft powered by gas turbine engines has a significant interest on simulation models for design, development and maintenance activities. These play a crucial role in understanding the aircraft mission performance. The simulation models can be used to understand the behavior of gas turbine engine running at various operating conditions, which are used for studying the aircraft performance and also vital for engine diagnostics. Other significant advantage of simulation model is that it can generate required data at intermediate stages in gas turbine engine, which sometimes cannot be obtained by measurement. Thus engine simulation model / virtual engine building is one of the important aspects towards development of Engine Health Management (EHM) system. This paper describes in detail the engine simulation model development for a typical twin spool turbo jet engine using commercially available Gas turbine Simulation Program (GSP). The engine simulation model has been used for typical aero-engine to get aero-thermodynamic gas path performance analysis related to engine run at Design point, Off Design points and the engine Acceleration-Deceleration Cycles (ADC). Simulations at different operating conditions have been carried out using scaled up characteristic maps of engine components. Design point data as well as engine gas path data obtained from test bed has been used to develop scaled up characteristic maps of the engine components. The simulation results have been compared with various test bed data sets for the purpose of validation. Predicted results of engine parameters like engine mass flow rate and thrust are in good agreement with the test bed data. This validated model can be used to simulate faulty engine components and to develop the fault identification modules and subsequently an EHM system.

scholarly journals The Formation of High Temperature Minerals From an Evaporite-Rich Dust in Gas Turbine Engine Ingestion Tests

2020 ◽  
Author(s):  
Jacob Elms ◽  
Alison Pawley ◽  
Nicholas Bojdo ◽  
Merren Jones ◽  
Rory Clarkson
Keyword(s):  
High Temperature ◽  
Gas Turbine ◽  
Operating Conditions ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Test Bed ◽  
Turbine Engine ◽  
Mineral Assemblages ◽  
Mineral Dusts ◽  
Engine Components

Abstract The ingestion of multi-mineral dusts by gas turbine engines during routine operations is a significant problem for engine manufacturers because of the damage caused to engine components and their protective thermal barrier coatings. A complete understanding of the reactions forming these deposits is limited by a lack of knowledge of compositions of ingested dusts and unknown engine conditions. Test bed engines can be dosed with dusts of known composition under controlled operating conditions, but past engine tests have used standardised test dusts that do not resemble the composition of the background dust in the operating regions. A new evaporiterich test dust was developed and used in a full engine ingestion test, designed to simulate operation in regions with evaporiterich geology, such as Doha or Dubai. Analysis of the engine deposits showed that mineral fractionation was present in the cooler, upstream sections of the engine. In the hotter, downstream sections, deposits contained new, high temperature phases formed by reaction of minerals in the test dust. The mineral assemblages in these deposits are similar to those found from previous analysis of service returns. Segregation of anhydrite from other high temperature phases in a deposit sample taken from a High Pressure Turbine blade suggests a relationship between temperature and sulfur content. This study highlights the potential for manipulating deposit chemistry to mitigate the damage caused in the downstream sections of gas turbine engines. The results of this study also suggest that the concentration of ingested dust in the inlet air may not be a significant contributing factor to deposit chemistry.

An Integrated Approach for Gas Turbine Engine Simulation

2000 ◽  
Author(s):  
Zhiwu Xie ◽  
Ming Su ◽  
Shilie Weng
Keyword(s):  
Gas Turbine ◽  
Local Area Network ◽  
Integrated Approach ◽  
Local Area ◽  
Gas Turbine Engine ◽  
Future Research ◽  
Area Network ◽  
Turbine Engine ◽  
Engine Simulation ◽  
Engine Components

Abstract The static and transient performance of a gas turbine engine is determined by both the characteristics of the engine components and their interactions. This paper presents a generalized simulation framework that enables the integration of different component and system simulation codes. The concept of engine simulation integration and its implementation model is described. The model is designed as an object-oriented system, in which various simulation tasks are assigned to individual software components that interact with each other. A new design rationale called “message-based modeling” and its resulting class structure is presented and analyzed. The object model is implemented within a heterogeneous network environment. To demonstrate its flexibility, the codes that deal with different engine components are separately programmed on different computers running various operating systems. These components communicate with each other via a CORBA compliant ORB, which simulates the overall performance of an engine system. The resulting system has been tested on a Local Area Network (LAN) to simulate the transient response of a three-shaft gas turbine engine, subject to small fuel step perturbations. The simulation results for various network configurations are presented. It is evident that in contrast to a standalone computer simulation, the distributed implementation requires much longer simulation time. This difference of simulation efficiency is analyzed and explained. The limitations of this endeavor, along with some future research topics, are also reported in this paper.

Cycle Design Exploration Using Multi-Design Point Approach

2012 ◽  
Author(s):  
Jeffrey Schutte ◽  
Jimmy Tai ◽  
Jonathan Sands ◽  
Dimitri Mavris
Keyword(s):  
Gas Turbine ◽  
Design Space ◽  
Traditional Approach ◽  
Gas Turbine Engine ◽  
Operating Conditions ◽  
Feasible Region ◽  
Turbine Engine ◽  
Design Point ◽  
Performance Requirements ◽  
Design Cycle

The focus of this study is to compare the aerothermodynamic cycle design space of a gas turbine engine generated using two on-design approaches. The traditional approach uses a single design point (SDP) for on-design cycle analysis, where off-design cycle analysis must be performed at other operating conditions of interest. A multi-design point (MDP) method performs on-design cycle analysis at all operating conditions where performance requirements are specified. Effects on the topography of the cycle design space as well as the feasibility of the space are examined. The impacts that performance requirements and cycle assumptions have on the bounds and topography of the feasible space are investigated. The deficiencies of a SDP method in determining an optimum gas turbine engine will be shown for a given set of requirements. Analysis will demonstrate that the MDP method, unlike the SDP method, always obtains a properly sized engine for a set of given requirements and cycle design variables, resulting in an increased feasible region of the aerothermodynamic cycle design space from which the optimum performance engine can be obtained.

How to Create a Performance Model of a Gas Turbine From a Limited Amount of Information

2005 ◽  
Author(s):  
Joachim Kurzke
Keyword(s):  
Gas Turbine ◽  
Reference Point ◽  
Pressure Ratio ◽  
Simulation Models ◽  
Performance Model ◽  
Operating Conditions ◽  
Test Facility ◽  
Secondary Importance ◽  
Engine Simulation ◽  
A Performance

Gas turbine manufacturers develop complex performance simulation models for their products; these proprietary models are based on design information and the many measurements taken during engine development. For subcontractors in collaborative projects, for gas turbine users and outsiders there is often only a limited amount of data accessible for creating a performance model of the engine. User-friendly, accurate and fast PC-based engine simulation tools are available for anybody from several sources. With these tools it is possible to create from a limited amount of data full thermodynamic models. In this paper a methodology is presented which minimizes the effort needed for creating such models. It consists of four steps: Firstly a suitable cycle reference point is chosen and the model is tailored to the data of this point. Secondly compressor and turbine maps are added and scaled such that they fit exactly to the cycle reference point. In this step a second operating point is considered and the location of the cycle reference point in the component maps is adapted such that the simulation fits optimally to the given data of the second point. In a third step, the rest of the data are compared graphically with the simulation. Here many modelers fall in a trap: They plot the data versus spool speed as x-axis because speed is accurately measurable and regarded as reliable information. However, spool speed is — from the view of thermodynamics — a parameter of secondary importance. If the correlation of spool speed with corrected flow in the compressor map is incorrect — which is very probable at the beginning of the modeling process — then all graphics will show discrepancies. This makes the adaptation of the model to the data an extended iterative process. If one uses for the model checks a primary thermodynamic parameter — like corrected mass flow, overall pressure ratio or thrust respectively shaft power — as basis then the task is very much simplified. In the fourth and final step the speed values in the estimated compressor maps are adjusted. This has little effect on the matching accuracy of the previous steps, so the model is finished quickly. The procedure is demonstrated by creating a model for a two-spool turbojet which was tested over quite a range of operating conditions in an altitude test facility. Without much iteration a model is quickly created which matches all the measured data within the quoted uncertainty of the measurements.

scholarly journals An Empirically-Based Simulation Model for Heavy-Duty Gas Turbine Engines Using Treated Residual Fuel

1982 ◽  
Author(s):  
J. C. Blanton ◽  
W. F. O’Brien
Keyword(s):  
Simulation Model ◽  
Gas Turbine ◽  
Combustion Products ◽  
Heavy Duty ◽  
Turbine Engine ◽  
Engine Simulation ◽  
Turbine Efficiency ◽  
Rate Of Increase ◽  
Ash Deposit ◽  
Heavy Duty Gas Turbine

An empirically-based engine simulation model was developed to analyze the operation of a heavy-duty gas turbine on ash-bearing fuel. The effect of the ash in the combustion products on turbine efficiency was determined employing field data. The model was applied to the prediction of the performance of an advanced-cooled turbine engine with a water-cooled first-stage nozzle, when operated with ash-bearing fuels. Experimental data from a turbine simulator rig were used to estimate the expected rates of ash deposit formation in the advanced-cooled turbine engine, so that the results could be compared with those for current engines. The results of the simulations indicate that the rate of decrease in engine power would be 32 percent less in the advanced-cooled engine with water cooling. An improvement in predicted specific fuel consumption performance was also noted, with a rate of increase of 38 percent for the advanced-cooled engine.

An Empirically Based Simulation Model for Heavy-Duty Gas Turbine Engines Using Treated Residual Fuel

1983 ◽  
Vol 105 (1) ◽  
pp. 167-171
Author(s):  
J. C. Blanton ◽  
W. F. O’Brien
Keyword(s):  
Simulation Model ◽  
Gas Turbine ◽  
Combustion Products ◽  
Heavy Duty ◽  
Turbine Engine ◽  
Engine Simulation ◽  
Turbine Efficiency ◽  
Rate Of Increase ◽  
Ash Deposit ◽  
Heavy Duty Gas Turbine

An empirically based engine simulation model was developed to analyze the operation of a heavy-duty gas turbine on ash-bearing fuel. The effect of the ash in the combustion products on turbine efficiency was determined employing field data. The model was applied to the prediction of the performance of an advanced-cooled turbine engine with a water-cooled first-stage nozzle, when operated with ash-bearing fuels. Experimental data from a turbine simulator rig were used to estimate the expected rates of ash deposit formation in the advanced-cooled turbine engine, so that the results could be compared with those for current engines. The results of the simulations indicate that the rate of decrease in engine power would be 32 percent less in the advanced-cooled engine with water cooling. An improvement in predicted specific fuel consumption performance was also noted, with a rate of increase of 38 percent for the advanced-cooled engine.

Towards Large Eddy Simulation of Rotating Turbomachinery for Variable Speed Gas Turbine Engine Operation

2019 ◽  
Author(s):  
Nishan Jain ◽  
Luis Bravo ◽  
Dokyun Kim ◽  
Muthuvel Murugan ◽  
Anindya Ghoshal ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Operating Conditions ◽  
Variable Speed ◽  
Solution Quality ◽  
Engine Operation ◽  
Turbine Engine ◽  
Design Point ◽  
Large Eddy ◽  
Flow Through

Abstract In this work, massively parallel wall-modeled Large Eddy Simulations (LES) are conducted to simulate flow through a single stage power turbine sector of a gas-turbine engine under realistic operating conditions. The numerical framework in the current work uses finite volume based compressible CharLES solver that utilizes a moving Voronoi diagram based grid generation. To test grid sensitivity and evaluate the capability of the solver in predicting turbomachinery flows, three grids of varying resolution are used to simulate flow through the baseline gas-turbine under design operating conditions. After assessing the flow solution quality and establishing simulation parameters, LES simulations are conducted to investigate the performance of gas-turbine at off-design conditions. The conditions include the rotor design point at 100% speed, and off-design points at 75%, and 50% speeds subject to high temperatures from the combustor exit flow. The results showed that the internal flow becomes highly unsteady as the rotational speed of rotor deviates from the design point leading to reduced aerodynamic performance. This study demonstrates that the current framework is able to robustly simulate the unsteady flow in a three-dimensional moving rotor environment towards the design of variable speed gas-turbine engines for US Army Future Vertical Lift program.

Novel Joint Time Frequency Vibration Diagnostics of Turbine Engine Accessories

2010 ◽  
Author(s):  
Matthew J. Watson ◽  
Jeremy S. Sheldon ◽  
Hyungdae Lee ◽  
Carl S. Byington ◽  
Alireza Behbahani
Keyword(s):  
Frequency Domain ◽  
Gas Turbine ◽  
Health Monitoring ◽  
Health Management ◽  
Operating Conditions ◽  
Vibration Diagnostics ◽  
Turbine Engine ◽  
Time Frequency ◽  
Engine Components ◽  
Highly Loaded

Traditional engine health management development has focused on major gas turbine engine components (i.e., disks, blades, bearings, etc.) due to the fact that these components are expensive to maintain and their failures frequently have safety implications. However, the majority of events that lead to standing down of aircraft arise from gas turbine accessory components such as pumps, generators, auxiliary power units, and motors. Common vibration diagnostics, which are based on frequency domain analysis that assumes the monitored signal is “stationary” during the analysis period, are not effective for these components. This is true because operating conditions are often non-stationary and evolving, which leads to spectral smearing and erroneous analysis that can cause missed detections and false alarms. Traditionally, this is avoided by defining steady state operating conditions in which to perform the analysis. Although this may be acceptable for major engine components, which are typically highly loaded during normal steady operation, many engine accessories are only high loaded during transients, especially startup. For example, an engine starter or fuel pump may be more highly loaded and therefore susceptible to damage during engine start up, typically avoided by traditional vibration analysis methods. More importantly, certain component faults and their progression can also lead to non-stationary vibration signals that, because of the smearing they induced, would be missed by traditional techniques. As a result, the authors have developed a novel engine accessory health monitoring methodology that is applicable during non-stationary operation through application of joint time-frequency analysis (JTFA). These JTFA approaches have been proven in other disciplines, such as speech analysis, radar processing, telecommunications, and structural analysis, but not yet readily applied to engine accessory component diagnostics. This paper will highlight the results obtained from applying JTFA techniques, including Short-Time Fourier Transform, Choi-Williams Distribution, Continuous Wavelet Transform, and Time-Frequency Domain Averaging, to very high frequency (VHF) vibration data collected from healthy and damaged turbine engine accessory components. The resulting accuracy of the various approaches were then evaluated and compared with conventional signal processing techniques. As expected, the JTFA approaches significantly outperformed the conventional methods. On-board application of these techniques will increase prognostics and health management (PHM) coverage and effectiveness by allowing accessory health monitoring during the most life influencing regimes regardless of operating speed and reducing inspection and replacement costs resulting in minimizing the vehicle down time.

Flexible manufacturing in repair of gas turbine engine components

1992 ◽  
Author(s):  
KIRK D ◽  
ANDREW VAVRECK ◽  
ERIC LITTLE ◽  
LESLIE JOHNSON ◽  
BRETT SAYLOR
Keyword(s):  
Gas Turbine ◽  
Flexible Manufacturing ◽  
Gas Turbine Engine ◽  
Turbine Engine ◽  
Engine Components

Life assessment of a high temperature probe designed for performance evaluation and health monitoring of an aero gas turbine engine

2020 ◽  
Vol 0 (0) ◽  
Author(s):  
Benny George ◽  
Nagalingam Muthuveerappan
Keyword(s):  
Performance Evaluation ◽  
Gas Turbine ◽  
Health Monitoring ◽  
Gas Turbine Engine ◽  
Life Assessment ◽  
Exhaust Gas ◽  
Cycle Fatigue ◽  
Creep Life ◽  
Turbine Engine ◽  
Engine Components

AbstractTemperature probes of different designs were widely used in aero gas turbine engines for measurement of air and gas temperatures at various locations starting from inlet of fan to exhaust gas from the nozzle. Exhaust Gas Temperature (EGT) downstream of low pressure turbine is one of the key parameters in performance evaluation and digital engine control. The paper presents a holistic approach towards life assessment of a high temperature probe housing thermocouple sensors designed to measure EGT in an aero gas turbine engine. Stress and vibration analysis were carried out from mechanical integrity point of view and the same was evaluated in rig and on the engine. Application of 500 g load concept to clear the probe design was evolved. The design showed strength margin of more than 20% in terms of stress and vibratory loads. Coffin Manson criteria, Larsen Miller Parameter (LMP) were used to assess the Low Cycle Fatigue (LCF) and creep life while Goodman criteria was used to assess High Cycle Fatigue (HCF) margin. LCF and HCF are fatigue related damage from high frequency vibrations of engine components and from ground-air-ground engine cycles (zero-max-zero) respectively and both are of critical importance for ensuring structural integrity of engine components. The life estimation showed LCF life of more than 4000 mission reference cycles, infinite HCF life and well above 2000 h of creep life. This work had become an integral part of the health monitoring, performance evaluation as well as control system of the aero gas turbine engine.

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